EP2735798A1 - Gasturbinenbrennkammer - Google Patents

Gasturbinenbrennkammer Download PDF

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Publication number
EP2735798A1
EP2735798A1 EP12194055.5A EP12194055A EP2735798A1 EP 2735798 A1 EP2735798 A1 EP 2735798A1 EP 12194055 A EP12194055 A EP 12194055A EP 2735798 A1 EP2735798 A1 EP 2735798A1
Authority
EP
European Patent Office
Prior art keywords
inner diameter
premixing tube
combustion cylinder
fuel
flame
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
EP12194055.5A
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English (en)
French (fr)
Other versions
EP2735798B1 (de
Inventor
Shigeru Tachibana
Masamichi Koyama
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.)
TACHIBANA, SHIGERU
IHI Power Systems Co Ltd
Original Assignee
Niigata Power Systems Co Ltd
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Publication date
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Priority to EP12194055.5A priority Critical patent/EP2735798B1/de
Publication of EP2735798A1 publication Critical patent/EP2735798A1/de
Application granted granted Critical
Publication of EP2735798B1 publication Critical patent/EP2735798B1/de
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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
    • F23R3/16—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
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • the present invention relates to a gas turbine combustor. More particularly, the present invention relates to a structure of the gas turbine combustor, which adds a special structure to an open part communicated with a premixing tube and a combustion cylinder to allow a position of a flame retained within the combustion cylinder to be easily set and changed in accordance with intensity of radiation heat of the fuel in use so as to prevent deterioration in durability of the combustion cylinder by the heat of the flame.
  • Japanese Unexamined Patent Application Publication No. 2009-198054 discloses a gas turbine combustor 1 provided with a combustion cylinder 2, a premixing tube 3, and a fuel supply unit 5.
  • the gas turbine combustor 1 is configured to allow the fuel supply unit to supply the fuel to an annular fuel passage 16 along a tangential direction so that the fuel is uniformly injected through an annular nozzle portion 19.
  • the injected fuel is atomized by air from a circumferential air passage 22 that surrounds the nozzle portion, and an axial flow is generated in the combustor.
  • air flowing inside through holes 25 in a peripheral wall surface of the premixing tube generates a swirl flow that surrounds the axial flow within the combustor.
  • the flame is retained at a position apart from a top portion of the combustion cylinder so that a heat shield plate 6 is not excessively heated, resulting in improved durability.
  • U.S. Patent Publication Nos. 5735681 and 5879148 disclose the gas turbine combustor configured to sufficiently mix the fuel and air by air of straight flow directed to the combustion cylinder and air of the swirl flow generated by a swirler for the burner that combusts the fuel so as to stabilize the combustion and realize low emission.
  • the generally employed gas turbine combustor as described above is normally configured to retain the flame generated by combusting the mixture supplied from the premixing tube in the combustion cylinder at the position apart from the top portion thereof in communication with the premixing tube by a predetermined distance so as to prevent the radiation heat of the flame from damaging the combustion cylinder.
  • the distance from the top portion of the combustion cylinder to the flame is called a lift distance.
  • the radiation heat of the flame varies with type of the fuel in use. Accordingly, the generally employed gas turbine combustor has been designed to balance the swirl air quantity from the premixing tube with the straight air quantity in accordance with the type of the fuel in use so that the flame lift distance has an appropriate length to prevent thermal damage to the device.
  • the number of swirls of the swirler in use, and the shape and structure of the premixing tube are adjusted to set the balance between the swirl air quantity and the straight air quantity to a desired value.
  • Such adjustment of the structure of the respective portions in accordance with the desired lift distance is very complicated and troublesome work, and considerably time-consuming and costly.
  • the gas turbine combustor is configured to set the lift distance in accordance with the fuel of the predetermined type, there may be the case where the fuel that generates different radiation heat upon combustion has to be used for certain reasons of usage.
  • structures of the respective parts of the gas turbine combustor have to be changed to adjust the swirl air quantity from the premixing tube and the straight air quantity for the purpose of setting a different lift distance in response to the change of the fuel type.
