KR970046925A - Premixed Burners - Google Patents

Premixed Burners Download PDF

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Publication number
KR970046925A
KR970046925A KR1019960072348A KR19960072348A KR970046925A KR 970046925 A KR970046925 A KR 970046925A KR 1019960072348 A KR1019960072348 A KR 1019960072348A KR 19960072348 A KR19960072348 A KR 19960072348A KR 970046925 A KR970046925 A KR 970046925A
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KR
South Korea
Prior art keywords
premix burner
partial shells
fuel
air inlet
tangential air
Prior art date
Application number
KR1019960072348A
Other languages
Korean (ko)
Inventor
한스 피터
Original Assignee
클라인 에르네스트
아세아 브라운 보베리 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 클라인 에르네스트, 아세아 브라운 보베리 악티엔게젤샤프트 filed Critical 클라인 에르네스트
Publication of KR970046925A publication Critical patent/KR970046925A/en

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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
    • F23R3/10—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
    • F23D—BURNERS
    • F23D5/00—Burners in which liquid fuel evaporates in the combustion space, with or without chemical conversion of evaporated fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Gas Burners (AREA)

Abstract

유동방향으로 서로 끼워맞춰진 두개 이상의 원추형 부분셸(101,102)로 구성되는 예비혼합 버너(100)에서, 대칭적인 이들의 종축선은, 부분셸들의 인접벽들이 그들의 종방향 범위로 접선방향 공기유입 슬릿(119,120)을 형성하도록, 버너 축선에 대해 편위되어 있다. 연소공기(115)는 이 슬릿들을 통해 예비혼합 버너의 내측 공동(114)안으로 유동한다, 예비혼합 버너의 헤드측에는 액체 연료(112)에 의해 바람직하게 작동하는 노즐(103)이 배치되어 있는 반면, 접선방향 공기유입 슬릿을 따라 가스상 연료(113)에 의해 바람직하게 작동하는 또다른 노즐(117)이 배치되어 있다. 전술한 연료(113)를 공급하기 위한 연료 라인은, 부분셸의 단부가 접선방향 공기유입슬릿들의 영역에서 둥글게 굽혀져서 접선방향 공기유입 슬릿의 유입영역 외측의 대응 부분셸에 대해 밀봉방식으로 폐쇄되는 점에서 각각의 부분셸의 연속 구조에 의해 형성된다.In the premix burner 100 consisting of two or more conical partial shells 101, 102 fitted together in the flow direction, their longitudinal axes are symmetrical, such that the adjacent walls of the partial shells have tangential air inlet slits in their longitudinal range. 119 and 120 are biased relative to the burner axis. Combustion air 115 flows through these slits into the inner cavity 114 of the premix burner. On the head side of the premix burner, a nozzle 103 which is preferably operated by liquid fuel 112 is arranged, Along the tangential air inlet slit is another nozzle 117 which is preferably operated by the gaseous fuel 113. The fuel line for supplying the fuel 113 described above has an end portion of the partial shell bent round in the region of the tangential air inlet slits and closed in a sealing manner with respect to the corresponding partial shell outside the inlet region of the tangential air inlet slit. In this regard, each partial shell is formed by a continuous structure.

Description

예비혼합 버너Premixed Burners

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음Since this is an open matter, no full text was included.

제1도는 적절히 절개한 예비혼합 버너의 사시도.1 is a perspective view of a premixed burner properly cut out.

제2도는 한 형태의 연료 라인을 나타내는 도1의 Ⅱ-Ⅱ선 단면도.FIG. 2 is a cross-sectional view taken along the line II-II of FIG. 1 showing one type of fuel line. FIG.

Claims (10)

