| Entries |
| Document | Title | Date |
|---|
| 20080206042 | METHODS AND SYSTEM FOR RECUPERATED CIRCUMFERENTIAL COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES - A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface. | 08-28-2008 |
| 20080232954 | VACUUM SYSTEM FOR CONVEYING A HIGH AMOUNT OF SUPPLEMENTAL LIQUID - A pump apparatus for conveying a gas-liquid mixture comprises a first pump ( | 09-25-2008 |
| 20080292450 | BLOWER APPARATUS - Blower apparatus has: an air duct having suction and supply openings; a blower fan for creating a flow of air in the duct; and an electrostatic atomizer. The atomizer includes a hollow body exposed to the air in the duct. The body is provided therein with an electrostatic atomization chamber, and has a barrier, an inlet and an outlet. The barrier is put in the duct so that a part of the air flowing in the duct collides with the front of the barrier and thereby pressure-increased air is obtained. The inlet is located at the front side of the barrier so that the pressure-increased air can enter the chamber through the inlet. The outlet is located at the rear side of the barrier so that all the pressure-increased air higher than that of the air flowing in the duct, from the chamber can flow out into the duct. | 11-27-2008 |
| 20080310950 | Flow cavity arrangement - It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred. | 12-18-2008 |
| 20090003990 | FLANGE WITH AXIALLY EXTENDING HOLES FOR GAS TURBINE ENGINE CLEARANCE CONTROL - A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface. | 01-01-2009 |
| 20090010751 | ANGLED ON-BOARD INJECTOR - A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an engine centerline to communicate cooling airflow to an angled annular section of a turbine rotor disk coverplate. | 01-08-2009 |
| 20090035124 | Hot-Gas-Ducting Housing Element, Protective Shaft Jacket and Gas Turbine System - Disclosed is a hot-gas-conducting housing element for a hot-gas-conducting housing of a gas turbine system encompassing a compressor, a turbine, and a turbine rotor. The hot gas-conducting housing element is embodied so as to surround a protective shaft jacket placed around the turbine rotor and conduct a hot gas to the turbine. The hot gas-conducting housing element comprises: —at least one hot gas inlet; —an opening facing the turbine; —a section for conducting the hot gas from the at least one hot gas inlet to the opening facing the turbine, said conducting section being provided with an inner housing hub which is configured so as to surround the protective surface facing the protective shaft jacket. Said rib extends in the circumferential direction, protrudes from the circumferential surface, and is disposed in the zone of the circumferential surface bordering the opening that faces the turbine. The rib and/or the inner housing hub is/are fitted with cooling fluid ducts. | 02-05-2009 |
| 20090035125 | IMPINGEMENT COOLED STRUCTURE - An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto. | 02-05-2009 |
| 20090053040 | APPARATUS AND METHOD FOR PRESSURIZED INLET EVAPORATIVE COOLING OF GAS TURBINE ENGINES - An apparatus for cooling air for an intake to a gas turbine, is provided and includes a pressurized water piping and nozzle apparatus for producing a water spray in an airflow to the intake; and evaporative media for receiving the spray and causing a pressurizing of the air in the airflow. | 02-26-2009 |
| 20090053041 | GAS TURBINE ENGINE CASE FOR CLEARANCE CONTROL - A gas turbine engine includes an active clearance control (ACC) system within the engine casing. The case includes a wall structure with a cast-in cooling configuration through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth. | 02-26-2009 |
| 20090067988 | Mixer for cooling and sealing air system for turbomachinery - A system for mixing flows from a compressor is provided. The system comprises an ejector that combines a first flow and a second flow, from the compressor, into a third flow. A bypass flow is connected between the first flow and the third flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the respective pressures and temperatures of the bypass flow and the third flow. | 03-12-2009 |
| 20090097963 | Vane and a Vane assembly for a gas turbine engine - A fan outlet guide vane for a gas turbine engine comprises a generally radially-extending internal structural member and at least one surface member securable in use to the internal structural member so as to define an aerofoil. The gas turbine engine includes an annular first structure and an annular second structure, the second structure being radially outward of the first structure so as to define a duct between them, and in use the internal structural member of the vane is secured between the first structure and the second structure. In a preferred embodiment, the surface member or surface members are secured only to the internal structural member, and not to the first or second structures. | 04-16-2009 |
| 20090097964 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 04-16-2009 |
| 20090155053 | Turbine cooling flow modulation - Cooling air flow in a gas turbine engine, for example to a first turbine rotary stage is modulated in accordance with a predetermined cooling schedule by means of a fluidic valve arrangement disposed in the interior of the engine. Since fluidic valves have no moving parts they are more reliable than conventional mechanical and electrically operated valves and able to withstand better the environment in the interior of a gas turbine engine. The fluidic valves are operated remotely by a relatively small control flow that may be governed by an electrically operated valve mounted externally and under the control of a predetermined cooling schedule. | 06-18-2009 |
| 20090208325 | LARGE FILLET AIRFOIL WITH FANNED COOLING HOLE ARRAY - A turbine airfoil has a fillet connecting the nominal portion of the airfoil into an end wall. Cooling holes are formed over a greater circumferential extent in the fillet than they are through the nominal portion of the airfoil. | 08-20-2009 |
| 20090226300 | Passage obstruction for improved inlet coolant filling - A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage. | 09-10-2009 |
| 20090232637 | Cooling Air Manifold Splash Plates and Gas Turbines Engine Systems Involving Such Splash Plates - Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially. | 09-17-2009 |
| 20090238678 | COLD AIR BUFFER SUPPLY TUBE - A cold air buffer supply tube for a gas turbine engine includes a tube body having a first tube end and a second tube end. A fitting is secured to the first tube end, and a metering cap is secured to the tube second end. The metering cap includes a cap body having a peripheral wall with a plurality of holes to direct flow from an air supply into a bearing compartment for the gas turbine engine. | 09-24-2009 |
| 20090252597 | VALVE SYSTEM FOR A GAS TURBINE ENGINE - A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher pressure plenum into a lower pressure flowpath. | 10-08-2009 |
| 20090252598 | Gas turbine inlet temperature suppression during under frequency events and related method - A method is provided for augmenting power output in a gas turbine electrical power-generating plant including a multistage compressor, a combustor and a multistage turbine component, during events when grid frequency drops below a predetermined target frequency. The method is carried out by a) providing a supply of liquified air arranged to permit selective addition of liquified air to an ambient air inlet to the compressor; and b) flowing controlled amounts of the liquified air into the ambient air inlet during such events. | 10-08-2009 |
| 20090257862 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 10-15-2009 |
| 20090263235 | Damper | 10-22-2009 |
| 20090285671 | VORTEX COOLED TURBINE BLADE OUTER AIR SEAL FOR A TURBINE ENGINE - A cooling system for a turbine blade outer air seal that is positioned in close proximity to a tip of a rotatable turbine airfoil to seal the gap between the tip of the turbine blade and the blade ring carrier. The turbine blade outer air seal may be formed from a housing including a cooling fluid collection chamber and one or more vortex cooling channels in fluid communication with the cooling fluid collection chamber via one or more vortex channel feed holes. In one embodiment, a plurality of vortex cooling channels may extend from proximate to an upstream edge of an outer sealing plate of the outer air seal to a downstream edge of the outer sealing plate. During use, cooling fluids pass through the vortex channel feed holes and into the vortex cooling channels, in which vortices may be created. | 11-19-2009 |
| 20090304495 | DEVICE FOR SUPPLYING VENTILATION AIR TO THE LOW PRESSURE BLADES OF A GAS TURBINE ENGINE - The present invention relates to a device for supplying ventilation air to a turbine rotor of a gas turbine engine comprising a first and a second turbine disk ( | 12-10-2009 |
| 20090324388 | GAS TURBINE AND COOLING AIR SUPPLY STRUCTURE THEREOF - The present invention includes an introducing passage that is provided within a turbine stationary blade fixed within a turbine casing and that communicates an interior of the turbine casing with an exterior thereof; a nozzle that is provided in an inner circumference of the turbine stationary blade in a manner that the nozzle communicates with the introducing passage and that includes an outlet facing the opening of the rotor cavity and a swirler at the outlet; and a pressurizing passage that communicates a cooling passage with a rotor cavity. In this arrangement, the outlet of the nozzle and the connecting opening of the pressurizing passage are arranged so that distances of the outlet and of the connecting opening from the central axis line in the radial direction of the rotor are the same distance r. | 12-31-2009 |
