EP0902237A2 - Combustor swirler with twisted vanes - Google Patents

Combustor swirler with twisted vanes Download PDF

Info

Publication number
EP0902237A2
EP0902237A2 EP98116591A EP98116591A EP0902237A2 EP 0902237 A2 EP0902237 A2 EP 0902237A2 EP 98116591 A EP98116591 A EP 98116591A EP 98116591 A EP98116591 A EP 98116591A EP 0902237 A2 EP0902237 A2 EP 0902237A2
Authority
EP
European Patent Office
Prior art keywords
swirler
angle
fuel nozzle
fuel
air
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.)
Granted
Application number
EP98116591A
Other languages
German (de)
French (fr)
Other versions
EP0902237A3 (en
EP0902237B1 (en
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/en
Publication of EP0902237A3 publication Critical patent/EP0902237A3/en
Application granted granted Critical
Publication of EP0902237B1 publication Critical patent/EP0902237B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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 gas turbine.
  • Fig. 4 is an entire constructional view of one example of a premixed 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 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. 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.
  • the present invention provides a three-dimensional swirler characterized in that 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 present invention provides a three-dimensional swirler as mentioned above, characterized in that in said swirler vane, 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.
  • 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)

Abstract

Pre-mixture forming swirler in gas turbine pre-mixed flame type low NOx combustor is improved so as to accelerate mixing of fuel and air and to prevent occurrence of flame stagnation and burning of component.
Three-dimensional swirler is constructed such that swirler vane (101a) is twisted from hub side thereof to tip side so that fitting angle (β) of the tip side relative to fuel nozzle (102) center axis (C) is larger than that (α) of the hub side. Thereby, while the angle (α) of the hub side is set smaller so that flame stagnation and burning of components resulted therefrom may be prevented from occurring, the angle (β) of the tip side may be selected so that shearing flow necessary for appropriate mixing of fuel (F) and air (A) is obtained, thus favorable pre-mixing is done, life deterioration due to the burning etc. is prevented and combustion efficiency is enhanced.

