| Entries |
| Document | Title | Date |
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| 20080202122 | ARRANGEMENT WITH A TWIST-LOCK COUPLING FOR A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector mounted on the downstream side of the chamber end wall in the opening by means of an annulus, said injector system including a pinch ring mounted on the upstream side and fastened against the annulus with the pinch ring and the annulus together defining a groove, and a bowl mounted in the opening, the bowl being made up of at least two distinct parts, at least a first part forming an end plate suitable for sliding radially in the groove, and a second part forming a bowl collar that is provided with a collar extending parallel to the chamber end wall on its downstream side, said first and second bowl parts being fastened together by means of a twist-lock coupling. | 08-28-2008 |
| 20080229749 | Plug in rabbat engine - By using a plug to charge a medium-sized battery of the most up-to-date technology, the Rabbat PLUG-IN ENGINE benefits from the most up-to-date and most economical available grid supply at any point in time, to start the engine. The Direct Current from the battery sequentially activates an Ultrasound Transducer. The ultrasound waves break down physically electrolyte water into H and OH. The electrolyte carrying H or OH according to whether it is the cathode or the anode, is absorbed into a microfiber substance. The microfiber contains a wire-grid electrode, either anode or cathode. The electrolytic process finally breaks down chemically the partially ionized electrolyte into Hydrogen and Oxygen making use of the H and OH produced by sonic waves The Oxygen produced is passed through an Ionizer. Ionized ambient air, ionized Oxygen, and Hydrogen are injected into and piezzoelectrically sparked in the combustion chamber of a special cored type of gas turbine. The expanding gases rotate the turbine to which a Direct Current generator is attached. The Direct Current is henceforth used to drive electric motors externally and all electric and electronic components internally. It may be used to drive the electric motor driving either the front or rear axle of a car (or both in case of 4-wheel drive), or trucks, trolleys, locomotives, train segments, or compressing air-jets of airplanes, or pod-propellers of boats and ships, for example. Electronic controls regulate the timing and proportions of different gas elements involved. | 09-25-2008 |
| 20080289337 | COMBINED-CYCLE POWER PLANT AND STEAM THERMAL POWER PLANT - A combined-cycle power plant, a steam thermal power plant, and a method for operating the power plant, which are capable of effectively utilizing raw fuel produced from medium- or small-scaled gas fields and oil fields. Raw fuel produced from a gas field is separated into a gas component and a liquid component by a separator. The gas component is burnt in a combustor of a gas turbine, and resulting motive power is converted to electricity by a power generator. The liquid component separated by the separator is burnt in a steam generator to generate steam that is supplied to a steam turbine. Resulting motive power of the steam turbine is converted to electricity by a power generator. Since the electricity generated by the power generators is AC power, the AC power is converted by a converter to DC power that is transferred from the vicinity of the gas field to a consuming area via a cable. | 11-27-2008 |
| 20090145130 | Building energy recovery, storage and supply system - A building having an energy conversion apparatus and method for distributed energy systems using recovered energy of stationary structure wind resistance and solar radiation in conjunction with normal and off-peak operation of a gas turbine engine. The energy sources are combined, as available, for electric generation and to drive an air liquefier. Liquid air compression and pre-compression cooling of an atmospheric air portion of engine working fluid reduces compression work while increasing engine efficiency. The liquefied air is stored and transferred between buildings and between buildings and vehicles, as required. | 06-11-2009 |
| 20090266077 | Mixing chamber - A mixing chamber with a wall and at least one vortex generating element arranged on the wall is provided. The vortex generating element has at least three surfaces, at least one of the surfaces forming a top surface and the other surfaces forming at least first and second side surfaces, the first and second side surfaces arranged not in parallel, the top surface being in contact with the wall via a front edge of the top surface, the front edge extending traverse to a flow direction, the top surface further abutting the first and second side faces forming first and second edges, the first side surface extending in parallel to the flow direction so that the first edge does not contribute to generating a vortex, and the second side surface extending not in parallel to the flow direction so that the second edge contributes to generating the vortex. | 10-29-2009 |
| 20100154422 | CMAS MITIGATION COMPOSITIONS, ENVIRONMENTAL BARRIER COATINGS COMPRISING THE SAME, AND CERAMIC COMPONENTS COMPRISING THE SAME - Calcium magnesium aluminosilcate (CMAS) mitigation compositions selected from zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof wherein the CMAS mitigation composition is included as a separate CMAS mitigation layer in an environmental barrier coating for a high temperature substrate component. | 06-24-2010 |
| 20100170248 | COMBUSTOR AND COMBUSTION METHOD FOR COMBUSTOR - A combustor and a combustion method for the combustor, which can suppress backfire and ensure stable combustion. The combustor comprises a mixing-chamber forming member for forming therein a mixing chamber in which air for combustion and fuel are mixed with each other, and a combustion chamber for burning a gas mixture mixed in the mixing chamber and producing combustion gases. A channel for supplying the air for combustion to the mixing chamber from the outer peripheral side of the mixing-chamber forming member is provided inside the mixing-chamber forming member. The fuel and the air are premixed in the channel, and a resulting premixed gas mixture is supplied to the mixing chamber. | 07-08-2010 |
| 20100205969 | Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner - The invention relates to a burner for a turbomachine, comprising a guide plate that is arranged in a flame chamber and engages a wall section via spacers. The invention further relates to a guide plate, the fastening section of which comprises a plurality of raised areas for fastening to a wall section of a flame chamber. The invention further relates to a turbomachine having a burner of said kind. | 08-19-2010 |