| 20100003123 | INLET AIR HEATING SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine has an inlet for delivering air into a compressor section. The compressor section is connected to feed air into a combustion section, wherein the air mixes with fuel and combusts. The combustion section is connected to turbine rotors such that products of combustion can pass over the turbine rotors to drive the turbine rotors. An exhaust communicates with the turbine sections to receive the products of combustion. A bleed tap communicates the exhaust to the inlet. A control controls the amount of exhaust gasses tapped into the inlet to achieve desired operating conditions. | 01-07-2010 |
| 20100021283 | SYSTEM AND METHOD FOR PROVIDING SUPERCRITICAL COOLING STEAM INTO A WHEELSPACE OF A TURBINE - A system for cooling a high pressure section of a turbomachine includes a conduit configured to carry cooling steam from a boiler to a space upstream of a first stage nozzle of the turobmachine. The conduit extends through a housing of the turbomachine and a nozzle diaphragm of the first stage nozzle. The system further includes a control valve in the conduit configured to regulate the flow of cooling steam. A turbomachine includes a housing; a turbine shaft rotatably supported in the housing; and a plurality of turbine stages located along the turbine shaft and contained within the housing. Each turbine stage includes a diaphragm attached to the housing. The diaphragm comprises a plurality of nozzles. A hole is provided in the diaphragm upstream of a first stage of the plurality of stages for the introduction of cooling steam. A method of cooling a high pressure section of a turbomachine includes introducing cooling steam into the turbomachine through the at least one hole. | 01-28-2010 |
| 20100028132 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 02-04-2010 |
| 20100034641 | STEAM TURBINE AND STEAM TURBINE PLANT SYSTEM - A steam turbine | 02-11-2010 |
| 20100054915 | AIRFOIL INSERT - An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall. | 03-04-2010 |
| 20100068035 | APPARATUS AND METHOD FOR COOLING A TURBINE - A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine. | 03-18-2010 |
| 20100111673 | TURBINE WITH INTERRUPTED PURGE FLOW - A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft turbine blades, respectively, fore and aft of a turbine nozzle and a central portion proximate the turbine nozzle and an attachment retained between the fore and aft disk posts and the fore and aft turbine blades and coupled to the central portion, such that a portion of the attachment interrupts a purge flow through the turbine. | 05-06-2010 |
| 20100111674 | System and Method for Reducing Bucket Tip Losses - A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface. | 05-06-2010 |
| 20100129200 | PELTON HYDRAULIC MACHINE INCLUDING MEANS FOR INJECTING A FLOW DRAWN FROM A MAIN FLOW - The invention relates to a Pelton machine through which a main flow (E) of water passes, including at least one Pelton turbine ( | 05-27-2010 |
| 20100129201 | HYDRAULIC MACHINE INCLUDING MEANS FOR INJECTING A FLOW DRAWN FROM A MAIN FLOW - The invention relates to a machine through which a main flow (E) of water passes, including a turbine wheel ( | 05-27-2010 |
| 20100150700 | BYPASS AIR SCOOP FOR GAS TURBINE ENGINE - A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine. | 06-17-2010 |
| 20100178158 | TURBINE WASH PORT FOR A GAS TURBINE ENGINE - An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings. | 07-15-2010 |
| 20100202873 | Ceramic Matrix Composite Turbine Engine - In one embodiment a transition section for a turbine engine is provided that includes one or more components constructed of a ceramic matrix composite. The transition section may fluidly connect a high-pressure turbine and a low-pressure turbine within the gas turbine engine. The transition section may include a transition duct and a variable area turbine nozzle. One or both of the transition duct and the variable area turbine nozzle may be constructed of the ceramic matrix composite. | 08-12-2010 |
| 20100215476 | GAS TURBINE COMBUSTION SYSTEM COOLING ARRANGEMENT - Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which is located a hula seal, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member. | 08-26-2010 |
| 20100221099 | APPARATUS, METHODS, AND/OR SYSTEMS RELATING TO THE DELIVERY OF A FLUID THROUGH A PASSAGEWAY - A method of constructing an industrial machine such that, in operation, a supply of a fluid coolant through a hollow passageway is delivered at a reduced temperature, the method including the steps of: a) identifying at least a section of the hollow passageway that transports or is meant to transport the fluid coolant through a space that resides at a temperature that is significantly higher than a desired temperature of the fluid coolant; and b) through at least a majority of the identified section of the hollow passageway that transports the fluid coolant through the space that resides at the temperature that is significantly higher than the desired temperature of the fluid coolant, constructing the hollow passageway such that the outer surface of the hollow passageway has an emissivity coefficient less than about 0.1. | 09-02-2010 |
| 20100239413 | APPARATUS FOR TURBINE ENGINE COOLING AIR MANAGEMENT - An exemplary embodiment of the invention is directed to a turbine engine having a first, rotatable turbine rotor assembly, a second, stationary nozzle assembly disposed adjacent thereto and a wheel space which is defined between the first, rotatable turbine rotor assembly and the second, stationary nozzle assembly. The wheel space is operable to receive cooling air therein and includes a sealing feature located on the first rotatable turbine rotor assembly that extends axially into the wheel space to terminate adjacent to a sealing land positioned on the second, stationary nozzle assembly. The sealing feature and the sealing land operate to control the release of cooling air from within the wheel space and the sealing land is constructed of shape memory alloy. | 09-23-2010 |
| 20100247291 | GAS TURBINE ENGINE ARTICLE HAVING COLUMNAR MICROSTRUCTURE - A gas turbine engine article includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side. A gaspath layer is bonded to the inner side of the substrate and includes a metallic alloy having a columnar microstructure. | 09-30-2010 |
| 20110038711 | STEAM TURBINE AND SYSTEM FOR START-UP - A steam turbine and a start-up system for a steam turbine are disclosed comprising: a plurality of stages, a steam path through the plurality of stages, an inlet port for introducing steam to a first stage, an exhaust port at a last stage for allowing exhaust to exit the steam turbine, an admission port for allowing steam to enter the steam path at a location downstream from the inlet port, and a ventilator port for allowing steam to exit the steam path, the ventilator port located upstream of the admission port to create a reverse flow of steam towards the ventilator port from the admission port. | 02-17-2011 |
| 20110268556 | PLASMA ACTUATOR CONTROLLED FILM COOLING - A film cooling apparatus with a cooling hole ( | 11-03-2011 |
| 20110293402 | GAS TURBINE - A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls. | 12-01-2011 |
| 20110305557 | WIND TURBINE - A wind turbine has a spindle, a first fan device and a second fan device. The first fan device is rotatably mounted around the spindle and has a first pivot hole and at least two first blades. The first pivot hole is formed through a center of the first fan device and is mounted around the spindle. The at least two first blades are radially mounted on and protrude from an external surface of the first fan device. The second fan device is rotatably mounted around the spindle, abuts with the first fan device and has a second pivot hole and at least two second blades. The second pivot hole is formed through a center of the second fan device and is mounted around the spindle. The at least two second blades are mounted on and protrude from an external surface of the second fan device. | 12-15-2011 |
| 20120045313 | FLOW DEVICE COMPRISING A CAVITY COOLING SYSTEM - A flow device having a cooling-air injection system for injecting cooling air into cavities ( | 02-23-2012 |
| 20120163957 | DEVICE FOR SUPPORTING A TURBINE RING, TURBINE HAVING SUCH A DEVICE, AND TURBINE ENGINE HAVING SUCH A TURBINE - A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and/or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook. | 06-28-2012 |
| 20120177481 | GAS TURBINE - This gas turbine includes a turbine cooling structure of cooling a turbine by using cooling air and a filter that reduces dust in the cooling air on an upstream side of the turbine. Furthermore, the gas turbine includes a supply pipe for supplying the cooling air to the filter, a branch pipe that is branched from the supply pipe on an upstream of the filter, and a unit that calculates or estimates a circulation amount of dust in the cooling air. In this gas turbine, at a time of start-up of a turbine, the supply pipe is closed and the branch pipe is opened, and when the circulation amount of dust in the cooling air becomes equal to or less than a predetermined threshold, the supply pipe is opened and the branch pipe is closed. | 07-12-2012 |
| 20120201654 | TURBINE ENGINE COMPRESSOR HAVING AIR INJECTIONS - A turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing. | 08-09-2012 |
| 20120201655 | RADIO COMMUNICATION SYSTEM, TRANSMITTING APPARATUS, RECEIVING APPARATUS, RECEIVING METHOD AND TRANSMITTING METHOD - The invention relates to a turbine casing ( | 08-09-2012 |
| 20120207585 | Centrifugal Compressor - A centrifugal compressor is provided. The centrifugal compressor includes a housing and a rotatable assembly mounted for rotation about an axis within the housing. The rotatable assembly includes an impeller forming part of a compressor stage and a motor rotor forming an armature of a motor for driving the rotating assembly about the axis. A first air intake is located at a first end of the apparatus, the first air intake providing an air source for the compressor stage and a second air intake is located at a second end of the apparatus, the second air intake providing an air source for at least two air cooling passageways. | 08-16-2012 |
