EP0902237B1 - Combustor comprising swirler with twisted vanes - Google Patents
Combustor comprising swirler with twisted vanes Download PDFInfo
- 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
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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)
Description
Claims (1)
- A gas turbine combustor comprising:a pilot fuel nozzle adapted to form a flame portion in a central part of said gas turbine combustor;a plurality of main fuel nozzles (102) arranged so as to surround said pilot fuel nozzle, for forming a pre-mixed gas of fuel and air, each of said plurality of main fuel nozzles (102) comprising an outer casing surrounding said main fuel nozzle (102) and a plurality of nozzle holes (105) bored in said main fuel nozzle (102) along a circumferential direction thereof; anda plurality of main swirlers (101), each of said main swirlers (101) being arranged to surround a respective one of said plurality of main fuel nozzles (102) upstream of said plurality of nozzle holes (105) thereof, each of said main swirlers (101) comprising a hub fitted around said respective one main fuel nozzle (102) and a plurality of swirler vanes (101a) fixedly connected to said hub and extending radially outward from said hub to said outer casing, each of said plurality of swirler vanes (101a) being twisted from a hub side thereof to a tip side thereof,
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP245477/97 | 1997-09-10 | ||
JP24547797A JPH1183016A (en) | 1997-09-10 | 1997-09-10 | Three-dimensional swirler |
JP24547797 | 1997-09-10 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0902237A2 EP0902237A2 (en) | 1999-03-17 |
EP0902237A3 EP0902237A3 (en) | 2000-09-20 |
EP0902237B1 true EP0902237B1 (en) | 2003-12-03 |
Family
ID=17134250
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19980116591 Expired - Lifetime EP0902237B1 (en) | 1997-09-10 | 1998-09-02 | Combustor comprising swirler with twisted vanes |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0902237B1 (en) |
JP (1) | JPH1183016A (en) |
CA (1) | CA2246219C (en) |
DE (1) | DE69820183T2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103807879A (en) * | 2012-11-06 | 2014-05-21 | 阿尔斯通技术有限公司 | Axial swirler |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1406047A4 (en) * | 2001-07-10 | 2010-04-07 | Mitsubishi Heavy Ind Ltd | Premixing nozzle, burner and gas turbine |
EP1394471A1 (en) | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Burner |
JP4486549B2 (en) * | 2005-06-06 | 2010-06-23 | 三菱重工業株式会社 | Gas turbine combustor |
JP4476176B2 (en) * | 2005-06-06 | 2010-06-09 | 三菱重工業株式会社 | Gas turbine premixed combustion burner |
EP1985924A1 (en) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Swirler |
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 |
KR101853442B1 (en) | 2015-06-30 | 2018-04-30 | 두산중공업 주식회사 | Gas turbine provided with a device for improved fuel flow distribution. |
KR101857280B1 (en) | 2015-06-30 | 2018-05-11 | 두산중공업 주식회사 | Gas turbine provided with a device for improved fuel flow distribution. |
US11041621B2 (en) * | 2016-07-26 | 2021-06-22 | Jfe Steel Corporation | Auxiliary burner for electric furnace |
JPWO2019230165A1 (en) | 2018-06-01 | 2021-01-07 | 株式会社Ihi | Liquid fuel injector |
CN113776084A (en) * | 2021-10-08 | 2021-12-10 | 浙江浙能技术研究院有限公司 | Integrated low-pollution combustion chamber nozzle structure and method |
Family Cites Families (7)
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 (en) * | 1983-08-30 | 1987-04-15 | Bbc Brown Boveri & Cie | AXIAL SWIRL FOR GENERATING TURNING FLOWS. |
JPH02503106A (en) * | 1987-12-28 | 1990-09-27 | サンドストランド・コーポレーション | Gas turbine with forced vortex fuel injection |
JPH02147610U (en) * | 1989-05-11 | 1990-12-14 | ||
GB2263763B (en) * | 1992-02-05 | 1995-03-22 | Ind Tech Res Inst | A swirl generator with axial vanes |
-
1997
- 1997-09-10 JP JP24547797A patent/JPH1183016A/en active Pending
-
1998
- 1998-09-02 DE DE69820183T patent/DE69820183T2/en not_active Expired - Lifetime
- 1998-09-02 EP EP19980116591 patent/EP0902237B1/en not_active Expired - Lifetime
- 1998-09-02 CA CA 2246219 patent/CA2246219C/en not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103807879A (en) * | 2012-11-06 | 2014-05-21 | 阿尔斯通技术有限公司 | Axial swirler |
CN103807879B (en) * | 2012-11-06 | 2016-06-01 | 通用电器技术有限公司 | Axial swirler |
Also Published As
Publication number | Publication date |
---|---|
CA2246219A1 (en) | 1999-03-10 |
JPH1183016A (en) | 1999-03-26 |
EP0902237A2 (en) | 1999-03-17 |
DE69820183T2 (en) | 2004-08-26 |
DE69820183D1 (en) | 2004-01-15 |
CA2246219C (en) | 2002-11-19 |
EP0902237A3 (en) | 2000-09-20 |
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