| 20100281868 | GAS TURBINE ENGINE COMBUSTER - A combustor for a gas turbine engine, and including an integrated dome and deflector having a conical shape optimized for each individual combustor cup in an array of combustor cups, as determined by CFD analysis for eliminating combustor air recirculation zones and swirling. A related method is also disclosed. | 11-11-2010 |
| 20100313567 | GAS TURBINE - In a gas turbine that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance starting from a leading edge of a turbine first stage nozzle toward a trailing edge side of the first stage nozzle and ending at center of transition pieces of such combustors that are adjacent in a circumferential direction is set relative to a circumferential pitch of such first stage nozzles within a range of 0.05≦S/P≦0.15, and an axial distance between a leading edge of the first stage nozzle and a transition piece rear end of the combustor is set relative to the circumferential pitch of the first stage nozzles within a range of 0.00≦L/P≦0.13. By improving the relative position of a transition piece of the combustor and the first stage nozzle, both suppression of inner pressure fluctuations of the combustor and enhancement in aerodynamic efficiency can be achieved. | 12-16-2010 |
| 20110016865 | GAS TURBINE AND METHOD OF FORMING COMBUSTOR INSERTION HOLE OF GAS TURBINE - A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a circumferential direction of the combustor casing is formed larger than that in the circumferential direction of the combustor casing, and when the combustor inserted into the hole, a member moved together with the combustor, and the hole are viewed from a moving direction of the combustor, the hole includes an entire external form of the combustor and the member moved together with the combustor. | 01-27-2011 |
| 20110048017 | METHOD OF DEPOSITING PROTECTIVE COATINGS ON TURBINE COMBUSTION COMPONENTS - A method is provided for high velocity air plasma spraying (APS) application of a protective coating system, such as a bond coat with or without an overlying ceramic thermal barrier coat, to a superalloy metal substrate. Application of MCrAlY alloy bond particles (where M is at least one of iron, cobalt, or nickel) onto the metal substrate is maintained at a particle velocity of at least 400 meters per second (m/s), for example within a range of 400 m/s to 700 m/s. The resulting bond coat on the metal substrate has a surface roughness of about 300 to about 500 μinch Ra, and a density of at least 90% of theoretical density. The protective coating may include a ceramic thermal barrier coat applied over the bond coat by any suitable process. | 03-03-2011 |
| 20110048018 | COMBUSTION DEVICE OF A GAS TURBINE - A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper. | 03-03-2011 |
| 20110048019 | TURBINE ENHANCEMENT SYSTEM - The present invention is concerned with a system and method for enhancing the performance of a wind turbine, which involves injecting air from an array of nozzles into the airflow upstream of the turbine in order to reduce the turbulence and/or increase the velocity and/or control the pressure of the airflow, thereby improving the performance of the turbine. | 03-03-2011 |
| 20110162369 | Gas Turbine, Exhaust Diffuser, and Method of Modifying Gas Turbine Plant - A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressure turbine. | 07-07-2011 |
| 20110179794 | PRODUCTION PROCESS - A transition duct ( | 07-28-2011 |
| 20110197586 | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor - A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower combustor annular passageway. The second flow path places the diffuser in direct fluid communication with the combustor cap assembly. | 08-18-2011 |
| 20110203281 | ARTICLE FOR HIGH TEMPERATURE SERVICE - An article comprises a substrate and a coating disposed over the substrate, wherein the coating comprises a monoclinic silicate phase that undergoes no solid state phase transformation reaction in the temperature range from about 1100 degrees Celsius to about 1275 degrees Celsius. Another article comprises a substrate comprising a silicon-bearing ceramic material; a bondcoat disposed over the substrate, wherein the bondcoat comprises silicon; a coating disposed over the bondcoat, wherein the coating comprises a monoclinic silicate phase, the silicate phase comprising a) yttrium and b) at least one other species selected from the group consisting of ytterbium and lutetium, wherein the material undergoes no solid state phase transformation reaction in the temperature range from about 1100 degrees Celsius to about 1275 degrees Celsius; and a topcoat disposed over the coating, wherein the topcoat comprises at least one selected from the group consisting of an aluminate, an aluminosilicate, a silicate (such as a rare earth monosilicate, for example), and zirconia. | 08-25-2011 |
| 20110203282 | ASSEMBLY FOR DIRECTING COMBUSTION GAS - An arrangement ( | 08-25-2011 |
| 20110232288 | METHOD OF REDUCING COMBUSTION INSTABILITIES BY CHOOSING THE POSITION OF A BLEED AIR INTAKE ON A TURBOMACHINE - Method of reducing acoustic vibratory phenomena in the environment of a combustion chamber of a turbomachine, said chamber being positioned in a cavity delimited by an exterior casing and an interior chamber casing, characterized in that it includes at least the following steps:
| 09-29-2011 |
| 20110265481 | DUAL FUEL CAN COMBUSTOR WITH AUTOMATIC LIQUID FUEL PURGE - A lean, low NOx gas-fired can combustor having liquid fuel operation capability includes a housing, a combustor liner disposed within the housing and defining a combustion zone for combusting fuel with air, and a head assembly for joining the longitudinal housing and liner ends and for supporting swirler vanes that admit about 45-55% of a total combustor air flow to the combustion zone. The head assembly includes multiple gaseous fuel injection ports upstream of the swirler vanes, and a single liquid fuel injector positioned along the liner axis for directing atomized liquid fuel into the combustion zone. The head assembly further includes a heat shield disposed between the injector and the combustion zone, and the head assembly is configured to provide a flow of air for cooling the heat shield during all operations of the can combustor. The can combustor may also include apparatus for automatically purging the liquid fuel injector with compressed air, such as cooled compressed air from a gas turbine engine compressor stage. The apparatus includes a shuttle valve controller including a shuttle member biased by a first pressure towards a first position interconnecting the liquid fuel input to the liquid fuel injector inlet, while blocking compressed purging air flow, and biased by a second pressure towards a second position interconnecting the compressed purging air input to the liquid fuel injector inlet, while blocking liquid fuel flow. | 11-03-2011 |