| 20120251296 | AROMATIC NEBULIZING DIFFUSER - An aromatic nebulizing diffuser includes a base panel, a holder defining therein an oscillation chamber, a power switch, an electric fan, a fluid container, an ultrasonic oscillator, a fluid intake control device set in between the oscillation chamber and the fluid container, a dip tube in communication between the oscillation chamber and the fluid container and changeable between an open status and a close status to control the fluid intake control device in closing/opening the passage between the oscillation chamber and the fluid container, an outer housing, an air passage in air communication between the oscillation chamber and the cover for the passing of currents of air caused by the electric fan, an exhaust passage for guiding a generated fine mist of aromatic fluid droplets out of the oscillation chamber into the atmosphere. | 10-04-2012 |
| 20120257959 | STEAM TURBINE IN A THREE-SHELLED DESIGN - A turbomachine including a rotor and an inner interior housing an outer interior housing and an exterior housing, wherein the turbomachine has a first flow and a second flow arranged opposite the first flow for a high-pressure blading or medium-pressure blading, wherein the inner interior housing is made of a higher quality material tan the outer interior housing and solely accommodates the high-pressure and medium-pressure inflow regions including the balance piston is provided. | 10-11-2012 |
| 20120269615 | BLADE MEMBER AND ROTARY MACHINE - The airfoil member of the present invention is provided with an airfoil body, an end wall which is installed at an end part of the airfoil body in a blade span direction and extends so as to intersect in the blade span direction, a fillet portion which smoothly connects the end part of the airfoil body with the end wall, and a cooling channel which allows a cooling medium to circulate inside the airfoil body and the end wall and in which two main channels extending along the blade span direction are connected so as to bend in a folding manner at a return channel formed on the end wall side. The return channel is formed so as to run along the fillet portion on a cross section intersecting with a center line of a profile of the airfoil body and also formed in such a manner that the width thereof in the profile thickness direction is greater than the width of the main channel in the profile thickness direction. | 10-25-2012 |
| 20120282080 | COOLING APPARATUS, GAS TURBINE SYSTEM USING COOLING APPARATUS, HEAT PUMP SYSTEM USING COOLING SYSTEM, COOLING METHOD, AND METHOD FOR OPERATING COOLING APPARATUS - The amount of water to be injected in an intercooler is controlled to cool the compressed gas to the saturation temperature. It is difficult to adjust the amount of the water to be injected, however, since the temperature of the compressed gas at an intercooler outlet is actually higher than the saturation temperature. An intercooling system is configured so as to cool a gas to the saturation temperature without controlling the amount of water injection and thereby maintain the reliability of the compressor while improving the cooling efficiency. The intercooling system is located between a plurality of compression stages of a gas compressor to cool the gas that has been in the compressor. A desired amount of liquid is sprinkled to cool the compressed gas while restraining inflow of the liquid into the compression stages. | 11-08-2012 |
| 20120321442 | TURBOMOLECULAR PUMP DEVICE - A turbomolecular pump device includes: a turbomolecular pump main body; a power unit that drives the turbomolecular pump main body; and a water cooling unit that is provided between the turbomolecular pump main body and the power unit, wherein components provided in a casing of the power unit are classified into an intensive cooling required component that requires intensive cooling, a moderate cooling required component that requires moderate cooling, and a no cooling required component that requires substantially no cooling, the intensive cooling required component is mounted on a first high-conductivity substrate contacting to the water cooling unit, the moderate cooling required component is mounted on a second high heat-conductive substrate contacting to an inner surface of the casing, and the no cooling required component is mounted on a substrate arranged in a space between the first high heat-conductive substrate and the second high heat-conductive substrate. | 12-20-2012 |
| 20120328414 | Gas Turbine For Aeronautic Engines - In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages. | 12-27-2012 |
| 20130058760 | AXIAL COMPRESSOR WITH AN INJECTION DEVICE FOR INJECTING A FLUID - An axial compressor is disclosed for compressing air, such as for a gas turbine. The axial compressor can include a rotor, having a multiplicity of rotor blades, and rotor casing. The casing and rotor can form an annular gas passage. Outside the gas passage an annular and concentric bleed air chamber, can include at least one bleed air slot in functional communication with the gas passage. At least one injection device having at least one nozzle which can inject the fluid into the gas passage via the bleed air slot. | 03-07-2013 |
| 20130064647 | GAS TURBINE - A gas turbine configured to prevent eccentricity of a rotor ( | 03-14-2013 |
| 20130084162 | Gas Turbine - A gas turbine is provided that can suppress an increase in the supplied amount of cooling air in clearance adjustment through casing cooling. | 04-04-2013 |
| 20130089408 | TURBINE BLADE TIP CLEARANCE CONTROL - An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising. | 04-11-2013 |
| 20130121809 | REFRIGERANT COMPRESSOR - A refrigerant compressor comprises an electric element; a compression element; and a sealed container; wherein the compression element includes: a crankpin; a piston pin; and a connecting rod having a large hole portion into which the crankpin is inserted, a small hole portion in which the piston pin is rotatably disposed, and a coupling rod portion; wherein an oil guide hole is provided in the coupling rod portion of the connecting rod such that the large hole portion and the small hole portion are communicated with each other via the oil guide hole; a circular first groove is provided on an outer peripheral surface of the piston pin such that the first groove communicates with the oil guide hole; and a second groove extending in a center axis direction of the piston pin is provided in a first region of the small hole portion of the connecting rod. | 05-16-2013 |
| 20130121810 | INTER-BLADE SEALING FOR A TURBINE OR COMPRESSOR WHEEL OF A TURBINE ENGINE - An inter-blade sealing for a turbine or compressor wheel of a turbine engine includes inserts engaged in longitudinal cavities in side edges of platforms of blades and bearing, in operation, against facing side edges of platforms of adjacent blades. Each insert has a cylindrical elongate shape and includes in its outer cylindrical surface at least one annular groove for passing platform cooling air. | 05-16-2013 |
| 20130129480 | COMPRESSION APPARATUS - Provided is a compression apparatus for cooling multiple devices using a single fan with a small amount of electric power. An upper limit temperature, a first gain applied in a case in which a suction adjustment valve is opened, and a second gain applied in a case in which the suction adjustment valve is closed are set in advance for each of multiple temperature detectors provided at different locations of the compression apparatus; and, for each of the multiple temperature detectors, a difference between a detected value and the upper limit temperature is calculated, and a rotation speed of the fan is determined based on the smallest value in the differences, and the first gain or the second gain set for the temperature detector having the smallest difference. | 05-23-2013 |
| 20130142623 | COMPRESSOR HOUSING AND TWO-STAGE TURBOCHARGER THEREOF - A compressor housing surrounds an impeller of a compressor, compressing and discharging air suctioned from the impeller, the compressor may include a body having an impeller seating portion where the impeller is installed at the center of the body, an air inflow hole being in communication with the impeller seating portion formed at one side of the body, an air outflow hole formed at the other side of the body, and a scroll-shaped air path being in communication with the air inflow hole to the air outflow hole while surrounding the impeller seating portion, and a cooling chamber provided in the body, which has a cooling water path through which cooling water cooling air that flows on the air path flows and a plurality of exits being in communication with the cooling water path. | 06-06-2013 |
| 20130149107 | GAS TURBINE OUTER CASE ACTIVE AMBIENT COOLING INCLUDING AIR EXHAUST INTO A SUB-AMBIENT REGION OF EXHAUST FLOW - A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end. | 06-13-2013 |
| 20130170955 | EXHAUST PUMP - Provided is an exhaust pump that comprises connecting opening portions that can be deburred easily and that are suitable for enhancing gas evacuation performance. A rotor (a cylindrical rotating member) of an exhaust pump comprises a plate body that has a ring-like projection on a reverse side outer peripheral section of the rotor, and a cylindrical body that is fitted into an outer periphery of the ring-like projection. Connecting opening portions of the exhaust pump comprise holes that are formed by notching an outer peripheral section of the plate body and an outer peripheral section of the ring-like projection, and a portion (specifically, a hole) of the holes that opens in the form of a horizontal hole is covered by an outer-peripheral upper end portion of the cylindrical body. | 07-04-2013 |