유동방향으로 서로 끼워맞춰진 두개 이상의 원추형 부분셸로 구성되고, 이 부분셸들의 대칭적인 각각의 종방향 축선은, 부분셸들의 인접벽들이 그들의 종방향 범위로 부분셸들에 의해 형성된 원추형 공동안으로 연소공기가 통과하여 흐르게 하는 접선방향 공기유입 슬릿을 형성하도록, 버너 축선에 대해 편위되어 있고, 서로 평행하며, 최소한 접선방향 공기 유입 슬릿들의 영역에 연료노즐들이 배치되어 있는 예비혼합 버너에 있어서, 연료 노즐들(117,117a)이 연료라인(108,109,109a)에 작동적으로 접속되어 있으며, 상기 연료 라인은 접선방향 공기유입 슬릿들(119, 120)의 영역에서 원추형 부분셸들(101,102)의 내장 연속구조에 의해 형성되는 것을 특징으로 하는 예비혼합 버너.Composed of two or more conical partial shells fitted together in the flow direction, each symmetrical longitudinal axis of these partial shells comprises combustion air into the conical cavity in which the adjacent walls of the partial shells are formed by the partial shells in their longitudinal range. 12. Pre-mixed burners, which are biased with respect to the burner axis, parallel to each other, with fuel nozzles arranged at least in the region of the tangential air inlet slits, so as to form a tangential air inlet slit through which gas flows. 117 and 117a are operatively connected to the fuel lines 108, 109 and 109a, which are connected by a built-in continuous structure of conical partial shells 101 and 102 in the region of tangential air inlet slits 119 and 120. A premix burner, characterized in that formed. 제1항에 있어서, 상기 예비혼합 버너(100)의 헤드측에 하나이상의 또 다른 노즐(103)이 배치되어 있는 것을 특징으로 하는 예비혼합 버너.The premix burner according to claim 1, wherein at least one further nozzle (103) is arranged on the head side of the premix burner (100). 제1항 또는 제2항에 있어서, 상기 연료 노즐(103)은 액체 연료(112)에 의해 작동될 수 있고, 상기 연료 노즐(117,117a)은 가스상 연료(113)에 의해 작동될 수 있는 것을 특징으로 하는 예비혼합 버너.The fuel nozzle (103) of claim 1 or 2, wherein the fuel nozzle (103) can be operated by the liquid fuel (112), and the fuel nozzles (117, 117a) can be operated by the gaseous fuel (113). Premixed burners. 제2항에 있어서, 상기 연료 노즐(103)이 버너 축선상에 배치되어 있는 것을 특징으로 하는 예비혼합 버너.3. The premix burner according to claim 2, wherein the fuel nozzle (103) is disposed on a burner axis. 제1항에 있어서, 상기 부분셸들(101,102)은 유동방향으로 균일하게 증가하는 유동 단면을 형성하는 것을 특징으로 하는 예비혼합 버너.2. The premix burner of claim 1, wherein the partial shells (101,102) form a flow cross section that increases uniformly in the flow direction. 제1항에 있어서, 상기 부분셸들(101,102)은 유동방향으로 증가하는 원추테이퍼를 갖는 것을 특징으로 하는 예비혼합 버너.2. The premix burner of claim 1, wherein the partial shells (101,102) have a conical taper that increases in the flow direction. 제1항에 있어서, 상기 부분셸들(101,102)은 유동방향으로 감소하는 원추 테이퍼를 갖는 것을 특징으로 하는 예비혼합 버너.The premix burner of claim 1, wherein the partial shells (101, 102) have a conical taper that decreases in the flow direction. 제1항에 있어서, 상기 부분셸들(101,102)은 서로 나선형으로 끼워맞춰진 것을 특징으로 하는 예비혼합 버너.2. The premix burner according to claim 1, wherein the partial shells (101,102) are helically fitted together. 제1항에 있어서, 상기 접선방향 공기유입 슬릿들(119,120)의 통과 유동단면이 상기 예비혼합 버너(100)의 종방향으로 감소하는 것을 특징으로 하는 예비혼합 버너.The premix burner according to claim 1, wherein the passage flow cross section of the tangential air inlet slits (119,120) decreases in the longitudinal direction of the premix burner (100). 제1항에 있어서, 상기 연료 라인의 형성후에, 상기 부분셸(101,102)의 단부가 상기 접선방향 공기유입 슬릿들(119,120)의 아래, 위, 또는 아래 및 위에서 관련 부분셸의 외면에 밀봉방식으로 접속되는 것을 특징으로 하는 예비혼합 버너.The method of claim 1, wherein after formation of the fuel line, the ends of the partial shells 101, 102 are sealed to the outer surface of the associated partial shell below, above, below, and above the tangential air inlet slits 119,120. A premix burner, characterized in that connected.
KR1019960072348A 1995-12-27 1996-12-26 Premixed Burners KR970046925A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19548851.2 1995-12-27
DE19548851A DE19548851A1 (en) 1995-12-27 1995-12-27 Premix burner

Publications (1)

Publication Number Publication Date
KR970046925A true KR970046925A (en) 1997-07-26

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ID=7781502

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1019960072348A KR970046925A (en) 1995-12-27 1996-12-26 Premixed Burners

Country Status (5)

Country Link
EP (1) EP0786626A1 (en)
JP (1) JPH09189405A (en)
KR (1) KR970046925A (en)
CA (1) CA2192741A1 (en)
DE (1) DE19548851A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100361976B1 (en) * 1999-09-15 2002-11-25 오창선 Combuster for high viscosity fuel

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59709791D1 (en) * 1997-09-19 2003-05-15 Alstom Switzerland Ltd Burner for operating a heat generator
DE59710380D1 (en) * 1997-11-21 2003-08-07 Alstom Burner for operating a heat generator
DE102018005192B3 (en) 2018-07-02 2019-12-05 Truma Gerätetechnik GmbH & Co. KG burner device
CN115435324B (en) * 2022-11-04 2023-03-14 佛山市德力泰科技有限公司 Backfire-proof multi-fuel mixing device and burner

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0210462B1 (en) * 1985-07-30 1989-03-15 BBC Brown Boveri AG Dual combustor
DE3819899C1 (en) * 1988-06-11 1989-11-30 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Apparatus for generating a homogeneous mixture from a first and second medium
CH680157A5 (en) * 1989-12-01 1992-06-30 Asea Brown Boveri
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
CH687831A5 (en) * 1993-04-08 1997-02-28 Asea Brown Boveri Premix burner.
DE4330083A1 (en) * 1993-09-06 1995-03-09 Abb Research Ltd Method of operating a premix burner
SE9304194L (en) * 1993-12-17 1995-06-18 Abb Stal Ab fuel spreader
DE4426353A1 (en) * 1994-07-25 1996-02-01 Abb Research Ltd burner
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100361976B1 (en) * 1999-09-15 2002-11-25 오창선 Combuster for high viscosity fuel

Also Published As

Publication number Publication date
JPH09189405A (en) 1997-07-22
EP0786626A1 (en) 1997-07-30
DE19548851A1 (en) 1997-07-03
CA2192741A1 (en) 1997-06-28

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