EP2182285A1 - Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine - Google Patents

Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine Download PDF

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Publication number
EP2182285A1
EP2182285A1 EP08018907A EP08018907A EP2182285A1 EP 2182285 A1 EP2182285 A1 EP 2182285A1 EP 08018907 A EP08018907 A EP 08018907A EP 08018907 A EP08018907 A EP 08018907A EP 2182285 A1 EP2182285 A1 EP 2182285A1
Authority
EP
European Patent Office
Prior art keywords
burner
combustion chamber
wall
gas turbine
burner insert
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Withdrawn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
EP08018907A
Other languages
German (de)
English (en)
French (fr)
Inventor
Andreas Dr. Böttcher
Andre Kluge
Tobias Krieger
Jürgen Dr. Meisl
Kai-Uwe Dr. Schildmacher
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 EP08018907A priority Critical patent/EP2182285A1/de
Priority to US13/126,239 priority patent/US9074771B2/en
Priority to ES09823099T priority patent/ES2426395T3/es
Priority to EP09823099.8A priority patent/EP2340397B1/de
Priority to RU2011121647/06A priority patent/RU2530684C2/ru
Priority to PCT/EP2009/061854 priority patent/WO2010049206A1/de
Priority to JP2011533647A priority patent/JP5349605B2/ja
Priority to CN200980142861.0A priority patent/CN102203509B/zh
Publication of EP2182285A1 publication Critical patent/EP2182285A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a combustor liner for a gas turbine combustor having a burner port for inserting a combustor.
  • the invention relates to a gas turbine.
  • Gas turbine combustors have a burner-side end and a turbine-side end.
  • the turbine-side end is open and allows outflow of combustion gases in the hot combustion gases to the turbine.
  • a burner insert is present, which has a heat-resistant hot side and a cooled cold side. The burner is inserted into an opening of the burner insert.
  • cooling air which usually comes from the compressor, flows along the cold side from the burner opening of the burner insert to its outer edge, from where the cooling air flows into the combustion chamber.
  • An example of a burner insert in a tube combustion chamber is in US 2005/0016178 A1 described.
  • annular combustion chambers that is to say of combustion chambers which extend annularly around the turbine rotor
  • a multiplicity of combustion inserts in the circumferential direction of the annular combustion chamber are usually arranged next to one another.
  • the cooling air flowing past the cold side of the burner side then flows into the combustion chamber between the radially outer wall and the radially inner wall of the combustion chamber.
  • cooling air can also be introduced into the combustion chamber by gaps between circumferentially adjacent combustion inserts.
  • Such an annular combustion chamber is, for example, in EP 1 557 607 A1 described.
  • FIG. 1 A burner insert for an annular combustion chamber is shown schematically in FIG. 1 shown.
  • the figure shows a burner insert for an annular combustion chamber in a cut perspective view on its cold side 103.
  • an opening 105 In the center of the cold side 103 of the burner insert 100 is an opening 105 into which the burner can be used.
  • the burner insert is fastened by means of an annular ridge 107 in a cold side projecting portion 109 of the burner insert 100 to a support structure in the gas turbine housing.
  • the cold side 103 of the burner insert 100 is provided with ribs 111.
  • support screws 113 are present, which in FIG. 1 are indicated only schematically.
  • the screws 113 and the ribs 111 represent support sections, with which the cold side comes to rest on the support structure in the gas turbine housing.
  • it may lead to the formation of a non-uniform gap along the peripheral edge of the burner insert, which can lead to an oversupply of cooling air in places with increased gap.
  • this is due to the fact that in addition to the ribs 111 and the support bolts 113 are present, a static overdetermination, since the burner insert 100 is to rest on the screws except at the same time on the ribs 11.
  • the first object is achieved by a burner insert according to claim 1, the second object by a gas turbine combustion chamber according to claim 9 and a gas turbine according to claim 13.
  • the dependent claims contain advantageous embodiments of the invention.
  • An inventive burner insert for a gas turbine combustor has a burner insert wall with a cold side and a hot side.
  • a burner opening for inserting a burner is formed in the burner insert wall.
  • the burner insert has an outer edge delimiting the burner insert wall with an at least partially encircling edge web projecting over the cold side.
  • the edge may in this case be substantially circular, for example in the case of a tube combustion chamber, or, for example in the case of an annular combustion chamber, have the shape of the edge of a circular ring cutout. Other contours are basically possible depending on the shape of the combustion chamber.
  • the edge web of the burner insert according to the invention leads to an increase in the natural frequencies in comparison to a burner insert according to the prior art, as with reference to FIG. 1 has been described.
  • the vibration load of the burner insert during operation of the combustion chamber is therefore reduced in comparison to the burner insert from the prior art.
  • the edge web can rest completely on the support structure in the gas turbine housing, so that a uniform gap, preferably a zero gap, is present along the entire edge.
  • the edge web is to be provided in an embodiment of the invention with openings for the passage of cooling fluid.