  • the lift distance is intended to be shortened, the modification by increasing the swirl air quantity and reducing the straight air quantity will be necessary.
  • the lift distance is intended to be extended, the modification by reducing the swirl air quantity and increasing the straight air quantity will be necessary.
  • the aforementioned modifications are far more complicated and troublesome than providing a newly manufactured gas turbine combustor, even more time-consuming and costly.
  • a first aspect of the present invention provides a gas turbine combustor which includes a combustion cylinder that combusts a mixture of fuel and air for supply of a combustion gas to a turbine, a premixing tube which is open to the combustion cylinder, and mixes the supplied fuel and air so as to be supplied to the combustion cylinder, and a fuel supply unit attached to the premixing tube for supplying the fuel to the premixing tube, wherein an inner diameter enlarging portion is provided at an open end of the premixing tube, which is open to the combustion cylinder.
  • a second aspect of the present invention is the gas turbine combustor according to the first aspect wherein the inner diameter enlarging portion includes a planer processed portion at a predetermined angle.
  • a third aspect of the present invention is the gas turbine combustor according to the first aspect wherein the inner diameter enlarging portion includes a curved portion.
  • the gas turbine combustor according to the present invention is provided with an inner diameter enlarging portion at an open end of the premixing tube that faces the combustion cylinder.
  • the flame lift distance within the combustion cylinder is determined in accordance with the shape of the inner diameter enlarging portion. That is, the inner diameter enlarging portion is configured to enlarge the inner diameter along the axial direction from the premixing tube to the combustion cylinder. Therefore, the swirl flow of air flowing along the inner circumferential surface of the premixing tube moves along the inner diameter enlarging portion at the opening of the premixing tube, and flows into the combustion cylinder while spreading outward.
  • the enlargement of the inner diameter by the inner diameter enlarging portion becomes relatively large so that the spread to the outside is larger, the swirl flow of air is guided to the outside to higher degree in the combustion cylinder. Then the cross-section area of the air straight flow that moves along the center of the premixing tube becomes relatively large. Assuming that each quantity of the fuel and air is kept constant, the flow velocity of the mixture becomes relatively low, and the flame is retained at the position closer to the premixing tube, resulting in the lift distance becoming relatively short.
  • the inner diameter enlarging portion that makes relatively small enlargement of the inner diameter may be employed to make the lift distance of the flame relatively long.
  • the inner diameter enlarging portion that makes relatively large enlargement of the inner diameter may be employed to make the lift distance of the flame relatively short.
  • the flame lift distance may be arbitrarily set in accordance with the heat radiation of the fuel to be used only by replacing the inner diameter enlarging portion without making an extensive change in the structure to change the swirl air quantity and the straight air quantity. This ensures to prevent deterioration in durability of the combustion cylinder caused by heat of the flame irrespective of the fuel type.
  • FIG. 1 a general structure of a gas turbine combustor 1 according to a first embodiment will be described.
  • the gas turbine combustor 1 includes a substantially cylindrical combustion cylinder 2.
  • the combustion cylinder 2 has a top portion closed, and a lower opening communicated with an exhaust side of a not shown gas turbine.
  • the top portion of the combustion cylinder 2 is provided with a premixing tube 3, which will be described in detail later.
  • a top portion of the premixing tube 3 is provided with a pressure injection unit 4 as a fuel supply unit.
  • the combustion cylinder 2 and the premixing tube 3 are encased with an outer cylinder 5 communicated with a compressed air inlet of a not shown turbo-compressor.
  • a part of a fuel supply system connected to the pressure injection unit 4 is guided to the outside while penetrating the top portion of the outer cylinder 5.
  • the premixing tube 3 includes a cylindrical peripheral wall 6 provided outside the top portion of the combustion cylinder 2, and a cylindrical protruding wall 7 that is provided at the top portion of the combustion cylinder 2 so as to partially protrude downward by a predetermined dimension into the combustion cylinder 2.
  • the peripheral wall 6 has a straight cylindrical outer shape, and an inner shape with the inner diameter gradually reduced toward the combustion cylinder 2 in the downward direction.
