EP0902237B1 - Gasturbinenbrennkammer mit verwundenen Drallschaufeln - Google Patents

Gasturbinenbrennkammer mit verwundenen Drallschaufeln Download PDF

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Publication number
EP0902237B1
EP0902237B1 EP19980116591 EP98116591A EP0902237B1 EP 0902237 B1 EP0902237 B1 EP 0902237B1 EP 19980116591 EP19980116591 EP 19980116591 EP 98116591 A EP98116591 A EP 98116591A EP 0902237 B1 EP0902237 B1 EP 0902237B1
Authority
EP
European Patent Office
Prior art keywords
swirler
fuel nozzle
main
main fuel
nozzle
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
EP19980116591
Other languages
English (en)
French (fr)
Other versions
EP0902237A3 (de
EP0902237A2 (de
Inventor
Shigemi c/o Takasago R & D Center Mandai
Masataka c/o Takasago R & D Center Ohta
Mitsuru c/o Takasago Machinery Works Inada
Shinji c/o Takasago Machinery Works Akamatsu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP0902237A2 publication Critical patent/EP0902237A2/de
Publication of EP0902237A3 publication Critical patent/EP0902237A3/de
Application granted granted Critical
Publication of EP0902237B1 publication Critical patent/EP0902237B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Definitions

  • the present invention relates to a swirler for forming a pre-mixture in a pre-mixed flame type low NO X combustor of a gas turbine.
  • Fig. 4 is an entire constructional view of one example of a pre-mixed flame type low NO X combustor in the prior art
  • Fig. 5 is a cross sectional view of a main fuel nozzle as part of the combustor of Fig. 4.
  • a fuel supply nozzle for supplying fuel and air or mixture thereof into a combustor consists of a pilot fuel nozzle 204 for forming a flame portion in a cross sectional center of the combustor, a plurality of main fuel nozzles 202, each having an outer casing 206, arranged surrounding said pilot fuel nozzle 204 for forming a pre-mixed gas of fuel and air, etc.
  • a main swirler 201 surrounding the main fuel nozzle 202 and extending to a position of the outer casing 206.
  • the main swirlers 201 in plural units and a pilot swirler 203 in a single unit at a center of the combustor, and combustion air is supplied through the plurality of main swirlers 201 and the pilot swirler 203 and fuel is supplied from the plurality of main fuel nozzles 202 and the pilot fuel nozzle 204.
  • the fuel is injected from the nozzle holes 205 bored in the wall of body of the main fuel nozzle 202 and is mixed with the air flowing on an outer periphery of the nozzle via the main swirler 201 to form a pre-mixed gas.
  • the main swirler 201 When the air flows through the main swirler 201, it is given a swirling angle by the main swirler 201 and this angle is governed by a fitting angle in which a swirler vane is fitted to a hub portion thereof relative to a center axis of the fuel nozzle.
  • Fig. 2(a) is a view showing arrangement of a swirler relative to the fuel nozzle
  • Fig. 2(b) is a development of arrangement of swirler vanes.
  • Fig. 3(a) is a view showing arrangement of a swirler relative to the fuel nozzle
  • Fig. 3(b) is a development of arrangement of swirler vanes.
  • WO 89/06307A discloses a gas turbine 'with forced vortex fuel injection.
  • the document qualitatively shows that the swirler vanes extend relatively axially at their radially inner edges and relatively non-axially at their radially outer edges.
  • the fuel injection nozzle of D1 is obviously of a different type with only a single central injection nozzle.
  • the injector is comprised of three generally concentric cylindrical tubes wherein the fuel is injected axially from the central tube and an concentrated oxidant is ejected coaxially through the surrounding intermediate tube. In this type of injector the specific problem of a large stagnation point at the tip portion of the main fuel nozzle is not present.
  • the present invention provides gas turbine combuster with the features defined in the claim.
  • a swirler vane fitted around a fuel nozzle is twisted from a hub side thereof to a tip side thereof so that a fitting angle of the tip side relative to a center axis of the fuel nozzle is larger than that of the hub side.
  • the swirler vane in the swirler vane fitted around the fuel nozzle, the swirler vane is twisted from the hub side to the tip side so as to change the fitting angle relative to the center axis of the fuel nozzle and said angle of the tip side is formed larger than that of the hub side.
  • said angle of the hub side is set to a smaller angle so that flame stagnation, and burning of components resulted therefrom, may be prevented from occurring
  • the swirler vane is twisted so that said angle of the tip side may be selected to an angle in which shearing flow necessary for appropriate mixing of fuel and air is obtained, thereby such a three-dimensional swirler as is able to make a favorable pre-mixing, to prevent a life deterioration due to the burning etc . and to enhance a combustion efficiency is obtained.
  • the fitting angle of the hub side relative, to the center axis of the fuel nozzle is 25° and that of the tip side is 45°.
  • the fitting angle of the hub side relative to the center axis of the fuel nozzle is set to 25° in which flame stagnation and burning of components do not occur and said angle of the tip side is set to 45° in which shearing flow becomes strong, thus occurrence of problem of flame stagnation and burning on the hub side is restrained and strong shear flow on the tip side is secured, thereby such a three-dimensional swirler as is able to make a favorable pre-mixing of fuel and air, to prevent a life deterioration due to the burning etc. and to enhance a combustion efficiency is obtained.
  • FIG. 1 shows a three-dimensional swirler of an embodiment of the present invention, wherein Fig. 1(a) shows arrangement of a swirler relative to a fuel nozzle, Fig. 1(b) is a development of arrangement of swirler vanes and Fig. 1(c) is a perspective view of one of the swirler vanes.
  • a main swirler 101 is provided around a main fuel nozzle 102 and there are bored a plurality of nozzle holes 105 in a wall of the main fuel nozzle 102 along a circumferential direction thereof at position downstream of the main swirler 101, so that fuel F injected from the nozzle holes 105 mixes with air A which has passed through the main swirler 101 to form so-called a pre-mixture, and this basic concept and structure of swirler is same as that of the described prior art one.
  • the present embodiment is featured in that said main swirler 101 is constructed in a specific form as follows:
  • a fitting angle ⁇ of a swirler vane 101a on a hub side thereof is 25° relative to a center axis C of the main fuel nozzle 102 and a fitting angle ⁇ of the swirler vane 101a on a tip side thereof is 45° likewise relative to the center axis C of the main fuel nozzle 102.
  • the swirler vane 101a is twisted from the hub side to the tip side and the fitting angle ⁇ on the tip side of the swirler vane 101a is 45°, hence there can be formed a strong shear flow there.
  • the fuel F of natural gas and the like is supplied into a swirling flow of the air A so formed via the nozzle holes 105 bored in the main fuel nozzle 102 and a pre-mixture of the fuel F and the air A is formed.
  • the fitting angle on the hub side of the swirler vane 101a is set to 25° so that the stagnation point at the tip portion of the main fuel nozzle 102 is small and no substantial flame stagnation occurs there even if a back fire occurs, hence there is no fear of burning of components as well.
  • the fitting angle on the tip side of the swirler vane 101a is set to 45° so that the shear flow of the air A on an outer side in a radial direction of the swirler is strong and mixing of the fuel F and the air A is accelerated, hence an excellent pre-mixture can be obtained.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (1)

