EP0228091A2 - In axialer Richtung kompakter Gasturbinenbrenner und Verfahren zu seiner Kühlung - Google Patents

In axialer Richtung kompakter Gasturbinenbrenner und Verfahren zu seiner Kühlung Download PDF

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Publication number
EP0228091A2
EP0228091A2 EP86118098A EP86118098A EP0228091A2 EP 0228091 A2 EP0228091 A2 EP 0228091A2 EP 86118098 A EP86118098 A EP 86118098A EP 86118098 A EP86118098 A EP 86118098A EP 0228091 A2 EP0228091 A2 EP 0228091A2
Authority
EP
European Patent Office
Prior art keywords
burner
air
injection end
combustion
wall
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.)
Withdrawn
Application number
EP86118098A
Other languages
English (en)
French (fr)
Other versions
EP0228091A3 (de
Inventor
George D. Lewis
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.)
Kongsberg Gruppen ASA
Original Assignee
Kongsberg Vapenfabrikk AS
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 Kongsberg Vapenfabrikk AS filed Critical Kongsberg Vapenfabrikk AS
Publication of EP0228091A2 publication Critical patent/EP0228091A2/de
Publication of EP0228091A3 publication Critical patent/EP0228091A3/de
Withdrawn legal-status Critical Current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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/06—Disposition of air supply not passing through burner for heating the incoming air