| 20110271678 | TURBOMACHINE COMBUSTION CHAMBER WALL HAVING A SINGLE ANNULAR ROW OF INLET ORIFICES FOR PRIMARY AIR AND FOR DILUTION AIR - A turbomachine combustion chamber including coaxial walls forming surfaces of revolution that include inlet orifices for admitting primary air and dilution air into the chamber, the orifices in each wall being substantially in alignment with one another along the longitudinal axis of the chamber and forming a single annular row of orifices. | 11-10-2011 |
| 20120000203 | Method for operating a burner and burner, in particular for a gas turbine - A method for operating a burner comprising a burner axis and at least one jet nozzle is provided. The nozzle or nozzles include a central axis, a jet nozzle outlet, a wall that runs in a radial direction starting from the central axis and that faces the burner axis and a volumetric fluid flow that includes a fuel and flows through the jet nozzle or nozzles to the jet nozzle outlet. An air film is formed at the jet nozzle outlet between the volumetric fluid flow including the fuel and the wall that faces the burner axis by means of air that is injected into the jet nozzle or nozzles along the wall that faces the burner axis. | 01-05-2012 |
| 20120017594 | SEAL ASSEMBLY FOR CONTROLLING FLUID FLOW - A seal assembly ( | 01-26-2012 |
| 20120023949 | APPARATUS AND FILTERING SYSTEMS RELATING TO COMBUSTORS IN COMBUSTION TURBINE ENGINES - A combustor for a combustion turbine engine that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; and a multilayer screen filter comprising at least two layers of screen over at least a portion of the windows and at least one layer of screen over the remaining portion of the windows. The windows include a forward end and a forward portion, and an aft end and an aft portion. The multilayer screen filter is positioned over the windows such that, in operation, a supply of compressed air entering the chamber through the windows passes through at least one layer of screen. The multilayer screen filter is configured such that the aft portion of the windows include at least two layers of screen, and the forward portion of the windows includes one less layer of screen than the aft portion of the windows. | 02-02-2012 |
| 20120023950 | CONTROLLABLE FLAMEHOLDER - The present invention relates to a flameholder ( | 02-02-2012 |
| 20120102956 | TURBINE EXHAUST DIFFUSION SYSTEM AND METHOD - A system includes multiple blades coupled to a rotor, a stationary shroud disposed about the multiple blades, and a clearance between the stationary shroud and each blade end of the multiple blades, wherein the clearance is configured to enable over tip leakage flow. The system also includes a diffuser section that includes an outer wall defining an expanding flow path downstream from the multiple blades. The outer wall includes a first wall portion having a first angle relative to a rotational axis of the multiple blades, and the clearance is configured to enable an increase in the first angle by maintaining the boundary layer along the outer wall with the over tip leakage flow. | 05-03-2012 |
| 20120111011 | BYPASS TURBINE INTAKE - A system, that includes a bypass turbine intake configured to route a bypass supply of air to a turbine engine to bypass an air filter of a main turbine intake, wherein the bypass turbine intake comprises a louvered door having a plurality of louvers configured to move between a closed position and an open position, the open position enables flow of the bypass supply of air to the turbine engine, and the closed position disables flow of the bypass supply of air to the turbine engine. | 05-10-2012 |
| 20120159952 | GAS TURBINE COMPONENT HAVING THERMAL BARRIER COATING AND A GAS TURBINE USING THE COMPONENT - The present invention provides gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also provides a gas turbine equipped with the components. One of the components is a gas turbine bucket/nozzle comprising a substrate made from an alloy containing Ni, Co, or Fe, a bonding layer made from an alloy and disposed over the substrate, and a thermal barrier coating disposed over the bonding layer. The thermal barrier coating includes a thermal barrier layer of porous ceramics, an environmental barrier layer containing silica, and an impregnation layer having a silica-containing material in the pores of the porous ceramics. | 06-28-2012 |
| 20120186254 | DAMAGE-REPAIRING METHOD OF TRANSITION PIECE AND TRANSITION PIECE - A damage-repairing method of a transition piece in an embodiment includes; an oxide removing step of removing an oxide on an outer surface | 07-26-2012 |
| 20120198849 | MULTIPLEXED OPTICAL FIBER CRACK SENSOR - An optical fiber crack detector that includes a plurality of FBG sensors positioned within one or more fibers that are operable to reflect a defined wavelength of an optical input beam. The crack detector includes a light source for generating the optical input beam that propagates down the optical fiber and interacts with the FBG sensors. A wavelength of the optical beam that is reflected by the FBG sensors is detected, and if a crack in the component damages the fiber between an FBG sensor and the detector circuit, where one or more of the reflected signals are not received, the detector knows that a crack has occurred. By strategically placing a plurality of the FBG sensors along the fiber, a crack that damages the fiber in multiple locations between multiple FBG sensors, or in multiple fibers, can provide an indication of the length of the crack. | 08-09-2012 |
| 20120240583 | SEGMENTED COMBUSTION CHAMBER HEAD - A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners | 09-27-2012 |
| 20120240584 | COMBUSTION CHAMBER FOR A TURBINE ENGINE - A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall. | 09-27-2012 |
| 20120247108 | COMBUSTOR PROBE FOR GAS TURBINE - Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor. | 10-04-2012 |
| 20120291437 | TURBINE COMBUSTION SYSTEM COUPLING WITH ADJUSTABLE WEAR PAD | 11-22-2012 |