  1. Gasturbinen-Combustor mit:
    einer Pilot-Brennstoffdüse, die einen Flammenabschnitt in einem zentralen Teil des Gasturbinen-Combustors zu bilden vermag,
    mehreren Hauptbrennstoffdüsen (102), die so angeordnet sind, dass sie die Pilot-Brennstoffdüse umgeben, um ein vorgemischtes Gas aus Brennstoff und Luft zu bilden, wobei jede der mehreren Hauptbrennstoffdüsen (102) ein äußeres Gehäuse, das die Hauptbrennstoffdüse (102) umgibt, und mehrere Düsenlöcher (105), die in die Hauptbrennstoffdüse (102) entlang einer Umfangsrichtung derselben gebohrt sind, umfasst, und
    mehreren Hauptverwirbelungselementen (101), wobei jedes der Hauptverwirbelungselemente (101) so angeordnet ist, dass es jeweils eine der mehreren Hauptbrennstoffdüsen (102) stromauf der mehreren Düsenlöcher (105) derselben umgibt, wobei jedes der Hauptverwirbelungselemente (101) eine um die jeweilige Hauptbrennstoffdüse (102) herum eingesetzte Nabe und mehrere fest mit der Nabe verbundene und sich radial von der Nabe nach außen zu dem äußeren Gehäuse erstreckende Verwirbelungsflügel (101a) umfasst, wobei jeder der mehreren Verwirbelungsflügel (101a) von seiner Nabenseite zu seiner Außenseite verdreht ist,
       wobei jeder der mehreren Verwirbelungsflügel (101a) einen Einsetzwinkel (β) an der Außenseite von 45° relativ zu einer Mittelachse (C) der jeweiligen Hauptbrennstoffdüse (102) aufweist, und einen Einsetzwinkel (α) an der Nabenseite von 25° relativ zu der Mittelachse (C) der betreffenden Hauptbrennstoffdüse (102).
EP19980116591 1997-09-10 1998-09-02 Gasturbinenbrennkammer mit verwundenen Drallschaufeln Expired - Lifetime EP0902237B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP24547797 1997-09-10
JP245477/97 1997-09-10
JP24547797A JPH1183016A (ja) 1997-09-10 1997-09-10 ３次元スワーラ

