EP1880140A1 - Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz - Google Patents

Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz

Info

Publication number
EP1880140A1
EP1880140A1 EP06755116A EP06755116A EP1880140A1 EP 1880140 A1 EP1880140 A1 EP 1880140A1 EP 06755116 A EP06755116 A EP 06755116A EP 06755116 A EP06755116 A EP 06755116A EP 1880140 A1 EP1880140 A1 EP 1880140A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
gas turbine
wall
outlet end
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP06755116A
Other languages
German (de)
English (en)
Inventor
Claus Krusch
Jens Kleinfeld
Andreas Böttcher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP06755116A priority Critical patent/EP1880140A1/fr
Publication of EP1880140A1 publication Critical patent/EP1880140A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • the present invention relates to a combustion chamber wall for a combustion chamber, in particular a combustion chamber outer wall for a Can combustion chamber or an annular combustion chamber with a combustion exhaust outlet enabling the exit of a hot combustion exhaust gas, wherein the combustion chamber wall comprises an outlet end surrounding the combustion chamber outlet.
  • the combustion chamber wall can be designed both as a support structure or a hot gas limitation against the hot gases occurring in a gas turbine plant.
  • the present invention relates to a gas turbine plant and a method for starting or stopping a gas turbine plant.
  • the outlet end of a combustion chamber wall in particular the outlet end of a combustion chamber outer wall of a gas turbine ⁇ combustion chamber (also called Aftend) heats up much slower during the starting than the rest of the combustion chamber itself.
  • the slower heating leads during the start-up phase to a lower thermal expansion of the combustion chamber wall at its outlet end compared to the other areas. If the outer wall is divided, then the outlet end may invaginate due to the different heating. Due to the different thermal expansion deformations occur, which can lead to high mechanical stresses at the outlet end.
  • the lower thermal expansion of the outlet end in a rotationally symmetrical combustion chamber with a circular outlet end leads to a constriction at the outlet end and thus to an ovalization of the combustion chamber cross section at the outlet end.
  • the high voltages occurring due to the uneven deformation can lead to damage of the supporting structure, in particular in the transition section between the outlet end and an adjacent region with passage openings for the passage of compressed air of the compressor mass flow through the combustion chamber wall.
  • axially symmetrical combustion chambers usually have two-part combustion chamber outer walls, which are screwed together along an axial outer line by means of screws.
  • the high mechanical stresses which occur when the gas turbine starts up in the transition region between the outlet end and the rest of the combustion chamber wall can exceed the load limit of the screw located directly at the outlet end. This screw can therefore be exposed to enormous bending loads, which can ultimately lead to the destruction of the screw.
  • the Turbinenleitschaufein of the first guide vane ring of the turbine in the outlet end of the internal chamber also ⁇ are integrated, for example.
  • the Turbinenleitschaufein of the first guide vane ring of the turbine in the outlet end of the internal chamber also ⁇ are integrated, for example.
  • Turbine blades at a ring combustion chamber in which the above-mentioned ovalization occurs, radially shift according to the ovalization. Therefore, large gaps must be kept between the exit end and the vanes to allow the vanes to shift to prevent the vanes from hitting the housing.
  • the size of the column is measured so according to occur during transient states of the gas turbine plant, and in particular when starting the gas turbine plant deformations of the outlet ⁇ end.
  • large gaps present problems in creating a sealing concept in the area of the transition between the turbine guide vane and the combustion chamber wall, which must be taken into account in the sealing concept.
  • large column that comparatively much working medium of the gas turbine plant can escape through the column. Since the escaping working medium for driving the turbine is lost, large gaps reduce the efficiency of the gas turbine plant.
  • the object of the present invention is therefore to provide a combustion chamber wall, in particular a combustion chamber outer wall, and a gas turbine plant with which the stated problems can be reduced.
  • Another object of the present invention is to provide a method for starting up a gas turbine plant in which the above-mentioned problems occur to a lesser degree.
  • the first object is or a gas turbine plant according to claim 8 and the second object is achieved by a combustor wall according to claim 1. ⁇ by a method of starting a gas turbine plant according to claim. 11
  • the dependent claims contain advantageous embodiments of the combustion chamber wall and the method.
