KR920010141A - 가스 터빈 엔진의 다-홀 필림 냉각 연소기 라이너 및 그 제조 방법 - Google Patents

가스 터빈 엔진의 다-홀 필림 냉각 연소기 라이너 및 그 제조 방법 Download PDF

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KR920010141A
KR920010141A KR1019910011753A KR910011753A KR920010141A KR 920010141 A KR920010141 A KR 920010141A KR 1019910011753 A KR1019910011753 A KR 1019910011753A KR 910011753 A KR910011753 A KR 910011753A KR 920010141 A KR920010141 A KR 920010141A
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South Korea
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liner
gas turbine
downward angle
degrees
cell
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KR1019910011753A
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KR940004340B1 (ko
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죠지 웨이크맨 토마스
워커 앨런
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아더 엠. 킹
제너럴 일렉트릭 캄파니
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    • 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
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/36—Removing material
    • B23K26/38—Removing material by boring or cutting
    • B23K26/382—Removing material by boring or cutting by boring
    • B23K26/389—Removing material by boring or cutting by boring of fluid openings, e.g. nozzles, jets
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Abstract

내용 없음

Description

가스 터빈 엔진의 다-홀 필림 냉각 연소기 라이너 및 그 제조 방법
본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음
제1도는 코어 엔진 연소 섹션과 본 발명에 따른 연소기라이너를 가진 애프터 버닝 배기 섹션을 포함하는 전형적인 가스 터빈 엔진의 개략도.
제2도는 제1도에 도시된 엔진의 코어 엔진 연소 섹션의 사시도.

Claims (17)

  1. 소형이고 가깝게 이격되어 샤프하게 아래로 경사진 필름 냉각홀의 적어도 한 패턴을 가지는 싱글 벽 셀을 포함하는 것을 특징으로 하는 뜨거운 측면과 차가운 측면을 가진 가스 터빈 연소기 라이너.
  2. 제1항에 있어서, 상기 셀의 한부분은 얇은 물결형 벽 단면을 형성하기 위해 주름 형상인 것을 특징으로 하는 가스 터빈 연소기 라이너.
  3. 제1항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 20도의 제1양호한 값을 가지는 것을 특징으로 하는 가스 터빈 연소기 라이너.
  4. 제1항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 15도의 제2양호한 값을 가지는 것을 특징으로 하는 가스 터빈 연소기 라이너.
  5. 제1항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 10도 내지 20도의 양호한 범위의 값을 가지는 것을 특징으로 하는 가스 터빈 연소기 라이너.
  6. 얇은 물결형 벽 단면을 형성하기 위해 주름형상인 셀의 한부분 가지는 싱글 벽 시이트 금속 셀과, 상기 셀을 통해 배치된 소형이고 가깝게 이격되어 샤프하게 아래로 경사진 필림 냉각 홀의 적어도 한 패턴을 포함하는 것을 특징으로 하는 뜨거운 후면과 차가운 측면을 가지는 애프터 버닝 가스 터빈 엔진 배기섹션 연소기 라이너.
  7. 제6항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 20도의 제1양호한 값을 가지는 것을 특징으로 애프터 버닝 가스 터빈 엔진 배기섹션 연소기 라이너.
  8. 제6항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 15도의 제2양호한 값을 가지는 것을 특징으로 애프터 버닝 가스 터빈 엔진 배기섹션 연소기 라이너.
  9. 제6항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 10도 내지 20도의 양호한 범위의 값을 가지는 것을 특징으로 애프터 버닝 가스 터빈 엔진 배기섹션 연소기 라이너.
  10. 외부 케이싱과, 외부 케이싱의 내향으로 배치되는 소형이고 가깝게 이격되어 샤프하게 아래로 경사진 필림 냉각홀의 적어도 한 패턴을 가지는 싱글 벽 시이트 금속 외부 라이너와, 외부 라이너의 내향으로 배치되고 소형이고 가깝게 이격되어 샤프하게 아래로 경사진 필림 냉각 홀의 적어도 한패턴을 가지는 싱글 벽 시이트 금속 내부 라이너를 포함하는 것을 특징으로 하는 가스 터빈 연소 섹션.
  11. 제10항에 있어서, 상기 외부 라이너의 적어도 한 부분이 얇은 물결형 단면을 형성하기 위해 주름 형상인 것을 특징으로 하는 가스 터빈 연소 섹션.
  12. 제11항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 20도의 제1양호한 값을 가지는 것을 특징으로 하는 가스 터빈 연소 섹션.
  13. 제12항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 15도의 제2, 양호한 값을 것을 특징으로 하는 가스 터빈 연소 섹션.
  14. 제12항에 있어서, 상기 필림 냉각 홀은 라이너의 차가운 표면에서 뜨거운 표면으로 경사진 하향각을 갖는데, 상기 하향각은 약 10도 내지 20도의 양호한 범위의 값을 가지는 것을 특징으로 하는 가스 터빈 연소 섹션.
  15. 얇은 시이트 금속으로부터 가스 터빈 연소기의 뜨거운 분위기에 적합한 환형 라이너 셀은 형성하는 공정과, 환형 셀내로 소형이고 가깝게 이격되어 샤프하게 아래로 경사진 필림 냉각 홀의 적어도 한 패턴을 셀의 뜨거운 측면에서부터 차가운 측면으로 레이저 드릴 가공하는 공정을 포함하는 것을 특징으로 하는 가스 터빈 연소기 제조방법.
  16. 제15항에 있어서, 셀내에 얇은 주름 형상을 만들기 위해 상기 셀을 확장형성하는 공정도 포함하는 것을 특징으로 하는 가스 터빈 연소기 제조방법.
  17. 제15항에 있어서, 얇은 주름 형상과 셀의 단부에 장착 수단을 형성하도록 셀을 확장 형성하는 공정도 포함하는 것을 특징으로 하는 가스 터빈 연소기 제조방법.
    ※ 참고사항 : 최초출원 내용에 의하여 공개하는 것임.
KR1019910011753A 1990-11-15 1991-07-11 가스 터빈 엔진의 다-홀 필림 냉각 연소기 라이너 및 그 제조 방법 KR940004340B1 (ko)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US07/614,418 US5181379A (en) 1990-11-15 1990-11-15 Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US614,418 1990-11-15

Publications (2)

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KR920010141A true KR920010141A (ko) 1992-06-26
KR940004340B1 KR940004340B1 (ko) 1994-05-23

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Country Status (8)

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US (1) US5181379A (ko)
EP (1) EP0486133B1 (ko)
JP (1) JP2693665B2 (ko)
KR (1) KR940004340B1 (ko)
AU (1) AU638331B2 (ko)
CA (1) CA2048727C (ko)
DE (1) DE69123707T2 (ko)
IL (1) IL98657A (ko)

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DE69123707T2 (de) 1997-07-03
IL98657A (en) 1993-08-18
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CA2048727A1 (en) 1992-05-16
IL98657A0 (en) 1992-07-15
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AU7817591A (en) 1992-05-21
US5181379A (en) 1993-01-26
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JP2693665B2 (ja) 1997-12-24

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