Matches 1 - 20 out of 20


Match Document Document Title
US20150121885 Gas Turbine Combustor  
There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural...
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...
US20090255268 Divergent cooling thimbles for combustor liners and related method  
A cooling arrangement for a turbine combustor liner includes a combustor liner; a flow sleeve surrounding at least a portion of the combustor liner with a flow annulus therebetween, the flow...
US20080066468 Splash plate dome assembly for a turbine engine  
A splash plate dome assembly for a combustion liner of a turbine engine is disclosed. The splash plate may include an outer periphery having a plurality of corners and an inner periphery defining...
US20130145767 TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE  
A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. First and second combustion stages are defined between the liners. Each combustion stage has a...
US20140190175 3D NON-AXISYMMETRIC COMBUSTOR LINER  
A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The...
US20090077977 COMBUSTION CHAMBER OF A TURBOMACHINE  
Annular combustion chamber of a turbomachine, comprising two walls of revolution each having an annular groove extending around the longitudinal axis of the chamber and opening out inside the...
US20140352316 Combustor Leakage Control System  
The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the...
US20090282833 Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface  
A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing...
US20080092547 Combustor assembly for gas turbine engine  
A combustor liner assembly includes a liner assembly, including a hot dome, a hot wall, and an impingement shield. The liner assembly further includes a convector assembly. The combustor liner...
US20100242483 COMBUSTOR FOR GAS TURBINE ENGINE  
A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber. The liner assembly includes an inner liner and an...
US20140083112 Cooled Combustor Liner Grommet  
A combustor liner grommet is disclosed. The grommet may include a peripheral wall defining a hole in a combustor liner and further including at least one cooling air flow channel. The cooling air...
US20110247341 COMBUSTOR LINER HELICAL COOLING APPARATUS  
A combustor liner is provided. The combustor liner may include an upstream portion and a downstream end portion. The upstream portion may have a radius and a length along a generally longitudinal...
US20170167728 GAS TURBINE ENGINE WITH IGNITER STACK OR BORESCOPE MOUNT HAVING NONCOLLINEAR COOLING PASSAGES  
A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is...
US20170009990 GAS TURBINE  
The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform...
US20160312624 GAS TURBINE ENGINE COMPONENT COOLING CAVITY WITH VORTEX PROMOTING FEATURES  
A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features...
US20160281516 WIRE SEAL  
The disclosure concerns a wire seal for sealing a gap between two components of a gas turbine, the wire seal including a first core and a second core spaced apart from one another, a wire pack...
US20160153658 COMBUSTOR WALL FOR A GAS TURBINE ENGINE AND METHOD OF ACOUSTIC DAMPENING  
A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air...
US20150338103 TURBINE ENGINE WALL HAVING AT LEAST SOME COOLING ORIFICES THAT ARE PLUGGED  
A turbine engine wall having a cold side and a hot side and including a plurality of cooling orifices for enabling air flowing on the cold side of the wall to penetrate to the hot side at least...
US20150292742 GAS TURBINE ENGINE COMBUSTOR BASKET WITH INVERTED PLATEFINS  
A gas turbine engine combustor basket has nested outer and inner liners that are separated by a gap at their respective distal downstream ends for passage of cooling air between the liners....

Matches 1 - 20 out of 20