Definitions

  • This invention relates to gas turbine burners, particularly burners for gas turbines which are intended for vehicular applications.
  • Gas turbine burners for supplying hot combustion gases to the turbine component are known. These burners typically mix pressurized air with fuel injected through nozzles in a cylindrical or annular-shaped combustion chamber, combust the mixture, and dilute the combustion gases with additional pressurized air to achieve a desired gas temperature prior to admission to the turbine. To maintain combustion chamber wall temperatures at an acceptable level, these burners typically inject pressurized air along the inside of the combustion chamber wall to provide an insulating cooling film.
  • film cooling can degrade burner performance by causing uneven burner exit temperature patterns, as would be understood by one skilled in the art.
  • pressurized air must be injected within the burner for mixing with fuel for combustion. It is difficult to intermix air and fuel for combustion and dilute the resulting combustion products, without a relatively lengthy burner chamber.
  • the present invention overcomes the problems of the prior art and achieves the objects listed above by means of an entirely convectively cooled gas turbine burner having low hot gas axial velocities and a novel cooling air flow pattern.
  • the burner apparatus invention as embodied and as broadly described herein, for combusting fuel and for supplying hot combustion gases to a turbine component comprises a burner chamber having an injection end, an exit end, and a burner wall extending axially therebetween,
  • the conveying means including ducting means for decreasing the temperature, and increasing the mass flow rate, of the combustion air used to convectively cool the portion of the burner wall adjacent the injection end of the burner chamber, and the ducting means including a longitudinal member concentrically surrounding the burner wall and sealingly attached at one end thereof to the burner wall at a location between the exit end and the injection end.
  • the longitudinal member is spaced from the burner wall from the location of the sealing attachment to the injection end, and the flow of the compressed air used for cooling is in the direction toward the injection end over the burner wall portion between the exit end and the attachment location, and in the direction away from the injection end for the burner wall portion between the attachment location and the injection end.
  • the burner apparatus further includes means for directing air from the space between the longitudinal member and the burner wall into the burner chamber to provide secondary air flow, the directing means including two series of apertures, the series being axially spaced from one another and from the injection end and dividing the burner chamber into three functionally ; distinct areas, namely, a primary area proximate the injection end providing for diffusion and expansion of the air-fuel mix- ture, a secondary area axially adjacent the primary area for mixing the air-fuel mixture with a part of the air from the secondary air of the air-fuel mixture, and a tertiary area axially adjacent the secondary area for diluting combustion gases formed in the secondary area with another part of the air from the secondary air flow.
  • the directing means including two series of apertures, the series being axially spaced from one another and from the injection end and dividing the burner chamber into three functionally ; distinct areas, namely, a primary area proximate the injection end providing for diffusion and expansion of the air-fuel mix- ture, a secondary area
  • the primary area and the secondary area contain a weight ratio of fuel to air of about 9.5% and about 5.5%, respectively, and that the combustion gases flow along the axis of the burner chamber between about 125 to about 175 feet per second.
  • the convectively cooled gas turbine burner apparatus diffusion zone between the injection end and the proximate one of the two series of apertures has an axial length of about 60% to about 120% of the diameter of the burner chamber, and that the mixing and combustion zone between the two series of apertures has an axial length of about 30% of the diameter of the burner chamber.
  • the method for convectively cooling an axially compact gas turbine burner having a longitudinal burner wall with an injection end, an exit end, and with the combustion gas flow direction being generally from the injection end axially toward the exit end, and with the burner having a source of combustion air proximate the exit end comprises the steps of flowing the combustion air along the burner wall in a direction counter to the combustion gas flow direction, from the exit end to a point intermediate the exit and the injection end; directing the combustion air away from the burner wall and toward the injection end; and flowing at least part of the combustion air back along the burner wall in a direction concurrent with the combustion gases, from the injection end to the intermediate point.
  • the method includes the further step of directing the concurrent combustion air flow through the burner wall for use as secondary air.
  • the Figure is a schematic cross-sectional view of a convectively cooled gas turbine burner made in accordance with the present invention.
  • Burner 10 includes a generally cylindrical inner casing 12 defining a burner chamber 14 which is convectively cooled by air used for combustion as will be described in greater detail hereinafter and has a fuel injection end 16 and an exit end 18.
  • An outer casing 20 substantially envelops the inner casing 12, as well as the injection end 16 of the burner chamber 14.
  • Means are provided for injecting fuel within the burner chamber at injection end 16, to be discussed in detail henceforth.
  • means are provided for admitting air within the burner chamber 14 for combustion as also will be discussed henceforth.
  • the present invention is directed to a convectively cooled gas turbine burner for combusting fuel and air.
  • the burner includes means for conveying air along the external periphery of at least a substantial portion of the burner chamber.
  • the conveying means include a passageway 22 formed between inner casing 12 and outer casing 20.
  • a longitudinal member 24 is attached to the outer surface 26 of the inner casing 12 and is formed between the outer casing 20 and the inner casing 12.
  • the annular longitudinal member 24 defines a second passageway 28 between the longitudinal member 24 and the outer casing 20, as well as a third passageway 30 between the longitudinal member 24 and the inner casing 12.
  • the flow of air, as denoted by arrows A is directed into the first passageway 22, the second passageway 28 and, then, either to a third passageway 30 or to a plenum 32 at the injection end of the burner chamber 14.
  • the flow of air within the first and third passageways 22, 30 along the inner casing 12 convectively cools the heat from combustion generated within the burner chamber 14.
  • the burner includes means for admitting a primary flow of air within the burner chamber for combustion.
  • the burner 10 includes an arrangement of spaced and slanted curvilinear vanes for admitting air within the burner chamber from the plenum 32. The air passes through the vanes 34 in a swirling motion within an angle of about 42° to about 52° relative to the axis X of the burner chamber 14.
  • the burner 10 includes means proximate the injection end for injecting fuel into the burner chamber for mixing with the primary air flow.
  • the fuel injection means may be any conventional gas turbine fuel injection apparatus providing a fuel spray, preferably at an angle greater than about 100°, that is greater than about 50° to either side of the burner axis X.
  • An acceptable injection unit is one manufactured by Excello Corporation and is depicted in the Figure.
  • the injection means thus includes a fuel injection unit 36 mounted on the outer casing 20 and having a radial fuel inlet 37 (shown with screen filter).
  • the fuel injection upit 36 further includes a housing 38 having an inner and outer air passage 40, 42.
  • annular fuel channel 44 Interposed between inner and outer air supply passages 40, 42 (which have swirlers - not shown) is an annular fuel channel 44 preferably concentrically positioned between the inner and outer air supply passages 40, 42, and interconnected with inlet 37.
  • a smooth, thin sheet of film forms on the wall of channel 44 and then is broken into a spray by the swirling air streams from passages 40, 42.
  • the housing 38 includes a series of spaced circumferential slots 50 for admitting air to inner passage 40.
  • slots 50 have an angle of at least about 42° relative to the axis X of the burner chamber 14.
  • the burner 10 includes means connected to the conveying means for directing a secondary flow of air within the burner chamber 14.
  • the means for directing a secondary flow of air within the burner chamber 14 include at least two series of apertures 60 and 62 spaced about the circumference of the inner casing 12 along the third passageway 30.
  • air passing through the second passageway 28 and into plenum 32 provides a primary flow of air within the burner chamber 14.
  • Air passing into the third passageway 30 and through either apertures 60 or apertures 62 provide a secondary flow of air into the burner chamber 14.
  • Air flow is directed into the first passageway 22 by a compressor or similar means at an air velocity of 200 feet per second, which provides a reasonable wall temperature without an unacceptable pressure loss; however, a velocity of 100 to 150 feet per second may be adequate. If a lower wall temperature is desired, the air velocity can be increased or fins (not shown) may be affixed to the outer surface 26 of the inner casing 12 in the first passageway 22 and in the third passageway 30.
  • the air flows from the first passageway 22 into a second passageway 28, which is defined by the outer casing 20 and the longitudinal member 24, the latter member being sized to provide the desired cooling air velocity of about 200 ft/sec of air passing within passageway 30, and the former member being positioned so that the air is conveyed to the burner chamber 14 without creating a significant pressure loss.
  • the fuel injection unit 36 receives air and fuel through an inner and outer air passage 40, 42 and fuel channel 44, respectively.
  • the direction and magnitude of the swirl imparted to the lair passed through fuel injection unit 36 is similar to that im- parted by the vanes 34 to the primary air flow into the burner I chamber 14. It is noted, however, that the swirl of the air through fuel injection unit 36 may be greater than an angle of about 52° relative to the axis of the burner chamber 14, though the relative angle may not be less than about 42°.
  • the secondary flow of air into the burner chamber 14 is pas- i sed through the apertures 60 and 62 adjacent the third passageway 30.
  • the two series of apertures 60 and 62 divide the burner chamber 14 into three functionally distinct, axially adjacent areas, namely, a primary area I between apertures 60 and the injection end 16 that enabled mixing and expansion of the air-fuel mixture, a secondary area II adjacent the primary area I and lying between apertures 60 and apertures 62 that allows further mixing and combustion of the air-fuel mixture, and a tertiary area III adjacent the secondary area II and downstream of apertures 62 that allows dilution of the air-fuel mixture.
  • the air not used in the combustion process is added to lower the gas temperature to the desired temperature for entering the turbine within the dilution zone.
  • the weight ratio of fuel to air mixture in the primary area I is about 9.5%, whereas the ratio corresponding to the secondary area II is about 5.5% at design oper- ! ation conditions.
  • the primary area I defined by the axial position of the series of apertures 60 has a length of not less than 60% and not more than 120% of the burner-diameter.
  • the axial position of the series of apertures 62 is not less than 30% the burner diameter downstream of apertures 60.
  • the resultant axial velocity of hot gases within the burner chamber 14 is between about 125 to 175 feet per second and preferably about 150 feet per second.
  • the relatively low axial velocity of the hot gas, in conjunction with the secondary flow of air through the apertures 60 and 62 allows rapid and efficient mixing of the primary and secondary flows of air. Hence, only a relatively short burner chamber is required.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP86118098A 1986-01-03 1986-12-29 In axialer Richtung kompakter Gasturbinenbrenner und Verfahren zu seiner Kühlung Withdrawn EP0228091A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US81590986A 1986-01-03 1986-01-03
US815909 1986-01-03