  • the edge web may have crenels between which the openings are formed, and / or with through-holes, for example Holes, be equipped. Due to the fact that defined openings in the edge web can be produced by means of the battlements or holes, an exact adjustment of the amount of cooling air passing through the edge web is possible by suitable choice of the pebble size or the free diameter of the holes. In the case of battlements, these can be generated, for example, by interrupting the edge web. It is advantageous, however, if the edge web is not interrupted and, instead, the edge web projects further in the crenellated areas over the cold side than in the remaining regions of the edge web. In addition to the openings described also other forms of openings are conceivable, for example. Slots.
  • the edge web runs around the entire edge of the burner insert.
  • the rigidity of the edge of the burner insert is then particularly high.
  • the burner opening is surrounded by an annular, over the cold side projecting and provided with an annular web wall portion. Otherwise, the burner insert wall is formed flat, d. H.
  • the existing in the art ribs there are no other structures, such as the existing in the art ribs. In the case of the burner insert according to the invention such ribs are superfluous, since it has been shown that a uniform distribution of the cooling air takes place even without such ribs. Also, a stiffening function of the ribs is not needed in the burner insert according to the invention.
  • the burner insert according to the invention makes it possible to save cooling air, since no uneven gap dimensions occur, which can lead to an oversupply in the cooling air supply.
  • the reduced supply of cooling air into the combustion chamber results in a reduced pollutant emissions of the gas turbine and higher turbine inlet temperatures, which in turn allows an increase in efficiency of the gas turbine.
  • the amount of cooling air flowing into the combustion chamber can be set in a defined manner.
  • the setting of a zero gap between the end face of the edge web or the pinnacles and the support structure or the combustion chamber wall is possible.
  • the design of the burner insert according to the invention also enables a cost reduction, since the stiffening screws are eliminated and therefore fewer components are required in comparison to the burner insert described in the introduction.
  • a gas turbine combustor according to the invention has at least one burner, at least one combustion chamber wall surrounding a combustion chamber interior, and at least one burner end wall on the burner side. It comprises a burner insert according to the invention whose burner insert wall forms the combustion chamber end wall, the hot side of the burner insert wall facing the combustion chamber interior.
  • the combustion chamber wall may be cylindrical in the case of a tube combustion chamber. In the case of an annular combustion chamber, however, two combustion chamber walls are present, namely a radially outer and a radially inner combustion chamber wall.
  • a gap may be present between the combustion chamber closure wall formed by the at least one burner insert and the at least one combustion chamber wall, which allows the outflow of cooling air from the cold side of the combustion insert into the combustion chamber.
  • the burner-side combustion chamber end wall can be formed in particular by a number in the circumferential direction of the combustion chamber juxtaposed burner inserts. There may be gaps between adjacent burner inserts which allow the flow of cooling air between the burner inserts into the annular combustion chamber.
  • a gas turbine according to the invention is equipped with at least one gas turbine combustion chamber, which is designed as a gas turbine combustion chamber according to the invention.
  • the gas turbine according to the invention comprises a cooling fluid reservoir, for example a combustion chamber plenum communicating with the output of a compressor, wherein the cold side of the burner insert wall is fluidically connected to the cooling fluid reservoir.
  • FIG. 1 shows a burner insert according to the prior art.
  • FIG. 2 shows a gas turbine in a longitudinal section.
  • FIG. 3 shows an annular combustion chamber in a partially sectioned perspective view.
  • FIG. 4 shows a burner insert according to the invention.
  • FIG. 5 shows the edge of the burner insert FIG. 4 .
  • FIG. 6 shows the edge of the burner insert in a detailed view.
  • FIG. 7 shows the edge of a modified burner insert in a detailed view.
  • FIG. 2 shows a gas turbine 1 in a longitudinal section.
  • This comprises a compressor section 3, a combustion chamber section 5 and a turbine section 7.
  • a shaft 9 extends through all sections of the gas turbine 1.
  • the shaft 9 is provided with rings of compressor blades 11 and in the turbine section 7 with rings of turbine blades 13.
  • Wreaths of compressor guide vanes 15 are located between the rotor blade rings in the compressor section 3 and rings of turbine guide vanes 17 in the turbine section 17.
  • the guide vanes extend from the housing 19 of the gas turbine installation 1 essentially in the radial direction to the shaft 9.
  • air 23 is sucked in through an air inlet 21 of the compressor section 3 and compressed by the compressor rotor blades 11.
  • the compressed air is supplied to a combustion chamber 25 arranged in the combustion chamber 25, which is configured in the present embodiment as an annular combustion chamber, into which a gaseous or liquid fuel via at least one burner 27 is injected.
  • the resulting air-fuel mixture is ignited and burned in the combustion chamber 25.
  • the hot combustion exhaust gases flow from the combustor 25 into the turbine section 7, where they expand and cool, imparting momentum to the turbine blades 13.
