| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415178000 | Working fluid on at least one side of heat exchange wall | 66 |
| 20080273968 | System for regulating a cooling fluid within a turbomachine - A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to the at least one wheelspace area. The system may also include a plurality of bypass plugs, wherein each of the plurality of bypass plugs is insertable into a bypass chamber opening on each of the plurality of bypass chambers. | 11-06-2008 |
| 20080310955 | Hybrid cooling of a gas turbine engine - A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component. | 12-18-2008 |
| 20090081029 | Gas Turbine Component with Reduced Cooling Air Requirement - Introducing a plurality of geometrically shaped members ( | 03-26-2009 |
| 20090097972 | Gas Turbine Engine Systems and Related Methods Involving Heat Exchange - Gas turbine engine systems and related methods involving heat exchange are provided. In this regard, a representative heat exchange system for a gas turbine engine includes: a heat exchanger; and a flow restrictor operative to selectively restrict a flow of gas flowing along an annular gas flow path; in an open position, the flow restrictor enabling gas to flow along the gas flow path and, in a closed position, the flow restrictor restricting the flow of gas such that at least a portion of the gas is provided to the heat exchanger, the heat exchanger being located radially outboard of the flow restrictor. | 04-16-2009 |
| 20090104029 | Flow Machine - A flow machine is described having a first space adapted to contain a hot fluid and delimited by a wall. The wall having a first wall surface facing the first space and a second wall surface turned away from the first space. Cooling is provided for a region of the wall by supplying a relatively cool fluid onto the second wall surface. The cooling means includes a supply chamber containing the second fluid, a cavity adjacent the second wall surface, at least one duct, which has an inlet opening at the supply chamber and an outlet opening at the cavity for conveying the cool fluid to the cavity, and a deflection surface facing the cavity. | 04-23-2009 |
| 20090238684 | Cooling arrangement for CMC components with thermally conductive layer - A CMC wall ( | 09-24-2009 |
| 20090252603 | AIRFOIL FOR NOZZLE AND A METHOD OF FORMING THE MACHINED CONTOURED PASSAGE THEREIN - A nozzle in which an airfoil includes a pressure surface and a suction surface that join at substantially opposing chordal ends of the airfoil to form a leading edge of the airfoil and a trailing edge of the airfoil. A trailing edge passage is defined through the airfoil through which coolant flows. The trailing edge passage is proximate to the trailing edge of the airfoil and has a contoured shape that conforms to that of the trailing edge. | 10-08-2009 |
| 20090324397 | Gas Turbine Engine With Insulated Cooling Circuit - A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at least one rotor disposed in the compression chamber, the at least one stator comprising a stator body having a plurality of tubes for transporting cooling air through passages in the stator body into the compression chamber. The plurality of tubes are surrounded by an air gap for insulating the tubes from the stator body. | 12-31-2009 |
| 20100028139 | TURBOJET FOR AIRCRAFT - A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine. | 02-04-2010 |
| 20100028140 | HEAT PIPE INTERCOOLER FOR A TURBOMACHINE - A turbomachine includes a compressor having an intake portion and an outlet portion. The compressor compresses air received at the intake portion to form a compressed airflow that is passed from the outlet portion. The turbomachine also includes an intercooler operatively connected downstream from the compressor. The intercooler includes a plurality of heat pipes that are configured to extract heat from the compressed airflow. | 02-04-2010 |
| 20100054926 | SYSTEM AND METHOD FOR THERMAL MANAGEMENT OF A GAS TURBINE INLET - A thermal management system includes: a turbine assembly including an inlet housing, a compressor in fluid communication with the inlet housing, a power turbine in fluid communication with the compressor, and an exhaust assembly in fluid communication with the power turbine; and at least one heat pipe having a first portion disposed in thermal communication with the inlet housing and a second portion disposed in thermal communication with the exhaust assembly, the at least one heat pipe configured to transfer thermal energy from the exhaust assembly to at least one of input gas entering the inlet housing and at least one component of the inlet housing. | 03-04-2010 |
