EP1865259A3 - Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre - Google Patents

Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre Download PDF

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Publication number
EP1865259A3
EP1865259A3 EP07109395.9A EP07109395A EP1865259A3 EP 1865259 A3 EP1865259 A3 EP 1865259A3 EP 07109395 A EP07109395 A EP 07109395A EP 1865259 A3 EP1865259 A3 EP 1865259A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbine combustion
gas
lean
chamber wall
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Withdrawn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
EP07109395.9A
Other languages
German (de)
English (en)
Other versions
EP1865259A2 (fr
Inventor
Miklós Gerendás
Michael Ebel
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 EP1865259A2 publication Critical patent/EP1865259A2/fr
Publication of EP1865259A3 publication Critical patent/EP1865259A3/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Withdrawn legal-status Critical Current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
    • F23R3/02—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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
EP07109395.9A 2006-06-09 2007-06-01 Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre Withdrawn EP1865259A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006026969A DE102006026969A1 (de) 2006-06-09 2006-06-09 Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer

Publications (2)

Publication Number Publication Date
EP1865259A2 EP1865259A2 (fr) 2007-12-12
EP1865259A3 true EP1865259A3 (fr) 2014-08-06

Family

ID=38457606

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07109395.9A Withdrawn EP1865259A3 (fr) 2006-06-09 2007-06-01 Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre

Country Status (3)

Country Link
US (1) US7926278B2 (fr)
EP (1) EP1865259A3 (fr)
DE (1) DE102006026969A1 (fr)

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US9995151B2 (en) 2015-08-17 2018-06-12 General Electric Company Article and manifold for thermal adjustment of a turbine component
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GB201518345D0 (en) * 2015-10-16 2015-12-02 Rolls Royce Combustor for a gas turbine engine
US10520193B2 (en) * 2015-10-28 2019-12-31 General Electric Company Cooling patch for hot gas path components
DE102016104957A1 (de) * 2016-03-17 2017-09-21 Rolls-Royce Deutschland Ltd & Co Kg Kühleinrichtung zur Kühlung von Plattformen eines Leitschaufelkranzes einer Gasturbine
US10309228B2 (en) * 2016-06-09 2019-06-04 General Electric Company Impingement insert for a gas turbine engine
US11131456B2 (en) * 2016-07-25 2021-09-28 Siemens Energy Global GmbH & Co. KG Gas turbine engine with resonator rings
JP2018054210A (ja) * 2016-09-28 2018-04-05 株式会社Ihi 燃焼装置用ライナ
US10724739B2 (en) 2017-03-24 2020-07-28 General Electric Company Combustor acoustic damping structure
US11204164B2 (en) * 2017-03-30 2021-12-21 Siemens Energy Global GmbH & Co. KG System with conduit arrangement for dual utilization of cooling fluid in a combustor section of a gas turbine engine
US10415480B2 (en) 2017-04-13 2019-09-17 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US10663168B2 (en) * 2017-08-02 2020-05-26 Raytheon Technologies Corporation End rail mate-face low pressure vortex minimization
US11149948B2 (en) 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
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
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
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
US11156162B2 (en) 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine
US11268696B2 (en) 2018-10-19 2022-03-08 Raytheon Technologies Corporation Slot cooled combustor
DE102019204746A1 (de) * 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Hitzeschildkachel mit Dämpfungsfunktion
DE102019205540A1 (de) * 2019-04-17 2020-10-22 Siemens Aktiengesellschaft Resonator, Verfahren zur Herstellung eines solchen sowie mit einem solchen versehene Brenneranordnung
US11959641B2 (en) 2020-01-31 2024-04-16 Rtx Corporation Combustor shell with shaped impingement holes
JP7393262B2 (ja) * 2020-03-23 2023-12-06 三菱重工業株式会社 燃焼器、及びこれを備えるガスタービン
CN111648866A (zh) * 2020-04-14 2020-09-11 南京航空航天大学 一种冲击气膜-发散孔复合冷却结构
US20210372616A1 (en) * 2020-05-27 2021-12-02 Raytheon Technologies Corporation Multi-walled structure for a gas turbine engine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US20220282688A1 (en) * 2021-03-08 2022-09-08 Raytheon Company Attenuators for combustion noise in dual mode ramjets and scramjets
US11867402B2 (en) 2021-03-19 2024-01-09 Rtx Corporation CMC stepped combustor liner
CN113701193B (zh) * 2021-08-13 2023-02-28 中国航发沈阳发动机研究所 一种燃气轮机火焰筒
CN114811649A (zh) * 2022-04-07 2022-07-29 中国联合重型燃气轮机技术有限公司 燃烧室和具有它燃气轮机
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Citations (4)

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EP0937946A2 (fr) * 1998-02-18 1999-08-25 ROLLS-ROYCE plc Structure de paroi pour une chambre de combustion d'une turbine à gaz
EP1098141A1 (fr) * 1999-11-06 2001-05-09 Rolls-Royce Plc Eléments de paroi pour turbomachine
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EP1213538A2 (fr) * 2000-12-08 2002-06-12 ABB Turbo Systems AG Dispositif pour gaz d'échappement comprenant un résonateur de Helmholtz

Also Published As

Publication number Publication date
EP1865259A2 (fr) 2007-12-12
US20070283700A1 (en) 2007-12-13
DE102006026969A1 (de) 2007-12-13
US7926278B2 (en) 2011-04-19

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