| 20120317984 | CELL STRUCTURE THERMAL BARRIER COATING - A combustor component of a gas turbine engine includes a thermal barrier coating on a substrate, the thermal barrier coating defines a multiple of cells. | 12-20-2012 |
| 20120317985 | ELECTRIC FIELD CONTROL OF TWO OR MORE RESPONSES IN A COMBUSTION SYSTEM - A combustion system may include a plurality of heated volume portions. At least two of the plurality of heated volume portions may include corresponding respective electrodes. The electrodes may be driven to produce respective electric fields in their respective volumes. The electric fields may be configured to drive desired respective responses. | 12-20-2012 |
| 20120324894 | STRAIN TOLERANT COMBUSTOR PANEL FOR GAS TURBINE ENGINE - A combustor component of a gas turbine engine includes a substrate with a cold side, a central core section and a hot side, the cold side and the hot side have a porosity different than the central core section. | 12-27-2012 |
| 20130008166 | TURBOMACHINE COMBUSTION CHAMBER HAVING A CENTRIFUGAL COMPRESSOR WITH NO DEFLECTOR - An annular combustion chamber for a turbomachine, including an external wall and an internal wall which are oriented substantially axially relative to the rotation axis of the turbomachine, the combustion chamber being closed upstream by a chamber end wall oriented substantially radially, the chamber being supplied with compressed air coming from a compressor via a nozzle, the output direction of which is offset radially relative to the mid-axis of the combustion chamber, the chamber end wall including cooling air supply holes inclined to the direction normal to the chamber end wall. The number of holes oriented radially in the direction opposite to that where the outlet of the nozzle is located is greater than the number of holes oriented radially in the direction of the outlet of the nozzle. | 01-10-2013 |
| 20130025281 | GASIFICATION SYSTEM AND METHOD - A system configured for the production of at least one product selected from the group consisting of syngas, Fischer-Tropsch synthesis products, power, and chemicals, the system comprising a dual fluidized bed gasification apparatus and at least one apparatus selected from power production apparatus configured to produce power from the gasification product gas, partial oxidation reactors configured for oxidation of at least a portion of the product gas, tar removal apparatus configured to reduce the amount of tar in the product gas, Fischer-Tropsch synthesis apparatus configured to produce Fischer-Tropsch synthesis products from at least a portion of the product gas, chemical production apparatus configured for the production of at least one non-Fischer-Tropsch product from at least a portion of the product gas, and dual fluidized bed gasification units configured to alter the composition of the product gas. Methods of operating the system are also provided. | 01-31-2013 |
| 20130031904 | COMBUSTION CHAMBER - A combustion chamber includes at least one annular wall. The annular wall includes a plurality of segments and each segment has a first portion, a second portion and a third portion. The first portion of each segment extends circumferentially, the third portion of each segment extends circumferentially and the second portion of each segment extends radially to connect the first portion and third portion of the segment. The segments are arranged such that the first portion of each segment overlaps the third portion of an adjacent segment and the first portion of each segment is bolted to the third portion of the adjacent segment. The segments are cast and define a double wall combustion chamber and enable easier construction of the combustion chamber and replacement of damaged segments. | 02-07-2013 |
| 20130047618 | WALL ELEMENTS FOR GAS TURBINE ENGINES - A double-wall structure for use in components in gas turbine engines that are exposed to high temperatures has a first wall spaced apart from a second wall. The first wall has a protrusion extending therefrom towards the second wall. The second wall has a cooling fluid orifice, or hole, through which cooling fluid is directed in use towards the protrusion. The protrusion extends across a significant percentage of the gap between the first and second walls. The cooling fluid removes heat from protrusion as it flows over it through convection, thereby cooling the first wall. The cooling fluid is also redirected so as to become more aligned with the first wall as it flows over the protrusion. In some cases, a trench is provided at the base of the protrusion. The cooling fluid causes a vortex to form in the trench, thereby further assisting cooling. | 02-28-2013 |
| 20130055716 | Gas-turbine combustion chamber with a holding means of a seal for an attachment - Gas-turbine combustion chamber with a combustion chamber head made from a metallic material and mounting at least one burner, and with a combustion chamber wall made from a ceramic material, where at least one igniter plug or other combustion chamber attachments such as acoustic dampers, sensors or valves are arranged in a recess of the combustion chamber wall, and where in the area of the recess a seal is arranged that is mounted by means of a metallic holding means from another component than the CMC combustion chamber wall. | 03-07-2013 |
| 20130055717 | TRANSITIONAL REGION FOR A SECONDARY COMBUSTION CHAMBER OF A GAS TURBINE - A gas turbine is provided having a secondary combustion chamber and a first guide vane row of a low-pressure turbine, the row being arranged directly downstream of the chamber. The radially outer boundary of the secondary combustion chamber is formed by at least one outer wall segment, which is secured on at least one support element arranged radially outwardly. The flow path of the hot gases is bounded radially outwardly, in the region of the guide vane row, by an outer platform which is secured at least indirectly on at least one guide vane support. A substantially radially extending gap-shaped cavity having a width in the range of 1-25 mm in the axial direction in the inlet region is arranged between the wall segment and the outer platform. At least one step element, which reduces the width by at least 10% in at least one step, extending substantially perpendicularly to the direction of flow of the hot gas in the cavity, is arranged in the inlet region. | 03-07-2013 |