| 20100074736 | Thermal management system - In one embodiment a gas turbine engine is disclosed having a heat exchanger at least partially disposed in a bypass duct. In one form the gas turbine engine is a high bypass ratio engine. The heat exchanger may be coupled with a directed energy weapon to provide coolant flow and regulate the temperature of the directed energy weapon. Other devices may also be coupled with the heat exchanger, either as an alternative to in addition to the directed energy weapon. | 03-25-2010 |
| 20100092280 | Steam Cooled Direct Fired Coal Gas Turbine - A gas turbine includes a combustor configured to burn a hydrocarbon fuel input and provide a combustion product hot gas output to a turbine inlet having a turbine inlet temperature exceeding about 2200° F., the hot gas output also includes ash in an amount of 0.1% or more by weight of the hydrocarbon fuel input. The turbine also includes a stationary nozzle configured to receive the hot gas output that includes a plurality of circumferentially spaced vanes and a vane cooling circuit located within vane sidewalls configured for circulation of steam as a coolant. The turbine also includes a rotatable rotor configured to receive the hot gas output exiting the nozzle that includes a plurality of buckets and a bucket cooling circuit located within the bucket sidewalls and shank that is configured for circulation of steam as a coolant for the bucket. | 04-15-2010 |
| 20100119360 | Heatable part of a pump housing - The description relates to a heatable pump housing part comprising a heat distribution sheet fixed on the housing part and a tubular heating element fixed on the heat distribution sheet. According to the invention the tubular heating element is positioned in a groove or a step on the housing part that is covered by the heat distribution sheet. | 05-13-2010 |
| 20100226762 | Structural members in a pedestal array - A turbine engine component has a flow path wall and a support wall. The turbine engine component has at least one cooling compact heat exchanger. Each cooling compact heat exchanger has a pedestal array and at least one structural member within the pedestal array for preventing modal crossing in operation range, for preventing panel bulging, and/or for connecting the flow path wall to at least one outer diameter support structure. | 09-09-2010 |
| 20100284800 | TURBINE NOZZLE WITH SIDEWALL COOLING PLENUM - A turbine nozzle segment includes an outer band portion, an inner band portion, and at least one nozzle vane extending between the band portions. A cooling plenum is defined in a mating side face of at least one of the band portions and extends transversely at least partially through the respective band portion. First and second cooling passages extend from the cooling plenum to respective first and second cooling chambers. | 11-11-2010 |
| 20100303616 | COOLING SYSTEM FOR AN AERO GAS TURBINE ENGINE - A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone. | 12-02-2010 |
| 20110085895 | OIL TUBE WITH INTEGRATED HEAT SHIELD - A gas turbine engine has an oil tube for delivering oil through a high temperature zone of the engine to an engine component for cooling and lubrication. An insulation tube surrounds the oil tube and extends in a substantial length of the oil tube. The opposed ends of the insulation tube are integrally and sealingly connected to respective end portions of the oil tube to form a dead air annulus between the oil tube and the insulation tube. | 04-14-2011 |
| 20110135455 | OIL COOLER - An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by: (I) diverting air flow from the inner side of the oil cooler towards the outer side of the oil cooler, (ii) enhancing heat exchange performance at the leading edge of the cooler, and/or (iii) suppressing airflow wake at the trailing edge of the cooler. | 06-09-2011 |
| 20110150637 | Radial fan - A radial fan, preferably a high-speed radial fan, includes a blower wheel, a housing which receives a rotor and a stator of an electrical drive of the blower wheel shaft, and a cooling system. To develop one such radial fan in terms of the cooling system required, paths for a first cooling medium and a second cooling medium are provided in the housing, the second cooling medium being cooled by the first cooling medium as provided for by the housing, and the paths are separated from each other by intact material walls of the housing. | 06-23-2011 |
