Matches 1 - 28 out of 28


Match Document Document Title
US20100300116 Expansion Hula Seals  
The present invention provides a hula seal for use with a combustor. The hula seal includes a number of legs that define a number of slots. The slots may include a number of expansion slots.
US20140123678 ADJUSTABLE HANGER AND METHOD FOR GAS TURBINE ENGINE EXHAUST LINER  
A hanger assembly includes a hanger having a threaded bore, a bushing attaching to an outer duct, a rotator cooperating with the hanger so that the hanger may rotate relative to an inner duct, and...
US20150184528 SYSTEM FOR SEALING BETWEEN COMBUSTORS AND TURBINE OF GAS TURBINE ENGINE  
A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas...
US20110005234 CONNECTION STRUCTURE OF EXHAUST CHAMBER, SUPPORT STRUCTURE OF TURBINE, AND GAS TURBINE  
In a gas turbine, an exhaust casing (27) and an exhaust chamber (14) are connected by an exhaust chamber support (32) that can absorb thermal expansion, and the exhaust chamber (14) and an exhaust...
US20130283817 FLEXIBLE SEAL FOR TRANSITION DUCT IN TURBINE SYSTEM  
A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the...
US20130283818 CONVOLUTION SEAL FOR TRANSITION DUCT IN TURBINE SYSTEM  
A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the...
US20140223921 GAS TURBINE  
A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order...
US20090188258 ALTERING A NATURAL FREQUENCY OF A GAS TURBINE TRANSITION DUCT  
A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with...
US20150107264 STRUCTURAL MOUNTING ARRANGEMENT FOR GAS TURBINE ENGINE COMBUSTION GAS DUCT  
A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors...
US20140130505 CROSS-FIRE TUBE PURGING ARRANGEMENT AND METHOD OF PURGING A CROSS-FIRE TUBE  
A cross-fire tube purging arrangement includes a cross-fire tube extending from proximate a combustor chamber to proximate an adjacent combustor chamber for fluidly coupling the combustor chamber...
US20140144148 Cooled Combustor Seal  
A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed....
US20080053107 Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine  
One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second,...
US20150128610 FLEXIBLE COMPONENT PROVIDING SEALING CONNECTION  
A sealing component (61) for a turbine (15) positionable at an interface between a transition section (21) for carrying exhaust gas and a turbine inlet section (32). A U-shaped section (45)...
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,...
US20130042631 SEAL END ATTACHMENT  
A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating...
US20080236170 Transition-to turbine seal apparatus and transition-to-turbine seal junction of a gas turbine engine  
One embodiment of a transition-to-turbine seal (320) comprises an upstream portion (322) adapted to engage a flange (416) of a transition (400). The upstream portion (322) may be U-shaped in...
US20110072830 COMBUSTOR INTERFACE SEALING ARRANGEMENT  
A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring...
US20080276622 FUEL NOZZLE AND METHOD OF FABRICATING THE SAME  
A fuel nozzle includes a swirler assembly including a radially inner surface and a radially outer surface, a plurality of vanes coupled to the swirler assembly radially outer surface. Each vane...
US20090241553 Replaceable orifice for combustion tuning and related method  
A combustor assembly having a transition piece and at least one orifice assembly in the transition piece, the orifice assembly comprising: a boss having an outside periphery and an inside...
US20100115966 GAS TURBINE COMBUSTOR  
In a gas turbine combustor, a cavity (49) with which a plurality of first air passages (66) communicates is formed by covering with a cover (62) a concave portion (65) of a top hat main body (61)...
US20110120144 ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE  
An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution...
US20090288422 Component arrangement, combustion chamber arrangement and gas turbine  
A component arrangement is provided which includes two component elements with portions pushed one into the other, leaving a gap and arranged statically with respect to one another. The component...
US20170082030 SYSTEM FOR SEALING BETWEEN COMBUSTORS AND TURBINE OF GAS TURBINE ENGINE  
A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas...
US20170059165 CMC CROSS-OVER TUBE  
A fluid conduit may be provided comprising a ceramic matrix composite (CMC) cross-over tube and a flange. The CMC cross-over tube may comprise a first end configured to extend into a first...
US20170030582 COMBUSTOR FOR A GAS TURBINE ENGINE  
A combustor for a gas turbine engine which includes a flame tube made of a ceramic material and a metal casing which surrounds the flame tube. The combustor further includes a thermal insulation...
US20160334102 CONTROLLED-LEAK COMBUSTOR GROMMET  
A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top...
US20160238252 THERMALLY EXPANDABLE TRANSITION PIECE  
A gas turbine engine (GTE) including a thermally expandable transition piece is disclosed. The GTE includes at least a combustor section having a combustor sleeve, also known as top hat, and a...
US20150052910 APPARATUS AND METHOD FOR SERVICING GAS TURBINE ENGINES  
The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas...

Matches 1 - 28 out of 28