KR850001956A - 세라믹 코팅 연소실 - Google Patents

세라믹 코팅 연소실 Download PDF

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Publication number
KR850001956A
KR850001956A KR1019840004681A KR840004681A KR850001956A KR 850001956 A KR850001956 A KR 850001956A KR 1019840004681 A KR1019840004681 A KR 1019840004681A KR 840004681 A KR840004681 A KR 840004681A KR 850001956 A KR850001956 A KR 850001956A
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KR
South Korea
Prior art keywords
ceramic coating
combustion chamber
basket
coating
thickness
Prior art date
Application number
KR1019840004681A
Other languages
English (en)
Other versions
KR920006113B1 (ko
Inventor
패트릭 셔얼록 토마스
Original Assignee
알. 브이. 가버어트
웨스팅 하우스 일렉트릭 코오포레이숀
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 알. 브이. 가버어트, 웨스팅 하우스 일렉트릭 코오포레이숀 filed Critical 알. 브이. 가버어트
Publication of KR850001956A publication Critical patent/KR850001956A/ko
Application granted granted Critical
Publication of KR920006113B1 publication Critical patent/KR920006113B1/ko

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/30—Preventing corrosion or unwanted deposits in gas-swept spaces
    • 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
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

내용 없음

Description

세라밀 코팅 연소실
본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음
제1도는 종래 형태의 연소 터어빈에 쓰이던 연소실의 종단면도, 제2도는 본 발명에 따라 두께의 변화를 갖는 세라믹 코팅을 적용한 연소실의 종단면도. 제3도는 세라믹 코팅에 의한 연소실의 내부가 대체로 원통형을 이루도록 연소실자체의 외형을 원추형으로 구성한 본 발명에 따른 변형연소실의 종단면도.

Claims (6)

  1. 연소 터어빈에서 사용되는 다수개의 공기 흡입구와 최소 한 개의 연료흡입구를 갖는 금속제 바스켓 포함의 연소실에 있어 상기 바스켓의 내부에서 연소가 이루어지고, 상기 바스켓의 내부면에 세라믹코팅을 가하여, 그 코팅의 두께를 상기 공기 흡입구 근처에서 제로에 가깝게하였다가 바스켓의 길이 방향 즉, 하강류 방향으로 가면서 점차 중가시켜 코팅두께에 변화가 있게 하며, 상기 세라믹코팅은 최소 10％이상의 공동부 체적을 포함하도록 하여 상기 금속제 바스켓의 온도를 상당히 감소시키며, 더우기 상기 바스켓의 길이 방향에 따른 온도의 변화를 두드러지게 감소시키는 것을 특징으로 하는 세라믹코팅 연소실.
  2. 제1항에 있어, 상기 세라믹코팅의 최고 두께를 적어도 20miℓs로 하는 것을 특징으로 하는 세라믹 코팅 연소실.
  3. 제1항내지 제2항에 있어, 상기 세라믹 코팅의 공동부 체적을 적어도 25％이상으로 하는 것을 특징으로 하는 세라믹 코팅 연소실.
  4. 제1항내지 제3항에 있어, 최소 2개이상의 공기 흡입구를 길이 방향으로 구성하고, 상기 세라믹코팅의 두께를 상승류쪽에 있는 하나의 공기 흡입구 근처에서 거의 재로로 하였다가 하강류 방향, 즉 다음에 위치한 또 하나의 공기 흡입구쪽의 방향으로 가면서 상당히 증가시키고 상기 하강류쪽의 공기 흡입구근처에서 다시 코팅의 두께를 거의 제로의 치수로 감소시켰다가 여기서부터 하강류 방향으로 가면서 다시 증가시키는 것을 특징으로 하는 세라믹코팅 연소실.
  5. 제1항내지 제4항중 어느 한항에 있어서, 다수의 공기 흡입구를 갖는 금속제 바스켓을 포함하는 연소실을 갖는 것을 특징으로 하는 연소 터어빈.
  6. 연소터어빈에 사용되며 다수개의 공기 흡입구를 포함하고 첨부하는 도면을 참고로 하여 이상에서 밝힌 바와 같은 용도에 적용하기 위해 구성되고, 응용시킨 금속제 바스켓을 갖는 것을 특징으로 하는 세라믹코팅 연소실.
    ※ 참고사항 : 최초출원 내용에 의하여 공개하는 것임.
KR1019840004681A 1983-08-26 1984-08-04 세라믹 코팅 연소실 KR920006113B1 (ko)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US52671483A 1983-08-26 1983-08-26
US526,714 1983-08-26
US526714 1983-08-26