  • the peripheral wall 6 has a plurality of holes 8 along the tangential direction, which allow air to flow inside.
  • the protruding wall 7 connected to the lower end of the peripheral wall 6 has the straight cylindrical shape with the same inner diameter as that of the opening of the peripheral wall 6 at the lower end.
  • an inner diameter enlarging portion 10 is attached to an open end of the protruding wall 7 of the premixing tube 3, which is open within the combustion cylinder 2.
  • the inner diameter enlarging portion 10 is an annular member, and has a chamfer 11 as a planar worked portion directed diagonally downward at a predetermined angle formed on an inner circumferential edge.
  • the chamfer with dimensions in horizontal and vertical directions of 8 mm is applied at the angle of 45°, that is, the chamfer corresponding to type C8 specified as JIS code is applied to the inner circumferential edge.
  • a cylindrical inner wall 9 is provided inside the peripheral wall 6 of the premixing tube 3 coaxially at a predetermined interval therebetween.
  • An outer circumferential surface of the inner wall 9 has an outer diameter gradually reduced toward the combustion cylinder 2 in the downward direction.
  • the radial distance between the peripheral wall 6 and the inner wall 9 is kept constant, which defines a cylindrical gap S penetrating downward.
  • the gap S has its upper end at one end side of the premixing tube 3 closed, and a lower end opened around the upper end of the protruding wall 7.
  • the inner circumferential surface of the inner wall 9 has a straight cylindrical shape.
  • the upper end of the inner wall 9 at one end side of the premixing tube 3 is opened to the outer cylinder 5.
  • the compressed air from the turbo-compressor which is guided into the outer cylinder 5 flows inside through the holes 8 formed in the peripheral wall 6 of the premixing tube 3, and then forms a swirl flow in the cylindrical gap S between the peripheral wall 6 and the inner wall 9. It moves to the open end while swirling along the inner circumferential surface of the protruding wall 7 so as to be fed into the combustion cylinder 2 via the inner diameter enlarging portion 10.
  • the compressed air is supplied to the inside of the inner wall 9 from the opening at the upper end thereof together with the fuel supplied from the pressure injection unit 4, which are formed into the mixture.
  • the mixture forms the homogeneous straight flow along the axial direction of the inner wall 9 over the whole region inside thereof under no influence of the interference of the swirl flow. It is then supplied into the combustion cylinder 2.
  • the chamfer 11 of the inner diameter enlarging portion 10 is diagonally directed downward, and is shaped to have the inner diameter increased toward the combustion cylinder 2 along the center axis.
  • the air swirl flow out of the gap S flows along the chamfer 11 of the inner diameter enlarging portion 10 at the open end of the protruding wall 7 of the premixing tube 3 so as to flow into the combustion cylinder 2 while spreading outward.
  • the effect of guiding the air swirl flow outward in the combustion cylinder 2 is generated in accordance with the enlargement of the inner diameter by the inner diameter enlarging portion 10. Therefore, the cross-section area of the air straight flow that moves along the center of the premixing tube 3 is influenced as described below depending on the degree of guiding the swirl flow outward.
  • the cross-section area of the air straight flow becomes large. Assuming that each quantity of the fuel and air is kept constant, the flow velocity of the mixture becomes relatively low. The lift distance is then reduced so that the flame is brought into closer to the top portion of the combustion cylinder 2. As the degree of guiding the air swirl flow to the outside by the inner diameter enlarging portion 10 is reduced, the cross-section area of the air straight flow becomes small. Assuming that each quantity of the fuel and air is kept constant, the flow velocity of the mixture becomes relatively high. The lift distance is increased so that the flame is farther apart from the top portion of the combustion cylinder 2. In this way, the lift distance of the flame is determined in accordance with enlargement of the inner diameter by the chamfer 11 of the inner diameter enlarging portion 10 (in this case, size of the chamfer).
  • the pressure injection unit 4 is provided at the center of the opening at the upper end of the peripheral wall 6 at one end side of the premixing tube 3.
