EP1507116A1 - Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz - Google Patents

Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz Download PDF

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Publication number
EP1507116A1
EP1507116A1 EP03018415A EP03018415A EP1507116A1 EP 1507116 A1 EP1507116 A1 EP 1507116A1 EP 03018415 A EP03018415 A EP 03018415A EP 03018415 A EP03018415 A EP 03018415A EP 1507116 A1 EP1507116 A1 EP 1507116A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
coolant
cooling
combustion chamber
support structure
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Withdrawn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
EP03018415A
Other languages
German (de)
English (en)
Inventor
Stefan Dahlke
Heinrich Pütz
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 EP03018415A priority Critical patent/EP1507116A1/fr
Priority to EP04763361.5A priority patent/EP1654495B1/fr
Priority to PCT/EP2004/008116 priority patent/WO2005019730A1/fr
Priority to US10/568,115 priority patent/US7849694B2/en
Priority to CNA2004800216354A priority patent/CN1829879A/zh
Priority to JP2006522925A priority patent/JP4436837B2/ja
Publication of EP1507116A1 publication Critical patent/EP1507116A1/fr
Withdrawn legal-status Critical Current

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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
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the invention relates to a heat shield assembly for a Hot gas leading component, leaving a majority of under a gap arranged side by side on a supporting structure
  • a heat shield element attachable to the support structure, leaving an interior space is formed, the area by area to be cooled Hot gas wall is limited, with an inlet channel for inflow a coolant in the interior.
  • the invention further relates to a combustion chamber having an inner combustion liner, such a heat shield assembly has and a gas turbine with such a combustion chamber.
  • EP 0 224 817 B1 is a heat shield arrangement, in particular for structural parts of gas turbine plants, described.
  • the heat shield assembly serves to protect a support structure towards a hot fluid, in particular to Protection of a hot gas duct wall in gas turbine plants.
  • the Heat shield assembly has an inner lining made of heat-resistant Material on, which assembled nationwide is made of heat shield elements anchored to the support structure. These heat shield elements are under leave of Columns for the flow of cooling fluid arranged side by side and heat-mobile.
  • Each of these heat shield elements has a hat part and a shaft part in the manner of a mushroom on.
  • the hat part is a flat or spatial, polygonal Plate body with straight or curved boundary lines.
  • the shank part connects the central area of the plate body with the supporting structure.
  • the hat part has preferably a triangular shape, whereby by identical hat parts an inner lining can be produced almost any geometry.
  • the hat parts and possibly other parts of the heat shield elements consist of a high temperature resistant material, especially from a steel.
  • the support structure has holes through which a cooling fluid, in particular air, into a Gap in between space between hat and support structure can and from there through the column to flow through the Cooling fluid in a surrounded by the heat shield elements Room area, for example a combustion chamber of a gas turbine plant, can flow in. This cooling fluid flow is reduced the penetration of hot gas into the space.
  • US 5,216,886 is a metallic lining for a Combustion chamber described.
  • This lining consists of a plurality of juxtaposed cube-shaped Hollow components (cells) attached to a common metal plate welded or soldered.
  • the common metal plate assigns each cube-shaped cell associated with exactly one Opening for the inflow of cooling fluid.
  • the cube-shaped Cells are each adjacent to each other leaving a gap arranged. They are included in every sidewall in near the common metal plate has a respective opening for the outflow of cooling fluid.
  • the cooling fluid thus enters the gap between adjacent cube-shaped cells flows through this column and forms a hot gas at one exposable, parallel to the metallic plate directed Surface of the cells, a cooling film off.
  • a structure of a wall structure is described defined open cooling system in which cooling air over a Wall structure through the cells into the interior of the Combustion chamber got into it. The cooling air is therefore for more Cooling lost.
  • a wall in particular for gas turbine plants, described having cooling fluid channels.
  • the wall is preferably in gas turbine plants between a Hot room and a cooling fluid space arranged. she is off assembled together individual wall elements, wherein each of the wall elements a made of heat resistant material plate body is. Each plate body points over its base distributed, mutually parallel cooling channels on a End with a cooling fluid space and at the other end with the Hot room communicate. The inflowing into the hot room, through the cooling fluid channels guided cooling fluid forms on the the hot room facing surface of the wall element and / or adjacent wall elements a cooling fluid film.