| 20130170956 | DISABLING CIRCUIT IN STEAM TURBINES FOR SHUTTING OFF SATURATED STEAM - A cooling option for a steam turbine is provided, wherein the steam turbine includes a high-pressure zone and a medium-pressure zone, wherein the saturated steam streaming out of the high-pressure zone is discharged via a saturated steam conduit to a first pressure chamber in a second flow channel of the medium-pressure zone and thus the possibility of the saturated steam causing damage by corrosion and erosion in the high-pressure zone is prevented. | 07-04-2013 |
| 20130177398 | SYSTEM FOR PRESSURING THE BEARING CHAMBERS OF TURBINE ENGINES MACHINES USING AIR TAKEN FROM THE INTAKE DUCT - A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor. | 07-11-2013 |
| 20130183140 | FAN SHROUD WITH COOLING PASSAGE - A fan shroud includes a cylindrical body which is made of a heat conducting material and which enclose an annular passage. The shroud also has a flange projecting radially outwardly from the body. The body forms a wall interposed in the passage. An inlet port and an outlet port communicate with the passage on opposite sides of the wall. Inlet and outlet supply lines are connected to the inlet and outlet ports. | 07-18-2013 |
| 20130189080 | ROTARY COMPRESSOR - A refrigerant being low in both ODP and GWP and containing at least hydrofluoroolefin having a double bond of carbon is used. By providing a first compression-chamber oil feed path for feeding refrigerating machine oil to a compression chamber | 07-25-2013 |
| 20130195619 | EXHAUST TURBOCHARGER OF AN INTERNAL COMBUSTION ENGINE - The invention relates to an exhaust turbocharger ( | 08-01-2013 |
| 20130195620 | EXHAUST TURBOCHARGER - The invention relates to an exhaust turbocharger ( | 08-01-2013 |
| 20130209232 | MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS - A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed. | 08-15-2013 |
| 20130209233 | COOLING HOLE WITH ENHANCED FLOW ATTACHMENT - A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet. | 08-15-2013 |
| 20130209234 | MULTIPLE DIFFUSING COOLING HOLE - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge. | 08-15-2013 |
| 20130209235 | GAS TURBINE ENGINE COMPONENT WITH CUSPED, LOBED COOLING HOLE - A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes. | 08-15-2013 |
| 20130209236 | GAS TURBINE ENGINE COMPONENT WITH COMPOUND CUSP COOLING CONFIGURATION - A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition. | 08-15-2013 |
| 20130209237 | OIL SUPPLY APPARATUS - In an oil supply apparatus, a valve body includes first and second radially protruding lands, and a small-diameter portion continuously connecting the first and second lands and having a diameter smaller than at least the outer diameter of the first and second lands. Rotational speeds of a rotor are set as first, second and third rotational ranges in the ascending order. In the first rotational range, work oil from a second discharge port is fed to a first oil passage via the small diameter portion. In the second rotational range, work oil from the second discharge port is fed to a return oil passage via the small diameter portion. In the third rotational range after the second oil passage is blocked relative to the return oil passage by the second land, work oil from the second discharge port is fed to the first oil passage. | 08-15-2013 |
| 20130209238 | SET OF ROTOR DISKS FOR A TURBINE ENGINE - A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk. | 08-15-2013 |
| 20130216356 | APPARATUS FOR EXTRACTING ENERGY FROM A FLUID FLOW - An apparatus for extracting energy from a fluid flow including a secondary fluid channel, a fluid driveable generator unit and a primary fluid channel. The primary fluid channel comprises a fluid intake in fluid communication with a throat. The throat is configured to increase the flow velocity and reduce the pressure of the primary fluid flowing through the primary fluid channel and includes at least one plenum in the interior of the throat configured to further reduce the pressure of the primary fluid flowing through the primary fluid channel. The plenum includes at least one perforation through its exterior surface in fluid communication with the secondary fluid channel. As such, the flow of primary fluid through the primary fluid channel draws the secondary fluid into the primary fluid channel through the secondary fluid channel and the perforation and thereby into driving engagement with the generator. | 08-22-2013 |
| 20130243575 | COOLING PEDESTAL ARRAY - A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals. | 09-19-2013 |
| 20130243576 | GAS TURBINE - A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring | 09-19-2013 |
| 20130272850 | COMPONENTS WITH MICROCHANNEL COOLING - A component includes a substrate having outer and inner surfaces, where the inner surface defines at least one hollow, interior space. The outer surface defines pressure side and suction side walls, which are joined together at leading and trailing edges of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface. The coating comprises at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge. A method of forming cooling channels in the vicinity of the trailing edge is also provided. | 10-17-2013 |
| 20130280041 | OIL PUMP - An oil pump including an upstream pump unit including an upstream inner rotor and an upstream outer rotor; a downstream pump unit including a downstream inner rotor and a downstream outer rotor as being arranged adjacently to the upstream pump unit in a predetermined axis line direction; a rotary shaft concurrently rotating the upstream inner rotor and the downstream inner rotor; and a housing which contains the upstream pump unit and the downstream pump unit as supporting the rotary shaft and which includes an inlet port for sucking oil from the outside into the upstream pump unit, an ejection port for ejecting a part thereof to the outside in a pressurization process of the upstream pump unit, a communication port for providing communication between the upstream pump unit and the downstream pump unit, and a discharge port for discharging oil from the downstream pump unit to the outside. | 10-24-2013 |
| 20130280042 | JOURNAL BEARING WITH DUAL PASS COOLING FOR AIR MACHINE - A compressor rotor compresses air and delivers the compressed air to a downstream inlet and across a turbine rotor. A shaft rotates with the turbine rotor and the compressor rotor. The shaft is hollow with an inner bore and an outer periphery. At least one journal bearing supports a portion of the shaft, and has an inner bore spaced from the outer periphery of the shaft. A cooling air path is provided between the shaft outer periphery and the bearing inner periphery, and along a length of the bearing to at least one connection hole. The connection hole provides cooling air from an outer periphery of the shaft to the inner bore of the shaft. In a separate feature, a shaft for use in an air supply machine includes a hollow interior, with such a connection hole. | 10-24-2013 |
| 20130287547 | BEARING, BEARING ASSEMBLY COMPRISING SUCH A BEARING AND TURBOCHARGER COMPRISING SUCH A BEARING ASSEMBLY - This bearing comprises a fixed outer ring and a rotatable inner ring, and at least one lubrication ring having at least one lubrication duct extending between an outer surface and an inner surface of the lubrication ring. The at least one lubrication duct is placed so that the scalar product of a vector collinear to the longitudinal axis of the lubrication duct, and a vector (VL | 10-31-2013 |
| 20130294890 | REVERSE BRAYTON CYCLE WITH BLADELESS TURBO COMPRESSOR FOR AUTOMOTIVE ENVIRONMENTAL COOLING - An automotive cabin cooling system uses a bladeless turbocompressor driven by automobile engine exhaust to compress incoming ambient air. The compressed air is directed to an intercooler where it is cooled and then to another bladeless turbine used as an expander where the air cools as it expands and is directed to the cabin interior. Excess energy may be captured by an alternator couple to the expander turbine. The system employs no chemical refrigerant and may be further modified to include another intercooler on the output of the expander turbine to isolate the cooled cabin environment. | 11-07-2013 |
| 20130302143 | COOLING DEVICE FOR A JET ENGINE - The present invention relates to a cooling device for a jet engine having an axial compressor with several compressor stages including a rotor with rotor blades, a stator with stator vanes and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor by simple measures and hence to increase the efficiency of a jet engine, a slot-like branch opening surrounding the rotor for a cooling airflow diverted from the main airflow into a first cavity upstream of the rotor is provided upstream of the last compressor stage of the axial compressor, with passage openings being arranged in the rotor for passing on the diverted cooling airflow from the first cavity into a second cavity downstream of the rotor. | 11-14-2013 |
| 20130315710 | GAS TURBINE ENGINE COMPONENTS WITH COOLING HOLE TRENCHES - An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface. | 11-28-2013 |
| 20130315711 | APPARATUS AND SYSTEM FOR CHANGING TEMPERATURE OF VANE SEPARATORS IN A POWER GENERATING SYSTEM - This disclosure describes embodiments of a vane conditioning apparatus for use in power generating systems. These embodiments generate one or more fluid streams, which impinge on vane separators in the power generating system to change the temperature of the vane separators. In one embodiment, the vane conditioning apparatus comprises a vortex tube to convert pressurized supply air to a hot fluid stream and a cold fluid stream. A flow control device couples with the vortex tube to regulates flow of the hot fluid stream and the cold fluid stream to the vane separators. | 11-28-2013 |
| 20130315712 | TURBOCHARGER WITH COOLED TURBINE HOUSING AND REDUCED PRESSURE LOSS - A turbocharger has a turbine housing formed with a coolant inlet channel and a coolant outlet channel. The turbine housing contains a coolant separating region in which delivered coolant is separated and a coolant combining region in which coolant is combined again. Each of the coolant separating region and the coolant combining region is equipped with a conical conducting body. | 11-28-2013 |
