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US20110265484 COMBUSTION DEVICE FOR A GAS TURBINE  
A combustion device (1) for a gas turbine includes portions (12) having an inner and an outer wall (13, 14) with an interposed noise absorption plate (15) having a plurality of holes (16). The...
US20140318140 PREMIXER ASSEMBLY AND MECHANISM FOR ALTERING NATURAL FREQUENCY OF A GAS TURBINE COMBUSTOR  
A system and method are provided for altering the natural frequency of a dome plate portion of a premixer assembly of a gas turbine combustor. The plate assembly has a dome plate with a central...
US20150184857 MICROCIRCUIT COOLING FOR GAS TURBINE ENGINE COMBUSTOR  
A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and...
US20140331681 WAKE MANIPULATNIG STRUCTURE FOR A TURBINE SYSTEM  
A wake manipulating structure for a turbine system includes a combustor liner defining a combustor chamber. Also included is an airflow path located along an outer surface of the combustor liner....
US20100307166 COMBUSTOR-TURBINE SEAL INTERFACE FOR GAS TURBINE ENGINE  
A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the...
US20110088402 ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE  
An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection...
US20110154826 GAS TURBINE, METHOD OF CONTROLLING AIR SUPPLY AND COMPUTER PROGRAM PRODUCT FOR CONTROLLING AIR SUPPLY  
The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber...
US20090145099 TRANSITION DUCT COOLING FEED TUBES  
Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are...
US20110030378 COMBUSTOR TILE MOUNTING ARRANGEMENT  
A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use,...
US20090249791 TRANSITION PIECE IMPINGEMENT SLEEVE AND METHOD OF ASSEMBLY  
Disclosed herein is an impingement sleeve for a gas turbine combustion transition piece. The impingement sleeve includes, a housing positionable proximate a first portion of a transition piece...
US20120117973 GAS-TURBINE COMBUSTION CHAMBER WITH A COOLING-AIR SUPPLY DEVICE  
A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall 6 to be cooled. The cooling-air supply device includes at least one air-supply...
US20090193810 Combustion chamber lining  
A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2...
US20120125006 GAS TURBINE COMBUSTOR AND GAS TURBINE  
In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply...
US20080155988 ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE  
An annular combustion chamber for a turbomachine, the chamber comprising an inner wall, an outer wall, and a chamber end wall disposed between said inner and outer walls in the upstream region of...
US20080141674 DEFLECTOR FOR A COMBUSTION CHAMBER ENDWALL, COMBUSTION CHAMBER EQUIPPED THEREWITH AND TURBINE ENGINE COMPRISING THEM  
The deflector (22) takes the form of a plate provided with a hole (40). This plate is a portion of a conical surface of revolution about a cone axis (300), comprises a concave face (62) and a...
US20090019855 Low emissions gas turbine combustor  
A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece;...
US20150007573 ANNULAR-COMBUSTION-CHAMBER BYPASS  
An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine...
US20100263384 COMBUSTOR CAP WITH SHAPED EFFUSION COOLING HOLES  
A combustor cap assembly for a gas turbine includes a plurality of effusion cooling apertures that allow air to pass through the cooling apertures to cool the combustor cap assembly. An inner...
US20130318992 Combustor with a Brief Severe Quench Zone  
The present application provides a combustor for combusting a number of flows of air and a number of flows of fuel. The combustor may include a central swirler for producing a high swirl quench...
US20080256956 Methods and systems to facilitate reducing combustor pressure drops  
A method for assembling a gas turbine combustor includes providing a combustor case having a first end, a second end, and a centerline extending there between, coupling an end cover to the case...
US20110011093 GAS-TURBINE COMBUSTION CHAMBER WITH STARTER FILM FOR COOLING THE COMBUSTION CHAMBER WALL  
A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the...
US20140318139 PREMIXER ASSEMBLY FOR GAS TURBINE COMBUSTOR  
A novel and improved combustion liner for use in a gas turbine engine is provided in which the premixer assembly is removably fastened to the combustion liner. Apparatus and method for removably...
US20120297778 COMBUSTORS WITH QUENCH INSERTS  
A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side,...
US20140060063 Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times  
A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the...
US20080271458 Zero-Cross-Flow Impingement Via An Array of Differing Length, Extended Ports  
A jet impingement array design and method are disclosed for efficiently cooling the liner of a gas turbine combustion chamber, while eliminating almost all effects of coolant gas crossflow. The...