  • GB-A-849255 is a cooling system for cooling a Combustor wall shown.
  • the combustion chamber wall is by wall elements educated.
  • Each wall element has a hot gas wall with a hot gas-actable outside and with a Inside up. Perpendicular to the inside nozzles are arranged. From these nozzles occurs cooling fluid in the form of a concentrated Current and hits the inside. Thereby the hot gas wall is cooled.
  • the cooling fluid is in a Collection chamber collected and discharged from the collection chamber.
  • the object of the invention is to provide a heat shield assembly, the Coolable with a coolant, specify so that at a Cooling of the heat shield assembly at most a smaller Loss of cooling fluid occurs.
  • the heat shield assembly should be used in a combustion chamber of a gas turbine.
  • the invention is based on the consideration that due to the very high flame temperatures in hot gas ducts or other hot gas spaces, for example in combustion chambers of stationary gas turbines, the hot gas leading components must be actively cooled.
  • a variety of cooling technologies - also in combination - can be used.
  • the most commonly used cooling concepts are convection cooling, convection cooling with turbulence-increasing measures and impingement cooling. Due to the very intensive efforts, in particular, to reduce the pollutant emissions of open-cooled systems, for example of open-cooled combustors of gas turbines, the saving of cooling air is a particularly important factor in achieving these goals - here an increased NO x reduction.
  • the goal for open-cooled cooling concepts is therefore to minimize the required cooling air mass flow.
  • the cooling air finally escapes through the gap of adjacent heat shield elements after the cooling task has ended, in order subsequently to reach the combustion chamber.
  • the outflow of cooling air protects the system from hot gas entering the gap.
  • the uncontrolled blowing out of the cooling air however, more cooling air is used to lock the column, as required for the cooling task. This overdose results in excessive cooling air consumption with detrimental consequences for the overall system efficiency and pollutant emissions of the hot gas generating combustion system.
  • the heat shield assembly is particularly easy to implement and compared to the closed cooling concepts with coolant return design associated with significantly lower manufacturing costs. Due to the controlled coolant outlet into the gap can be compared to the conventional concepts coolant, for. As cooling air, can be saved and at the same time a significant reduction in pollutant emissions are effected, in particular the NO x emission. This is achieved in that a coolant outlet channel is provided for the controlled exit of coolant from the interior, which opens from the interior into the gap.
  • this is in the gap by the targeted and metered admission of the gap with coolant a particularly high cooling efficiency and blocking effect of the coolant against a hot gas attack in the gap on the Support structure achieved.
  • the controlled discharge of coolant from the interior can thereby in a simple manner appropriate dimensioning of the coolant outlet channel, for example, with regard to the channel cross-section and the channel length, be made.
  • the heat shield element has a Side wall on, facing the hot gas wall in the direction the support structure is inclined.
  • the coolant outlet channel penetrates the side wall.
  • the coolant outlet channel can be done simply as a hole through the side wall be, wherein the interior with the formed by the gap Gap space is connected.
  • coolant may be due the pressure difference between the interior and the through The gap defined gap in a controlled manner exit the interior through the coolant outlet channel.
  • a sealing element between the side wall and the support structure attached.
  • the side wall in the direction of the support structure can at a releasably securing the heat shield element to the support structure provided a gap for thermo-mechanical reasons be, which can lead to unwanted refrigerant leaks. Therefore, it is particularly advantageous to use any column that an uncontrolled blowing out of coolant from the interior can lead to sealing by suitable sealing measures. This creates a tight connection between the Heat shield element and the support structure is provided.
  • the sealing element between the side wall and the supporting structure is a particularly simple but effective measure to to further reduce the coolant consumption.
  • the sealing element depending on the design additionally a damping function take over, so that the heat shield elements of the Heat shield assembly mechanically damped on the support structure are attached.
  • the interior of a heat shield element is a Impact cooling device assigned, so that the hot gas wall by means Impact cooling is coolable.