| 20130055718 | DEVICE FOR REDUCING THE NOISE EMITTED BY THE JET OF AN AIRCRAFT PROPULSION ENGINE - A gas exhaust nozzle for aircraft propulsion includes at least a downstream part with a trailing edge of chevron type formed of chevrons distributed along the periphery of the nozzle. Each chevron extends downstream between an upstream transverse plane and a downstream transverse plane with free edges oriented in two converging downstream directions and defining the trailing edge. The chevrons generate vortices at the boundary of the jet emitted by the nozzle. The gas exhaust nozzle includes a device to inject auxiliary gas jets upstream of the free edges of the chevrons in the main jet through orifices placed upstream of the upstream plane in such a way as to discharge upstream of the upstream plane of the chevrons to generate the vortices upstream of the free edges of the chevrons. | 03-07-2013 |
| 20130061593 | SYSTEM AND METHOD FOR CONTROLLING A COMBUSTOR ASSEMBLY - A system and method for controlling a combustor assembly are disclosed. The system includes a combustor assembly. The combustor assembly includes a combustor and a fuel nozzle assembly. The combustor includes a casing. The fuel nozzle assembly is positioned at least partially within the casing and includes a fuel nozzle. The fuel nozzle assembly further defines a head end. The system further includes a viewing device configured for capturing an image of at least a portion of the head end, and a processor communicatively coupled to the viewing device, the processor configured to compare the image to a standard image for the head end. | 03-14-2013 |
| 20130104550 | TURBINE OF A TURBOMACHINE | 05-02-2013 |
| 20130125547 | METHOD FOR OPERATING A COMBUSTION DEVICE DURING TRANSIENT OPERATION - A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L). | 05-23-2013 |
| 20130139510 | METHOD FOR MANUFACTURING A HOT GAS PATH COMPONENT AND HOT GAS PATH TURBINE COMPONENT - According to one aspect of the invention, a method for manufacturing a hot gas path component of a turbine is provided, the method including forming cooling channels in a surface of a member. The method also includes disposing a layer on the surface of the member to enclose the cooling channels, the layer being disposed on a portion of the member to be cooled and bonding the layer to the surface, wherein bonding comprises heating the member and the layer. | 06-06-2013 |
| 20130139511 | GAS TURBINE COMBUSTOR AND GAS TURBINE - A gas turbine combustor includes: an external cylinder ( | 06-06-2013 |
| 20130160452 | AERODYNAMIC SHROUD FOR THE BACK OF A COMBUSTION CHAMBER OF A TURBOMACHINE - An annular shroud has an internal face intended to cover the back end wall of an annular combustion chamber of a turbomachine fitted with a centrifugal compressor, together with an external face opposite the internal face. The shroud includes multiple apertures intended to allow fuel injectors supported by the back end wall to pass through. The shroud includes multiple bosses which extend as projections on the external face radially towards the interior respectively from the respective radially internal edges of the apertures. Each of the bosses delimits an extension of the corresponding aperture open radially towards the exterior so as to form an air intake scoop. | 06-27-2013 |
| 20130167537 | QUICK DISCONNECT COMBUSTION ENDCOVER - A clamp assembly for facilitating attachment and removal of a first component to or from a second component includes plural clamp bodies, each having at least two mutually perpendicular surfaces arranged about the first component. A substantially rigid ring is located between one surface of the clamp body and a surface of the first component. At least one fastener is provided for each of the plural clamp bodies, adapted to extend through a respective one of the plural clamp bodies and into the second component. Tooling is provided to allow for simultaneous tightening or loosening of all bolts on a single combustor. | 07-04-2013 |
| 20130174557 | COMBUSTOR FOR A GAS TURBINE ENGINE - A combustor in a gas turbine engine has a wall which forms a gap with an outer nozzle guide vane platform. A closure mechanism is operable to open or close the gap. Opening of the gap, for example during cruise conditions, reduces the mass flow rate of air through an open end of the combustor, so enriching the air fuel ratio and improving flame stability and combustion efficiency. Under high power conditions, the gap is closed, causing an increase in air flow rate through the open end to achieve a lean burn air fuel ratio when the fuel flow rate is increased. | 07-11-2013 |
| 20130192231 | Turbine Wheel Arrangement For A Gas Turbine - The invention relates to a turbine wheel arrangement for a gas turbine comprising two successive turbine wheels ( | 08-01-2013 |
| 20130199186 | Fan-less Thrust Generating Component for Air-bypass Engine - A fan-less thrust generating component for air-bypass engine includes an outer casing, a fluid moving device, and a plurality of core components. The fluid moving device and the plurality of core components are positioned within an intake opening of the outer casing. The fluid moving device is positioned in front of the plurality of core components and connected to with the plurality of core components. The fluid moving device includes a hub, a helical fin, and a fluid inlet. The helical fin is connected around the hub and the fluid inlet is positioned on the helical fin. The fluid moving device pulls air fluid into the intake opening through the fluid inlet upon rotation so that thrust can be generated within the air-bypass engine. | 08-08-2013 |
| 20130199187 | Gas-turbine combustion chamber having non-symmetrical fuel nozzles - The present invention relates to an annular gas-turbine combustion chamber having a radially outer and a radially inner combustion chamber wall relative to a machine axis, a combustion chamber head and a combustion chamber outlet nozzle, where the combustion chamber head includes several fuel nozzles spread over its circumference for supplying air and fuel, the latter exiting in an outlet surface of the fuel nozzles, where the respective fuel nozzle has a burner axis which is vertical to the outlet surface and where the intersections of the burner axes with the outlet surfaces define a circular burner centerline around the engine axis, characterized in that a cross-sectional area of the fuel nozzle radially outside the burner centerline is identical to a cross-sectional area radially inside the burner centerline. | 08-08-2013 |
| 20130205786 | COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE - A gas turbine engine 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 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, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge. | 08-15-2013 |