  • the pressure injection unit 4 is a pressure injection nozzle of hollow cone type, which atomizes liquid fuel in a highly advanced manner by injecting the fuel in a hollow conical shape.
  • the pressure injection unit 4 is configured to discharge the fuel supplied from two fuel supply channels, a main supply channel 20 and a pilot supply channel 21, through a single injection nozzle 22.
  • the swirl motion is applied to the fuel so that the fuel discharged through the injection nozzle 22 spreads under centrifugal force to form a hollow cone film.
  • the simplex injection valve is known.
  • An injection angle of the injection nozzle 22 of the pressure injection unit 4 is set so that the conically injected fuel is not adhered to the inner diameter enlarging portion 10 attached to the open end of the protruding wall 7 of the premixing tube 3.
  • the injection nozzle 22 is provided with a flow channel 25 at the periphery thereof, which guides the compressed air within the outer cylinder 5 so as to be injected from an inlet 24 for injection. Air from the flow channel 25 serves to suppress spread of the conically injected fuel through the injection nozzle 22. This makes it possible to further alleviate and suppress adhesion of the fuel to the protruding wall 7 or the inner diameter enlarging portion 10.
  • the compressed air from the turbo-compressor is generally at the temperature of approximately 300°C.
  • the compressed air is guided into the outer cylinder 5, flows inside through the holes 8 formed in the peripheral wall 6 of the premixing tube 3, and forms the swirl flow in the cylindrical gap S between the peripheral wall 6 and the inner wall 9.
  • the swirl flow out of the gap S reaches the open end of the protruding wall 7 while flowing along the inner circumferential surface of the protruding wall 7, and further flows along the chamfer 11 of the inner diameter enlarging portion 10. Finally, it flows into the combustion cylinder while spreading outward.
  • the compressed air is also supplied into the inner space of the inner wall 9 from the opening at the upper end of the premixing tube 3, and mixed with the fuel injected from the pressure injection unit 4 to form the mixture as the straight flow. It is fed into the combustion cylinder 2 from the protruding wall 7, and combusted to generate combustion gas at the temperature ranging from 1000 to 2000°C, for example.
  • the aforementioned temperatures of the air and gas are taken as example values.
  • the swirl flow is guided and spread outward along the inner diameter enlarging portion 10. Therefore, the cross-section area of the air straight flow along the center of the premixing tube 3 corresponds to the one in the case where the swirl flow spreads to the outside. Assuming that each quantity of the fuel and air is kept constant, as the swirl flow is guided outward largely, and the cross-section area of the air straight flow becomes larger, the mixture flow velocity becomes relatively low. As a result, the lift distance of the flame becomes short. If the cross-section area of the air straight flow does not expand because the swirl flow is not largely guided outward, the mixture flow velocity becomes relatively high. As a result, the lift distance of the flame becomes long.
  • the compressed air and the fuel, or the mixture thereof in the inner wall 9 form the homogeneous straight flow along the axial direction of the inner wall 9 over the entire region inside thereof under no influence of the interference of the swirl flow of the compressed air formed in the gap S between the peripheral wall 6 and the inner wall 9. Since the cross-section area of the straight flow is adjusted in association with outward spread of the swirl flow by the inner diameter enlarging portion 10 as described above, combustion occurs at the lift distance in accordance with the flow velocity corresponding to the adjusted cross-section area of the flow.
  • the cross-section area of the mixture straight flow in the premixing tube 3 is reduced by the air swirl flow through the holes 8 formed in the peripheral wall 6 of the premixing tube 3.
  • the flow is fed into the protruding wall 7 at the stabilized constant flow velocity without excessively accelerating, and subjected to the flow velocity adjustment in accordance with the shape of the inner diameter enlarging portion 10 from the time of passage therethrough to the time immediately thereafter. It generates the flame F at the predetermined lift distance L1 in the combustion cylinder 2 as shown in Fig. 3A .
  • the flame is kept in the stabilized state as shown in Fig. 3B .