  • the impingement cooling is a particularly effective method of cooling the heat shield arrangement, wherein the coolant is in a plurality of discrete coolant jets perpendicular to the hot gas wall the hot gas wall bounces and the hot gas wall accordingly Cools efficiently from the inside.
  • the impact cooling device is characterized by a Variety of inlet channels for coolant formed in the support structure are introduced.
  • a Variety of inlet ducts for coolant formed in the support structure are introduced.
  • the support structure has in addition to the function to carry the heat shield assembly at the same time a coolant distribution function by the plurality inlet channels for the coolant entering the support structure are introduced.
  • the inlet channels can be used as holes be executed in the wall of the support structure.
  • the heat shield element made of a metal or a metal alloy. Offer for this in particular high-temperature metallic alloys on iron, chromium, nickel, or cobalt basis. As metals or metal alloys are well suited for a casting process, is the heat shield element advantageously as a Casting designed.
  • the heat shield assembly is in a particularly preferred embodiment suitable for use in a combustion chamber lining a combustion chamber.
  • a heat shield assembly provided combustion chamber is preferred as a combustion chamber of a gas turbine, in particular a stationary Gas turbine.
  • the gas turbine 1 has a compressor 2 for the combustion air, a combustion chamber 4 and a turbine 6 for driving a compressor 2 and a non-illustrated Generator or a working machine. These are the turbine 6 and the compressor 2 on a common, Turbine shaft 8, also referred to as a turbine runner, is arranged. with the generator or the working machine is connected, and mounted rotatably about its central axis 9 is.
  • the running in the manner of an annular combustion chamber combustion chamber 4 is with a number of burners 10 for combustion a liquid or gaseous fuel equipped.
  • the turbine 6 has a number of with the turbine shaft. 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 includes a number of stationary vanes 14, which is also coronal under the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft by momentum transfer from the turbine. 6 flowing through the hot medium, the working medium or the Hot gas M.
  • the guide vanes 14 serve to guide the flow of the working medium M between two in each case Flow direction of the working medium M seen consecutive Blades of blades or blades rims.
  • Turbine level One successive pair of a ring of vanes 14 or a vane 3 and a ring of blades 12 or a blade row is also called Turbine level called.
  • Each vane 14 has a so-called blade root Platform 18 on which is to fix the respective Guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component, the outer Limiting a hot gas channel for the turbine 6 flowing through working medium M forms.
  • Each blade 12 is in an analogous manner via a so-called blade root Platform 20 attached to the turbine shaft 8.
  • each guide ring 21 on the inner housing 16 of Turbine 6 is arranged between the spaced apart platforms 18 of the vanes 14 of two adjacent rows of vanes.
  • the outer surface of each guide ring 21 is also the hot, the turbine 6 flowing through Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite it 12 spaced by a gap.
  • the between adjacent Guide blade rows arranged guide rings 21st serve in particular as cover elements that the inner wall 16 or other housing-mounted components before a thermal Overuse by the turbine 6 flowing through hot Working medium M, the hot gas, protects.
  • the combustion chamber 4 is bounded by a combustion chamber housing 29, wherein combustion chamber side a combustion chamber wall 24 is formed is.
  • the combustion chamber 4 as designed a so-called annular combustion chamber, in whose Variety of circumferentially around the turbine shaft 8 around arranged burners 10 in a common combustion chamber space lead.
  • the combustion chamber 4 in its entirety as annular structure which around the turbine shaft. 8 is positioned around.
  • the combustion chamber for a comparatively high temperature of Working medium M designed from about 1200 ° C to 1500 ° C.
  • a heat shield assembly 26 which forms a combustion chamber lining. Due to the high temperatures inside the combustion chamber 4 is also for the heat shield assembly 26 provided a cooling system.
  • the Cooling system is based on the principle of impingement cooling, in the cooling air as coolant K under sufficiently high Pressure at a variety of locations on the cooling component is blown vertically under its component surface under pressure.
  • the cooling system can also be based on the principle of convective cooling are based or this cooling principle in addition to the impact cooling make use of.
  • the cooling system with a simple construction, is a reliable, area-wide exposure of the heat shield arrangement with coolant K and also to a particularly low Coolant consumption designed.
  • the cooling concept 2 shows a heat shield arrangement of the invention 26, as for use as a heat-resistant lining a combustion chamber 4 of a gas turbine 1 particularly suitable is.