Publications (2)

Publication Number Publication Date
KR850001956A true KR850001956A (ko) 1985-04-10
KR920006113B1 KR920006113B1 (ko) 1992-07-27

Family

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Application Number Title Priority Date Filing Date
KR1019840004681A KR920006113B1 (ko) 1983-08-26 1984-08-04 세라믹 코팅 연소실

Country Status (8)

Country Link
EP (1) EP0136071B1 (ko)
JP (1) JPS6064129A (ko)
KR (1) KR920006113B1 (ko)
CA (1) CA1231240A (ko)
DE (1) DE3468515D1 (ko)
IE (1) IE55883B1 (ko)
IT (1) IT1183201B (ko)
MX (1) MX160895A (ko)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4655044A (en) * 1983-12-21 1987-04-07 United Technologies Corporation Coated high temperature combustor liner
ES2051519T3 (es) * 1990-07-17 1994-06-16 Siemens Ag Trozo de tubo, especialmente tubo de combustion con bastidor de apoyo refrigerado para un revestimiento resistente al calor.
US5144793A (en) * 1990-12-24 1992-09-08 United Technologies Corporation Integrated connector/airtube for a turbomachine's combustion chamber walls
US5220786A (en) * 1991-03-08 1993-06-22 General Electric Company Thermally protected venturi for combustor dome
US5439348A (en) * 1994-03-30 1995-08-08 United Technologies Corporation Turbine shroud segment including a coating layer having varying thickness
US6250082B1 (en) * 1999-12-03 2001-06-26 General Electric Company Combustor rear facing step hot side contour method and apparatus
US6438958B1 (en) * 2000-02-28 2002-08-27 General Electric Company Apparatus for reducing heat load in combustor panels
GB2359882B (en) * 2000-02-29 2004-01-07 Rolls Royce Plc Wall elements for gas turbine engine combustors
US6875476B2 (en) 2003-01-15 2005-04-05 General Electric Company Methods and apparatus for manufacturing turbine engine components
US7421842B2 (en) * 2005-07-18 2008-09-09 Siemens Power Generation, Inc. Turbine spring clip seal
CN107429920B (zh) * 2014-11-21 2019-11-05 安萨尔多能源英国知识产权有限公司 火焰面燃烧器定外形的衬套
US10648669B2 (en) * 2015-08-21 2020-05-12 Rolls-Royce Corporation Case and liner arrangement for a combustor
US10684014B2 (en) * 2016-08-04 2020-06-16 Raytheon Technologies Corporation Combustor panel for gas turbine engine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH210266A (de) * 1939-06-13 1940-06-30 Oerlikon Maschf Temperatur-Schutzeinrichtung für rotierende Wärmekraftmaschinen.
US2564497A (en) * 1947-11-26 1951-08-14 Gen Electric Combustion chamber liner
DE1626032A1 (de) * 1967-08-31 1971-01-14 Daimler Benz Ag Thermischer Belastung ausgesetzter und mit einem Gas zu kuehlender Teil eines Gasturbinentriebwerkes
BE790956A (fr) * 1971-11-05 1973-03-01 Penny Robert N Tube de flamme pour chambre de combustion de moteur a turbine agaz
US3793861A (en) * 1972-03-03 1974-02-26 Mc Donnell Douglas Corp Transpiration cooling structure
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
US4255495A (en) * 1979-10-31 1981-03-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Corrosion resistant thermal barrier coating
US4321310A (en) * 1980-01-07 1982-03-23 United Technologies Corporation Columnar grain ceramic thermal barrier coatings on polished substrates

Also Published As

Publication number Publication date
CA1231240A (en) 1988-01-12
IE55883B1 (en) 1991-02-14
JPS6064129A (ja) 1985-04-12
IE842093L (en) 1985-02-26
IT1183201B (it) 1987-10-15
KR920006113B1 (ko) 1992-07-27
IT8422389A0 (it) 1984-08-22
JPH038446B2 (ko) 1991-02-06
DE3468515D1 (en) 1988-02-11
EP0136071B1 (en) 1988-01-07
EP0136071A1 (en) 1985-04-03
MX160895A (es) 1990-06-11

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