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Match Document Document Title
US20110296841 GAS TURBINE ENGINE DIFFUSER  
An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow...
US20130000308 Diffuser Pipe and Assembly for Gas Turbine Engine  
A diffuser pipe (38) of a compressor diffuser assembly (28) for gas turbine engines defines a depressed local area (58) in the pipe wall of an upstream section of the diffuser pipe (38). The...
US20140116056 GAS TURBINE DIFFUSER WITH FLOW SEPARATOR  
A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity...
US20110265483 Combustor For A Turbine, and Gas Turbine Outfitted With A Combustor of This Kind  
Combustor for a turbine, and gas turbine outfitted with a combustor. The combustor has a housing in which an air collecting chamber, a combustion antechamber, and a combustion chamber are formed....
US20130255263 AIR BLOCKER RING ASSEMBLY WITH RADIAL RETENTION  
An air blocker ring assembly includes a proximal end and a distal end, a blocker ring, and a blocker ring support. The blocker ring support includes at least one flange radially overlapping a...
US20150068211 RADIAL MIDFRAME BAFFLE FOR CAN-ANNULAR COMBUSTOR ARRANGEMENT HAVING TANGENTIALLY ORIENTED COMBUSTOR CANS  
A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the...
US20100101230 Flow splitter for gas turbine engine  
A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter...
US20120144841 CORE DIFFUSER FOR DEOILER/BREATHER  
A breather assembly for use with a gas turbine engine includes a static housing for accepting a fluidic mixture of substances, a rotatable separator having one or more fluid inlets and arranged...
US20140352313 DIFFUSER STRUT FAIRING  
A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction...
US20090308076 AIR CYCLE MACHINE TURBINE OUTLET HEATED DIFFUSER  
The turbine outlet heated diffuser may include a cavity positioned immediately downstream of an air cycle machine turbine. The turbine outlet heated diffuser may be designed to prevent or reduce...
US20110314828 BLEEDING OF AIR VIA THE DIFFUSER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE  
Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form...
US20140137559 GAS TURBINE ENGINE COMBUSTOR WITH INTEGRATED COMBUSTOR VANE  
A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.
US20110192166 OUTLET GUIDE VANE STRUCTURE  
An outlet guide vane structure 6 for a gas turbine engine comprises outlet guide vanes 18 supported between inner and outer outlet guide walls 20, 22. The guide walls 20, 22 form a diffuser 24 aft...
US20140331678 SYSTEM FOR DISTRIBUTING COMPRESSED AIR IN A COMBUSTOR  
A system for distributing compressed air in a combustor of a gas turbine engine. The system may include a flow splitter, a center duct, an outer duct, and an inner duct configured to separate and...
US20080022688 Air cycle machine for an aircraft environmental control system  
An ECS system includes an ACM mounted adjacent an air-liquid heat exchanger through a diffuser that contains a diffuser plate. The diffuser plate receives airflow from the ACM which strikes the...
US20090260340 Combustor of a Turbine, a Method of Retro-Fitting a Combustor of a Turbine and a Method of Building a Combustor of a Turbine  
A combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine are each provided. The combustor includes a combustion chamber along...
US20080256926 DIFFUSER WITH IMPROVED EROSION RESISTANCE  
A diffuser for a centrifugal compressor in a gas turbine engine, the diffuser including a diffuser ring having a series of bores defined therethrough to receive and direct air exiting the...
US20070271924 DEVICE FOR GUIDING A STREAM OF AIR ENTERING A COMBUSTION CHAMBER OF A TURBOMACHINE  
Device for guiding a stream of air entering a combustion chamber of a turbomachine, comprising a flow straightener (14) followed by a diffuser (16), one of the shrouds (40) of the flow...
US20140144145 GAS TURBINE COMBUSTION CHAMBER  
The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with...
US20110179803 BLED DIFFUSER FED SECONDARY COMBUSTION SYSTEM FOR GAS TURBINES  
The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a...
US20120167572 GAS TURBINE ENGINE AND DIFFUSER  
One embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and...
US20100077768 DIFFUSER WITH ENHANCED SURGE MARGIN  
A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed...
US20140260289 MULTI-PASSAGE DIFFUSER WITH REACTIVATED BOUNDARY LAYER  
A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction...
US20090272120 Diffuser for a gas turbine, and gas turbine for power generation  
The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least...
