Class / Patent application number | Description | Number of patent applications / Date published |
060390370 | Plural combustion products generators in ring coaxial with turbine | 28 |
20080282667 | 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, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly. | 11-20-2008 |
20090145099 | 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 disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct. | 06-11-2009 |
20100077719 | 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 including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades. | 04-01-2010 |
20100170216 | 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 turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages. | 07-08-2010 |
20100186365 | 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 produced from a solidified cast ceramic material into which a plurality of reinforcing elements are integrated, to increase the tensile strength of the thermal shield element. | 07-29-2010 |
20100251687 | 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 sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate. | 10-07-2010 |
20110067377 | 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 control combustion dynamics. The tubular connection system comprises tubes for connecting at least a pair of the combustor cans. | 03-24-2011 |
20110271654 | 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 about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet. The outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct. Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity. | 11-10-2011 |
20120073259 | 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 axially against the outer casing and is blocked in an axial direction by the upstream end of an inner casing of a high pressure turbine. | 03-29-2012 |
20130061570 | GAS TURBINE ENGINE WITH HIGH AND INTERMEDIATE TEMPERATURE COMPRESSED AIR ZONES - A gas turbine combustor ( | 03-14-2013 |
20130152543 | RADIAL INFLOW GAS TURBINE ENGINE WITH ADVANCED TRANSITION DUCT - A gas turbine engine ( | 06-20-2013 |
20140053528 | 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 portion of the combustor and a combustion chamber downstream from the cap assembly. Each cap assembly includes a plurality of tubes that extend axially through the cap assembly to provide fluid communication through the cap assembly to the combustion chamber and a fuel injector that extends through each tube to provide fluid communication into each tube. Each cap assembly has an axial length, and the axial length of the cap assembly in the first combustor is different than the axial length of the cap assembly in the second combustor. | 02-27-2014 |
20140060000 | GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION - An industrial gas turbine engine ( | 03-06-2014 |
20140060001 | GAS TURBINE ENGINE WITH SHORTENED MID SECTION - An industrial gas turbine engine ( | 03-06-2014 |
20140123619 | 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 the liner of the first combustor, wherein the flow sleeve includes a window and a second passage aligned with the first passage. The assembly also includes a cross-fire tube disposed in the first passage to provide fluid communication between the first combustor and a second combustor and a retention clip disposed through the window to urge the cross-fire tube against an outer surface of the liner to enable the cross-fire tube to receive fluid through the first passage. | 05-08-2014 |
20140137535 | 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 a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation. | 05-22-2014 |
20140137536 | 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 second end region for fluidly connecting a combustor chamber and an adjacent combustor chamber. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a second position. | 05-22-2014 |
20140144122 | 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 communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves. | 05-29-2014 |
20150308345 | 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 flow conditioning components that manage fuel uniformity within a fuel annulus and make more efficient use of allocated space, thereby overcoming spatial constraints imposed on the overall fuel nozzle assembly. | 10-29-2015 |
20150345796 | 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 corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners. | 12-03-2015 |
060390380 | Intermittent combustion type | 8 |
20090320439 | PULSED DETONATION COMBUSTOR CLEANING DEVICE AND METHOD OF OPERATION - A pulse detonation cleaner system is described. The cleaner includes an elongated combustion chamber configured with at least one fuel injection inlet and one air inlet to provide fuel to the combustion chamber. The fuel and air are mixed and ignited to produce a flame. The flame is accelerated into a detonation as it propagates downstream through the combustion chamber. The detonation and its products are vented from the combustion chamber into a vessel to be cleaned. The shock and high-pressure products of the detonation are used to release debris from the walls of the vessel and blow them away. | 12-31-2009 |
20100050592 | Continuous Detonation Wave Engine - A continuous detonation wave engine (CDWE) is disclosed. An example embodiment includes a generally annular combustion chamber dimensioned to allow a fuel mixture to detonate, a mixing chamber, and a fuel mixture channel that provides for fluid communication between the mixing chamber and the combustion chamber. At least part of the fuel mixture channel features a quenching structure dimensioned to substantially prevent detonation from spreading from the combustion chamber via the fuel mixture channel to the mixing chamber. Other embodiments are described and claimed. | 03-04-2010 |
20100192536 | GROUND-BASED SIMPLE CYCLE PULSE DETONATION COMBUSTOR BASED HYBRID ENGINE FOR POWER GENERATION - An engine contains a compressor stage, a compressor plenum, an inlet valving stage, a PDC stage, a PDC exit nozzle stage, a transition stage, a high pressure turbine stage, a turbine plenum, and a low pressure turbine stage. The PDC stage contains at least one pulse detonation combustor and each of the compressor plenum, PDC exit nozzle stage and turbine plenum contain a volume used to reduce and/or widen pressure peaks generated by the operation of the PDC stage. | 08-05-2010 |
20100212282 | CONSTANT VOLUME COMBUSTOR - A constant volume combustor device includes detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings. | 08-26-2010 |
20110302904 | Pulsed Detonation Cleaning Device with Multiple Folded Flow Paths - The present application provides a pulsed detonation cleaning device. The pulsed detonation cleaning device may include an air inlet, a fuel inlet, an ignition device in communication with the air inlet and the fuel inlet for creating detonation waves, a number of folded flow paths in communication with the ignition device, and a number of flow turning devices positioned about the folded flow paths such that the detonation waves reverse direction a number of times. | 12-15-2011 |
20120216503 | ENGINE AND COMBUSTION SYSTEM - One embodiment of the present invention is a unique engine. Another embodiment of the present invention is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 08-30-2012 |
060390390 | Common rotary distributing valve | 2 |
20090139199 | PULSE DETONATION COMBUSTOR VALVE FOR HIGH TEMPERATURE AND HIGH PRESSURE OPERATION - A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor. | 06-04-2009 |
20100236214 | ROTARY AIR VALVE FIRING PATTERNS FOR RESONANCE DETUNING - An engine contains a compressor stage, a plurality of pulse detonation combustors and a rotary inlet valve structure having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage. Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer. | 09-23-2010 |