MX2016014952A - Camisa de camara de combustion con enfriamiento por efusion sesgada. - Google Patents

Camisa de camara de combustion con enfriamiento por efusion sesgada.

Info

Publication number
MX2016014952A
MX2016014952A MX2016014952A MX2016014952A MX2016014952A MX 2016014952 A MX2016014952 A MX 2016014952A MX 2016014952 A MX2016014952 A MX 2016014952A MX 2016014952 A MX2016014952 A MX 2016014952A MX 2016014952 A MX2016014952 A MX 2016014952A
Authority
MX
Mexico
Prior art keywords
combustion liner
bias
cooling
liner
effusion cooling
Prior art date
Application number
MX2016014952A
Other languages
English (en)
Inventor
Oumejjoud Khalid
Richardson Brian
Cutright John
Mcmullen Nikki
John Stuttaford Peter
Parker Richard
SONI Sumit
Original Assignee
General Electric Technology Gmbh
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 General Electric Technology Gmbh filed Critical General Electric Technology Gmbh
Publication of MX2016014952A publication Critical patent/MX2016014952A/es

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
    • 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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Se describen un sistema y método para mejorar el enfriamiento de una porción de una camisa de cámara de combustión de una cámara de combustión de turbinas de gas. La camisa de la cámara de combustión se enfría al suministrar aire a través de una pluralidad de orificios de enfriamiento dispuestos en filas espaciadas axialmente en una porción superior y una inferior de la camisa. Los orificios de enfriamiento son espaciados de manera acorde con el fin de dirigir flujo de enfriamiento adicional a un área de la camisa de cámara de combustión que no recibe suficiente flujo debido a una mala distribución de aire desde la descarga de compresor.
MX2016014952A 2014-05-15 2015-05-12 Camisa de camara de combustion con enfriamiento por efusion sesgada. MX2016014952A (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14/278,770 US9429323B2 (en) 2014-05-15 2014-05-15 Combustion liner with bias effusion cooling
PCT/US2015/030323 WO2015175501A1 (en) 2014-05-15 2015-05-12 Combustion liner with bias effusion cooling

Publications (1)

Publication Number Publication Date
MX2016014952A true MX2016014952A (es) 2017-08-24

Family

ID=53276275

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2016014952A MX2016014952A (es) 2014-05-15 2015-05-12 Camisa de camara de combustion con enfriamiento por efusion sesgada.

Country Status (5)

Country Link
US (1) US9429323B2 (es)
KR (1) KR102335092B1 (es)
CA (1) CA2949066A1 (es)
MX (1) MX2016014952A (es)
WO (1) WO2015175501A1 (es)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4923371A (en) 1988-04-01 1990-05-08 General Electric Company Wall having cooling passage
US5233828A (en) 1990-11-15 1993-08-10 General Electric Company Combustor liner with circumferentially angled film cooling holes
US5241827A (en) 1991-05-03 1993-09-07 General Electric Company Multi-hole film cooled combuster linear with differential cooling
US6393828B1 (en) * 1997-07-21 2002-05-28 General Electric Company Protective coatings for turbine combustion components
US6205789B1 (en) 1998-11-13 2001-03-27 General Electric Company Multi-hole film cooled combuster liner
US7269957B2 (en) * 2004-05-28 2007-09-18 Martling Vincent C Combustion liner having improved cooling and sealing
GB0601413D0 (en) 2006-01-25 2006-03-08 Rolls Royce Plc Wall elements for gas turbine engine combustors
US7856830B2 (en) * 2006-05-26 2010-12-28 Pratt & Whitney Canada Corp. Noise reducing combustor
US8171634B2 (en) 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
US7905094B2 (en) 2007-09-28 2011-03-15 Honeywell International Inc. Combustor systems with liners having improved cooling hole patterns
US8104288B2 (en) * 2008-09-25 2012-01-31 Honeywell International Inc. Effusion cooling techniques for combustors in engine assemblies

Also Published As

Publication number Publication date
CA2949066A1 (en) 2015-11-19
WO2015175501A1 (en) 2015-11-19
US20150330634A1 (en) 2015-11-19
US9429323B2 (en) 2016-08-30
KR20170005098A (ko) 2017-01-11
KR102335092B1 (ko) 2021-12-03

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