| 20130323020 | TURBOCHARGER WITH COOLED TURBINE HOUSING - A turbocharger has a turbine housing, a bearing housing, and a compressor housing. The turbine housing has a coolant inlet, a cooling jacket formed in the interior of the turbine housing, and a coolant outlet. The cooling jacket is divided into two subregions. | 12-05-2013 |
| 20130323021 | TURBOCHARGER WITH COOLED TURBINE HOUSING, COOLED BEARING HOUSING, AND A COMMON COOLANT SUPPLY - A turbocharger has a turbine housing and a bearing housing that is connected to the turbine housing. Coolant is supplied to the bearing housing via the turbine housing. | 12-05-2013 |
| 20130323022 | TURBOCHARGER WITH COOLED TURBINE HOUSING, COOLED BEARING HOUSING, AND A COMMON COOLANT SUPPLY - A turbocharger has a turbine housing and a bearing housing that is connected to the turbine housing. The turbine housing is formed with a coolant inlet, a cooling jacket in the interior of the turbine housing, and a coolant outlet. The bearing housing has a coolant inlet, a cooling jacket in the interior of the bearing housing, and a coolant outlet. The coolant inlet of the bearing housing is connected to a branched coolant outlet of the turbine housing. The coolant outlet of the bearing housing is connected to a coolant return inlet of the turbine housing. | 12-05-2013 |
| 20130330172 | METHOD, SYSTEM AND APPARATUS FOR ENHANCED OFF LINE COMPRESSOR AND TURBINE CLEANING - Methods, systems and apparatus for cleaning turbines, such as power generation turbines, are disclosed. Supplemental piping is connected to existing compressor air extraction and turbine nozzle cooling air piping, to supply water and/or cleaning agents into areas of a turbine not ordinarily accessible by injection of water and/or cleaning agents into the bellmouth of the turbine alone. Pressure and flow sensors, pumps, valving, and a control system to regulate the operation of the pumps and valving are provided to control the introduction of water and/or cleaning agents into the turbine. | 12-12-2013 |
| 20130336768 | MULTI-PRESSURE RADIAL TURBINE SYSTEM - A multi-pressure radial turbine system including a high-pressure pump and a low-pressure pump for pressurizing liquid-phase heating media introduced therein to different pressures; a high-pressure evaporator and a low-pressure evaporator for vaporizing the liquid-phase heating media delivered from the high-pressure pump and the low-pressure pump by absorbing heat from a high-temperature heat source; one multi-pressure radial turbine that expands the gaseous heating media having different pressures and temperatures, supplied from the high-pressure evaporator and the low-pressure evaporator, to obtain output power; and a condenser for condensing the gaseous heating medium expanded in the multi-pressure radial turbine by making the medium release heat to a low-pressure heat source. A cycle circuit is formed through which the heating medium circulates while repeatedly changing its state between vapor and liquid. | 12-19-2013 |
| 20130343874 | Advection Fan and A Fan Frame Thereof - An advection fan includes a fan frame, an impeller and a cover plate. The fan frame has a bottom plate and a lateral wall. A shaft seat is arranged on the bottom plate. The lateral wall surrounds the shaft seat and has an inner peripheral face. The lateral wall includes first and second air-guiding portions. An air inlet and an air outlet are formed between the first and second air-guiding portions. The first air-guiding portion includes a first guiding face intersecting the inner peripheral face by a first included angle, which is smaller than 180 degrees. The second air-guiding portion includes a second guiding face. A distance between the first and second guiding faces is gradually reduced from the air inlet towards the center of the fan frame. The impeller is rotatably coupled with the shaft seat. The cover plate is coupled with the lateral wall. | 12-26-2013 |
| 20130343875 | System for Cooling a Hyperbaric Chamber - A system for cooling a hyperbaric chamber includes a compressor, a first hose, a cooling unit, a second hose, and a hyperbaric chamber. The first hose fluidly connects the compressor to the cooling unit, and the second hose fluidly connects the cooling units to the hyperbaric chamber. Compressed air from the compressor travels through a first pressure relief fitting and a second pressure relief fitting, where the compressed air is depressurized according to the system requirements. During the depressurization, the compressed air cools down because of the depressurization and creates a comfortable environment within the hyperbaric chamber. | 12-26-2013 |
| 20140010634 | PRESWIRLER CONFIGURED FOR IMPROVED SEALING - A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart from the outer flange. The inner ring also includes an inner cylindrical portion located within the outer cylindrical portion and a back portion extending from the inner flange to the inner cylindrical portion. The inner ring further includes a plurality of second holes. | 01-09-2014 |
| 20140010635 | FLUID INTAKE AND SYSTEM FOR ROTARY MACHINES - This invention relates to a fluid supply system for a rotary machine, the system comprising: a rotor assembly comprising an array of blades arranged to be driven about a primary axis in use, the rotor assembly comprising a casing structure, wherein the casing structure is rotatable in unison with the blades about the primary axis; a directional fluid intake, said intake being rotatably mounted at an outer surface of the casing structure about a second axis which is angularly offset from the primary axis. | 01-09-2014 |
| 20140017067 | GAS TURBINE ENGINE - A gas turbine engine ( | 01-16-2014 |
| 20140023484 | COOLING STRUCTURE OF GENERATOR MOTOR AND GENERATOR MOTOR - A cooling structure of a generator motor includes: a first passage provided to an end side member placed at one end of a housing of a generator motor, the first passage extending toward a rotation center axis of an input/output shaft housed in the housing, the first passage opening to a side of the input/output shaft, and the first passage including a restriction section halfway through; and a second passage provided to the end side member, branching off from the first passage at a position on an outer side in a radial direction of the input/output shaft than the restriction section and subsequently extending toward a rotor attached to an outside of the input/output shaft, and the second passage opening to a side of the rotor. | 01-23-2014 |
| 20140023485 | CENTRIFUGAL PUMP - The invention relates to a centrifugal pump for conveying a gaseous suspension, in particular a fiber pulp suspension, which has a pump impeller ( | 01-23-2014 |
| 20140030066 | ACTIVE CLEARANCE CONTROL MANIFOLD SYSTEM - Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15. | 01-30-2014 |
| 20140030067 | GAS TURBINE APPARATUS - Provided is a gas turbine apparatus including: a turbine unit comprising an output shaft; a cooling gas generation unit, comprising a rotation shaft, which receives power from the output shaft through the rotation shaft and generates a compressed cooling gas; a first duct unit which transfers the generated compressed cooling gas to the turbine unit; a clutch unit which controls a power transfer connection between the output shaft and the rotation shaft; and a control unit which controls the transferring of the generated compressed cooling gas. | 01-30-2014 |
| 20140030068 | STEAM SUPPLY CIRCUIT FROM A TURBINE - The technical field of the invention is steam turbines including a steam feed circuit based on a functional steam generator set that may be nuclear- or fossil-fuel powered, and in particular a steam feed circuit ( | 01-30-2014 |
| 20140050564 | THREADED FULL RING INNER AIR-SEAL - A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal. | 02-20-2014 |
| 20140072404 | BLADE WHEEL FOR A CONTINUOUS-FLOW MACHINE AND METHOD FOR PRODUCING A TURBINE WHEEL FOR A CONTINUOUS-FLOW MACHINE - A turbine wheel for a continuous-flow machine includes a centrally arranged hub with circumferentially arranged blades and a pressure equalizing channel. The hub is configured to enclose a cavity, and a resulting principle axis of inertia of the turbine wheel coincides with an axis of rotation of the turbine wheel. The pressure equalizing channel is configured to fluidically connect the cavity to at least one axial end face of the hub and to an environment of the turbine wheel. A diameter of the pressure equalizing channel is smaller than a diameter of the cavity. In one embodiment, the turbine wheel is for an exhaust gas turbocharger. | 03-13-2014 |
| 20140072405 | DEVICE FOR DE-ICING A TURBOMACHINE SEPARATOR - A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange. | 03-13-2014 |
| 20140086727 | GAS TURBINE ENGINE TURBINE DIAPHRAGM WITH ANGLED HOLES - A gas turbine engine turbine diaphragm ( | 03-27-2014 |
| 20140099190 | GAS TURBINE ENGINE TURBINE HOUSING WITH ENLONGATED HOLES - A turbine housing ( | 04-10-2014 |
| 20140112759 | GAS TURBINE CASING THERMAL CONTROL DEVICE - A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed. | 04-24-2014 |
| 20140126995 | MICROCHANNEL COOLED TURBINE COMPONENT AND METHOD OF FORMING A MICROCHANNEL COOLED TURBINE COMPONENT - A microchannel cooled turbine component includes a first portion of the microchannel cooled turbine component having a substrate surface. Also included is a second portion of the microchannel cooled turbine component comprising a substance that is laser fused on the substrate surface. Further included is at least one microchannel extending along at least one of the first portion and the second portion, the at least one microchannel formed and enclosed upon formation of the second portion. | 05-08-2014 |
| 20140147250 | TURBINE BLADE ANGEL WING WITH PUMPING FEATURES - A gas turbine engine, including: a plurality of blades ( | 05-29-2014 |