Description

BACKGROUND OF THE INVENTION: Field of the Invention:
The present invention relates to a swirler for forming a pre-mixture in a pre-mixed flame type low NOx combustor of gas turbine.
Description of the Prior Art:
Above-mentioned type of combustor in the prior art will be outlined below with reference to Figs. 2 to 5. Fig. 4 is an entire constructional view of one example of a premixed flame type low NOx combustor in the prior art and Fig. 5 is a cross sectional view of a main fuel nozzle as part of the combustor of Fig. 4.
What is called 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.
In an upstream portion of each of the main fuel nozzles 202, there is provided a main swirler 201 surrounding the main fuel nozzle 202 and extending to a position of the outer casing 206.
And in a wall of body of the main fuel nozzle 202 on a downstream side of the main swirler 201, there are bored a plurality of nozzle holes 205 along a circumferential direction of the main fuel nozzle 202.
In the prior art combustor constructed as above, there are provided 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.
In the main fuel nozzle 202, as shown in Fig. 5, 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.
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.
In the prior art swirler, while there is seen such an example that the fitting angle of the swirler vane is changed and adjusted for changing the swirling angle, the swirler in actual use remains such that when the fitting angle of the swirler vane to the hub portion (hub portion fitting angle) is changed and adjusted, that hub portion fitting angle is maintained same as far as to a tip portion of the swirler vane and there is seen no more example of angle change.
As concrete examples of changing the hub portion fitting angle of the swirler vane, there are ones shown in Figs. 2 and 3.
That is, one example is that the hub portion fitting angle of a swirler vane 201a relative to a center axis C of the main fuel nozzle 202 is 25°, as shown in Fig. 2, wherein Fig. 2(a) is a view showing arrangement of a swirler relative to the fuel nozzle and Fig. 2(b) is a development of arrangement of swirler vanes.
Also, another example is that the hub portion fitting angle of a swirler vane 201b relative to the center axis C of the main fuel nozzle 202 is 45°, as shown in Fig. 3, wherein Fig. 3(a) is a view showing arrangement of a swirler relative to the fuel nozzle and Fig. 3(b) is a development of arrangement of swirler vanes.
In either of Figs. 2 and 3, air A supplied from upstream runs into the swirler vane 201a or 201b to form an outward swirling flow and fuel F of natural gas and the like is supplied into this swirling flow of air via nozzle holes 205 of the main fuel nozzle 202 to form a pre-mixture of the fuel F and the air A.
In the prior art swirler in which the hub portion fitting angle of the swirler vane 201b shown in Fig. 3 is 45°, because said angle is as large as 45°, shearing flow of the air A is strong, so that mixing of the fuel F and the air A is accelerated very favorably.
However, due to said strong shearing flow, there is formed a large stagnation point P at a tip portion of the main fuel nozzle 202, as shown by a hatched portion in Fig. 3(a), and if a back fire phenomenon once occurs, flame stagnates at the stagnation point P, so that there arises a problem that the main fuel nozzle 202 is apt to burn.
On the other hand, in the prior art swirler in which the hub portion fitting angle of the swirler vane 201a shown in Fig. 2 is 25°, because said angle of 25° is comparatively small, shearing flow of the air A is not so strong and the stagnation point P which is formed at the tip portion of the main fuel nozzle 202, as shown by a hatched portion in Fig. 2(a), is small, hence even if a back fire phenomenon occurs, flame does not specifically stagnate there.
However, this effect is obtained by the shearing flow of the air A which is not very strong and as a result reversely, mixing of the fuel F and the air A, which is a function required for a pre-mixed type combustor, becomes worse, as clearly understood when compared with the swirler of Fig. 3 in which the hub portion fitting angle of the swirler vane 201b is 45° and there is a problem of narrow range of condition within which a low NOx combustion is attained.
SUMMARY OF THE INVENTION:
It is therefore an object of the present invention to provide a swirler which is able to accelerate mixing of fuel and air as well as to make a stagnation point formed at a tip portion of a main fuel nozzle smaller to thereby prevent occurrence of flame stagnation and burning of components so as to dissolve problems in the prior art.
In order to attain said object, the present invention provides a three-dimensional swirler characterized in that 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.
That is, 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. Thus, while 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.
Also, the present invention provides a three-dimensional swirler as mentioned above, characterized in that in said swirler vane, 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°.
That is, 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.
BRIEF DESCRIPTION OF THE DRAWINGS:
  • Fig. 1 is a view showing one embodiment according to the present invention, wherein Fig. 1(a) is a view showing 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.
  • Fig. 2 is a view of one example of swirler in the prior art, wherein Fig. 2(a) is a view showing arrangement of a swirler relative to a fuel nozzle and Fig. 2(b) is a development of arrangement of swirler vanes.
  • Fig. 3 is a view of another example of swirler in the prior art, wherein Fig. 3(a) is a view showing arrangement of a swirler relative to a fuel nozzle and Fig. 3(b) is a development of arrangement of swirler vanes.
  • Fig. 4 is an entire constructional view showing one example of a pre-mixed flame type low NOx 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.
    • DESCRIPTION OF THE PREFERRED EMBODIMENTS:
    One embodiment according to the present invention will be described with reference to Fig. 1. 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.
    In the present embodiment, 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:
    That is, as shown in Figs. 1(b) and (c), a fitting angle α 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 β 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.
    Thus, as understood from Fig. 1(c), the swirler vane 101a is twisted from the hub side to the tip side by a differential angle between the hub side angle α = 25° and the tip side angle β = 45°.
    In the present embodiment constructed as above, while the air A is changed of its flow direction by the swirler vane 101a of the main swirler 101, because the fitting angle α on the hub side of the swirler vane 101a is 25°, a stagnation point P, if formed, at a tip portion of the main fuel nozzle 102 is not so large.
    Also, the swirler vane 101a is twisted from the hub side to the tip side and the fitting angle β on the tip side of the swirler vane 101a is 45°, hence there can be formed a strong shear flow there.
    And 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.
    Thus, according to the present embodiment, 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.
    Also, 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.
    The invention has been described with respect to the embodiment as illustrated, but it is not limited to such embodiment but, needless to mention, may be added with various modifications as come within the scope of the claims as set forth below.