Publications (2)

Publication Number Publication Date
EP0228091A2 true EP0228091A2 (de) 1987-07-08
EP0228091A3 EP0228091A3 (de) 1988-08-24

Family

ID=25219159

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86118098A Withdrawn EP0228091A3 (de) 1986-01-03 1986-12-29 In axialer Richtung kompakter Gasturbinenbrenner und Verfahren zu seiner Kühlung

Country Status (2)

Country Link
EP (1) EP0228091A3 (de)
JP (1) JPS62217019A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0669500A1 (de) * 1994-02-18 1995-08-30 ABB Management AG Verfahren zur Kühlung einer selbstzündenden Brennkammer
EP0754917A3 (de) * 1995-07-19 1999-04-14 Tokai Corporation Brenngerät für Feuerzeug
EP0930462A3 (de) * 1998-01-15 2000-01-12 Clemm v. Hohenberg, Eberhard Flammrohrausbildung für Brenner
CN107013912A (zh) * 2017-05-31 2017-08-04 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 自冷却引射式燃烧器
CN107062223A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 点火喷嘴装置
WO2018218526A1 (zh) * 2017-05-31 2018-12-06 深圳智慧能源技术有限公司 点火喷嘴装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1892474A1 (de) * 2006-08-23 2008-02-27 Siemens Aktiengesellschaft Brenner mit einem Schutzelement für Zündelektroden
JP2015135212A (ja) * 2014-01-17 2015-07-27 ヤンマー株式会社 ガスタービンエンジン

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
EP0066570B1 (de) * 1980-12-12 1984-04-25 Volvo Flygmotor Ab Hochtemperaturbrenner
GB2124747A (en) * 1982-07-23 1984-02-22 Heung Duk Dan A gas turbine combustion system
JPS59229114A (ja) * 1983-06-08 1984-12-22 Hitachi Ltd ガスタ−ビン用燃焼器

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0669500A1 (de) * 1994-02-18 1995-08-30 ABB Management AG Verfahren zur Kühlung einer selbstzündenden Brennkammer
EP0754917A3 (de) * 1995-07-19 1999-04-14 Tokai Corporation Brenngerät für Feuerzeug
EP0930462A3 (de) * 1998-01-15 2000-01-12 Clemm v. Hohenberg, Eberhard Flammrohrausbildung für Brenner
CN107013912A (zh) * 2017-05-31 2017-08-04 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 自冷却引射式燃烧器
CN107062223A (zh) * 2017-05-31 2017-08-18 深圳智慧能源技术有限公司 点火喷嘴装置
WO2018218526A1 (zh) * 2017-05-31 2018-12-06 深圳智慧能源技术有限公司 点火喷嘴装置
CN107062223B (zh) * 2017-05-31 2023-08-18 深圳智慧能源技术有限公司 点火喷嘴装置
CN107013912B (zh) * 2017-05-31 2023-09-19 深圳智慧能源技术有限公司 自冷却引射式燃烧装置
CN107062225B (zh) * 2017-05-31 2023-09-19 深圳智慧能源技术有限公司 自冷却引射式燃烧器

Also Published As

Publication number Publication date
EP0228091A3 (de) 1988-08-24
JPS62217019A (ja) 1987-09-24

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