  • combustion-chamber wall for a combustion chamber with the exit of a hot combustion exhaust gas ⁇ possible combustor exit end, that a heating and / or cooling device is provided to a combustor exit surrounding outlet end which riervorides with a ⁇ Tempe.
  • the combustion chamber wall may in particular be designed to form a combustion chamber outer wall either alone or in conjunction with at least one further combustion chamber wall.
  • the present invention is based on the realization that the difference in temperature between the outlet end and the combustion chamber wall can be reduced when the egress ⁇ end of the combustion chamber wall is heatable, thus heated or cooled, configured. Temperature differences between the outlet end and the adjacent remaining regions of the combustion chamber wall can thus be equalized. The reduction of the temperature difference leads to a ⁇ An equation of thermal expansion and hence to a reduction of the stresses in the transition area. As a result, the relative gaps between the exit end and guide vanes attached thereto can be reduced, thereby increasing the efficiency of the gas turbine plant.
  • the tempering that is, the heating or cooling of the outlet end can be structurally relatively simply achieved in that the temperature control device for the outlet end fluid channels includes channels which are in contact with a Temperiertluidzussel, ie a dressedfluidzuschreib and / or a cooling fluid supply.
  • the Temperiertluid the Ver ⁇ dense mass flow or a part of the compressor mass flow. If air from the compressor mass flow is used as tempering fluid, then it is possible in a particularly simple and elegant manner to bring about an approximation of the temperature of the outlet end to the immediately adjacent regions of the combustion chamber wall.
  • Combustion chambers often have a rotational symmetry, so ⁇ they have an axial direction and a circumferential direction.
  • the axial direction would be given by the axis of the turbine shaft, in a silo combustion chamber, however, by the flow direction of the combustion gases in the combustion chamber.
  • an axial direction and a circumferential direction can also be specified for the combustion chamber walls from which these combustion chambers are constructed.
  • the fluid channels may extend at least partially axially through the exit end in such a combustion chamber wall.
  • the combustion chamber wall has an outer side which faces after installation in a gas turbine plant, in particular the Brennkam ⁇ merplenum the system and an inner side, facing the combustor interior.
  • fluid passages which are provided to the outside of the combustion chamber wall open towards openings, ie with openings which open after installation in a gas turbine plant in the Brennschplenum.
  • fluid channels are provided with opening to the combustion chamber interior openings, which are fluidly connected to the opening into the Brennschplenum openings. The fluidic connection of said openings makes it possible to direct the temperature control fluid after flowing through the outlet end of the combustion chamber wall in flow channels, which are formed between the combustion chamber wall and towards the combustion chamber interior upstream heat shield elements.
  • this embodiment can achieve cooling of the heat shield elements in the region of the combustion chamber adjoining the outlet end, in particular in stationary gas turbine states. In the case of combustion chamber walls according to the prior art, this would only be possible with great effort.
  • a failure of the seal would lead to a leakage mass flow with which further operation of the gas turbine plant would not be possible.
  • the seal can be arranged between the openings of the fluid channels opening into the combustion chamber plenum and the combustion chamber exit, without departing from the proven sealing concept.
  • the combustion chamber wall according to the invention can in particular be equipped as a combustion chamber outer wall of an annular combustion chamber for gas turbine plants.
  • a gas turbine according to the invention ⁇ system then comprises a plenum having at least one combustion chamber therein and a combustion chamber of the combustion chamber fluidically downstream turbine stage.
  • the combustion chamber has at least one combustion chamber wall according to the invention.
  • the combustion chamber wall can also be arranged in a Can combustion chamber.
  • the combustion chamber wall comprises fluid channels, which have openings opening into the combustion chamber plenum on the outside of the combustion chamber wall.
  • this can be realized, for example., By providing all the fluid channels additional openings, which open into a groove which is to face in one of a turbine stage portion of the outlet end EXISTING ⁇ . By covering the groove by means of a cover member, a flow channel is formed.
  • the openings arranged in the outside of the combustion chamber wall and the fluid catalytic converter Ducts can then flow compressor air from the Brennschplenum in the groove.