| 20140161590 | COVER DEVICE, INTEGRALLY BLADED MAIN ROTOR BODY, METHOD AND TURBOMACHINE - A covering device for an integrally bladed rotor base body of a turbomachine for preventing or reducing a cooling air stream that flows from a high-pressure side to a low-pressure side through channels that are formed between adjacent rotor blades, a plurality of cover elements being provided that are individually insertable into the channels and have at least one peripheral sealing surface. Also an integrally bladed rotor base body having a covering device of this kind, a method for producing such an integrally bladed rotor base body, as well as a turbomachine having such an integrally bladed rotor base body. | 06-12-2014 |
| 20140169943 | COMPONENTS WITH POROUS METAL COOLING AND METHODS OF MANUFACTURE - A manufacturing method includes providing a substrate with an outer surface and at least one interior space and machining the substrate to selectively remove a portion of the substrate and define one or more cooling supply holes therein. Each of the one or more cooling supply holes is in fluid communication with the at least one interior space. The method further includes disposing an open cell porous metallic layer on at least a portion of the substrate. The open cell porous metallic layer is in fluid communication with the one or more cooling supply holes. A coating layer is disposed on the open cell porous metallic layer. The coating layer having formed therein one or more cooling exit holes in fluid communication with the open cell porous metallic layer. The substrate, the one or more cooling supply holes, the open cell porous metallic layer and the cooling exit holes providing a cooling network for a component. | 06-19-2014 |
| 20140193240 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 07-10-2014 |
| 20140193241 | INTERNALLY COOLABLE COMPONENT FOR A GAS TURBINE WITH AT LEAST ONE COOLING DUCT - An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators. | 07-10-2014 |
| 20140205436 | Sealed Rotor Valve Engine - A rotary engine powered by external heat with a gas that is reactive to temperature sealed inside a casing where a portion, of the sealed in gas is heated and expands within a chamber on one side of the engine and is separated by a partition from another portion of the gas which is cooled and contracts within a chamber on the opposite side of the engine as the heated gas pushes the partition which rotates a rotor while simultaneously the cooled gas pulls the partition and every 180° of rotation the heated gas moves over the rotor to the cooling side of the engine while the cooled gas moves under the rotor through a valve to the heating side of the engine. | 07-24-2014 |
| 20140212271 | DENTAL HANDPIECE STRUCTURE - Disclosed is a dental handpiece structure including a head having a turbine chamber, a rotor installed in the turbine chamber and having a transmission shaft, and a transmission element composed of a plurality of turbine vanes. A high-pressure air entering into the turbine chamber can push each turbine vane to drive and rotate the rotor, and a breach is upwardly formed between two adjacent turbine vanes. A head cap is covered onto the turbine chamber, and a circular groove is formed at the head cap and between an end surface facing the turbine chamber and the transmission element, and the circular groove and each breach are arranged opposite to each other for collecting the high-pressure air guided out from each breach to enhance the cutting force of the dental hand-piece. | 07-31-2014 |
| 20140219779 | SUPERCHARGER - An inlet portion ( | 08-07-2014 |
| 20140219780 | COOLING STRUCTURE FOR TURBOMACHINE - A cooling structure for a turbomachine. In one embodiment, the cooling structure is for a seal slot of the turbomachine. The cooling structure includes a body coupled to a surface of the seal slot. The body includes a passageway on a first surface of the body for providing a cooling fluid to the seal slot. In an other embodiment, a apparatus includes a first component and a second component adjacent the first component. The apparatus also includes a seal slot extending between the first component and the second component, and a cooling structure positioned within the seal slot. The cooling structure includes a body coupled to a surface of the seal slot. The body has a passageway on a first surface of the body for providing a cooling fluid to the seal slot. | 08-07-2014 |
| 20140234076 | OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE - A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine. | 08-21-2014 |
| 20140234077 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas. | 08-21-2014 |
| 20140271130 | AIR FRESHENING SYSTEM AND METHOD - An airflow fan accessory comprising an accessory having a scented fabric and a fastening mechanism located along the outer edge of the scented fabric. In a preferred embodiment, the accessory may be easily attached to and detached from the fan blade enclosure of any typical airflow fan. Upon air flow through the fan and airflow fan accessory, a pleasant scent may be imparted to the room via release of scent from the scented fabric component. | 09-18-2014 |
| 20140271131 | TRENCHED COOLING HOLE ARRANGEMENT FOR A CERAMIC MATRIX COMPOSITE VANE - One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component. | 09-18-2014 |
| 20140286751 | COOLED TURBINE RING SEGMENTS WITH INTERMEDIATE PRESSURE PLENUMS - A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel. A plurality of cooling fluid feed passages supply cooling fluid to the intermediate plenum, and a plurality of convective cooling passages extend through the panel from the intermediate plenum to one of the leading and trailing edges for cooling the inner side of the panel. The intermediate plenum is located in axial alignment with and defines an area of reduced thermal mass receiving impingement cooling adjacent to the hook structure. | 09-25-2014 |
| 20140321981 | TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM - A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart. | 10-30-2014 |
| 20140334915 | Air Bleed System for an Axial Turbomachine - The present application relates to a bladed stator of a turbomachine compressor, configured to straighten an annular stream of the turbomachine. The stator includes at least one annular wall configured to define the annular stream, a row of blades extending radially from the annular wall and means of pressurizing in communication with the annular stream. The means of pressurizing are configured to pressurize a chamber which is separated from a lubrication housing by a labyrinth seal. The means of pressurizing comprise at least one passage extending through the thickness of the annular wall and connecting with the annular stream. The means of pressurizing further includes at least one scoop in communication with the passage and the annular stream. The scoop is open upstream so as to capture the dynamic pressure of the annular stream. | 11-13-2014 |
| 20140341711 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust. | 11-20-2014 |
| 20140348637 | INTERFACE DEVICE BETWEEN TWO TURBOMACHINE ELEMENTS - The main purpose of the invention is an interface device ( | 11-27-2014 |
| 20140348638 | POWER HARVESTING BEARING CONFIGURATION - A power generating bearing assembly providing a bearing retained by a bearing housing. The bearing housing includes a bearing cooling passage system having at least one integrated liquid cooling passage integrated within the bearing housing. A turbine receiving bore is formed through the bearing housing, penetrating the integrated liquid cooling segment. A turbine assembly is inserted into the turbine receiving bore, positioning a turbine blade subassembly of the turbine assembly within the integrated liquid cooling passage, wherein fluid flowing within the integrated liquid cooling passage causes the blade subassembly to rotate. The rotation of the blade subassembly rotates an electric power generator to create electric power. The turbine assembly can include an electro-magnetic subassembly mounting plate, wherein the turbine subassembly is located on an interior surface of the mounting plate and at least a portion of the power generating portion located on an exterior portion of the mounting plate. | 11-27-2014 |
| 20140369812 | TURBINE ENGINE NACELLE FITTED WITH A HEAT EXCHANGER - A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle. | 12-18-2014 |
| 20150023778 | MICRO GAS TURBINE SYSTEM WITH A PIPE-SHAPED RECUPERATOR - A micro gas turbine system ( | 01-22-2015 |
| 20150037140 | THERMAL ACTUATOR INCLUDING FLUID WITH HIGH TEMPERATURE STABILITY - A thermal actuator is provided and includes an expansion material disposed and configured to move a movable element from a first movable element position toward a second movable element position in accordance with an expansion condition of the expansion material. The expansion material includes an inorganic salt mixture or a metal oxide mixture. | 02-05-2015 |
| 20150044030 | Long-Duct, Mixed-Flow Nozzle System for a Turbofan Engine - A long-duct mixed-flow nozzle system for a turbofan engine, the nozzle system may include an inner housing configured to enclose a core and form a core flow duct, the inner housing terminating in a core nozzle having a core exit aperture, an outer housing forming a fan flow duct and terminating in a fan exit aperture at a location downstream of the core exit aperture, the fan exit aperture having a plurality of chevrons, and the core exit aperture having a plurality of chutes separated by radially extending lobes configured to mix exhaust gas from the core flow duct with bypass gas flow in the fan flow duct, the radially extending lobes varying in profile from each other. | 02-12-2015 |
| 20150063983 | TURBOMACHINE - A turbomachine having a cooling device for supplying cooling air onto a compressor region from an air distribution chamber is disclosed, the air distribution chamber being arranged between an outlet diffuser of a compressor and a combustion chamber, where the cooling device has cooling air pipes for supplying cooling air from the air distribution chamber into a cavity between the outlet diffuser and a rotor segment of the compressor. | 03-05-2015 |
