Matches 1 - 29 out of 29


Match Document Document Title
US20080159850 Replaceable blade outer air seal design  
A blade outer air seal system includes a body that extends between two circumferential sides, a leading edge and a trailing edge, and a radially inner side and a radially outer side. An attachment...
US20150121897 GAS TURBINE ENGINE WITH SOFT MOUNTED PRE-SWIRL NOZZLE  
An exemplary gas turbine engine may include a compressor, a turbine, and a combustor disposed between the compressor and the turbine. The combustor generally may have an inner casing. The...
US20080148738 Combustor construction  
A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in...
US20110209482 TANGENTIAL COMBUSTOR WITH VANELESS TURBINE FOR USE ON GAS TURBINE ENGINES  
A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine...
US20080155989 Operating line control of a compression system with flow recirculation  
A system for controlling the operating lines of a gas turbine engine comprising a compression system which compresses an incoming flow of a gas, a bleed system which extracts gas from a bleed...
US20080041065 Ultra-Micro Gas Turbine  
The present invention provides an ultra micro gas turbine engine which includes a wave rotor. In various embodiments, the ultra micro gas turbine engine of the present invention includes a...
US20130255224 REVERSE CORE GEAR TURBOFAN  
A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially...
US20080110174 COMBUSTOR DOME AND METHODS OF ASSEMBLING SUCH  
A method of assembling a dome assembly for use in a turbine engine combustor is disclosed. The method includes providing a dome assembly ring, an inner liner portion, and an outer liner portion....
US20090115141 Stage one nozzle to transition piece seal  
A transition piece seal assembly for sealing an interface between at least one transition piece extending between a turbine combustor and a first stage turbine nozzle. The seal assembly includes...
US20080006033 Gas turbine engine combustion systems  
One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods,...
US20070119183 Gas turbine engine combustor  
A gas turbine engine combustor includes a gas-turbine-engine-combustor outer annular case and a gas-turbine-engine-combustor premixer tube. The outer annular case has a longitudinal axis. The...
US20070251241 Hydrogen-fired hollow generator  
A hydrogen-fired all-in-one electric generator/turbine that requires less rotational energy, substantially fewer parts, and less space in the power plant than traditional designs. The turbine is...
US20080315529 EASE OF ASSEMBLY AID FOR BRUSH SEAL  
A brush seal assembly is formed of a bristle array receiving at least one housing member. Alignment structures are formed on the housing and bristle assembly to ensure that the bristle assembly...
US20080000238 HIGH EFFICIENCY THERMAL ENGINE  
The engine comprises a low pressure stage (1) and a high pressure stage (2) with two independent rotors (3,4) and associated fixed fluid preparation members (9,10,13,14), combining “compressor”...
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...
US20070180834 TRANSVERSE WALL OF A COMBUSTION CHAMBER PROVIDED WITH MULTI-PERFORATION HOLES  
The invention relates to an annular wall (10) intended to connect transversely longitudinal walls of an annular combustion chamber of a turbine engine. The wall (10) is essentially flat, inclined...
US20070084219 Performance of a combustion chamber by multiple wall perforations  
An annular wall for the combustion chamber of a turbomachine has a cold side and a hot side, said wall being provided with a plurality of primary holes and a plurality of dilution holes...
US20070151260 Crossfire tube assembly for gas turbines  
A crossfire tube for attachment between casing bosses of combustors includes a bellows assembly having a bellows with opposite cylindrical ends welded to annular flanges. The annular flanges...
US20150198054 ASSEMBLY FOR DIRECTING COMBUSTION GAS  
An arrangement is provided for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades including a first row of turbine...
US20090056342 Methods and Systems for Gas Turbine Part-Load Operating Conditions  
A method and system for operating at partial load a gas turbine system having a compressor, a combustor, and a turbine. The method and system may include the steps of lowering a flow of fuel to...
US20140157751 Screw Shaft Turbine Compressor and System  
Disclosed herein are screw shaft turbine compressors having (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section,...
US20070186559 ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE  
Annular combustion chamber (24) of a turbomachine, including an inner wall, an outer wall (28), a chamber bottom (30) disposed between said walls in the upstream region of said chamber, and two...
US20080087023 Cantilevered Tip Turbine Engine  
A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support...
US20090004012 COVER PLATE FOR TURBINE ROTOR HAVING ENCLOSED PUMP FOR COOLING AIR  
A cover plate for use with a rotor disk in a gas turbine engine includes an enclosed chamber associated with a web on the rotor disk. The enclosed chamber ensures that adequate cooling air is...
US20080284109 Seal assembly  
This invention provides a seal assembly for sealing a gap between first and second relatively movable members. The first member is provided with a sealing surface, and the second member is...
US20080098748 DUAL MODE COMBUSTION OPERATION OF A PULSE DETONATION COMBUSTOR IN A HYBRID ENGINE  
A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel...
US20070256420 METHODS AND APPARATUS FOR ASSEMBLING A LOW NOISE EJECTOR MOTIVE NOZZLE  
A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion...
US20060213203 Combustor  
A casing for a combustor of a gas turbine engine has a plurality of apertures, each aperture being reinforced with a band of material dividing the aperture. The casing and reinforcing member are...
US20170067639 SYSTEM AND METHOD HAVING ANNULAR FLOW PATH ARCHITECTURE  
A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a...

Matches 1 - 29 out of 29