| 20110182723 | TURBOMACHINE AIRCRAFT PROPELLER - The invention relates to an aircraft propeller ( | 07-28-2011 |
| 20110189000 | SYSTEM FOR REGULATING A COOLING FLUID WITHIN A TURBOMACHINE - Embodiments of the present invention provide a system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to a wheelspace area. The system includes a plurality of angular passages that aid in the mixing of a cooling fluid with a working fluid in the wheelspace area. | 08-04-2011 |
| 20110274536 | STEAM TURBINE - A plurality of blades are studded in a rotor disc integrated with the rotor along the circumferential direction of the rotor, a plurality of vanes are attached to a casing covering the rotor along the circumferential direction of the rotor, and an internal diaphragm disposed on rotor-side surfaces of the vanes in such a way that the internal diaphragm faces the rotor disc. The vanes and the blades adjacent to each other in the axial direction of the rotor form a turbine stage. A rotor-side cooling path is formed through the rotor disc in the axial direction of the rotor, and a diaphragm-side cooling path is formed through the internal diaphragm in the axial direction of the rotor, and a cooling medium flowing through the rotor-side cooling path diverts into the diaphragm-side cooling path and a labyrinth flow path provided between the internal diaphragm and the rotor. | 11-10-2011 |
| 20110305560 | COOLING DEVICE FOR COOLING THE SLOTS OF A TURBOMACHINE ROTOR DISK DOWNSTREAM FROM THE DRIVE CONE - The invention relates to a cooling device for cooling the slots of a turbomachine rotor disk, the turbomachine comprising an upstream rotor disk having a fastener flange with a periphery that is festooned, a downstream rotor disk, an endplate for holding blades and arranged around the ring of the downstream disk and co-operating therewith to form an air diffusion cavity, a cone for driving disks in rotation, the cone having a fastener flange with a periphery that is festooned, and a plurality of bolted connections passing from upstream to downstream through the solid portions of the fastener flanges of the upstream disk and of the cone, the fastener flange of the endplate, and the fastener flange of the downstream disk. The fastener flange of the endplate is pierced by ventilation orifices opening out into the air diffusion cavity in order to feed it with cooling air, said cavity opening out into the slots of the downstream disk at their upstream ends in order to cool them. | 12-15-2011 |
| 20120034075 | COOLING ARRANGEMENT FOR A TURBINE COMPONENT - A cooled component wall ( | 02-09-2012 |
| 20120039708 | GAS TURBINE ENGINE - A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side. | 02-16-2012 |
| 20120057967 | GAS TURBINE ENGINE - A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid channel between the shaft cover structure and the support structure. The support structure provides structural support for the shaft cover structure and receives cooling fluid from the diffuser section. One of the diffuser section and the support structure comprises a plurality of apertures through which at least a portion of the cooling fluid passes. The cooling fluid channel is in fluid communication with the apertures in the one of the diffuser section and the support structure for supplying cooling fluid to a blade disc structure located in a turbine section of the engine. | 03-08-2012 |
| 20120057968 | RING SEGMENT WITH SERPENTINE COOLING PASSAGES - A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system. | 03-08-2012 |
| 20120063891 | COOLED COMPONENT FOR A GAS TURBINE - A cooled component for a gas turbine is disclosed, which by an outer side of a wall delimits hot gas passage of the gas turbine and on an inner side has a device for impingement cooling. The impingement cooling device can include a multiplicity of impingement cooling chambers which are arranged next to each other, operate in parallel, are covered by impingement cooling plates which are equipped with impingement cooling holes, and are impinged upon by cooling air during operation. | 03-15-2012 |
| 20120076644 | COOLED COMPONENT WALL IN A TURBINE ENGINE - A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion. | 03-29-2012 |
