Matches 1 - 37 out of 37


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US20110271654 DIFFUSER FOR GAS TURBINE SYSTEM  
A diffuser for a gas turbine system having a longitudinal axis is disclosed. The diffuser includes a plurality of diffuser ducts. Each of the plurality of diffuser ducts is disposed annularly...
US20130291548 COMBUSTOR MIXING JOINT AND METHODS OF IMPROVING DURABILITY OF A FIRST STAGE BUCKET OF A TURBINE  
The present application and the resultant patent provide a method of improving durability of a first stage bucket of a turbine of a gas turbine engine. The method may include the steps of...
US20140137535 CLOCKED COMBUSTOR CAN ARRAY  
The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in...
US20150167979 FIRST STAGE NOZZLE OR TRANSITION NOZZLE CONFIGURED TO PROMOTE MIXING OF RESPECTIVE COMBUSTION STREAMS DOWNSTREAM THEREOF BEFORE ENTRY INTO A FIRST STAGE BUCKET OF A TURBINE  
The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams...
US20110067377 GAS TURBINE COMBUSTION DYNAMICS CONTROL SYSTEM  
A system comprises a gas turbine combustor having a plurality of combustor cans, crossfire tubes for connecting combustor cans, and a tubular connection system connecting the combustor cans to...
US20110072826 CAN TO CAN MODAL DECOUPLING USING CAN-LEVEL FUEL SPLITS  
In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor,...
US20140060000 GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION  
An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors...
US20130152543 RADIAL INFLOW GAS TURBINE ENGINE WITH ADVANCED TRANSITION DUCT  
A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial...
US20140137536 SUPER TELESCOPING CROSS-FIRE TUBE AND METHOD OF ASSEMBLING A COMBUSTOR STRUCTURE  
A super-telescoping cross-fire tube includes a cross-fire tube including a first portion and a second portion in mating engagement, the cross-fire tube extending from a first end region to a...
US20120073259 TURBOMACHINE HAVING AN ANNULAR COMBUSTION CHAMBER  
A turbomachine including an annular combustion chamber, the combustion chamber presenting a connection flange at its downstream end for connection to an outer casing. The connection flange bears...
US20140060001 GAS TURBINE ENGINE WITH SHORTENED MID SECTION  
An industrial gas turbine engine (10) rated for at least 75 MW maximum output, including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section...
US20060185345 Cooled transition duct for a gas turbine engine  
A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40)...
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...
US20110259015 Tangential Combustor  
A combustion section for a gas turbine includes a casing defining a chamber, a plurality of combustor cans disposed in the casing and oriented in an annular pattern, and a plurality of transition...
US20130061570 GAS TURBINE ENGINE WITH HIGH AND INTERMEDIATE TEMPERATURE COMPRESSED AIR ZONES  
A gas turbine combustor (26) disposed in a combustion air plenum (65) and a transition piece (28) for the combustor disposed in a separate cooling air plenum (58, 67). The combustion air plenum...
US20110247314 COMBUSTOR EXIT TEMPERATURE PROFILE CONTROL VIA FUEL STAGING AND RELATED METHOD  
A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the...
US20100229570 BURNER FOR A GAS TURBINE AND METHOD FOR LOCALLY COOLING A HOT GASES FLOW PASSING THROUGH A BURNER  
The burner (1) for a gas turbine includes a duct (2) housing a plurality of tetrahedron shaped vortex generators (3) and a lance (4) to inject a fuel to be combusted. Within the duct (2), a...
US20070028592 Thermal shield, especially for lining the wall of a combustion chamber  
The aim of the invention is to provide a highly durable, high-strength thermal shield element for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal...
US20130145741 TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE  
A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage...
US20100170216 LATE LEAN INJECTION SYSTEM CONFIGURATION  
A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a...
US20130180260 COMBUSTOR RECOVERY METHOD AND SYSTEM  
A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a...
US20100077719 Modular Transvane Assembly  
An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement...
US20140123619 COMBUSTOR ASSEMBLY  
According to one aspect of the invention, a combustor assembly for a pair of adjacent combustors includes a first passage formed in a liner of a first combustor and a flow sleeve disposed outside...
US20140053528 SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS  
A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a cap assembly that extends radially across at least a...
US20130213049 SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID  
The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can...
US20140144122 CROSSFIRE TUBE ASSEMBLY BETWEEN ADJACENT COMBUSTORS  
A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid...
US20150241066 SYSTEM AND METHOD FOR CONTROL OF COMBUSTION DYNAMICS IN COMBUSTION SYSTEM  
A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a...
US20080282667 METHOD AND APPARATUS TO FACILITATE COOLING TURBINE ENGINES  
A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end,...
US20100251687 GAS TURBINE: SEAL BETWEEN ADJACENT CAN ANNULAR COMBUSTORS  
The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for...
US20100186365 Heat Shield Element, in Particular for Lining a Combustion Chamber Wall  
A highly durable, high-strength thermal shield element is provided for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal shield element comprises a base...
US20080041058 Resonator device at junction of combustor and combustion chamber  
One or more Helmholtz-type resonators (270) is/are provided at the junction (260) of a combustor (220) and a combustion chamber (240) of a gas turbine engine (100). In one embodiment, adjacent...
US20160298853 SERVICE-FRIENDLY CROSS FLAME TUBE WITH TWIST LOCK ATTACHMENT FOR CAN-ANNULAR GAS TURBINES  
A twist lock attachment mechanism for attaching a cross flame tube to a cross flame tube port that is part of a combustor basket in a combustion section of a gas turbine engine, where the cross...
US20160178207 AXIALLY STAGED MIXER WITH DILUTION AIR INJECTION  
A method is disclosed for operating an axially staged mixer arrangement with dilution air or dilution gas injection in connection with a combustion arrangement of a gas turbine engine or turbo...
US20160054002 COMBUSTOR CAP ASSEMBLY  
A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The...
US20150345796 COMBUSTION TURBINE WITH SIAMESED WALL PAIRED COMBUSTOR HOUSINGS  
A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a...
US20150308345 FUEL NOZZLE ASSEMBLY  
A fuel nozzle assembly having an inlet region of a fuel nozzle base assembly that provides more uniform flow of fuel within the fuel nozzle assembly. The embodiments described herein provide fuel...
US20130269359 COMBUSTOR FLOW SLEEVE WITH SUPPLEMENTAL AIR SUPPLY  
A gas turbine combustor includes a combustor liner enclosing a combustion chamber; at least one fuel nozzle arranged to provide fuel to the combustion chamber; a flow sleeve surrounding the...

Matches 1 - 37 out of 37