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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... |
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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... |
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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... |
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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.... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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;... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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)... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |