EP2900975A4 - Section de chambre de combustion de moteur à turbine à gaz - Google Patents

Section de chambre de combustion de moteur à turbine à gaz

Info

Publication number
EP2900975A4
EP2900975A4 EP13842455.1A EP13842455A EP2900975A4 EP 2900975 A4 EP2900975 A4 EP 2900975A4 EP 13842455 A EP13842455 A EP 13842455A EP 2900975 A4 EP2900975 A4 EP 2900975A4
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
turbine engine
engine combustion
chamber section
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Withdrawn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
EP13842455.1A
Other languages
German (de)
English (en)
Other versions
EP2900975A1 (fr
Inventor
Kevin J Low
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2900975A1 publication Critical patent/EP2900975A1/fr
Publication of EP2900975A4 publication Critical patent/EP2900975A4/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Withdrawn legal-status Critical Current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
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13842455.1A 2012-09-28 2013-09-30 Section de chambre de combustion de moteur à turbine à gaz Withdrawn EP2900975A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261707497P 2012-09-28 2012-09-28
PCT/US2013/062661 WO2014052966A1 (fr) 2012-09-28 2013-09-30 Section de chambre de combustion de moteur à turbine à gaz

Publications (2)

Publication Number Publication Date
EP2900975A1 EP2900975A1 (fr) 2015-08-05
EP2900975A4 true EP2900975A4 (fr) 2016-05-04

Family

ID=50389055

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13842455.1A Withdrawn EP2900975A4 (fr) 2012-09-28 2013-09-30 Section de chambre de combustion de moteur à turbine à gaz

Country Status (3)

Country Link
US (1) US20150260399A1 (fr)
EP (1) EP2900975A4 (fr)
WO (1) WO2014052966A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP3066388B1 (fr) * 2013-11-04 2024-04-10 RTX Corporation Bouclier thermique de chambre de combustion de moteur à turbine à ouvertures de refroidissement à inclinaisons multiples
JP6470135B2 (ja) * 2014-07-14 2019-02-13 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ 付加製造された表面仕上げ
US20180128485A1 (en) * 2016-11-04 2018-05-10 United Technologies Corporation Stud arrangement for gas turbine engine combustor
US10480351B2 (en) * 2017-05-01 2019-11-19 General Electric Company Segmented liner
US11181269B2 (en) * 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
CN117091162B (zh) 2022-05-13 2026-03-27 通用电气公司 具有稀释孔结构的燃烧器
CN117091161A (zh) 2022-05-13 2023-11-21 通用电气公司 燃烧器衬里的中空板设计和结构
CN117091157A (zh) 2022-05-13 2023-11-21 通用电气公司 用于耐用燃烧室衬里的板吊架结构
CN117091159A (zh) 2022-05-13 2023-11-21 通用电气公司 燃烧器衬里
CN117091158B (zh) 2022-05-13 2026-03-06 通用电气公司 燃烧器室网状结构

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus
US20030213250A1 (en) * 2002-05-16 2003-11-20 Monica Pacheco-Tougas Heat shield panels for use in a combustor for a gas turbine engine
US20100095679A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9926257D0 (en) * 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
US6973419B1 (en) * 2000-03-02 2005-12-06 United Technologies Corporation Method and system for designing an impingement film floatwall panel system
US7363763B2 (en) * 2003-10-23 2008-04-29 United Technologies Corporation Combustor
US8266914B2 (en) * 2008-10-22 2012-09-18 Pratt & Whitney Canada Corp. Heat shield sealing for gas turbine engine combustor
US20110185739A1 (en) * 2010-01-29 2011-08-04 Honeywell International Inc. Gas turbine combustors with dual walled liners

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus
US20030213250A1 (en) * 2002-05-16 2003-11-20 Monica Pacheco-Tougas Heat shield panels for use in a combustor for a gas turbine engine
US20100095679A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2014052966A1 *

Also Published As

Publication number Publication date
EP2900975A1 (fr) 2015-08-05
WO2014052966A1 (fr) 2014-04-03
US20150260399A1 (en) 2015-09-17

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