  • the heat shield assembly 26 includes heat shield elements 26A, 26B, the side by side leaving a gap 45 are arranged on a support structure 31.
  • the heat shield elements 26A, 26B have a hot gas wall to be cooled 39, the one facing the hot gas M and in the operation of the hot gas M acted upon hot side 35 and one of the hot side 35 opposite cold side 33 has.
  • the heat shield elements 26A, 26B of their Cold side 33 ago by a coolant K for example, cooling air, cooled, that between the heat shield elements 26A, 26B and the support structure 31 formed by suitable interior 37 Inlet channels 41, 41A, 41B, 41C is delivered and in a direction perpendicular to the cold side 33 of a respective Heat shield element 26A, 26B is passed.
  • a coolant K for example, cooling air
  • Inlet channels 41, 41A, 41B, 41C is delivered and in a direction perpendicular to the cold side 33 of a respective Heat shield element 26A, 26B is passed.
  • the Principle of open cooling used.
  • After completion of the Cooling task on the heat shield elements 26A, 26B is the at least partially heated air to the hot gas M admixed.
  • a coolant outlet channel 43 for a controlled discharge and a precise dosage of Coolant K from the interior 37 is a coolant outlet channel 43 provided, from the interior 37 into the gap 45 opens.
  • the gap 45 is a precisely predetermined Mass flow of coolant K deliverable.
  • the variety intake passages 41, 41A, 41B, 41C each having an interior space 37 of a respective heat shield element 26A, 26B assigned form a baffle device 53, so that the hot gas wall 39 is particularly effective by means of impingement cooling is coolable.
  • the inlet channels 41, 41A, 41B, 41C for the Coolant K are here by corresponding holes in introduced the wall 47 of the support structure.
  • the inlet channels 41, 41A, 41B, 41C open into the interior 37, that achieved a vertical admission of the hot gas wall 39 is.
  • Coolant K from the interior 37 in a controlled manner through the correspondingly dimensioned coolant outlet channel 43 in the gap 45, where a barrier effect against the hot gas M is achieved, which includes the critical components, such as the support structure 31, protects.
  • FIG. 3 shows an enlarged view of the detail III of the heat shield assembly shown in Figure 2.
  • the heat shield element 26A has a side wall 49 which opposite the hot gas wall 39 in the direction of the support structure 31 is inclined. That adjacent to the heat shield member 26A Heat shield element 26B is in the same way with a Sidewall 49 designed.
  • the coolant outlet channel 43 is as a bore through the side wall 43 of the heat shield element 26A executed, the side wall 43 under a oblique, slightly rising towards the hot side 35 Angle in the gap 45 opens.
  • the coolant K After performance a blocking effect in the gap 45, the gap 45 as possible under Forming a cooling film of coolant K along the hot side 35 of the heat shield element 26A adjacent heat shield element 26B leaves. Due to this additional film cooling effect, with the targeted supply of the coolant K in the gap 45 is reached, is advantageously a multiple use of the coolant K for different cooling purposes in the heat shield assembly 26.
  • the side walls 49 are not directly on the support structure 31, but are over a respective Sealing element 51 connected to the support structure 31.
  • the sealing elements 51 fulfill both a sealing function for the Coolant K as well as a mechanical damping function for the heat shield assembly 26.
  • the sealing element 51 is prevents coolant K in an uncontrolled manner reach the interior 37 in the gap 45 and blown in Direction of the hot side 35 can be. Rather, that causes Sealing member 51 an additional reduction in the need for Coolant K for cooling de heat shield assembly 26.
  • the sealing element 51 With the coolant outlet channel 43 becomes a particularly favorable coolant balance achieved.
  • the coolant outlet channel 43 extends through the wall 47 of the support structure 31. Also with this embodiment is a targeted Delivery of the coolant K into the gap 45 after operation the cooling task to a heat shield element 26A possible.
  • the gap 45 Limiting side walls 49 additionally convection cooled.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03018415A 2003-08-13 2003-08-13 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz Withdrawn EP1507116A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP03018415A EP1507116A1 (fr) 2003-08-13 2003-08-13 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
EP04763361.5A EP1654495B1 (fr) 2003-08-13 2004-07-20 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
PCT/EP2004/008116 WO2005019730A1 (fr) 2003-08-13 2004-07-20 Systeme de bouclier thermique pour element constitutif guidant un gaz chaud, notamment pour chambre a combustion de turbine a gaz
US10/568,115 US7849694B2 (en) 2003-08-13 2004-07-20 Heat shield arrangement for a component guiding a hot gas in particular for a combustion chamber in a gas turbine
CNA2004800216354A CN1829879A (zh) 2003-08-13 2004-07-20 用在引导热气的组件,尤其是一种燃气轮机燃烧室上的热屏蔽配置
JP2006522925A JP4436837B2 (ja) 2003-08-13 2004-07-20 燃焼ガスを案内する構成要素