| 20120087782 | GAS TURBINE - A gas turbine includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit. A blade is attached to the rotor and includes a blade tip having at least one dust hole. An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip. A blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove. The blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction. A hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip. | 04-12-2012 |
| 20120099974 | Methods for cooling a carrier fluid of an electric power plant, electric power plants and cooling system - A method for cooling a carrier fluid is provided. The carrier fluid is used to drive a turbine in an electric power plant. According to a first embodiment, at least part of a cooling process is performed by leading the carrier fluid and/or a cooling fluid for cooling the carrier fluid underground a soil to a depth in which the soil is substantially cooler than the ambient air. According to a second embodiment, at least part of a cooling process is performed by supplying at least some of the carrier fluid, and/or at least some of a cooling fluid used to cool the carrier fluid, from a cold storage which stores fluid at a significantly lower temperature than the temperature of the carrier fluid in the turbine. | 04-26-2012 |
| 20120114467 | GAS TURBINE ENGINE HEAT EXCHANGER WITH TAPERED FINS - A heat exchanger for a gas turbine engine includes first and second opposing sides enclosing a cavity. A first set of fins is supported on the first side and arranged outside the cavity. The fins have leading and trailing edges respectively including first and second heights. The first height is less than the second height. In one application, the heat exchanger is arranged in a gas turbine engine. A core is supported relative to a fan case. The core includes a core nacelle and a fan case. A fan duct is provided between the core nacelle and the fan case. A heat exchanger includes fins arranged in a fan duct. The fins are oriented such that the shorter leading edge faces into the airflow. | 05-10-2012 |
| 20120114468 | GAS TURBINE ENGINE HEAT EXCHANGER FINS WITH PERIODIC GAPS - A heat exchanger for a gas turbine engine is provided by a structure including an enclosed fluid cavity. The structure has opposing sides, and a set of fins is supported on one of the sides and arranged outside the cavity. The set of fins includes rows of discrete chevron fins separated by periodic gaps. In one application, the heat exchanger is arranged in a gas turbine engine. A core is supported relative to a fan case by structure. A fan duct is provided between a core nacelle and a fan case. The core includes a compressor section and a bleed cavity is provided within the core and is in fluid communication with the compressor section. The heat exchanger includes first and second sides opposite one another. The second side includes the set of rows of fins with the periodic gaps exposed to the bleed cavity. | 05-10-2012 |
| 20120128472 | TURBOMACHINE NOZZLE SEGMENT HAVING AN INTEGRATED DIAPHRAGM - A turbomachine nozzle segment includes a vane having a first end extending to a second end through an airfoil portion. An outer member is positioned at the first end of the vane. The outer member includes a mounting element configured and disposed to secure the turbomachine nozzle segment to a turbomachine. An inner member is positioned at the second end of the vane. The inner member includes an upstream section and a downstream section. An upstream diaphragm member extends substantially radially outwardly from the inner member at the upstream section, and a downstream diaphragm member extends substantially radially outwardly from the inner member at the downstream section. Each of the upstream diaphragm member and down stream member includes an outer surface and an inner surface. One of the outer surface and inner surface of each of the upstream diaphragm member and downstream diaphragm member includes a cartridge mounting member. | 05-24-2012 |
| 20120134788 | LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN - The invention relates to a low pressure turbine ( | 05-31-2012 |
| 20120251304 | LOW PRESSURE STEAM TURBINE - The invention provides a low-pressure steam turbine ( | 10-04-2012 |
