EP1351022A2 - Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux - Google Patents

Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux Download PDF

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Publication number
EP1351022A2
EP1351022A2 EP03001782A EP03001782A EP1351022A2 EP 1351022 A2 EP1351022 A2 EP 1351022A2 EP 03001782 A EP03001782 A EP 03001782A EP 03001782 A EP03001782 A EP 03001782A EP 1351022 A2 EP1351022 A2 EP 1351022A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shingle
air hole
mixed air
gas turbine
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.)
Granted
Application number
EP03001782A
Other languages
German (de)
English (en)
Other versions
EP1351022A3 (fr
EP1351022B1 (fr
Inventor
Miklos Dr.-Ing. Gerendas
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1351022A2 publication Critical patent/EP1351022A2/fr
Publication of EP1351022A3 publication Critical patent/EP1351022A3/fr
Application granted granted Critical
Publication of EP1351022B1 publication Critical patent/EP1351022B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to a gas turbine combustor with combustion chamber shingles, with the combustion chamber shingles on a support structure of the gas turbine combustion chamber are attached and each have at least one mixed air hole, which arranged in alignment with a mixed air hole in the supporting structure is.
  • the constructions known from the prior art are formed so that the diameter of the mixed air hole Support structure (shingle support) at most slightly larger is than the diameter of the mixed air hole of the combustion chamber shingle.
  • the difference in size is used in the prior art just to make sure that the worst possible combination of all manufacturing and assembly tolerances the edge of the Mixing air hole of the combustion chamber shingle not from the edge of the Mixed air hole of the support structure is towered over.
  • the object of the invention is a gas turbine combustion chamber with combustion chamber shingles of the type mentioned To create kind, which with simple construction, simpler, less expensive Manufacturability and easy assembly a high Has lifespan and overheating of the entire construction avoids.
  • the diameter of the Mixed air hole of the support structure is significantly larger than that Diameter of the mixed air hole in the combustion chamber shingle.
  • the configuration according to the invention is characterized by a A number of significant advantages.
  • Diameter of the mixed air hole of the support structure and the Mixing air hole of the combustion chamber shingle can be achieved that due to the strong back pressure on the thickened edge of the Combustion chamber shingle when there is a gap between the Combustion chamber shingle and the supporting structure, which by a Overheating of the clapboard is caused, additional Cooling air from the mixed air hole into the interior of the shingle flows and thus intensifies the cooling of the combustion chamber shingle.
  • Adaptive cooling is thus implemented according to the invention, in which the amount of cooling air automatically depends on the temperature load the combustion chamber shingle is adjusted.
  • the effusion holes can be on the back the surface of the combustion chamber shingle or in the edge of the shingle begin, being on the inside of the shingle or the Support structure facing side can enter.
  • the effusion holes end on the surface of the combustion chamber shingle or on the inside of the mixed air hole in the combustion chamber shingle.
  • the effusion holes can be without or with a peripheral component around the axis of the mixed air hole. Hot gas side the combustion chamber shingle.
  • the amount of cooling air in the initial state the gas turbine combustion chamber can be selected that it is just sufficient for normal operation.
  • the maximum amount of air thus stands for the reduction of harmful gas to disposal.
  • the Combustion chamber shingle is subjected to greater thermal stress automatically increases the cooling, so that a long-lasting and safe operation is possible.
  • Fig. 1 shows a schematic side sectional view of a gas turbine combustor known from the prior art.
  • a cover 1 of a combustion chamber head is shown.
  • Reference number 2 denotes a base plate
  • Combustion chamber shingles are identified by reference number 3.
  • the combustion chamber shingles 3 have mixed air holes 4 and are attached to a support structure 6.
  • With the reference symbol 5 is a heat shield with a hole for a burner Designated 8.
  • a turbine guide vane is located at the outlet of the combustion chamber 9 is shown schematically.
  • the reference number 10 denotes a guide vane in the compressor outlet.
  • On Combustion chamber outer casing 11 and a combustion chamber inner casing 12 limits the combustion chamber.
  • Fig. 2a and 2b show the design of a mixed air hole 4 of the combustion chamber shingle 3 and a corresponding one Mixed air hole of the support structure 6 according to the prior art. It can be seen that the diameter 13 of the Mixed air hole of the support structure 6 is slightly larger, than the diameter 14 of the mixed air hole 4 of the combustion chamber shingle 3. From Fig. 2b it can be seen that the air flow 15 in the mixed air hole 4, additional air from the interior of the shingle draws.
  • Figures 3a and 3b show the configuration according to the invention in an analogous representation to Figs. 2a and 2b. It can be seen that the diameter 13 of the mixed air hole of the Support structure 6 is clearer or significantly larger than that Diameter 14 of the mixed air hole 4 of the combustion chamber shingle 3. From Fig. 3b it can be seen that a dynamic pressure of the Air flow 15 for an additional inflow of cooling air leads into the interior of the shingle as soon as there is a gap forms between the support structure 6 and the shingle edge 7.
  • Fig. 4a shows a partial area in an enlarged view a combustion chamber shingle according to the invention 3 it can be seen that by the shingle edge 7 in the area of the mixed air hole 4 additional effusion holes 16 are provided are to cool air from the shingle interior to feed the combustion chamber shingle 3.
  • the effusion holes 16 in different orientations be arranged to the level of the combustion chamber shingle 3.
  • the Effusion hole 16a is arranged at a very shallow angle, while the effusion holes 16b and 16d extend through the Shingle edge 7 extend and at a larger angle to Main plane of the combustion chamber shingle 3 are aligned.
  • the Effusion hole 16e extends almost perpendicular to the main plane the combustion chamber shingle 3 and flows through the edge of the shingle 7th
  • Fig. 4b shows two different versions of the effusion holes 16 in the top view of the mixed air hole 4 of the combustion chamber shingle 3.
  • the effusion holes are each arranged radially (regardless of the respective angle of inclination according to Fig. 4a), while in the right figure of Fig. 4b an additional Tangential components around the axis of the mixed air hole or a tangential arrangement of the effusion holes 16 is realized is. This enables particularly efficient cooling respectively.