| 20130205787 | TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE - A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge. | 08-15-2013 |
| 20130247573 | GENERATOR COMPRESSOR COMBINATION POWER SYSTEM - Disclosed is a generator compressor combination power system based upon an internal combustion engine directly coupled to a generator and a compressor assembly. The engine, generator and compressor each having an operating drive shaft all positioned along the same axis, the generator is used to produce electricity and the compressor is used to compress gas. | 09-26-2013 |
| 20130263600 | ASSEMBLY INCLUDING A REVERSE THRUST DEVICE AND SYSTEM FOR ACTUATING SAID DEVICE - A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl. | 10-10-2013 |
| 20130263601 | INTAKE LINER FOR A GAS TURBINE ENGINE - A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled β relative to the radial line; the angles α and β are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion. | 10-10-2013 |
| 20130269348 | DESIGN AND MANUFACTURING OF AN ADVANCED LOW COST MICRO-TURBINE SYSTEM - A micro-turbine engine has been designed using vertically simple geometry, such that the engine components are designed with features that are defined geometrically, but not necessarily manufactured, by extruding two-dimensional features along a primary direction. This design approach reduces manufacturing and assembly costs. The present invention discloses designs to improve micro-turbine engine performance, and methods of manufacturing components that further reduce cost. The design improvements include methods of implementing a multi-stage micro-turbine engine using nested stages and nested flow paths, usage of multi-phase fuel injectors and supercritical fuel injectors to increase fuel flexibility and burner efficiency, and method of cooling a turbine rotor by building cooling blades on the opposite side of the rotor that act as a fluid pump to provide cooling by convection. The manufacturing methods include methods to build alignment features into components to improve ease of assembly, methods for manufacturing combustor components using sheet metal, and methods for manufacturing features that are not aligned with the primary direction of the vertically simple component. | 10-17-2013 |
| 20130276449 | COMBUSTOR CAP MOUNTING STRUCTURE FOR A TURBINE ENGINE - A mounting structure for mounting a combustor cap in a combustor of a turbine engine includes support struts that are connected between the combustor cap and a concentric combustor cap barrel flange. The support struts may have an airfoil shape to minimize wakes created in a flow of compressed air that is passing over the support struts. Also, the support struts may have an interior passageway that allows a portion of the compressed air to flow though the support strut. The flow of air passing through the support struts may also pass through corresponding vent apertures in the combustor cap barrel flange so that the flow of air passing through the support struts is delivered into a space between the exterior of the combustor cap barrel flange and a forward casing of the combustor. | 10-24-2013 |
| 20130283798 | COMBUSTOR AND A METHOD FOR ASSEMBLING THE COMBUSTOR - A combustor generally includes a plate that extends radially and circumferentially within at least a portion of the combustor. The combustor may also include a shroud that at least partially surrounds the plate and a plurality of tubes that extend through the plate. One or more flexible couplings may at least partially surround at least some of the plurality of tubes and the one or more flexible couplings may be connected to the plate. | 10-31-2013 |
| 20130333387 | ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE INCLUDING IMPROVED DILUTION OPENINGS - An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing 1 between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices. | 12-19-2013 |
| 20130340435 | GAS TURBINE ENGINE AFT SPOOL BEARING ARRANGEMENT AND HUB WALL CONFIGURATION - An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion. | 12-26-2013 |
| 20140013754 | POWER AUGMENTATION SYSTEM WITH DYNAMICS DAMPING - A power augmentation system for a gas turbine engine which may include a transition piece of a combustor and a steam manifold positioned about the transition piece. The transition piece may include a number of transition piece passageways therethrough and the steam manifold may include a number of manifold passageways therethrough. The manifold passageways align with the transition piece passageways. | 01-16-2014 |
| 20140020389 | COMBUSTOR CAP ASSEMBLY - One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion. | 01-23-2014 |
| 20140033717 | COMBUSTOR CAP ASSEMBLY - A support structure for a burner tube in a combustor cap assembly for a gas turbine combustor includes an outer annular ring; an inner annular hub; and a plurality of struts extending radially between said outer annular ring and the inner hub. The inner hub is provided with a piston ring groove and a piston ring adapted to receive and seal an inner end of the burner tube. | 02-06-2014 |
| 20140060056 | Rotational Engine - The rotational engine assembly includes a housing defining a rotor interior. The housing defining an inlet and an outlet extending into the rotor interior. The housing further defining a vane cavity between the inlet and the outlet. A vane movably mounted to the housing to move into and out of the vane cavity. A crankshaft extending through the rotor interior. A rotor radially fixed to the crankshaft in the rotor interior. The rotor defining a working chamber in the rotor interior between the rotor and the housing. The rotor includes at least one thruster extending from the rotor surface transverse to the crankshaft and dividing the working chamber. A compressor in fluid communication with the inlet for supplying compressed air to be mixed with the fuel. An ignition source mounted to the housing and having access to the working chamber for igniting the compressed air fuel charge. | 03-06-2014 |
| 20140109577 | DUCTING ARRANGEMENT FOR COOLING A GAS TURBINE STRUCTURE - A ducting arrangement ( | 04-24-2014 |
| 20140109578 | COMBUSTOR TRANSITION - The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. Besides the combustor transition a gas turbine comprising such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed. | 04-24-2014 |