  • the compressor air can then be forwarded by further fluid channels and the openings facing the interior of the combustion chamber in the direction of the interior of the combustion chamber.
  • the Brennschplenum can be sealed in this embodiment against the turbine stage by a the discharge end of the combustion chamber wall tightly surrounding Dich ⁇ tion.
  • the seal surrounds the outlet ⁇ end in the region between the portion of the turbine stage is to face the outlet end and opening into the combustion chamber plenum openings of the fluid channels. It can in particular be arranged between an exit end of the combustion chamber wall vice ⁇ reproduced turbine guide vane and the outlet end of the combustion chamber wall.
  • the outlet end is tempered during the startup or shutdown process.
  • Tempering of the discharge end reduces the Verformun ⁇ gene and tensions in the transitional region between the outlet end and the rest of the combustion chamber wall.
  • a radial sym metrical combustion chamber wall such as the combustion chamber outer wall of an annular combustion chamber
  • ovalization can be reduced.
  • the reduction of ovalization also leads to a reduction of the relative gap between the combustion chamber wall and attached to it ⁇ screwed Turbinenleitschaufein, thereby cooling concepts can be easily realized.
  • the efficiency of the gas turbine plant is increased and there is a lower Be ⁇ burden of arranged in the vicinity of the outlet end screws for screwing combustion chamber half walls together.
  • the temperature control of the outlet end can be achieved ⁇ who, that a tempering fluid is passed through the outlet end angeord ⁇ designated fluid channels. As the temperature- ⁇ particular a part of the compressor mass flow can be passed through the fluid channels at least.
  • Both the combustion chamber wall according to the invention and the method according to the invention lead overall to an increase in the service life of the combustion chamber support structure in the region of the combustion chamber exit and to a reduction in the load of heat shielding elements arranged in this area on the inside of the combustion chamber wall.
  • Fig. 1 shows a gas turbine plant in a partially ge ⁇ cut side view.
  • Fig. 2 shows the combustion chamber of a gas turbine plant in a sectional side view.
  • Fig. 3 shows the outlet end of a combustion chamber outer wall in detail in a sectional perspective view.
  • Fig. 4 shows a section of the outlet end of the combustion ⁇ chamber in a simplified perspective view.
  • FIG. 6 shows the outlet end of the combustion chamber shown in perspective in FIG. 3 in a plan view of the sectional plane.
  • 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular ring ⁇ combustion chamber 106, with a plurality of coaxially arrange ⁇ th burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are secured to an inner shell 138 of a stator 143, whereas the vanes 120 of a row 125 are mounted to the rotor 103 by means of a turbine disk 133, for example.
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the be at the turbine end of the compressor 105 ⁇ compressed air provided to the burners will lead 107 ge ⁇ where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 relaxes on the rotor blades 120 in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106.
  • the annular combustion chamber 110 comprises a combustion chamber outer wall 54 and combustion chamber inner wall 64 which delimits the combustion chamber 51 in the direction of the shaft 8.
  • heat shield elements 56 which are located upstream of the combustion chamber interior, can also be seen. The heat shield elements 56 not only serve to protect the combustion chamber walls 54, 64 from excessive thermal stress during operation of the gas turbine installation , but also to guide the expanding hot combustion exhaust gases to the combustion chamber exit 55.
  • flow channels 57 are formed, through which a cooling medium for cooling the heat shield elements 56 is passed.
  • the cooling medium passes through the passage openings 58 in the combustion chamber outer wall 54, which are arranged in the vicinity of the Brennkam ⁇ merausgangs 55 (see Fig. 3), in the flow ⁇ channel 57 between the combustion chamber outer wall 54 and 56 of the hit ⁇ zeschildianan and flows to either the Burner 52, where it is mixed with the supplied fuel for combustion or is introduced through gaps between the heat shield ⁇ elements 56 directly into the combustion chamber 110 to to block the column against the penetration of the hot combustion gases.
  • compressor air is used, i. at least a portion of the compressor mass flow is introduced via the combustor plenum 53 through the supply ports 58 into the flow passage 57 between the heat shield elements 56 and the combustion chamber outer wall 54.
  • the compressed air is usually already preheated, on the one hand due to the compression process and on the other ⁇ possibly also by a preheater, is transferred via the heat of the exiting the turbine stage 112 exhaust gas to the compressed air.
  • preheating takes place by means of a preheater, less waste heat from the gas turbine process is uselessly lost, so that the efficiency of the gas turbine plant can be increased.