| 20130034429 | BLADE OR VANE FOR A TURBOMACHINE - A blade or a vane component of a turbomachine includes an inner space between two opposite inner walls of the component, and a plurality of ribs projecting from the two opposite inner wall forming a plurality of channels on each of the two opposite inner walls to guide the cooling fluid towards the trailing edge. The inner space is divided into a leading section towards the leading edge of the component and a trailing section towards the trailing edge of the component. The ribs are arranged in the leading section. A plurality of pin-fins projecting from the two opposite inner walls is arranged in the trailing section in a discrete manner. | 02-07-2013 |
| 20130051994 | RETRACTABLE GAS TURBINE INLET COILS - A gas turbine inlet heat exchange coil assembly includes a gas turbine inlet housing formed to include an inlet and an outlet and a flow path therebetween. A plurality of adjacent coils are located in proximity to the inlet, and moveable between a closed operative position where the coils are aligned substantially in a plane so as to maximize resistance to flow along the flow path, and an open inoperative position where said coils are individually rotated substantially 90° such that the coils lie in individual, parallel planes so as to minimize resistance to flow along the flow path. | 02-28-2013 |
| 20130094947 | ROTOR SUPPORT THERMAL CONTROL SYSTEM - Systems for thermally regulating portions of a steam turbine are disclosed. In one embodiment, a thermal control system for a rotor bearing support includes: a housing fluidly connected to an inlet and adapted to substantially enclose the rotor bearing support, the housing defining a first annular cavity adapted to receive a fluid from the inlet; and an outlet fluidly connected to the housing, the outlet adapted to receive the fluid from the annular cavity. | 04-18-2013 |
| 20130108419 | RING SEGMENT WITH COOLING FLUID SUPPLY TRENCH | 05-02-2013 |
| 20130149121 | GAS TURBINE ENGINE WITH MULTIPLE COMPONENT EXHAUST DIFFUSER OPERATING IN CONJUNCTION WITH AN OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM - An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling. | 06-13-2013 |
| 20130156554 | BLOWER MOTOR COOLING TUBE NOISE SUPPRESSOR FOR TICKING/CHIRPING - A blower unit for a vehicle including a fan, a motor, a scroll case, a cooling chamber, a first partition, and a second partition. The fan is configured to generate airflow. The motor is connected to the fan. The scroll case accommodates the fan. The cooling chamber is connected to the scroll case and defines a cooling path for guiding airflow from the fan to the motor. The first partition is arranged in the cooling path. The second partition is arranged in the cooling path spaced apart from the first partition. | 06-20-2013 |
| 20130202421 | Passive Liquid Cooling System for Inverters Utilized for Wind Turbine Applications - A wind turbine with a thermal siphoning system is disclosed. The wind turbine comprises a tower of a wind turbine, the tower having a top and a base, and a thermal siphoning system for cooling heat generating components. The thermal siphoning system is located within the wind turbine tower and comprises a liquid coolant and at least one heat generating component located near the base of the tower. The heat generating component is adapted to receive the coolant through a coolant inlet port and adapted to discharge the coolant through a coolant outlet port. The thermal siphoning system further comprises a hot coolant tube connected to the coolant outlet port of the heat generating component. | 08-08-2013 |
| 20130302150 | OFF-SHORE WIND TURBINE WITH A THERMAL CONDITIONING SYSTEM - A thermal conditioning system for an off-shore wind turbine is provided. The thermal conditioning system comprises an insulating structure that reduces the thermal losses by convection of a treated air circulating through a duct inside the tower, from the base-level to the nacelle structure, for thermal conditioning purposes. The treated air is supplied by an air-treatment system located at the base level of the off-shore wind turbine. The insulating structure comprises insulating material of a greater thermal conductivity than the air and a plurality of voids arranged between insulating material so that air flow between said voids is prevented. | 11-14-2013 |
| 20130343882 | PUMP - An impeller radial pump includes a pump chamber with a central suction and with a pump chamber outlet, wherein an impeller is provided in the pump chamber. Radially outside of the impeller, a circular ring shaped and circumferential pump chamber ring section is provided as a part of the pump chamber, wherein the pump chamber ring section essentially has an extension along the axial direction of the pump from the impeller against the suction direction. The pump chamber ring section has a varying width and is configured to be narrower in a compression region in the circulation direction. | 12-26-2013 |