| 20140109579 | COMBUSTOR TRANSITION - The disclosure relates combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and an downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed. | 04-24-2014 |
| 20140130500 | DESIGN AND MANUFACTURING OF AN ADVANCED LOW COST MICRO-TURBINE SYSTEM - A micro-turbine engine has been designed using vertically simple geometry, such that the engine components are designed with features that are defined geometrically, but not necessarily manufactured, by extruding two-dimensional features along a primary direction. This design approach reduces manufacturing and assembly costs. The present invention discloses designs to improve micro-turbine engine performance, and methods of manufacturing components that further reduce cost. The design improvements include methods of implementing a multi-stage micro-turbine engine using nested stages and nested flow paths, usage of multi-phase fuel injectors and supercritical fuel injectors to increase fuel flexibility and burner efficiency, and method of cooling a turbine rotor by building cooling blades on the opposite side of the rotor that act as a fluid pump to provide cooling by convection. The manufacturing methods include methods to build alignment features into components to improve ease of assembly, methods for manufacturing combustor components using sheet metal, and methods for manufacturing features that are not aligned with the primary direction of the vertically simple component. | 05-15-2014 |
| 20140130501 | COMBUSTION CHAMBER TILE OF A GAS TURBINE - A combustion chamber tile of a gas turbine includes a bolt for mounting the combustion chamber tile on a combustion chamber wall, with the combustion chamber tile being designed substantially plate-like and having on one side at least one mounting element, on which the bolt, which is provided as a separate component, is positively anchored. | 05-15-2014 |
| 20140144138 | Combustion Chamber Housing and Gas Turbine Equipped Therewith - Combustion chamber housing ( | 05-29-2014 |
| 20140150433 | EXHAUST GAS COLLECTOR FOR AN EXHAUST AFTERTREATMENT SYSTEM - An exhaust gas collector for use in a duct of an exhaust gas aftertreatment system includes generally T-shaped tubular sample members having closed upstream ends, downstream ends and spaced apart exhaust collection holes. The downstream ends of the tubular members are fluidly coupled at a common collection location in the center of the duct. The tubular members are positioned in the duct with the exhaust collection holes at locations distributed across a cross sectional area of a duct to collect exhaust samples from across the cross sectional area of the duct. All exhaust gas samples collected by the exhaust gas collector are collected by one of the sample members having a downstream end coupled to the common collection location. A non-sample collecting accumulator tube is fluidly coupled to the common collection location of the tubular sample members. A sensor senses the mixed exhaust gas in the accumulator tube. | 06-05-2014 |
| 20140174088 | ALIGNMENT SYSTEM AND METHODOLOGY TO ACCOUNT FOR VARIATION IN A GAS TURBINE ENGINE - A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component. | 06-26-2014 |
| 20140182292 | INTEGRAL INSTRUMENTATION IN ADDITIVELY MANUFACTURED COMPONENTS OF GAS TURBINE ENGINES - An article includes a body portion made of a metal and configured for use in a gas turbine engine, a sensing feature monolithically formed with the body portion, and an interior passage connected to the sensing feature and passing through the body portion. An article with integrated sensing features may be made additive manufacturing, resulting in a structure having internal passageways connecting an aperture at one surface of the monolithic article to a second aperture at another surface of the monolithic article at the opposite end of the internal passageway. | 07-03-2014 |
| 20140190166 | COMBUSTION CHAMBER - A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed. | 07-10-2014 |
| 20140202158 | GAS TURBINE ENGINE HEAT EXCHANGERS AND METHODS OF ASSEMBLING THE SAME - A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel. The first fluid circuit also includes a plurality of cooling channels in flow communication with the first bypass valve. The first bypass valve is configured to channel a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation. | 07-24-2014 |
| 20140208755 | Gas Turbine Air Mass Flow Measuring System and Methods for Measuring Air Mass Flow in a Gas Turbine Inlet Duct - A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct. The sensor assembly includes a tube with a longitudinal axis disposed in a substantially laminar flow region of the inlet duct, and a flow conditioner disposed in the tube. A hot wire sensor disposed in the tube is also provided. | 07-31-2014 |
| 20140230440 | COMBUSTION CHAMBER - A combustion chamber comprises an outer wall and an inner wall. The outer wall has mounting apertures extending there-though and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs. Walls are positioned between the outer wall and the inner wall. Each wall is spaced from and extends around a respective fastener to form a chamber around the respective fastener. Apertures extend through the outer wall. Each aperture is spaced from a respective mounting aperture. Each aperture allows a flow of coolant into the associated chamber and around the associated fastener to cool the fastener. Each wall has an opening at a position diametrically opposite to associated aperture to allow the flow of coolant out of the chamber to a space between the outer wall and the inner wall. | 08-21-2014 |
| 20140260256 | CHECK VALVE FOR PROPULSIVE ENGINE COMBUSTION CHAMBER - A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate. | 09-18-2014 |
| 20140260257 | ANNULAR WALL OF A COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE LEVEL OF PRIMARY AND/OR DILUTION HOLES - An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall. | 09-18-2014 |
| 20140360193 | SUPPORT FRAME AND METHOD FOR ASSEMBLY OF A COMBUSTION MODULE OF A GAS TURBINE - A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate. | 12-11-2014 |
| 20140360194 | TOROIDAL HEAT EXCHANGER - A toroidal combustion chamber and a plurality of plates are disposed with respect to one another such that their labyrinthine walls are juxtaposed and form labyrinthine conduits leading from an exhaust outlet of the toroidal combustion chamber to an exit perpendicular to the exhaust outlet. | 12-11-2014 |
| 20150007570 | METHOD FOR MANUFACTURING OF A GAS TURBINE ENGINE COMPONENT - The invention concerns a method for manufacturing of a gas turbine engine component ( | 01-08-2015 |