  • pollutant emissions can be reduced by air preheating.
  • the temperature of the compressed air is still low, so that it can serve well as a cooling fluid.
  • heating channels 60, 61 are ⁇ arranged in the outlet end, which flows through the compressor mass flow (see Figures 3 to 6).
  • Some of the heating channels 61 have openings 63 in the region of the outlet end 59 facing the combustion chamber plenum 53 and openings 64 in the section 65 of the outlet end 59 facing the turbine stage 112.
  • FIG. 5 shows a section through the outlet end 59 along the line AA shown in FIG.
  • the turbine stage 112 facing portion 65 of the outlet end 59 is provided with an extending in the circumferential direction of the combustion chamber wall 54 profile groove 67, in the groove bottom 68, the openings 64 are arranged.
  • the pro ⁇ filnut 67 can be covered with a cover plate 69, wherein the profile of the profile groove 67 is selected such that between the groove bottom 68 and the cover plate, a flow ⁇ channel 70 is formed.
  • heating channels 60 are fluidically connected to the heating channels 61 - and thus the Brenncroplenum 53 opening out openings 63 with the opening to the combustion chamber openings 66th
  • the flow profile 71 of the compressor mass flow as heating fluid is indicated in FIG. 3 by arrows.
  • the compaction ⁇ termassenstrom enters through the Brennschplenum 53 facing openings 63 in the heating channels 61, flows through them and passes through the arranged in the groove bottom openings 64 from the heating channels 61 and into the flow channel 70 on. There, the compressor mass flow is deflected by the cover plate 69 (not shown in FIG. 3) so that it enters the heating channels 60 through the openings 64 of the heating channels 60.
  • the compressor mass flow After flowing through the heating channels 60, the compressor mass flow enters through the openings 66 opening into the interior of the combustion chamber into the flow channels 57 formed between the combustion chamber outer wall 54 and the heat shield elements 56, where it can be used to cool the heat shield elements 56, in particular in stationary gas turbine states. It can then be forwarded to the burner or introduced into the combustion chamber 110 via exit openings in heat shield elements 56 or gaps between heat shield elements 56.
  • the warmed through the exit end flowing pre ⁇ as described compressor mass flow leads to that the outlet end 59 of the combustion chamber outer wall 54 heats up faster the startup of the gas turbine plant, than without the presence ⁇ be of heating channels 60, 61.
  • the temperature difference Zvi ⁇ rule the outlet end 59 and the are adjacent portions of the combustion chamber outer wall 54 may in the first minutes of starting process so reduced and mechanical clamping ⁇ voltages at the transition from the flange of the outlet end 59 to the adjacent areas of the combustion chamber outer wall 54 can be reduced.
  • the outlet end 59 of the combustion chamber wall 54 is surrounded by Turbi ⁇ nenleitschaufelitati 114 of the turbine stage 112.
  • Turbi ⁇ nenleitschaufelitati 114 engages in a circumferential groove 119 of the combustion chamber wall 54.
  • a gasket 116 which extends around the entire circumference of the combustion chamber wall 54.
  • This sealing concept is used in particular in gas turbine plants with combustion chamber walls without fluid channels for controlling the temperature of the outlet end 59 and can be adopted without modification for gas turbine plants with combustion chamber walls according to the invention.
  • Existing experiences regarding the assembly, maintenance and dimensioning of the seal can be taken over.
  • a good sealing performance can be ensured.
  • the said alternative flow paths can also be combined with one another, for example by dividing the outlet end 59 into sections along the circumference of the combustion chamber outer wall 54, in each of which one of the described flow paths is realized.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une paroi de chambre de combustion (54) pour une chambre de combustion (110) pourvue d'une sortie de chambre de combustion (55) permettant la sortie d'un gaz de combustion chaud, ladite paroi de chambre de combustion (54) étant pourvue d'une extrémité de sortie (59) entourant la sortie de chambre de combustion (55). Selon la présente invention, cette extrémité de sortie (59) est pourvue d'un dispositif d'équilibrage de température (60).
EP06755116A 2005-05-13 2006-05-10 Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz Withdrawn EP1880140A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06755116A EP1880140A1 (fr) 2005-05-13 2006-05-10 Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05010539A EP1724526A1 (fr) 2005-05-13 2005-05-13 Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
PCT/EP2006/062181 WO2006120204A1 (fr) 2005-05-13 2006-05-10 Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz
EP06755116A EP1880140A1 (fr) 2005-05-13 2006-05-10 Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz