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)
EP03001782A 2002-04-02 2003-01-28 Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux Expired - Fee Related EP1351022B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10214570A DE10214570A1 (de) 2002-04-02 2002-04-02 Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln
DE10214570 2002-04-02

Publications (3)

Publication Number Publication Date
EP1351022A2 true EP1351022A2 (fr) 2003-10-08
EP1351022A3 EP1351022A3 (fr) 2005-01-26
EP1351022B1 EP1351022B1 (fr) 2010-08-04

Family

ID=27816106

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001782A Expired - Fee Related EP1351022B1 (fr) 2002-04-02 2003-01-28 Passage d'alimentation en air pour chambre de combustion de turbine comprenant des bardeaux

Country Status (3)

Country Link
US (1) US7059133B2 (fr)
EP (1) EP1351022B1 (fr)
DE (2) DE10214570A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2172708A3 (fr) * 2008-10-01 2014-05-14 United Technologies Corporation Structures dotées d'un refroidissement adaptatif
EP2738470A1 (fr) * 2012-11-28 2014-06-04 Rolls-Royce Deutschland Ltd & Co KG Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
EP2971668A4 (fr) * 2013-03-12 2016-03-02 United Technologies Corp Refroidissement actif de bossages d'oeillet pour un panneau de chambre de combustion d'un moteur à turbine à gaz
EP3077727A4 (fr) * 2013-12-06 2016-12-07 United Technologies Corp Refroidissement d'un corps à ouverture de refroidissement rapide de paroi de chambre de combustion
EP3306196A1 (fr) * 2016-10-06 2018-04-11 Rolls-Royce Deutschland Ltd & Co KG Assemblage de chambre de combustion d'une turbine à gaz ainsi que turbine à gaz d'avion
EP3431875A1 (fr) * 2017-07-19 2019-01-23 United Technologies Corporation Trous de dilution pour moteurs à turbine à gaz
US11137140B2 (en) 2017-10-04 2021-10-05 Raytheon Technologies Corporation Dilution holes with ridge feature for gas turbine engines

