KR970700846A - 압축 공기 중에서 연료의 연소 방법(method of burning fuel in compressed air) - Google Patents

압축 공기 중에서 연료의 연소 방법(method of burning fuel in compressed air)

Info

Publication number
KR970700846A
KR970700846A KR1019960703976A KR19960703976A KR970700846A KR 970700846 A KR970700846 A KR 970700846A KR 1019960703976 A KR1019960703976 A KR 1019960703976A KR 19960703976 A KR19960703976 A KR 19960703976A KR 970700846 A KR970700846 A KR 970700846A
Authority
KR
South Korea
Prior art keywords
fuel
stream
flow
compressed air
pilot flame
Prior art date
Application number
KR1019960703976A
Other languages
English (en)
Inventor
헬무트 마곤
Original Assignee
퀼, 노르트만
지멘스 악티엔게젤샤프트
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 퀼, 노르트만, 지멘스 악티엔게젤샤프트 filed Critical 퀼, 노르트만
Publication of KR970700846A publication Critical patent/KR970700846A/ko

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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/22—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants movable, e.g. to an inoperative position; adjustable, e.g. self-adjusting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

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)
  • Combustion Of Fluid Fuel (AREA)
  • Control Of Combustion (AREA)

Abstract

본 발명은 축(1)을 따른 흐름(2)내에 흐르는 압축 공기 중에서 연료를 연소시키는 방법에 관한 것이다. 먼저 흐름(2)으로부터의 다수의 부분 흐름(3)을 나누고, 연료의 일부를 별도로 상기 부분 흐름에 각각 공급하며 흐름(2)내로 돌출한 파일럿 불꽃(25)에 의해 연소시킨다. 나머지 연료를 흐름(2)내로 분배하고, 파일럿 불꽃(25)에 의해 점화시켜 연소시킨다. 흐름(2)내의 연료 분포(28)가 불 균일하며 각각의 파일럿 불꽃(25)에서 국부적인 최대값(29)을 갖는다. 본 방법은 가스 터빈에 특히 바람직하게 작용되며, 연료의 신속하고 완전한 연소를 보장한다.

Description

압축 공기 중에서 연료의 연소 방법(METHOD OF BURNING FUEL IN COMPRESSED AIR)
본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음
제1도는 압축 공기 중에서 연료를 연소시키기 위한 방법을 실시하기 위한 장치의 축방향 종단면도이고, 제2도는 제1도의 선 Ⅱ-Ⅱ를 따른 동일한 장치의 횡단면도이며, 제3도는 제2도의 선 Ⅲ-Ⅲ을 따른 동일한 장치의 접선 단면도이고, 제4도는 제1도의 선 Ⅳ-Ⅳ을 따른 제1도에 따른 장치의 횡단면도이며, 제5도는 여러 가지 상이한 연료의 이송을 위해 장치에 사용가능한 리브의 횡단면도이고, 제6도는 연료를 이송하기 위한 2개의 시스템을 갖춘 장치의 개략도이다.

Claims (5)