US20100126174 GAS TURBINE COMBUSTION CHAMBER  
A combustion chamber including: a flame tube having, in the direction of flow, a mixing zone for mixing a fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a...
US20100186416 FLOW CONDITIONER FOR USE IN GAS TURBINE COMPONENT IN WHICH COMBUSTION OCCURS  
A gas turbine component in which combustion occurs. The gas turbine component includes a liner, including a first surface facing a first space and a second surface facing a second space, the liner...
US20130160457 SYSTEM AND METHOD FOR IMPROVED COMBUSTOR TEMPERATURE UNIFORMITY  
A combustor and a method for reducing a temperature gradient of a combustor component are provided. The combustor includes a coating applied to at least a portion thereof with the coating serving...
US20100170260 GAS TURBINE COMBUSTOR  
A gas turbine combustor includes a fuel supplying section and a combustion tube. The fuel supplying section supplies fuel to a combustion zone inside the combustion tube. The combustion tube...
US20100251722 Wall elements for gas turbine engine combustors  
A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (50A) overlapping a downstream wall element (50B) and defining a gap (37) and an outlet (35)...
US20140223914 FLOW SLEEVE INLET ASSEMBLY IN A GAS TURBINE ENGINE  
A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve...
US20100077764 Structures with adaptive cooling  
Disclosed are exemplary structures with adaptive cooling and methods of adaptively cooling structures. A liner is affixed to a support and the liner deflects away from the support when exposed to...
US20110107766 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE WITH ENHANCED COOLING  
A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer...
US20090120096 Gas Turbine Engine Systems Involving Cooling of Combustion Section Liners  
Gas turbine engine systems involving cooling of combustion section liners are provided. In this regard, a representative liner includes: an outer side, an inner side, an upstream end and a...
US20110185740 COMBUSTOR LINER SEGMENT SEAL MEMBER  
A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and...
US20100180601 COOLING STRUCTURE OF GAS TURBINE COMBUSTOR  
It is required for a gas turbine combustor to exhaust low NOx. The gas turbine combustor is provided with a combustion tube which has a cooling passage through which cooling air flows in a double...
US20120144835 COMBUSTION CHAMBER  
A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the...
US20140116060 COMBUSTOR AND A METHOD FOR COOLING THE COMBUSTOR  
A combustor includes a first shroud extending circumferentially inside the combustor and at least partially defining an inlet passage. A second shroud extends circumferentially inside the...
US20100126184 COMBUSTION CHAMBER ARRANGEMENT FOR OPERATING A GAS TURBINE  
A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber...
US20130174569 SYSTEM AND METHOD FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR  
A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion...
US20130086915 FILM COOLED COMBUSTION LINER ASSEMBLY  
A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion...
US20110185739 GAS TURBINE COMBUSTORS WITH DUAL WALLED LINERS  
A combustor for a turbine engine includes a hot wall and a cold wall forming a dual walled liner and a liner cavity with the hot wall. The cold wall defines a plurality of impingement cooling...
US20150101336 Cooling Structure for Gas Turbine Combustor Liner  
A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a...
US20100257863 COMBINED CONVECTION/EFFUSION COOLED ONE-PIECE CAN COMBUSTOR  
An industrial turbine engine comprises a combustion section, an air discharge section downstream of the combustion section, a transition region between the combustion and air discharge section, a...
US20150068212 COMBUSTOR LINER STOP  
A combustion liner includes a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow...
US20120102960 GAS TURBINE ENGINE SYSTEMS INVOLVING COOLING OF COMBUSTION SECTION LINERS  
Gas turbine engine systems involving cooling of combustion section liners are provided. A representative liner includes: an outer side, an inner side, an upstream end, and a downstream end, the...
US20150153044 TURBOMACHINE COMBUSTOR ASSEMBLY  
A turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body. The combustor liner defines a combustion chamber having a head end and a...
US20150075171 TURBOMACHINE COMBUSTOR ASSEMBLY  
A turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body. The combustor liner defines a combustion chamber having a head end and a...
US20120055165 COMBUSTOR LINER ASSEMBLY WITH ENHANCED COOLING SYSTEM  
An enhanced cooling system for the downstream end of a combustor liner assembly is provided. The downstream end region of the combustor liner assembly is formed by a subassembly comprising an...
US20130298564 COOLING SYSTEM AND METHOD FOR TURBINE SYSTEM  
A cooling system and a method for cooling a liner in a turbine system are disclosed. The cooling system includes a liner defining a temperature boundary between a hot side and a cold side. The...

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