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03018415A EP1507116A1 (fr) 2003-08-13 2003-08-13 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1507116A1 true EP1507116A1 (fr) 2005-02-16

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EP03018415A Withdrawn EP1507116A1 (fr) 2003-08-13 2003-08-13 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
EP04763361.5A Active EP1654495B1 (fr) 2003-08-13 2004-07-20 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz

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Application Number Title Priority Date Filing Date
EP04763361.5A Active EP1654495B1 (fr) 2003-08-13 2004-07-20 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz

Country Status (5)

Country Link
US (1) US7849694B2 (fr)
EP (2) EP1507116A1 (fr)
JP (1) JP4436837B2 (fr)
CN (1) CN1829879A (fr)
WO (1) WO2005019730A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006045758A1 (fr) * 2004-10-25 2006-05-04 Siemens Aktiengesellschaft Procede d'evacuation a regulation optimale, de refroidissement par impact et de scellage d'un ecran thermique et element d'ecran thermique associe
WO2006111508A1 (fr) * 2005-04-19 2006-10-26 Siemens Aktiengesellschaft Systeme a ecran thermique
WO2008017551A2 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation d'incinération
WO2008017550A1 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation de combustion
WO2009150105A2 (fr) * 2008-06-12 2009-12-17 Siemens Aktiengesellschaft Dispositif de bouclier thermique
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US8522557B2 (en) 2006-12-21 2013-09-03 Siemens Aktiengesellschaft Cooling channel for cooling a hot gas guiding component
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US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
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EP2728255A1 (fr) * 2012-10-31 2014-05-07 Alstom Technology Ltd Agencement de segment de gaz chaud
US9714611B2 (en) 2013-02-15 2017-07-25 Siemens Energy, Inc. Heat shield manifold system for a midframe case of a gas turbine engine
EP3047127B1 (fr) 2013-09-16 2021-06-23 Raytheon Technologies Corporation Trous obliques de refroidissement de chemise de chambre de combustion formés à travers une structure transversale d'une chambre de combustion de turbine à gaz
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EP3060847B1 (fr) 2013-10-24 2019-09-18 United Technologies Corporation Géométrie de passage pour chambre de combustion de moteur de type turbine à gaz
EP3071816B1 (fr) 2013-11-21 2019-09-18 United Technologies Corporation Refroidissement d'une structure à parois multiples d'un moteur à turbine
WO2015077755A1 (fr) * 2013-11-25 2015-05-28 United Technologies Corporation Structure à multiples parois refroidie par film ayant une ou plusieurs indentations
EP3099976B1 (fr) * 2014-01-30 2019-03-13 United Technologies Corporation Flux de refroidissement pour un panneau principal dans une chambre de combustion de moteur à turbine à gaz
US10041675B2 (en) 2014-06-04 2018-08-07 Pratt & Whitney Canada Corp. Multiple ventilated rails for sealing of combustor heat shields
JP6282184B2 (ja) 2014-06-19 2018-02-21 三菱日立パワーシステムズ株式会社 伝熱装置及びそれを備えたガスタービン燃焼器
US10012385B2 (en) * 2014-08-08 2018-07-03 Pratt & Whitney Canada Corp. Combustor heat shield sealing
US9534785B2 (en) * 2014-08-26 2017-01-03 Pratt & Whitney Canada Corp. Heat shield labyrinth seal
DE102014221225A1 (de) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Hitzeschildelement und Verfahren zu seiner Herstellung