Families Citing this family (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1250906C (zh) * 2001-09-07 2006-04-12 阿尔斯托姆科技有限公司 减小燃气轮机装置中的燃烧室脉动的减振装置
EP1507116A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
US7140185B2 (en) * 2004-07-12 2006-11-28 United Technologies Corporation Heatshielded article
US8161752B2 (en) * 2008-11-20 2012-04-24 Honeywell International Inc. Combustors with inserts between dual wall liners
EP2463582B1 (fr) 2010-12-10 2019-06-19 Rolls-Royce plc Chambre de combustion
US9062884B2 (en) 2011-05-26 2015-06-23 Honeywell International Inc. Combustors with quench inserts
GB201116608D0 (en) * 2011-09-27 2011-11-09 Rolls Royce Plc A method of operating a combustion chamber
US9038395B2 (en) 2012-03-29 2015-05-26 Honeywell International Inc. Combustors with quench inserts
US9174309B2 (en) 2012-07-24 2015-11-03 General Electric Company Turbine component and a process of fabricating a turbine component
DE102012015452A1 (de) * 2012-08-03 2014-04-24 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand mit Mischluftöffnungen und Luftleitelementen
DE102012022199A1 (de) 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
DE102012022259A1 (de) 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
US20150354819A1 (en) * 2013-01-16 2015-12-10 United Technologies Corporation Combustor Cooled Quench Zone Array
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
US11112115B2 (en) * 2013-08-30 2021-09-07 Raytheon Technologies Corporation Contoured dilution passages for gas turbine engine combustor
EP3922829B1 (fr) * 2013-09-16 2023-11-08 RTX Corporation Chambre de combustion de turbine à gaz comprenant une chemise munie de trous de refroidissement à travers une structure transversale
EP3047128B1 (fr) 2013-09-16 2018-10-31 United Technologies Corporation Variation contrôlée de la chute de pression par refroidissement par effusion dans une chambre de combustion à double paroi d'une turbine à gaz
DE102013223258A1 (de) 2013-11-14 2015-06-03 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerhitzeabschirmelement einer Gasturbine
US10502422B2 (en) * 2013-12-05 2019-12-10 United Technologies Corporation Cooling a quench aperture body of a combustor wall
EP3077640B1 (fr) * 2013-12-06 2021-06-02 Raytheon Technologies Corporation Refroidissement d'orifice de trempe de chambre de combustion
WO2015147929A2 (fr) * 2013-12-20 2015-10-01 United Technologies Corporation Refroidissement d'un corps à ouverture d'une paroi de chambre de combustion
DE102014204466A1 (de) 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
DE102014204472A1 (de) 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
DE102014222320A1 (de) 2014-10-31 2016-05-04 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerwand einer Gasturbine mit Kühlung für einen Mischluftlochrand
US10788212B2 (en) * 2015-01-12 2020-09-29 General Electric Company System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
US10094564B2 (en) 2015-04-17 2018-10-09 Pratt & Whitney Canada Corp. Combustor dilution hole cooling system
EP3139090B1 (fr) 2015-09-04 2018-06-13 Rolls-Royce Deutschland Ltd & Co KG Composant comprenant un bardeau de chambre de combustion pour une turbine a gaz
DE102015217161A1 (de) 2015-09-04 2017-03-09 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe mit einer Brennkammerschindel für eine Gasturbine
DE102016222099A1 (de) 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
US11268438B2 (en) 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11339966B2 (en) 2018-08-21 2022-05-24 General Electric Company Flow control wall for heat engine
US11029027B2 (en) 2018-10-03 2021-06-08 Raytheon Technologies Corporation Dilution/effusion hole pattern for thick combustor panels
US11391460B2 (en) * 2019-07-16 2022-07-19 Raytheon Technologies Corporation Effusion cooling for dilution/quench hole edges in combustor liner panels
US11371701B1 (en) 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US11560837B2 (en) 2021-04-19 2023-01-24 General Electric Company Combustor dilution hole
US11572835B2 (en) 2021-05-11 2023-02-07 General Electric Company Combustor dilution hole
US11774098B2 (en) 2021-06-07 2023-10-03 General Electric Company Combustor for a gas turbine engine
US11959643B2 (en) 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
US11885495B2 (en) 2021-06-07 2024-01-30 General Electric Company Combustor for a gas turbine engine including a liner having a looped feature