Publications (3)

Publication Number Publication Date
EP0902237A2 EP0902237A2 (de) 1999-03-17
EP0902237A3 EP0902237A3 (de) 2000-09-20
EP0902237B1 true EP0902237B1 (de) 2003-12-03

Family

ID=17134250

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19980116591 Expired - Lifetime EP0902237B1 (de) 1997-09-10 1998-09-02 Gasturbinenbrennkammer mit verwundenen Drallschaufeln

Country Status (4)

Country Link
EP (1) EP0902237B1 (de)
JP (1) JPH1183016A (de)
CA (1) CA2246219C (de)
DE (1) DE69820183T2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103807879A (zh) * 2012-11-06 2014-05-21 阿尔斯通技术有限公司 轴向旋流器

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3970244B2 (ja) * 2001-07-10 2007-09-05 三菱重工業株式会社 予混合ノズルおよび燃焼器並びにガスタービン
EP1394471A1 (de) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brenner
JP4476176B2 (ja) * 2005-06-06 2010-06-09 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
JP4486549B2 (ja) 2005-06-06 2010-06-23 三菱重工業株式会社 ガスタービンの燃焼器
EP1985924A1 (de) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Drallvorrichtung
US20090139236A1 (en) * 2007-11-29 2009-06-04 General Electric Company Premixing device for enhanced flameholding and flash back resistance
US8925323B2 (en) * 2012-04-30 2015-01-06 General Electric Company Fuel/air premixing system for turbine engine
KR101857280B1 (ko) 2015-06-30 2018-05-11 두산중공업 주식회사 향상된 연료 유동 분포를 위한 장치가 구비된 가스 터빈 발전장치.
KR101853442B1 (ko) 2015-06-30 2018-04-30 두산중공업 주식회사 향상된 연료 유동 분포를 위한 장치를 포함한 가스 터빈 발전장치.
WO2018021249A1 (ja) * 2016-07-26 2018-02-01 Ｊｆｅスチール株式会社 電気炉用助燃バーナー
WO2019230165A1 (ja) * 2018-06-01 2019-12-05 株式会社Ihi 液体燃料噴射器
CN113776084A (zh) * 2021-10-08 2021-12-10 浙江浙能技术研究院有限公司 一种一体化低污染燃烧室喷嘴结构及方法
CN116241336B (zh) * 2023-01-17 2025-10-03 北京航空航天大学 应用于涡轮叶片进口处壁板抑旋结构、使用及验证方法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1931692A (en) * 1930-02-15 1933-10-24 Elliott Co Centrifugal blowing apparatus
US2798661A (en) * 1954-03-05 1957-07-09 Westinghouse Electric Corp Gas turbine power plant apparatus
US4221558A (en) * 1978-02-21 1980-09-09 Selas Corporation Of America Burner for use with oil or gas
CH660403A5 (de) * 1983-08-30 1987-04-15 Bbc Brown Boveri & Cie Axialer drallkoerper zur erzeugung von drehstroemungen.
EP0371090A4 (en) * 1987-12-28 1991-06-12 Sundstrand Corporation Gas turbine with forced vortex fuel injection
JPH02147610U (de) * 1989-05-11 1990-12-14
GB2263763B (en) * 1992-02-05 1995-03-22 Ind Tech Res Inst A swirl generator with axial vanes

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103807879A (zh) * 2012-11-06 2014-05-21 阿尔斯通技术有限公司 轴向旋流器
CN103807879B (zh) * 2012-11-06 2016-06-01 通用电器技术有限公司 轴向旋流器

Also Published As

Publication number Publication date
CA2246219A1 (en) 1999-03-10
EP0902237A3 (de) 2000-09-20
CA2246219C (en) 2002-11-19
EP0902237A2 (de) 1999-03-17
DE69820183T2 (de) 2004-08-26
DE69820183D1 (de) 2004-01-15
JPH1183016A (ja) 1999-03-26

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