DE102015202570A1 (de) 2015-02-12 2016-08-18 Rolls-Royce Deutschland Ltd & Co Kg Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer
DE102015205975A1 (de) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs-Hitzeschildelement
GB201603166D0 (en) * 2016-02-24 2016-04-06 Rolls Royce Plc A combustion chamber
KR101872856B1 (ko) * 2017-04-27 2018-07-02 연세대학교 산학협력단 다층 복합 충돌 및 유출 냉각이 가능한 중공 핀과 충돌 흡입 구조의 가스터빈 연소기 라이너
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US11073285B2 (en) * 2019-06-21 2021-07-27 Raytheon Technologies Corporation Combustor panel configuration with skewed side walls
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB849255A (en) 1956-11-01 1960-09-21 Josef Cermak Method of and arrangements for cooling the walls of combustion spaces and other spaces subject to high thermal stresses
EP0224817B1 (fr) 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Ecran de protection contre la chaleur pour éléments structuraux d'une turbine à gaz
US5216886A (en) 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
GB2298266A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc A cooling arrangement for heat resistant tiles in a gas turbine engine combustor
WO1998013645A1 (fr) 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1005620B1 (fr) 1997-08-18 2002-07-03 Siemens Aktiengesellschaft Element constitutif d'un bouclier thermique a recirculation du fluide de refroidissement
US6470685B2 (en) * 2000-04-14 2002-10-29 Rolls-Royce Plc Combustion apparatus

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
WO1992001891A1 (fr) * 1990-07-17 1992-02-06 Siemens Aktiengesellschaft Tube-foyer a chassis-support refroidi pour revetement refractaire
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
FR2752916B1 (fr) * 1996-09-05 1998-10-02 Snecma Chemise de protection thermique pour chambre de combustion de turboreacteur
US6397765B1 (en) * 1998-03-19 2002-06-04 Siemens Aktiengesellschaft Wall segment for a combustion chamber and a combustion chamber
DE19963371A1 (de) * 1999-12-28 2001-07-12 Alstom Power Schweiz Ag Baden Gekühltes Hitzeschild
US6606861B2 (en) * 2001-02-26 2003-08-19 United Technologies Corporation Low emissions combustor for a gas turbine engine
EP1284390A1 (fr) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz
DE10214570A1 (de) * 2002-04-02 2004-01-15 Rolls-Royce Deutschland Ltd & Co Kg Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln
ES2307834T3 (es) * 2003-01-29 2008-12-01 Siemens Aktiengesellschaft Camara de combustion.
US7219498B2 (en) * 2004-09-10 2007-05-22 Honeywell International, Inc. Waffled impingement effusion method

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB849255A (en) 1956-11-01 1960-09-21 Josef Cermak Method of and arrangements for cooling the walls of combustion spaces and other spaces subject to high thermal stresses
EP0224817B1 (fr) 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Ecran de protection contre la chaleur pour éléments structuraux d'une turbine à gaz
US5216886A (en) 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
GB2298266A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc A cooling arrangement for heat resistant tiles in a gas turbine engine combustor
WO1998013645A1 (fr) 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP0928396B1 (fr) 1996-09-26 2001-11-21 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1005620B1 (fr) 1997-08-18 2002-07-03 Siemens Aktiengesellschaft Element constitutif d'un bouclier thermique a recirculation du fluide de refroidissement
US6470685B2 (en) * 2000-04-14 2002-10-29 Rolls-Royce Plc Combustion apparatus