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0972992A2 (fr) 1998-07-16 2000-01-19 General Electric Company Chemise de chambre de combustion

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1055234A (en) * 1963-04-30 1967-01-18 Hitachi Ltd Ultra-high temperature combustion chambers
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
JPS5857658B2 (ja) * 1980-04-02 1983-12-21 工業技術院長 セラミツクスによる高熱曝露壁面の熱遮断構造
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US4653279A (en) * 1985-01-07 1987-03-31 United Technologies Corporation Integral refilmer lip for floatwall panels
GB8703101D0 (en) * 1987-02-11 1987-03-18 Secr Defence Gas turbine engine combustion chambers
US5687572A (en) * 1992-11-02 1997-11-18 Alliedsignal Inc. Thin wall combustor with backside impingement cooling
GB9803291D0 (en) 1998-02-18 1998-04-08 Chapman H C Combustion apparatus
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
GB9919981D0 (en) * 1999-08-24 1999-10-27 Rolls Royce Plc Combustion apparatus
GB9926257D0 (en) * 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
GB2368902A (en) * 2000-11-11 2002-05-15 Rolls Royce Plc A double wall combustor arrangement
US6606861B2 (en) 2001-02-26 2003-08-19 United Technologies Corporation Low emissions combustor for a gas turbine engine
GB2373319B (en) * 2001-03-12 2005-03-30 Rolls Royce Plc Combustion apparatus
GB2384046B (en) * 2002-01-15 2005-07-06 Rolls Royce Plc A double wall combuster tile arrangement

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0972992A2 (fr) 1998-07-16 2000-01-19 General Electric Company Chemise de chambre de combustion
US6145319A (en) 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2172708A3 (fr) * 2008-10-01 2014-05-14 United Technologies Corporation Structures dotées d'un refroidissement adaptatif
US9587832B2 (en) 2008-10-01 2017-03-07 United Technologies Corporation Structures with adaptive cooling
EP2738470A1 (fr) * 2012-11-28 2014-06-04 Rolls-Royce Deutschland Ltd & Co KG Assemblage pour attacher des éléments de bouclier thermique à la paroi d'une chambre de combustion d'une turbine à gaz
US9341372B2 (en) 2012-11-28 2016-05-17 Rolls-Royce Deutschland Ltd & Co Kg Tile fastening arrangement of a gas-turbine combustion chamber
EP2971668A4 (fr) * 2013-03-12 2016-03-02 United Technologies Corp Refroidissement actif de bossages d'oeillet pour un panneau de chambre de combustion d'un moteur à turbine à gaz
EP3077727A4 (fr) * 2013-12-06 2016-12-07 United Technologies Corp Refroidissement d'un corps à ouverture de refroidissement rapide de paroi de chambre de combustion
EP3306196A1 (fr) * 2016-10-06 2018-04-11 Rolls-Royce Deutschland Ltd & Co KG Assemblage de chambre de combustion d'une turbine à gaz ainsi que turbine à gaz d'avion
US10712006B2 (en) 2016-10-06 2020-07-14 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber arrangement of a gas turbine and aircraft gas turbine
EP3431875A1 (fr) * 2017-07-19 2019-01-23 United Technologies Corporation Trous de dilution pour moteurs à turbine à gaz
US10408453B2 (en) 2017-07-19 2019-09-10 United Technologies Corporation Dilution holes for gas turbine engines
US11137140B2 (en) 2017-10-04 2021-10-05 Raytheon Technologies Corporation Dilution holes with ridge feature for gas turbine engines

Also Published As

Publication number Publication date
DE10214570A1 (de) 2004-01-15
US20030182942A1 (en) 2003-10-02
EP1351022A3 (fr) 2005-01-26
DE50312938D1 (de) 2010-09-16
EP1351022B1 (fr) 2010-08-04
US7059133B2 (en) 2006-06-13

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