US20070175220 Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions  
A curved diffuser (210) in a gas turbine engine (201) directs a primary portion of air flow from a compressor (202) through a curved discharge opening (213) into a plenum (220). The curved...
US20100257869 Diffuser arranged between the compressor and the combustion chamber of a gas turbine  
The invention relates to a gas turbine, comprising an annular combustion chamber and an upstream diffuser, with a throughflow essentially parallel to a turbine longitudinal axis, at a distance...
US20130042623 CONICAL REVERSE-FLOW COMBUSTION CHAMBER FOR A TURBOMACHINE  
Assembly consisting of a reverse-flow combustion chamber for a turbomachine and a diffuser intended to be positioned at the outlet of a centrifugal compressor and comprising two faces running...
US20100037616 Diffuser for Decelerating a Compressed Fluid  
A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled...
US20110252804 Method And System For Providing A Splitter To Improve The Recovery Of Compressor Discharge Casing  
A splitter is provided for improving a pressure recovery of a compressor discharge casing (CDC) by substantially aligning a fluid vortex about a longitudinal axis of a gas turbine engine. The CDC...
US20090293485 DIFFUSERS, DIFFUSION SYSTEMS, AND METHODS FOR CONTROLLING AIRFLOW THROUGH DIFFUSION SYSTEMS  
A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a...
US20100229562 REDUCED EXHAUST EMISSIONS GAS TURBINE ENGINE COMBUSTOR  
A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas...
US20140090400 VARIABLE FLOW DIVIDER MECHANISM FOR A MULTI-STAGE COMBUSTOR  
The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow...
US20150159873 COMPRESSOR DISCHARGE CASING ASSEMBLY  
A compressor discharge casing assembly includes a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of...
US20110056207 DIFFUSER FOR TURBINE ENGINE INCLUDING INDENTED ANNULAR WEBS  
A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at...
US20100122536 PLASMA FLOW CONTROLLED DIFFUSER SYSTEM  
A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a...
US20120297783 SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE  
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the...
US20170097011 COMPRESSOR STATOR VANE, AXIAL FLOW COMPRESSOR, AND GAS TURBINE  
Within a compressor case, a plurality of stages of high-pressure compressor statorsare disposed alternately with a plurality of stages of high-pressure compressor rotorsalong an axial direction....
US20170051751 SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT  
Assemblies are provided for rotational equipment. One of these assemblies includes a rotor disk structure, a stator structure and a seal assembly. The rotor disk structure includes a rotor disk...
US20170044979 PRE-DIFFUSER WITH HIGH CANT ANGLE  
A gas turbine engine is provided. The engine includes a combustor configured at a combustor angle relative to an engine axis and a pre-diffuser configured to supply air to the combustor and...
US20170023015 DIFFUSER CASE FOR A GAS POWERED TURBINE  
A turbine engine includes a diffuser connecting a compressor section and a turbine section. The diffuser includes a diffuser frame and multiple diffuser case sections are connected to the diffuser...
US20170022834 High pressure compressor diffuser for an industrial gas turbine engine  
A gas turbine engine with an air cooled turbine part in which spent cooling air for the turbine part is discharged into the combustor instead of into the hot gas stream of the turbine in order to...
US20160348581 RETAINING TAB FOR DIFFUSER SEAL RING  
An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The...
US20160298646 GAS TURBINE DIFFUSER AND METHODS OF ASSEMBLING THE SAME  
A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path...
US20160290225 COMBUSTION EQUIPMENT  
Combustion equipment includes annular combustion chamber having an annular upstream wall structure. Annular outer casing surrounds and is spaced from annular combustion chamber and annular inner...
US20160265371 INNER DIFFUSER CASE FOR A GAS TURBINE ENGINE  
A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.
US20160258360 SPHERICAL BALL BEARING HOUSING  
A fuel supply manifold of a gas turbine engine, a method for assembling a fuel supply manifold for a gas turbine engine, and a gas turbine engine are disclosed. The fuel supply manifold for the...
US20160245521 GAS TURBINE ENGINE QUENCH PATTERN FOR GAS TURBINE ENGINE COMBUSTOR  
A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air...
US20160201688 GAS TURBINE ENGINE DIFFUSER COOLING AND MIXING ARRANGEMENT  
A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures...
US20160169514 Gas Turbine Engine Diffuser-Combustor Assembly Inner Casing  
An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut...
US20160169049 Pre-Diffuser Strut for Gas Turbine Engine  
A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for...

Matches 1 - 50 out of 63 1 2 >