  • the turbine guide vanes 17 serve as nozzles for optimizing the momentum transfer to the rotor blades 13.
  • the rotation of the shaft 9 brought about by the momentum transfer is used to drive a load, for example an electric generator.
  • the expanded and cooled combustion gases are finally discharged from the gas turbine 1 through an outlet 31.
  • the annular combustion chamber 25 of in FIG. 2 shown gas turbine is in FIG. 3 shown in a perspective, partially cutaway view.
  • Both the outer combustion chamber wall 33 and the inner combustion chamber wall 35 are provided with a hot gas-resistant lining, which is formed from heat shield elements 37.
  • heat shield elements in the present embodiment ceramic heat shield elements are used.
  • the turbine section 7 facing the end of the combustion chamber has a hot gas outlet opening 39, through which the resulting inside the combustion chamber 25 hot combustion gases can flow to the turbine.
  • At the hot gas outlet 39 opposite end of the annular combustion chamber 25 is formed from burner inserts 41 Brennschschschschillerwand available. In each burner insert 41, a burner 27 is received.
  • the burner inserts 41 are in this case not directly connected to the outer combustion chamber wall 33 and the inner combustion chamber wall 35, but arranged on a support structure (not shown), which in turn is attached to the housing of the gas turbine. Between the individual burner inserts 41 on the one hand and the outer wall 33 and the inner wall 35 on the other hand remains a gap which allows the inflow of cooling air along the respective wall into the interior of the combustion chamber.
  • the burner inserts 41 are arranged so that between them, ie between circumferentially adjacent edges of the burner inserts 41, remain gaps that allow the entry of cooling air into the combustion chamber interior.
  • a burner insert is in FIG. 4 shown in a partially cut perspective view. It comprises a burner insert wall 42 with a cold side 43 and a hot side 44, which is to be turned to the combustion chamber interior (the hot side is in FIG. 4 not recognizable).
  • the cold side 43 communicates with the outlet of the compressor in fluid communication so that compressor air can be bypassed for cooling purposes on the cold side 43 to the temperature of the hot side on one for the material of the burner insert 41 acceptable level.
  • the hot side is also provided with a heat-insulating coating, for example in the form of a ceramic coating, in order to reduce the need for cooling air.
  • the burner insert 41 has an opening 45 into which the outlet of a burner 27 can be inserted.
  • the opening 45 is delimited by a section 47 of the burner insert wall 42 projecting beyond the cold side 43. From this projecting portion 47 extending in the radial direction of the opening 45 extending annular ridge, with which the burner insert 41 can be attached to a support structure.
  • the entire outer edge 46 of the burner insert 41 is provided with an over the cold side 43 projecting edge web 51, which gives the edge 46 increased rigidity and ensures that the natural frequency of the burner insert wall 42 is increased.
  • Detail views of the edge 46 with the edge web 51 are in the FIGS. 5 and 6 shown.
  • the edge web 51 has battlements 53, which are formed by portions of the edge web 51, which project further beyond the cold side 43 than the remaining portions 54 of the edge web 51. If the burner insert is attached to a support structure and forms part of a combustion chamber end wall, lie Pinnacles 53 with the most distant from the cold side 43 end faces 55 on a contact surface of the support structure with a zero gap. Between the pinnacles 53 windows 57 are then formed, can flow through the cooling air, which is usually supplied in the region of the projecting wall portion 47 from the compressor into the combustion chamber. The cooling air can then flow along the cold side 43, which is completely flat except for the edge web 51 and the protruding wall region 47, for cooling.
  • the windows 57 between the pinnacles 53 represent openings for the flowing cooling air with a defined passage cross-section, since the end faces 55 of the pinnacles 53 abut with zero gap on the investment structure.
  • edge bar 51 in the FIGS. 4 to 6 shown embodiment with battlements 53 is provided to define window openings 57 for the cooling air, it is also possible to let the edge web 51 project uniformly over the cold side 43. Cooling air passages can then be realized by means of through-holes 59, for example in the form of bores.
  • a corresponding embodiment of the burner insert according to the invention is in FIG. 7 shown.
  • the edge web extends along the entire outer edge 46 of the burner insert 41
  • embodiments are conceivable in which areas of the outer edge 46 of the burner insert 41 have no edge web 51.
  • embodiments for cylindrical combustion chambers are possible.
  • the outer edge of the burner insert would be substantially circular and the edge web would be present at least along a part of the circumference, preferably around the entire circumference.
  • the invention makes it possible to increase the natural frequency of the burner insert and at the same time the targeted adjustment of the outflow of cooling air into the combustion chamber, so that the cooling air can flow only through the predefined column. Associated with this, there are further advantages of the invention such as a longer service life of the burner insert and - by the cooling air saved at the burner insert - a reduction of pollutants at the same power of the burner inserts provided with the gas turbine, when the saved cooling air is supplied to the burner. Alternatively, higher outputs can be achieved with the same emissions.