Publications (1)

Publication Number Publication Date
EP1880140A1 true EP1880140A1 (fr) 2008-01-23

Family

ID=35615549

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05010539A Withdrawn EP1724526A1 (fr) 2005-05-13 2005-05-13 Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
EP06755116A Withdrawn EP1880140A1 (fr) 2005-05-13 2006-05-10 Paroi de chambre de combustion, systeme de turbine a gaz et procede pour demarrer ou arreter un systeme de turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05010539A Withdrawn EP1724526A1 (fr) 2005-05-13 2005-05-13 Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz

Country Status (3)

Country Link
US (1) US8091364B2 (fr)
EP (2) EP1724526A1 (fr)
WO (1) WO2006120204A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2009216831B2 (en) * 2008-02-20 2014-11-20 General Electric Technology Gmbh Gas turbine
EP2119964B1 (fr) 2008-05-15 2018-10-31 Ansaldo Energia IP UK Limited Procédé pour réduire les émissions d'une chambre à combustion
EP2119966A1 (fr) 2008-05-15 2009-11-18 ALSTOM Technology Ltd Chambre de combustion à émissions réduites de monoxyde de carbone
EP2442033A1 (fr) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Segment d'accrochage de chambre de combustion et coque extérieure de chambre de combustion
EP2442032A1 (fr) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Segment d'usure dans l'accrochage de support d'aube directrice de turbines d'une coque extérieure d'une chambre de combustion annulaire
US8353165B2 (en) * 2011-02-18 2013-01-15 General Electric Company Combustor assembly for use in a turbine engine and methods of fabricating same
US9255484B2 (en) * 2011-03-16 2016-02-09 General Electric Company Aft frame and method for cooling aft frame
US20130318986A1 (en) * 2012-06-05 2013-12-05 General Electric Company Impingement cooled combustor
DE102014206018A1 (de) * 2014-03-31 2015-10-01 Siemens Aktiengesellschaft Gasturbinenanlage
US11480337B2 (en) * 2019-11-26 2022-10-25 Collins Engine Nozzles, Inc. Fuel injection for integral combustor and turbine vane

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2622395A (en) * 1947-01-02 1952-12-23 Parsons C A & Co Ltd Combustion system for gas turbines with heat exchangers
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US3965066A (en) * 1974-03-15 1976-06-22 General Electric Company Combustor-turbine nozzle interconnection
FR2624953B1 (fr) * 1987-12-16 1990-04-20 Snecma Chambre de combustion, pour turbomachines, possedant un convergent a doubles parois
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
DE59706065D1 (de) * 1996-09-26 2002-02-21 Siemens Ag Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente
JP2002243154A (ja) * 2001-02-16 2002-08-28 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器尾筒出口構造及びガスタービン燃焼器
EP1312865A1 (fr) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Chambre de combustion annulaire de turbine à gaz
US7363763B2 (en) * 2003-10-23 2008-04-29 United Technologies Corporation Combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006120204A1 *

Also Published As

Publication number Publication date
US8091364B2 (en) 2012-01-10
EP1724526A1 (fr) 2006-11-22
US20090094986A1 (en) 2009-04-16
WO2006120204A1 (fr) 2006-11-16

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