| 20140037436 | TURBINE HOUSING FOR TURBOCHARGER - A turbine housing ( | 02-06-2014 |
| 20140044530 | PORTABLE ELECTRONIC DEVICE WITH TILTEDLY INSTALLED CENTRIFUGAL FAN - A portable electronic device includes a main body and a heat dissipation module with a tiltedly installed centrifugal fan inside thereof. The main body includes an upper housing wall and a lower housing wall. The heat dissipation module includes a centrifugal fan, a heat dissipation fin array and a heat pipe. The centrifugal fan includes an impeller, a radial air outlet, an upper axial air inlet and a lower axial air inlet, wherein the centrifugal fan has a first side that is in contact with the upper housing wall and an opposite second side that is in contact with the lower housing wall. The heat dissipation fin array is located at the radial air outlet of the centrifugal fan. The heat pipe has a first end connected with the heat dissipation fin array and a second opposite end connected with a heat source. | 02-13-2014 |
| 20140064942 | TURBINE ROTOR BLADE PLATFORM COOLING - A cooling arrangement in a platform in a rotor blade or a sidewall in a stator blade in a turbine of a combustion turbine engine is described. The cooling arrangement may include: a cooling chamber configured to pass coolant from an inlet to an outlet; and a rib positioned within the cooling chamber. The rib may partially divide the cooling chamber so to form a switchback. The rib may be canted with respect to the cooling chamber such that the switchback has an ever narrowing channel. | 03-06-2014 |
| 20140079540 | TURBINE STATOR AIRFOIL ASSEMBLIES AND METHODS FOR THEIR MANUFACTURE - In accordance with an exemplary embodiment, a method of manufacturing a stator airfoil assembly includes forming an interior wall of a stator airfoil using an additive manufacturing technique, forming an exterior wall of the stator airfoil using the additive manufacturing technique, and forming a plurality of internal ribs between the interior wall and the exterior wall using the additive manufacturing technique. A cooling air circuit is formed in a space between the interior wall and the exterior wall. Further, the interior wall, the exterior wall, and the internal ribs are formed simultaneously as an integral structure by using the additive manufacturing technique. | 03-20-2014 |
| 20140093361 | AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT - An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length. | 04-03-2014 |
| 20140099193 | ROTOR BLADE AND METHOD FOR COOLING THE ROTOR BLADE - A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider. | 04-10-2014 |
| 20140112767 | COOLING-AIR GUIDANCE IN A HOUSING STRUCTURE OF A TURBOMACHINE - A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel ( | 04-24-2014 |
| 20140147259 | GAS TURBINE ENGINE TURBINE NOZZLE IMPINGEMENT COVER - An impingement cover ( | 05-29-2014 |
| 20140271154 | CASING FOR TURBINE ENGINE HAVING A COOLING UNIT - A turbine inner shell for a turbine engine includes one or more mounting grooves, each of which receives a fluid conduit. A temperature controlling fluid is circulated through fluid conduit to selectively heat or cool surrounding portions of the turbine inner shell, to thereby control the thermal growth of those portions of the turbine inner shell. This makes it possible to selectively control a clearance between the tips of rotating turbine blades and the surrounding shrouds of the turbine. | 09-18-2014 |
| 20140286763 | GAS TURBINE OUTER CASE ACTIVE AMBIENT COOLING INCLUDING AIR EXHAUST INTO SUB-AMBIENT CAVITY - A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct. | 09-25-2014 |
| 20150110611 | AIRFOIL COOLING CIRCUIT AND CORRESPONDING AIRFOIL - An airfoil cooling circuit for a gas turbine engine having at least one internal cavity with a lobed cross-sectional shape. | 04-23-2015 |