  1. 먼저 흐름(2)으로부터 다수의 부분 흐름(3)을 나누고, 연료의 일부를 별도로 상기 부분 흐름에 각각 공급하며 흐름(2)내로 돌출한 파일럿 불꽃(25)에 의해 연소시키며, 나머지 연료를 흐름(2)내로 분배하고, 파일럿 불꽃(25)에 의해 점화시켜 연소시키는 방식의, 축(1)을 따른 흐름(2)내에 흐르는 압축 공기 중에서 연료를 연소시키는 방법에 있어서, 나머지 연료를 흐름(2)에 불 균일하게 분포시킴으로써, 흐름(2)내의 연료 분포(28)가 각각의 파일럿 불꽃(25)에서 국부적인 최대값(29)을 갖게 하는 것을 특징으로 하는 압축 공기 중에서 연료의 연소 방법.
  2. 제1항에 있어서, 흐름(2)이 축(1)에 대한 선회를 갖는 것을 특징으로 하는 압축 공기 중에서 연료의 연소 방법.
  3. 제2항에 있어서, 부분 흐름(3)이 분기되는 흐름(2)의 부분에서 부분 흐름(3)의 분기 전에 선회를 없애는 것을 특징으로 하는 압축 공기 중에서 연료의 연소 방법.
  4. 전술한 항중 어느 한 항에 있어서, 가스 터빈의 압축기 부분(4)으로부터 흐름(2)을 만들어 연료의 연소 후에 가스 터빈의 터빈 부분에 공급하는 것을 특징으로 하는 압축 공기 중에서 연료의 연소 방법.
  5. 제4항에 있어서, 흐름(2)이 유입 갭(14)를 통해 터빈 부분(5)으로 흐르며, 상기 유입 갭(14)에는 블레이드(15)가 배치되고, 연료의 연소에 의해 24개의 블레이드(15) 사이에 국부적 최대치를 갖는 온도의 불 균일화 분포가 흐름(2)내에 생기는 것을 특징으로 하는 압축 공기 중에서 연료의 연소 방법.
    ※ 참고사항 : 최초출원 내용에 의하여 공개하는 것임.
KR1019960703976A 1994-01-24 1995-01-24 압축 공기 중에서 연료의 연소 방법(method of burning fuel in compressed air) KR970700846A (ko)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP94100989 1994-01-24
EP94100989.6 1994-01-24
EP94100988 1994-01-24
EP94100988.8 1994-01-24
PCT/EP1995/000244 WO1995020131A1 (de) 1994-01-24 1995-01-24 Verfahren zur verbrennung eines brennstoffes in verdichteter luft

Publications (1)

Publication Number Publication Date
KR970700846A true KR970700846A (ko) 1997-02-12

Family

ID=26135445

Family Applications (2)

Application Number Title Priority Date Filing Date
KR1019960703976A KR970700846A (ko) 1994-01-24 1995-01-24 압축 공기 중에서 연료의 연소 방법(method of burning fuel in compressed air)
KR1019960703975A KR970700845A (ko) 1994-01-24 1995-01-24 가스 터빈용 연소실(combustion chamber for a gas turbine)

Family Applications After (1)

Application Number Title Priority Date Filing Date
KR1019960703975A KR970700845A (ko) 1994-01-24 1995-01-24 가스 터빈용 연소실(combustion chamber for a gas turbine)

Country Status (10)

Country Link
US (1) US5735115A (ko)
EP (2) EP0741849B1 (ko)
JP (2) JPH09507703A (ko)
KR (2) KR970700846A (ko)
CN (2) CN1092777C (ko)
CZ (2) CZ217396A3 (ko)
DE (2) DE59504264D1 (ko)
ES (2) ES2117402T3 (ko)
RU (2) RU2142601C1 (ko)
WO (2) WO1995020131A1 (ko)

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Also Published As

Publication number Publication date
US5735115A (en) 1998-04-07
CN1140489A (zh) 1997-01-15
EP0741849B1 (de) 1998-11-18
JPH09507703A (ja) 1997-08-05
EP0741849A1 (de) 1996-11-13
EP0741850B1 (de) 1998-05-27
CN1139476A (zh) 1997-01-01
RU2133916C1 (ru) 1999-07-27
EP0741850A1 (de) 1996-11-13
DE59504264D1 (de) 1998-12-24
CZ217496A3 (en) 1997-02-12
ES2126881T3 (es) 1999-04-01
KR970700845A (ko) 1997-02-12
RU2142601C1 (ru) 1999-12-10
WO1995020131A1 (de) 1995-07-27
WO1995020130A1 (de) 1995-07-27
DE59502335D1 (de) 1998-07-02
JP3667757B2 (ja) 2005-07-06
ES2117402T3 (es) 1998-08-01
JPH09507704A (ja) 1997-08-05
CN1092777C (zh) 2002-10-16
CZ217396A3 (en) 1996-10-16

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