  • the flame F is stably retained at the appropriate position in the combustion cylinder 2. This makes it possible to prevent deterioration in durability of the combustion cylinder 2 by the heat, and realize stabilization of combustion and low emission.
  • Fig. 3A represents the case where the chamfer 11 applied to the inner diameter enlarging portion 10 is of type C8. It is assumed that the lift distance L is required to be even longer in order to use the fuel that generates higher radiation heat upon combustion in the gas turbine combustor 1. For example, since the radiation heat generated by the aromatic fuel is greater than the radiation heat generated by kerosene or light oil upon combustion, the use of the aromatic fuel in the aforementioned structure may damage the combustion cylinder 2 and the like by heat even if the structure shown in Fig. 3A is suitable for the use of the kerosene or light oil.
  • the inner diameter enlarging portion 10 is attached to the open end of the premixing tube 3 using a simple fixing member such as a bolt.
  • the inner diameter enlarging portion 10 with the chamfer 11 of type C3 is assumed to use as JIS (Japanese Industrial Standards) code, which is processed at 45° with dimensions of 3 mm in both horizontal and vertical directions as shown in Fig. 4A .
  • the C3 denotes the type of the process that chamfers an isosceles triangle part with each of two equal sides set to 3 mm at the angle of 45° in the cross-section.
  • the outward spread and guidance of the swirl flow is not as large as the case shown in Fig. 3A , and accordingly, the cross-section area of the straight flow of moving air along the center of the premixing tube 3 is narrower than the case shown in Fig. 3A .
  • the inner diameter enlarging portion 10 does not serve to enlarge the inner diameter, that is, the inner diameter is the same as that of the protruding wall 7 of the premixing tube 3.
  • the outward spread and guidance of the swirl flow in this case is not as large as in the case shown in Fig. 4A .
  • the flow is fed into the combustion cylinder 2 while flowing downward along the inner circumferential surface of the protruding wall 7.
  • the cross-section area of the straight flow of moving air along the center of the premixing tube 3 has no substantial change. Assuming that each quantity of the fuel and air is kept constant, the respective flow velocities do not largely change. That is, they become relatively higher than the case shown in Fig. 4A . As a result, the lift distance L3 of the flame F is longer than the lift distance L2 shown in Fig. 4A . The flame is stably retained at the farthest position as shown in Fig. 5B .
  • the adequacy of the lift distance of the flame F needs to be determined in accordance with radiation of heat generated by the flame F. If the lift distance is too short for the temperature of the flame F, the combustion cylinder 2 or the like may be damaged. If the lift distance is too long for the temperature of the flame F, the combustion becomes unstable, which may extinguish the flame F.
  • the embodiment allows the inner diameter enlarging portion 10 with appropriate structure to be selectively attached in accordance with radiation of heat generated by the flame F so as to easily set the optimal lift distance L of the flame F.
  • the angle, dimension and the like of the chamfer 11 of the inner diameter enlarging portion 10 may be arbitrarily set in accordance with the required lift distance of the flame and the overall structure of the device.
  • Fig. 6 represents data obtained from the gas turbine combustor according to the embodiment in the uncombusted state where air and the fuel gas flow without being ignited.
  • the unit of the distance X on x-axis is mm, and the unit of the axial flow velocity U on the y-axis is m/s.
  • Fig. 7 represents data obtained from the gas turbine combustor 1 according to the embodiment in the combustion state by igniting supplied air and fuel gas.
  • the units on the x-axis and the y-axis are the same as those shown in Fig. 6 .
  • the flow velocity is not constant for the respective inner diameter enlarging portions 10.
  • the position X at which the flow velocity starts increasing represents the lift distance L which is different in accordance with the structure of the inner diameter enlarging portion 10 as described above.
  • the respective flow velocities become lower in the order of the types C8, C3 and C0 at the point before the minimum value due to the structures of the respective inner diameter enlarging portions 10, and the lift distances L where the flame is generated become shorter in the order of C8, C3 and C0. From the position subsequent to generation of the flame, the respective flow velocities of the combustion gas are increasing to a set value.