| 20150071763 | OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE - A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path. | 03-12-2015 |
| 20150078887 | DISC SHAFT CENTER ADJUSTING MECHANISM IN GAS TURBINE - In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit. | 03-19-2015 |
| 20150118022 | RE-USE OF INTERNAL COOLING BY MEDIUM IN TURBINE HOT GAS PATH COMPONENTS - In one example, an arcuate segment for a ring-shaped, rotary machine component such as a stator nozzle or bucket shroud, includes a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between the segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies. A cooling channel is provided in the segment body in proximity to the seal slot, and is adapted to be supplied with cooling air. A passage extends from the cooling channel into the seal slot, at a location where the cooling air can be supplied to the higher pressure area on the radially-outer side of the seal. | 04-30-2015 |
| 20150125265 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 05-07-2015 |
| 20150125266 | Steam Turbine Equipment - Steam turbine equipment is provided that can sharply adjust power generation output based on a variation in power demand while improving power generation efficiency during operation at a rated power generation output. | 05-07-2015 |
| 20150132107 | ROTOR COOLING - Embodiments of the invention relate generally to rotor cooling and, more particularly, to a stator member having at least one passage for the delivery of cooling steam to a bucket root. In one embodiment, the invention provides a turbine comprising: a rotor including a first bucket root; and a stator member having: a rotor bore within which at least a portion of the rotor is disposed; a facing end adjacent to the first bucket root of the rotor; a plurality of seals within the rotor bore for sealing against the rotor, the plurality of seals including a first seal nearest the facing end and a second seal adjacent to the first seal; and a plurality of passages, each extending from a surface of the rotor bore at a point between the first seal and the second seal and extending through the facing end. | 05-14-2015 |
| 20150139782 | AIR SEPARATOR FOR GAS TURBINE ENGINE - An air separator in a gas turbine engine includes a cylindrical member and a seal flange having a flange body extending radially outward at a rearward end of the cylindrical member. A head portion is located at a radially outer free end of the flange body and includes an axial flange located axially rearward of the flange body and defining a rearward seal face for engagement with a blade disc forward face, and a forward cantilevered head mass extending axially forward from the flange body. An axial dimension of the head mass, from a connection with the forward side of flange body to an axially forward face of the head mass, is greater than a maximum radial dimension of the head mass, from a radially inner side of the head mass to a radially outermost side of the head mass. | 05-21-2015 |
| 20150139783 | Thermal protection device for equipment in a turbomachine engine compartment - A thermal protection device for equipment ( | 05-21-2015 |
| 20150139784 | Annular Cover Delimiting a Turbomachine Lubrication Chamber - The present application relates to an annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibres. The present application also relates to a turbomachine including a compressor linked to a turbine via a transmission shaft, an intermediate fan casing, and a bearing joining the transmission shaft to the intermediate casing. The casing is placed in a lubrication chamber delimited by an annular chamber cover, a chamber casing carrying the bearing and the cover. | 05-21-2015 |
| 20150139785 | BEARING SUPPORT HAVING A GEOMETRY FOR EASIER EVACUATION OF CASTING CORES - The invention relates to a turbomachine bearing support ( | 05-21-2015 |
| 20150292352 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING AN AIR FLOW VALVE WITH A VARIABLE FLOW RATE - A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°. | 10-15-2015 |
| 20150292517 | SWIRL INDUCING BEARING HOUSING SPACER AND CORE - A turbocharger ( | 10-15-2015 |
| 20150300180 | GAS TURBINE ENGINE TURBINE BLADE TIP WITH COATED RECESS - A blade for a gas turbine engine includes an airfoil that has a tip with a terminal end surface. The terminal end surface includes a recess that has a depth of less than 40 mils (1.016 mm). The recess is filled with a thermal barrier coating. The recess is without any cooling holes. | 10-22-2015 |
| 20150300192 | GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF - Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine. | 10-22-2015 |
| 20150300201 | METHOD OF REDUCING MANUFACTURING VARIATION RELATED TO BLOCKED COOLING HOLES - A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed. | 10-22-2015 |
| 20150300203 | TURBINE HOUSING - A turbine housing includes a scroll passage, a medium passage, an exhaust introduction passage, and a partition wall. The scroll passage extends spirally and is located outside a turbine wheel. The scroll passage includes a spiral beginning and a spiral end. The exhaust introduction passage is connected to the spiral beginning and introduces the exhaust into the scroll passage. The partition wall is located between the spiral end and the exhaust introduction passage and extends in the circumferential direction of the turbine wheel. The medium passage includes a start section that includes an adjacent portion. The adjacent portion is adjacent to the partition wall in the direction of the rotation axis of the turbine wheel. The start section includes an inlet that introduces the cooling medium into the medium passage. | 10-22-2015 |
| 20150300257 | GAS TURBINE ENGINE COMPONENT ARRANGEMENT - A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided. | 10-22-2015 |
| 20150303772 | Device For The Air-Cooling Of A Blower For A Heating, Ventilation Or Air-Conditioning Apparatus | 10-22-2015 |
| 20150308282 | ROTOR BLADE TIP CLEARANCE CONTROL - A gas turbine engine comprising first and second axially spaced turbine rotor stages ( | 10-29-2015 |
| 20150315929 | GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION - An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway. | 11-05-2015 |
| 20150315930 | REDUCING VARIATION IN COOLING HOLE METER LENGTH - An airfoil body includes an airfoil wall defined between an internal cavity surface and an external airfoil surface. A pad extends from the internal cavity surface. A cooling hole extends from the external airfoil surface, through the airfoil wall and through the pad for fluid communication through the airfoil wall. | 11-05-2015 |
| 20150322866 | Enhanced Turbine Cooling System Using a Blend of Compressor Bleed Air and Turbine Compartment Air - The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, a turbine compartment with a turbine compartment air flow, a turbine, and an eductor. The eductor blends the compressor bleed air flow and the turbine compartment air flow into a blended air flow for use in cooling the turbine. | 11-12-2015 |
| 20150330249 | FRAME STRUT COOLING HOLES - A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts, and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a plurality of film cooling holes formed through a circumferentially facing wall of each strut at a location distal from the outer frame junction. | 11-19-2015 |
| 20150330306 | GAS GENERATOR WITH MOUNT HAVING AIR PASSAGES - A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations. | 11-19-2015 |
| 20150337680 | TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN - Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint. | 11-26-2015 |
| 20150345317 | DOUBLE TUBE CONNECTING DEVICE - The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube ( | 12-03-2015 |
| 20150345328 | HOLDING DEVICE OF A COOLING TUBE FOR A TURBOJET CASING - A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube. | 12-03-2015 |
| 20150345335 | Instrumented flow passage of a turbine engine - The invention relates to an annular air flow passage ( | 12-03-2015 |
| 20150369068 | GAS TURBINE TRANSITION PIECE AFT FRAME ASSEMBLIES WITH COOLING CHANNELS AND METHODS FOR MANUFACTURING THE SAME - Aft frame assemblies for a gas turbine transition pieces include a body comprising an exterior surface and a plurality of interior surfaces, one or more exterior cooling holes disposed on the exterior surface of the body for capturing compressor discharge air outside of the transition piece, and a supplemental component bonded to at least one of the plurality of interior surfaces of the body. At least one cooling channel is at least partially defined by the supplemental component and the interior surface that the supplemental component is bonded to, wherein the at least one cooling channel fluidly connects at least one of the one or more exterior cooling holes to one or more interior cooling outlets that discharge the compressor discharge air captured from the at least one of the one or more exterior cooling holes. | 12-24-2015 |
| 20150377132 | NACELLE EQUIPPED WITH AN OIL-COOLING CIRCUIT COMPRISING AN INTERMEDIATE HEAT EXCHANGER - The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air. | 12-31-2015 |
| 20160003082 | CONTOURED BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position. | 01-07-2016 |
| 20160003100 | ROLLING ELEMENT BEARING CONFIGURED WITH A GUTTER AND ONE OR MORE FLUID PASSAGES - A rolling element bearing includes a plurality of rolling elements that are arranged circumferentially around an axis, and radially between a bearing inner ring and a bearing outer ring. The inner ring extends axially between a first end and a second end, and includes a plurality of passages that are fluidly coupled with a channel. The passages are arranged circumferentially around the axis. The channel extends axially into the inner ring from the second end, and includes a gutter that extends radially into and axially within the inner ring. | 01-07-2016 |