| 20150110612 | ARRANGEMENT FOR COOLING A COMPONENT IN THE HOT GAS PATH OF A GAS TURBINE - The invention relates to a cooled wall segment in the hot gas path of a gas turbine, particularly to a cooled stator heat shield. Such components have to be properly cooled in order to avoid thermal damages of these components and to ensure a sufficient lifetime. The wall segment according to the invention includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting said first and said second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet for the cooling medium and an outlet for the cooling medium. The at least one cooling channel includes at least two heat transfer sections, a first (in the direction of flow of the cooling medium) heat transfer section extending essentially parallel to the surface of relatively high temperature in a first distance and a second heat transfer section extending essentially parallel to the surface of relatively high temperature in a second distance, whereby the second distance is lower than the first distance. | 04-23-2015 |
| 20150308340 | AIRCRAFT - An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler. | 10-29-2015 |
| 20160097323 | ANTI-ICE SPLITTER NOSE - Splitter apparatus for gas turbine engines are disclosed. An example splitter apparatus may include a splitter including an annular outer wall substantially defining a convex leading edge; an annular splitter support positioned radially within the outer and including a forward end disposed substantially against a splitter inner; and an annular first bulkhead spanning between the outer wall and the splitter support. The outer wall, the splitter support, and the first bulkhead may define a generally annular splitter plenum. The forward end of the splitter support may include spaced apart, radially oriented metering slots. The outer wall may include an inner portion disposed radially inward from the splitter inner surface extending aft and including spaced-apart exit slots. The splitter plenum, the metering slots, and the exit slots may conduct airflow from the plenum, through the metering slots against the splitter inner surface, and through the exit slots. | 04-07-2016 |
| 20170234144 | COOLING CONCEPT FOR TURBINE BLADES OR VANES | 08-17-2017 |
| 415179000 | Interstage heat exchanger | 5 |
| 20080304958 | GAS TURBINE ENGINE WITH AIR AND FUEL COOLING SYSTEM - A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger. | 12-11-2008 |
| 20110268562 | GAS TURBINE ENGINE AIRFOIL INTEGRATED HEAT EXCHANGER - A heat exchanger apparatus includes: (a) an airfoil having opposed pressure and suction sides, a root, a tip, and spaced-apart leading and trailing edges; and (b) a plenum integrally formed within the airfoil which is configured to receive a flow of circulating working fluid; and (c) inlet and outlet ports communicating with the plenum and an exterior of the airfoil. | 11-03-2011 |
| 20110268563 | GAS TURBINE ENGINE - A heat exchanger arrangement for a gas turbine engine. The arrangement including a flow path within an outer cowl, which flow path locates a heat exchanger part way therealong. A valve is provided at an inlet end of the flow path to selectively receive fluid into the flow path from outside of the cowl and/or from a pressurised fluid flow. An exit from the flow path includes a plenum chamber to receive exhausted coolant flows from the heat exchanger and possibly other exhaust flows. The heat exchanger exhaust flow is then utilised to provide cooling to engine structures. | 11-03-2011 |
| 20140086733 | COMPRESSING SYSTEM - According to an aspect of an exemplary embodiment, there is provided a compressing system including: a casing including an inlet and an outlet; a first compression unit configured to receive an inlet fluid from the inlet and compressing the inlet fluid into a first pressure fluid; a first pressure chamber configured to receive the first pressure fluid; at least one first intercooler unit configured to cool the first pressure fluid; a second compression unit configured to compress the first pressure fluid into a second pressure fluid; a second pressure chamber configured to receive the second pressure fluid; at least one second intercooler unit configured to cool the second pressure fluid; and a third compression unit configured to compress the second pressure fluid. | 03-27-2014 |
| 20140105734 | TURBOCOMPRESSOR - A turbocompressor provided with a case, a centrifugal first stage and second stage compressing unit disposed on the case, and a driver unit for driving the first stage and second stage compressing units. The interior of the case is partitioned into a first cooling area which houses a first cooling device, a second cooling area which houses a second cooling device, an oil tank, and a blowoff silencer chamber. The blowoff silencer chamber is located between the oil tank and the first cooling area and the second cooling area in the interior of the case. | 04-17-2014 |