  • the inner diameter enlarging portion 10 with larger enlargement of the inner diameter makes the lift distance of the flame shorter, indicating the fact that the flame is approaching the lower end of the premixing tube 3 (or the top portion of the combustion cylinder 2).
  • FIG. 8A to 8C An example of a structure of an inner diameter enlarging portion 30 for a gas turbine combustor according to a second embodiment will be described referring to Figs. 8A to 8C .
  • Figs. 8A to 8C show a circumferential surface portion 31 with a fan-shape cross section, having a predetermined radius at the center angle of 90° as a curved portion on an inner circumferential edge of the inner diameter enlarging portion 30.
  • Fig. 8A represents the circumferential surface portion with a radius of 30 mm
  • Fig. 8B represents the circumferential surface portion with a radius of 20 mm
  • Fig. 8C represents the circumferential surface portion with a radius of 10 mm, respectively.
  • Each of the respective portions is attached to the open end of the protruding wall 7 of the premixing tube 3 so as to be continued with the inner circumferential surface of the protruding wall 7, and to serve as the inner diameter enlarging portion 30 to expand the inner diameter toward the combustion cylinder 2 in the downward direction.
  • It may be attached using an arbitrary method. As described in the first embodiment, it may be detachably fixed using the bolt or may be welded (not specifically shown). The inner diameter enlarging portion 30 may be replaced in spite of welding.
  • This embodiment provides the same effects as those described in the first embodiment.
  • This embodiment employs the circumferential surface portion 31 with a fan-like cross-section of a predetermined radius as the curved portion. However, such portion may be formed to have a curved surface that expands the inner diameter toward the combustion cylinder 2 in the downward dimension.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12194055.5A 2012-11-23 2012-11-23 Gasturbinenbrennkammer Active EP2735798B1 (de)

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EP12194055.5A EP2735798B1 (de) 2012-11-23 2012-11-23 Gasturbinenbrennkammer

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EP2735798A1 true EP2735798A1 (de) 2014-05-28
EP2735798B1 EP2735798B1 (de) 2020-07-29

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5592819A (en) * 1994-03-10 1997-01-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Pre-mixing injection system for a turbojet engine
EP0833105A2 (de) * 1996-09-30 1998-04-01 Abb Research Ltd. Vormischbrenner
US5735681A (en) 1993-03-19 1998-04-07 The Regents, University Of California Ultralean low swirl burner
US5879148A (en) 1993-03-19 1999-03-09 The Regents Of The University Of California Mechanical swirler for a low-NOx, weak-swirl burner
US6572366B2 (en) * 2001-06-09 2003-06-03 Alstom (Switzerland) Ltd Burner system
JP2009198054A (ja) 2008-02-20 2009-09-03 Niigata Power Systems Co Ltd ガスタービン燃焼器
US20110265482A1 (en) * 2010-04-28 2011-11-03 Nishant Govindbhai Parsania Pocketed air and fuel mixing tube

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3940705B2 (ja) * 2003-06-19 2007-07-04 株式会社日立製作所 ガスタービン燃焼器及びその燃料供給方法
EP2685161B1 (de) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Brenneranordnung, insbesondere für eine Gasturbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5735681A (en) 1993-03-19 1998-04-07 The Regents, University Of California Ultralean low swirl burner
US5879148A (en) 1993-03-19 1999-03-09 The Regents Of The University Of California Mechanical swirler for a low-NOx, weak-swirl burner
US5592819A (en) * 1994-03-10 1997-01-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Pre-mixing injection system for a turbojet engine
EP0833105A2 (de) * 1996-09-30 1998-04-01 Abb Research Ltd. Vormischbrenner
US6572366B2 (en) * 2001-06-09 2003-06-03 Alstom (Switzerland) Ltd Burner system
JP2009198054A (ja) 2008-02-20 2009-09-03 Niigata Power Systems Co Ltd ガスタービン燃焼器
US20110265482A1 (en) * 2010-04-28 2011-11-03 Nishant Govindbhai Parsania Pocketed air and fuel mixing tube

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