| 20160003151 | TURBINE CASE COOLING SYSTEM - A turbine case cooling system including a turbine assembly having an inlet and an outlet and surrounded by a turbine casing. The turbine case cooling system is arranged to selectively impingement cool at least part of the turbine casing. The system includes an annular structure that is radially spaced from the turbine casing and includes a downstream end. The system includes an annular duct that is spaced radially outwardly from the turbine casing and radially inwardly from the annular structure. The duct is sealingly coupled to the turbine casing at a first end towards the turbine inlet, and a second end extends axially towards the downstream end of the annular structure and the turbine outlet. | 01-07-2016 |
| 20160009399 | HYBRID COMPRESSOR BLEED AIR FOR AIRCRAFT USE | 01-14-2016 |
| 20160030786 | Pump Assemblies And Methods For Inhibiting Oxygen From Entering Water Supply Systems - A method of inhibiting oxygen in ambient air from entering a water supply system having at least one ingress point at which a fluid can enter the water supply system includes supplying an inert gas to the at least one ingress point of the water supply system. The inert gas enters the water supply system at the at least one ingress point and substantially inhibits ambient air including oxygen from entering the water supply system at the at least one ingress point to substantially inhibit oxygen corrosion in the water supply system. Example pump assemblies for coupling to water supply systems, piping networks, and water-based fire sprinkler systems for inhibiting ambient air, including oxygen it may contain, from entering the systems are also disclosed. | 02-04-2016 |
| 20160032764 | GAS TURBINE ENGINE END-WALL COMPONENT - An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes ( | 02-04-2016 |
| 20160040685 | WATER COOLING FAN WITH MULTIPLE AIR OUTLETS - A water cooling fan with multiple air outlets includes a housing having two opposite sides respectively formed with an air inlet and a first air outlet, and its topside bored with at least one second air outlet. An evaporative cooling pad is provided in the interior of the housing and an air discharge tube is installed at the location of the second air outlet of the housing. Thus, the water cooling fan of this invention can carry out cooling and temperature modulation to a designated region via the first air outlet and simultaneously can make use of the air discharge tube to carry out heat dissipation to respective mechanical equipment or a person. Therefore, the water cooling fan with multiple air outlets of this invention is excellent in heat dissipation speed and cooling effect, able to enhance efficiency of mechanical equipment in factory and efficacy of energy saving. | 02-11-2016 |
| 20160047249 | METHOD OF FORMING AN INFLATED AEROFOIL - There is proposed a method of forming an inflated aerofoil ( | 02-18-2016 |
| 20160047264 | BLADE OUTER AIR SEAL HAVING PARTIAL COATING - A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating. | 02-18-2016 |
| 20160047271 | DUCTING PLATFORM COVER PLATE - The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge. | 02-18-2016 |
| 20160061111 | GAS TURBINE SUBASSEMBLY - The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing ( | 03-03-2016 |
| 20160069198 | CASTING OPTIMIZED TO IMPROVE SUCTION SIDE COOLING SHAPED HOLE PERFORMANCE - A gas turbine engine component includes a pressure side, a suction side, a leading edge, a trailing edge, an outer surface and an inner surface. The inner surface is positioned within the outer surface and defines a core. The inner surface has a first protrusion. | 03-10-2016 |
| 20160076390 | MOUNTING AND SEALING ARRANGEMENT FOR A GUIDE VANE OF A GAS TURBINE - The invention relates to a mounting and sealing arrangement for a guide vane of a gas turbine, which includes a vane carrier for carrying said vanes in a ring-like arrangement, whereby the vanes each comprise an airfoil and an outer diameter platform. The thermal stress is reduced and lifetime improved by providing a separate intermediate mounting element between the vane carrier and the outer diameter platform of each of the vanes, and mounting the intermediate mounting element with an outer side on the vane carrier, whereby the intermediate mounting element abuts with an inner side on the outer diameter platform in a sealing fashion. | 03-17-2016 |
| 20160084095 | DIAPHRAGM ASSEMBLY WITH A PRESWIRLER - A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring. The outer ring includes an outer ring face, a first contact protrusion, and a second contact protrusion. The first and second contact protrusions are spaced apart and extend from an outer body portion at the outer ring face. The inner ring is located inward from the outer ring. The inner ring includes an inner ring face and a third contact protrusion. The third contact protrusion extends in from an inner body portion and at the inner ring face. | 03-24-2016 |
| 20160123152 | AIR SEPARATOR FOR A TURBINE ENGINE - An air separator for a turbine engine is provided. The air separator includes an aft air separator member ( | 05-05-2016 |
| 20160123186 | SHROUD ASSEMBLY FOR A TURBINE ENGINE - A shroud assembly for a turbine engine includes a shroud in thermal communication with a hot combustion gas flow and a baffle overlying the shroud to define a space. At least one separator is provided in the space such that a cooling fluid flow passing through the baffle is separated along two different flow paths. | 05-05-2016 |
| 20160130976 | TURBINE-END BEARING SUPPORT AND COOLING SYSTEM - A turbocharger ( | 05-12-2016 |
| 20160130980 | GAS TURBINE ENGINE AND FRAME - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine frames. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 05-12-2016 |
| 20160137291 | MODULAR PLENUM AND DUCT SYSTEM FOR CONTROLLING BOUNDARY LAYER AIRFLOW - A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system. | 05-19-2016 |
| 20160146225 | WASHER PUMP APPARATUS FOR VEHICLE PROVIDED WITH IMPROVED WATER-PROOF STRUCTURE - Provided is a washer pump apparatus for a vehicle, the washer pump apparatus having an improved waterproof structure. The water pump apparatus includes a pump housing including a washer liquid inlet, a washer liquid outlet, a closed lower portion, an impeller, and a motor configured to rotate the impeller, a terminal cap coupled to an upper portion of the pump housing and forming a waterproof structure, the terminal including a structure for connection to a waterproof connector, and an air vent for communication of an outer space of the terminal cap with an inner space, wherein a membrane member including multiple pores that block water molecules and allow passage of air molecules therethrough is placed in the air vent. | 05-26-2016 |
| 20160153281 | COMPONENTS WITH COMPOUND ANGLED COOLING FEATURES AND METHODS OF MANUFACTURE | 06-02-2016 |
| 20160153309 | AIRCRAFT TURBOMACHINE HAVING AN AIR INLET OF VARIABLE SECTION | 06-02-2016 |
| 20160167792 | AIRCRAFT ANTI-ICING SYSTEM | 06-16-2016 |
| 20160169027 | TIP CLEARANCE CONTROL FOR TURBINE BLADES | 06-16-2016 |
| 20160169038 | COOLING FEATURE FOR A TURBINE ENGINE COMPONENT | 06-16-2016 |
| 20160169039 | SLOTS FOR TURBOMACHINE STRUCTURES | 06-16-2016 |
| 20160186605 | SHROUD ASSEMBLY FOR A TURBINE ENGINE - A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow. | 06-30-2016 |
| 20160186606 | GAS TURBINE ENGINE DUCT ASSEMBLY - A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages. | 06-30-2016 |
| 20160194979 | CANTED BOAS INTERSEGMENT GEOMETRY | 07-07-2016 |
| 20160195103 | TURBO MACHINE HAVING A SEALING UNIT, MAINTENANCE METHOD, AND ASSOCIATED MAINTENANCE DEVICE | 07-07-2016 |
| 20160201492 | TANGENTIAL ON-BOARD INJECTION VANES | 07-14-2016 |
| 20160201507 | ENGINE COMPONENT FOR A GAS TURBINE ENGINE | 07-14-2016 |
| 20160376901 | TURBINE SHROUD SEGMENT WITH FLANGE-FACING PERIMETER SEAL - A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 12-29-2016 |
| 20160376921 | TURBINE SHROUD SEGMENT WITH INTEGRATED COOLING AIR DISTRIBUTION SYSTEM - A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 12-29-2016 |
| 20160376993 | DRAG LINK FITTING AND VENT COMBINATION - A nacelle is disclosed. The nacelle may comprise, in various embodiments, a drag link fitting mounted to an Inner Fixed Structure (IFS) and pivotally attached to an end of a drag link, and a vent defining a passageway through the IFS to bring cooling air through the IFS. The drag link fitting may be aerodynamically associated with the vent such that the drag link fitting helps direct air into the vent. | 12-29-2016 |
| 20170234135 | GAS TURBINE | 08-17-2017 |
| 20170234156 | GAS TURBINE HAVING AN ANNULAR PASSAGE SUBDIVIDED INTO ANNULUS SECTORS | 08-17-2017 |
| 20180023404 | RING SEGMENT SYSTEM FOR GAS TURBINE ENGINES | 01-25-2018 |
| 20180023511 | EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES | 01-25-2018 |
| 20220136511 | FLUID PUMP AND OUTLET CHECK VALVE ASSEMBLY THEREOF - A fluid pump includes a housing; an inlet passage; an outlet conduit; a pumping element within the housing; and a check valve assembly. The check valve assembly includes a valve stem within the outlet conduit such that a flow path is created radially between the outlet conduit and the valve stem, the valve stem moving along a check valve assembly axis between a closed position and an open position. The flow path includes a first restriction which increases velocity of fluid passing through the flow path; a first expansion, downstream of the first restriction, which decreases velocity of fluid passing through the flow path; a second restriction, downstream of the first expansion, which increases velocity of fluid passing through the flow path; and a second expansion, downstream of the second restriction, which decreases velocity of fluid passing through the flow path. | 05-05-2022 |