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006045758A1 (fr) * 2004-10-25 2006-05-04 Siemens Aktiengesellschaft Procede d'evacuation a regulation optimale, de refroidissement par impact et de scellage d'un ecran thermique et element d'ecran thermique associe
WO2006111508A1 (fr) * 2005-04-19 2006-10-26 Siemens Aktiengesellschaft Systeme a ecran thermique
US8006498B2 (en) 2006-08-07 2011-08-30 Alstom Technology Ltd Combustion chamber of a combustion system
WO2008017551A2 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation d'incinération
WO2008017550A1 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation de combustion
WO2008017551A3 (fr) * 2006-08-07 2008-04-17 Alstom Technology Ltd Chambre de combustion d'une installation d'incinération
US8122726B2 (en) 2006-08-07 2012-02-28 Alstom Technology Ltd Combustion chamber of a combustion system
US8522557B2 (en) 2006-12-21 2013-09-03 Siemens Aktiengesellschaft Cooling channel for cooling a hot gas guiding component
DE102008028025B4 (de) * 2008-06-12 2011-05-05 Siemens Aktiengesellschaft Hitzeschildanordnung
WO2009150105A3 (fr) * 2008-06-12 2011-01-06 Siemens Aktiengesellschaft Dispositif de bouclier thermique
DE102008028025A1 (de) 2008-06-12 2009-12-24 Siemens Aktiengesellschaft Hitzeschildanordnung
RU2508507C2 (ru) * 2008-06-12 2014-02-27 Сименс Акциенгезелльшафт Устройство с теплозащитным экраном, камера сгорания и газовая турбина
WO2009150105A2 (fr) * 2008-06-12 2009-12-17 Siemens Aktiengesellschaft Dispositif de bouclier thermique
EP2549063A1 (fr) 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Élément d'écran thermique pour une turbine à gaz
WO2013011126A2 (fr) 2011-07-21 2013-01-24 Siemens Aktiengesellschaft Élément formant écran thermique, turbine à gaz
WO2014169127A1 (fr) 2013-04-12 2014-10-16 United Technologies Corporation Refroidissement de jonction en t de panneau de chambre de combustion
EP2984317A4 (fr) * 2013-04-12 2016-03-30 United Technologies Corp Refroidissement de jonction en t de panneau de chambre de combustion
US10816201B2 (en) * 2013-09-13 2020-10-27 Raytheon Technologies Corporation Sealed combustor liner panel for a gas turbine engine
EP2927592A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Élément de bouclier thermique, bouclier thermique et turbomachine
US9896970B2 (en) 2014-11-14 2018-02-20 General Electric Company Method and system for sealing an annulus
US10619854B2 (en) 2016-11-30 2020-04-14 United Technologies Corporation Systems and methods for combustor panel
EP3330612A1 (fr) * 2016-11-30 2018-06-06 United Technologies Corporation Systèmes et procédés pour chambre de combustion
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
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EP3628928A1 (fr) * 2017-03-20 2020-04-01 United Technologies Corporation Ensemble de revêtement avec joint pour moteur à turbine à gaz
EP3379148A1 (fr) * 2017-03-20 2018-09-26 United Technologies Corporation Ensemble de revêtement avec joint pour moteur à turbine à gaz
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
DE102018212394A1 (de) * 2018-07-25 2020-01-30 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
US11137139B2 (en) 2018-07-25 2021-10-05 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with a flow guiding device comprising a wall element

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CN1829879A (zh) 2006-09-06
JP2007501927A (ja) 2007-02-01
WO2005019730A1 (fr) 2005-03-03
EP1654495A1 (fr) 2006-05-10
EP1654495B1 (fr) 2017-04-12
US20090077974A1 (en) 2009-03-26
US7849694B2 (en) 2010-12-14

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