    Claims (2)

    1. A three-dimensional swirler, characterized in that a swirler vane (101a) fitted around a fuel nozzle (102) is twisted from a hub side thereof to a tip side thereof so that a fitting angle (β) of the tip side relative to a center axis (C) of the fuel nozzle (102) is larger than that (α) of the hub side.
    2. A three-dimensional swirler as claimed in Claim 1, characterized in that in said swirler vane (101a), the fitting angle (α) of the hub side relative to the center axis (C) of the fuel nozzle (102) is 25° and that (β) of the tip side is 45°.
    EP19980116591 1997-09-10 1998-09-02 Combustor comprising swirler with twisted vanes Expired - Lifetime EP0902237B1 (en)

    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 true EP0902237A2 (en) 1999-03-17
    EP0902237A3 EP0902237A3 (en) 2000-09-20
    EP0902237B1 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 (6)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    WO2003006887A1 (en) * 2001-07-10 2003-01-23 Mitsubishi Heavy Industries, Ltd. Premixing nozzle, burner and gas turbine
    WO2004025183A3 (en) * 2002-09-02 2005-01-20 Siemens Ag Burner
    EP1985924A1 (en) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Swirler
    EP2728261A1 (en) * 2012-11-06 2014-05-07 Alstom Technology Ltd Axial swirler
    KR20170003050A (en) 2015-06-30 2017-01-09 두산중공업 주식회사 Gas turbine provided with a device for improved fuel flow distribution.
    KR20170003053A (en) 2015-06-30 2017-01-09 두산중공업 주식회사 Gas turbine provided with a device for improved fuel flow distribution.

    Families Citing this family (7)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    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
    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
    KR102211258B1 (en) * 2016-07-26 2021-02-02 제이에프이 스틸 가부시키가이샤 Supporting Burner for Electric Furnace
    WO2019230165A1 (en) 2018-06-01 2019-12-05 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

    Citations (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
    US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
    WO1989006307A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Gas turbine with forced vortex fuel injection
    EP0397046A2 (en) * 1989-05-11 1990-11-14 Mitsubishi Jukogyo Kabushiki Kaisha Burner apparatus
    US5186607A (en) * 1990-12-03 1993-02-16 Industrial Technology Research Institute Swirl generator with axial vanes

    Patent Citations (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
    US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
    WO1989006307A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Gas turbine with forced vortex fuel injection
    EP0397046A2 (en) * 1989-05-11 1990-11-14 Mitsubishi Jukogyo Kabushiki Kaisha Burner apparatus
    US5186607A (en) * 1990-12-03 1993-02-16 Industrial Technology Research Institute Swirl generator with axial vanes

    Cited By (12)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    WO2003006887A1 (en) * 2001-07-10 2003-01-23 Mitsubishi Heavy Industries, Ltd. Premixing nozzle, burner and gas turbine
    US7360363B2 (en) 2001-07-10 2008-04-22 Mitsubishi Heavy Industries, Ltd. Premixing nozzle, combustor, and gas turbine
    WO2004025183A3 (en) * 2002-09-02 2005-01-20 Siemens Ag Burner
    US7753677B2 (en) 2002-09-02 2010-07-13 Siemens Aktiengesellschaft Burner
    EP1985924A1 (en) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Swirler
    WO2008128955A1 (en) * 2007-04-23 2008-10-30 Siemens Aktiengesellschaft Swirler
    CN101668989B (en) * 2007-04-23 2012-01-04 西门子公司 Swirler
    EP2728261A1 (en) * 2012-11-06 2014-05-07 Alstom Technology Ltd Axial swirler
    EP2728260A1 (en) * 2012-11-06 2014-05-07 Alstom Technology Ltd Axial swirler
    US9557061B2 (en) 2012-11-06 2017-01-31 General Electric Technology Gmbh Axial swirler
    KR20170003050A (en) 2015-06-30 2017-01-09 두산중공업 주식회사 Gas turbine provided with a device for improved fuel flow distribution.
    KR20170003053A (en) 2015-06-30 2017-01-09 두산중공업 주식회사 Gas turbine provided with a device for improved fuel flow distribution.