| 20150040566 | HELICAL SEAL SYSTEM FOR A TURBOMACHINE - A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated. | 02-12-2015 |
| 20150040567 | Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine - A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange. | 02-12-2015 |
| 20150040568 | COMBUSTOR FLOATING COLLAR ASSEMBLY - A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss. | 02-12-2015 |
| 20150047356 | TURBINE ENGINE, SUCH AS A TURBOJET OR A TURBOPROP ENGINE - A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims. | 02-19-2015 |
| 20150059344 | TURBOMACHINE COMBUSTION CHAMBER SHELL RING - A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation. | 03-05-2015 |
| 20150082794 | APPARATUS FOR ACOUSTIC DAMPING AND OPERATIONAL CONTROL OF DAMPING, COOLING, AND EMISSIONS IN A GAS TURBINE ENGINE - Acoustic damping resonators ( | 03-26-2015 |
| 20150089950 | METHOD FOR DETERMINING THE TEMPERATURE INSIDE A COMBUSTOR - A method for determining the temperature of an aggressive and/or abrasive gas is described using an acoustic transmitter and an acoustic receiver. The transmitter emits an acoustic signal with varying frequencies and the receiver extracts from the acoustic input signal a frequency of the maximum. Based on this the frequency of this maximum the temperature of the gas between transmitter and receiver is calculated. | 04-02-2015 |
| 20150101331 | GAS TURBINE ENGINE - A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device. | 04-16-2015 |
| 20150121879 | Gas Turbine Combustor - There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions. | 05-07-2015 |
| 20150345394 | COOLING SYSTEMS AND METHODS - Provided are systems and methods for cooling to increase efficiency in power-generation facilities, to cool various other apparatus including buildings, and/or to generate water, including, but not limited to, systems for increasing the efficiency of power-generating turbines via inlet-cooling, optionally by expanding a portion of a pressurized fuel source that also feeds the turbine. | 12-03-2015 |
| 20160003789 | SENSOR APPARATUS FOR ANALYZING A GAS MIXTURE IN A PROCESS CHAMBER - A sensor apparatus for analyzing a gas in a process chamber, having a housing, a gas sensor for analyzing at least a part of the gas, the gas sensor being arranged at a determined position in the housing, a gas feed for connecting the housing to the process chamber to feed the part of the gas from the process chamber into the housing and to the determined position, and a gas discharge for discharging the gas from the housing, wherein the gas feed and the gas discharge are configured as tubes lying inside one another, characterized by a closure cap at the combustion chamber-side end of the tubes lying inside one another, the closure cap including an even number of at least four openings with the same area, which are connected alternately as a gas inlet and a gas outlet to the tubes lying inside one another is provided. | 01-07-2016 |
| 20160008755 | METHOD AND DEVICE FOR THE TREATMENT OF A GAS STREAM, IN PARTICULAR FOR THE TREATMENT OF A NATURAL GAS STREAM | 01-14-2016 |
| 20160010868 | COMBUSTOR WITH SPRING-LOADED CROSSOVER TUBES | 01-14-2016 |
| 20160025343 | VOID STRUCTURES WITH REPEATING ELONGATED-APERTURE PATTERN - Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features. | 01-28-2016 |
| 20160053998 | CYLINDER OF COMBUSTOR, METHOD OF MANUFACTURING OF CYLINDER OF COMBUSTOR, AND PRESSURE VESSEL - A cylinder of a combustor includes a cylinder body inside of which combustion gas flows, a jacket plate that covers the cylinder body from the outside and forms a fluid space into which high-pressure fluid flows between an inner peripheral surface of the jacket plate and an outer peripheral surface of the cylinder body, and a rib that connects the cylinder body and the jacket plate. The rib is connected to the cylinder body by a cylinder side end portion on the cylinder body side in a radial direction with respect to an axis of the cylinder body being welded from both sides in an axial direction of the axis. The rib is connected to the jacket plate by a jacket side end portion on the jacket plate side in the radial direction being welded from both sides in the axial direction. | 02-25-2016 |
| 20160069567 | SINGLE-WALLED COMBUSTOR FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURE - A single-walled combustor includes a multi-layered wall having a first face defining a cooling plenum and an opposite second face. A thermal barrier coating of the wall may be secured to the second face and defines at least in-part a combustion chamber. A plurality of cooling circuits each extend through the base layer and the thermal barrier coating for flowing cooling air from the plenum and into the combustion chamber. Each circuit includes a first surface recessed from the second face and spaced from the thermal barrier coating with a channel defined in-part by the first surface and covered by the thermal barrier coating. A hole in the thermal barrier coating is in fluid communication between the channel and the combustion chamber. A method of manufacturing the circuit includes fabricating the base layer with the aperture and hole; then placing an insert into the channel prior to application of the coating over the base layer and insert. The insert is then removed and the film cooling hole is formed through the coating. | 03-10-2016 |
| 20160146033 | GAS TURBINE ENGINE CLEARANCE CONTROL - A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment. | 05-26-2016 |
| 20160152320 | Gas Turbine Engine Spinner | 06-02-2016 |
| 20160153297 | GAS TURBINE ENGINE TURBINE VANE RING ARRANGEMENT | 06-02-2016 |
| 20160160668 | Inner Diffuser Case Cone and Skirt - An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone. | 06-09-2016 |
| 20160169114 | SHIELD ASSEMBLY FOR SHIELDING A HOUSING OF AN ELECTRO-MECHANICAL DEVICE FROM A HOT BODY | 06-16-2016 |
| 20160194964 | THREE DIMENSIONAL AIRFOIL MICRO-CORE COOLING CHAMBER | 07-07-2016 |
| 20160194981 | DUAL ANTI SURGE AND ANTI ROTATION FEATURE ON FIRST VANE SUPPORT | 07-07-2016 |
| 20160195275 | HYBRID DIFFUSER CASE FOR A GAS TURBINE ENGINE COMBUSTOR | 07-07-2016 |
| 20160201915 | SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR | 07-14-2016 |
| 20220136700 | METHOD OF GENERATING GAS TURBINE FUEL AND GAS TURBINE SYSTEM - Disclosed herein is a fuel for use in a combustor of a gas turbine, wherein the fuel is a gas mixture that comprises hydrogen and exhaust gas from a total combustor. | 05-05-2022 |