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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)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP08018907A 2008-10-29 2008-10-29 Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine Withdrawn EP2182285A1 (de)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP08018907A EP2182285A1 (de) 2008-10-29 2008-10-29 Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine
US13/126,239 US9074771B2 (en) 2008-10-29 2009-09-14 Burner inserts for a gas turbine combustion chamber and gas turbine
ES09823099T ES2426395T3 (es) 2008-10-29 2009-09-14 Pieza de implementación para el quemador de una cámara de combustión de una turbina de gas y turbina de gas
EP09823099.8A EP2340397B1 (de) 2008-10-29 2009-09-14 Brennereinsatz für eine gasturbinenbrennkammer und gasturbine
RU2011121647/06A RU2530684C2 (ru) 2008-10-29 2009-09-14 Подставка для горелки камеры сгорания газовой турбины и газовая турбина
PCT/EP2009/061854 WO2010049206A1 (de) 2008-10-29 2009-09-14 Brennereinsatz für eine gasturbinenbrennkammer und gasturbine
JP2011533647A JP5349605B2 (ja) 2008-10-29 2009-09-14 ガスタービン燃焼室用のバーナ挿入装置およびガスタービン
CN200980142861.0A CN102203509B (zh) 2008-10-29 2009-09-14 燃气轮机燃烧室的燃烧器插座和燃气轮机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08018907A EP2182285A1 (de) 2008-10-29 2008-10-29 Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine

Publications (1)

Publication Number Publication Date
EP2182285A1 true EP2182285A1 (de) 2010-05-05

Family

ID=40672584

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08018907A Withdrawn EP2182285A1 (de) 2008-10-29 2008-10-29 Brennereinsatz für eine Gasturbinenbrennkammer und Gasturbine
EP09823099.8A Active EP2340397B1 (de) 2008-10-29 2009-09-14 Brennereinsatz für eine gasturbinenbrennkammer und gasturbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09823099.8A Active EP2340397B1 (de) 2008-10-29 2009-09-14 Brennereinsatz für eine gasturbinenbrennkammer und gasturbine

Country Status (7)

Country Link
US (1) US9074771B2 (ja)
EP (2) EP2182285A1 (ja)
JP (1) JP5349605B2 (ja)
CN (1) CN102203509B (ja)
ES (1) ES2426395T3 (ja)
RU (1) RU2530684C2 (ja)
WO (1) WO2010049206A1 (ja)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
US9322560B2 (en) * 2012-09-28 2016-04-26 United Technologies Corporation Combustor bulkhead assembly
US20150033746A1 (en) * 2013-08-02 2015-02-05 Solar Turbines Incorporated Heat shield with standoffs
US9534786B2 (en) * 2014-08-08 2017-01-03 Pratt & Whitney Canada Corp. Combustor heat shield
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
DE102016206188A1 (de) * 2016-04-13 2017-10-19 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US11022307B2 (en) 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US20190285276A1 (en) * 2018-03-14 2019-09-19 United Technologies Corporation Castellated combustor panels
DE102018212394B4 (de) 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
US11015807B2 (en) * 2019-01-30 2021-05-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2107448A (en) * 1980-10-21 1983-04-27 Rolls Royce Gas turbine engine combustion chambers
US5396759A (en) * 1990-08-16 1995-03-14 Rolls-Royce Plc Gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US20050016178A1 (en) 2002-12-23 2005-01-27 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
US20050138931A1 (en) * 2002-05-14 2005-06-30 Monica Pacheco-Tougas Bulkhead panel for use in a combustion chamber of a gas turbine engine
EP1557607A1 (de) 2004-01-21 2005-07-27 Siemens Aktiengesellschaft Brenner mit gekühltem Bauteil, Gasturbine sowie Verfahren zur Kühlung des Bauteils
EP1767855A1 (de) 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Brennkammer und Gasturbinenanlage

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
GB2287310B (en) * 1994-03-01 1997-12-03 Rolls Royce Plc Gas turbine engine combustor heatshield
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US6032457A (en) * 1996-06-27 2000-03-07 United Technologies Corporation Fuel nozzle guide
US5974805A (en) * 1997-10-28 1999-11-02 Rolls-Royce Plc Heat shielding for a turbine combustor
RU31818U1 (ru) * 2002-11-21 2003-08-27 ОАО Самарский научно-технический комплекс им. Н.Д. Кузнецова Газотурбинный двигатель НК-37, компрессор, камера сгорания, турбина
RU52982U1 (ru) * 2005-08-03 2006-04-27 ЭКОЛ спол. с.р.о. Горелка для сжигания с низкими эмиссиями вредных веществ и система горелок
RU52992U1 (ru) 2005-10-24 2006-04-27 Ираклий Отарович Чиквиладзе Радиатор двигателя внутреннего сгорания гоночного автомобиля
US7665306B2 (en) * 2007-06-22 2010-02-23 Honeywell International Inc. Heat shields for use in combustors

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2107448A (en) * 1980-10-21 1983-04-27 Rolls Royce Gas turbine engine combustion chambers
US5396759A (en) * 1990-08-16 1995-03-14 Rolls-Royce Plc Gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US20050138931A1 (en) * 2002-05-14 2005-06-30 Monica Pacheco-Tougas Bulkhead panel for use in a combustion chamber of a gas turbine engine
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US20050016178A1 (en) 2002-12-23 2005-01-27 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
EP1557607A1 (de) 2004-01-21 2005-07-27 Siemens Aktiengesellschaft Brenner mit gekühltem Bauteil, Gasturbine sowie Verfahren zur Kühlung des Bauteils
EP1767855A1 (de) 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Brennkammer und Gasturbinenanlage

Also Published As

Publication number Publication date
WO2010049206A1 (de) 2010-05-06
RU2530684C2 (ru) 2014-10-10
EP2340397B1 (de) 2013-07-31
CN102203509A (zh) 2011-09-28
JP2012506991A (ja) 2012-03-22
US9074771B2 (en) 2015-07-07
ES2426395T3 (es) 2013-10-23
EP2340397A1 (de) 2011-07-06
RU2011121647A (ru) 2012-12-10
US20110197590A1 (en) 2011-08-18
CN102203509B (zh) 2014-07-09
JP5349605B2 (ja) 2013-11-20

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