    Also Published As

    Publication number Publication date
    DE69820183T2 (en) 2004-08-26
    CA2246219C (en) 2002-11-19
    EP0902237A3 (en) 2000-09-20
    CA2246219A1 (en) 1999-03-10
    DE69820183D1 (en) 2004-01-15
    EP0902237B1 (en) 2003-12-03
    JPH1183016A (en) 1999-03-26

    Similar Documents

    Publication Publication Date Title
    US6502399B2 (en) Three-dimensional swirler in a gas turbine combustor
    US6038861A (en) Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
    EP2530382B1 (en) Fuel injector
    US8468831B2 (en) Lean direct injection for premixed pilot application
    US6301899B1 (en) Mixer having intervane fuel injection
    CA2393863C (en) Pilot burner, premixing combustor, and gas turbine
    EP0902237A2 (en) Combustor swirler with twisted vanes
    JP2006300448A (en) Combustor for gas turbine
    JP2007285572A (en) Premixed combustion burner for gas turbine
    EP0952392B1 (en) Combustor
    US5094610A (en) Burner apparatus
    JP3903195B2 (en) Fuel nozzle
    CN113587145B (en) Gas turbine combustor
    KR20160143715A (en) Air fuel premixer for low emissions gas turbine combustor
    EP3425281B1 (en) Pilot nozzle with inline premixing
    KR20180110023A (en) Burner assemblies, combustors, and gas turbines
    JP3944609B2 (en) Fuel nozzle
    JP4066658B2 (en) Gas turbine combustor, gas turbine combustor premixing device, and gas turbine combustor premixing method
    CN115307177B (en) Bifurcated pilot premixer for a main micromixer array in a gas turbine engine
    JPH07332621A (en) Swirl burner for gas turbine combustion device
    JPH06101815A (en) Premixing combustion burner and combustion device
    JP2011099667A (en) Secondary fuel nozzle venturi
    GB2373043A (en) Fuel injector for a dual fuel turbine engine
    JPH08261464A (en) Turbulence-mixed fuel injection valve
    JP2002206742A (en) Premixing combustor

    Legal Events

    Date Code Title Description
    PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

    Free format text: ORIGINAL CODE: 0009012

    17P Request for examination filed

    Effective date: 19980929

    AK Designated contracting states

    Kind code of ref document: A2

    Designated state(s): CH DE FR GB IT LI

    AX Request for extension of the european patent

    Free format text: AL;LT;LV;MK;RO;SI

    PUAL Search report despatched

    Free format text: ORIGINAL CODE: 0009013

    AK Designated contracting states

    Kind code of ref document: A3

    Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

    AX Request for extension of the european patent

    Free format text: AL;LT;LV;MK;RO;SI

    AKX Designation fees paid

    Free format text: CH DE FR GB IT LI

    17Q First examination report despatched

    Effective date: 20020924

    GRAH Despatch of communication of intention to grant a patent

    Free format text: ORIGINAL CODE: EPIDOS IGRA

    RTI1 Title (correction)

    Free format text: COMBUSTOR COMPRISING SWIRLER WITH TWISTED VANES

    GRAS Grant fee paid

    Free format text: ORIGINAL CODE: EPIDOSNIGR3

    GRAA (expected) grant

    Free format text: ORIGINAL CODE: 0009210

    AK Designated contracting states

    Kind code of ref document: B1

    Designated state(s): CH DE FR GB IT LI

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: LI

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20031203

    Ref country code: IT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

    Effective date: 20031203

    Ref country code: FR

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20031203

    Ref country code: CH

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20031203

    REG Reference to a national code

    Ref country code: GB

    Ref legal event code: FG4D

    REG Reference to a national code

    Ref country code: CH

    Ref legal event code: EP

    REF Corresponds to:

    Ref document number: 69820183

    Country of ref document: DE

    Date of ref document: 20040115

    Kind code of ref document: P

    REG Reference to a national code

    Ref country code: CH

    Ref legal event code: PL

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: GB

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20040902

    PLBE No opposition filed within time limit

    Free format text: ORIGINAL CODE: 0009261

    STAA Information on the status of an ep patent application or granted ep patent

    Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

    26N No opposition filed

    Effective date: 20040906

    EN Fr: translation not filed
    GBPC Gb: european patent ceased through non-payment of renewal fee

    Effective date: 20040902

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: DE

    Payment date: 20170830

    Year of fee payment: 20

    REG Reference to a national code

    Ref country code: DE

    Ref legal event code: R071

    Ref document number: 69820183

    Country of ref document: DE