EP0178820A1 - Chambre de combustion de turbine à gaz refroidie par jet heurtant la paroi et avec refroidissement interne par film - Google Patents

Chambre de combustion de turbine à gaz refroidie par jet heurtant la paroi et avec refroidissement interne par film Download PDF

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Publication number
EP0178820A1
EP0178820A1 EP85307034A EP85307034A EP0178820A1 EP 0178820 A1 EP0178820 A1 EP 0178820A1 EP 85307034 A EP85307034 A EP 85307034A EP 85307034 A EP85307034 A EP 85307034A EP 0178820 A1 EP0178820 A1 EP 0178820A1
Authority
EP
European Patent Office
Prior art keywords
side wall
wall members
combustor
upstream
row
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Withdrawn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
EP85307034A
Other languages
German (de)
English (en)
Inventor
Edward Wayne Tobery
Ronald Joseph Kuznar
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of EP0178820A1 publication Critical patent/EP0178820A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Definitions

  • This invention relates to gas turbine combustors, and in particular to a combustor construction that provides both impingement and film cooling for the combustor wall.
  • Gas turbine combustor wall temperatures are maintained at or below design values by a combination of external convection and internal film convection.
  • the external cooling of the combustor is the result of the shell air passing over the external faces of the combustor walls before entering the combustor as nozzle air, primary and dilution air, and film cooling air.
  • the average heat transfer coefficient is relatively small, such as less than 100 BTU/hr.-ft. 2 -°F, (568 W/m 2- K) and with even smaller values at some localized areas.
  • Most of the heat load is removed by the film cooling, which results in a heat transfer coefficient at least three times that of the noted average.
  • An object of this invention is to further improve wall cooling of the combustor by increasing the external cooling while maintaining a high level of internal film cooling.
  • a gas turbine combustor comprises a tubular side wall, the side wall formed by a succession of tubular side wall members disposed in a telescopic arrangement spacer means for supporting an outwardly located upstream end portion of each of said side wall members outwardly of and relative to an inwardly located downstream end portion of the adjacent upstream side wall member to provide an annular coolant air admission slot between the end portions of the side wall members, characterized by the downstream end portions of the side wall members having a tubular lip extending downstream from the downstream end of the spacer means, the combustor including a cylindrical jacket encompassing the upstream one of said side wall members and at least a plurality of successive downstream side wall members, said jacket including at least one row of circumferentially closely spaced impingement ports for each side wall member, said at least one row being located in an axial direction closely upstream of said annular coolant air admission slot to provide impingement air cooling upon the relatively hotter portion of said side wall members relatively far downstream from the next upstream annular air admission
  • the cylindrical jacket encompassing the upstream portion of the side wall is formed by a plurality of successive side wall members in a telescopic arrangement, with the jacket including at least one row of circumferentially closely spaced impingement ports for each of the side wall members, with at least one row being located in an axial direction closely upstream of the annular coolant air admission slots formed at the joints of the side wall members to provide impingement air cooling upon the relatively hotter portions of the side wall members relatively far downstream from the next upstream annular air admission slot, this impingement cooling occurring before the air passes through the annular air slots into the combustor proper.
  • Figure 1 shows a combustor proper and includes the upstream dome 10 and a series of successively downstream side wall members denoted 12, 14, 16, 18, 20, and 22 which together form the side wall of the cylindrical combustor.
  • the side wall members are basically arranged in telescopic relation with the upstream margin of each side wall member, as at 14a, overlapping the downstream portion, as at 12b, of the radially inner successive upstream side wall member 12.
  • spacer means 24 which may conveniently take the form of a corrugated band, is interposed between the parts 14a and 12b of the successive side wall members. Since the band is disposed so that the crests and valleys extend axially, an air admission slot 26 is provided.
  • the band 24 projects upstream farther than the portion 14a of the side wall member 14, and the downstream portion 12b of the side wall member 12 includes a lip 12c projecting farther downstream than the downstream end of the band 24.
  • Fuel is fed through means not shown to the upstream portion 28 (Fig. 1) of the combustor and is mixed with combustion air delivered to the interior of the combustor through primary air scoops 30 and 32.
  • the hot mixture flows in the downstream direction as indicated by the directional arrow in Figure 1 with dilution air being introduced into the more downstream portion of the combustor through the dilution scoops 34.
  • the quantity of primary air required for combustion is basically fixed according to the particular combustion conditions.
  • the other two quantities of air which enter the combustor are the cooling air and the dilution air.
  • cooling air the quantity of air required for combustion is increased and this is considered desirable.
  • a cylindrical jacket 36 (Fig. 1) encompasses the upstream side wall member 12 and at least a plurality of successive downstream side wall members, in this case at least 14, 16, and a portion of 18. Rows of circumferentially closely spaced impingement ports are provided in the jacket to admit cooling air into the annular space between the jacket and combustor proper. In the currently preferred embodiment, two axially spaced rows are provided to accommodate each annular air admission slot, although the number of rows and holes per row can be different in accordance with the temperature level required. As best seen in Figure 2, the rows are identified by the numerals 38, 39, 40, 41, 42, 43, 44, and 45.
  • the axial location of the downstream row of each set of two rows is important in carrying out the invention.
  • the reason for this is that the film cooling effect upon the side wall members is better in the vicinity of the annular air admission slots before the integrity of the film is dissipated to a degree and, accordingly, the hotter portions of the side wall members are in the vicinity closely upstream from the annular air admission slot as in the location designated 16c in Figure 1.
  • the row of holes 43 is located, in an axial direction, closely upstream of the annular slot formed between the side wall members 16 and 18.
  • the other row of holes 42 of the set 42 and 43 is located, in an axial direction, again only slightly upstream of the row 43 to ensure that the portion of the side wall member between the film cooling area and the next successive annular slot downstream will be adequately cooled. After the air entering the impingement ports has impinged upon the respective facing side wall members, this air then flows to the annular air admission slots and flows into the combustor proper performing its film cooling function.
  • the downstream end 48 of the cooling jacket is upstream from the annular air admission slot formed between the side wall members 18 and 20. While the jacket could extend further downstream in an axial direction, at this point in the combustor the cooling problems are not as great as farther upstream in the primary zone. However, it is considered preferable that the row of holes 45 be inclined to direct the impingement air toward the corner formed between the end wall 48 of the jacket, and the side wall member 18. The air which impinges through the holes 44 and 45 against side wall member 18 must flow upstream within the annular space between the jacket and combustor proper and will enter the combustor through the annular slot between side wall members 16 and 18. Thus, there will be a tendency for the cooling air entering the farther upstream impingement ports to also have a component of air flowing upstream to the next upstream annular slot.
  • the arrangement as described is intended to utilize, to the degree possible, the cooling air most effectively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Spray-Type Burners (AREA)
EP85307034A 1984-10-04 1985-10-02 Chambre de combustion de turbine à gaz refroidie par jet heurtant la paroi et avec refroidissement interne par film Withdrawn EP0178820A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US65755484A 1984-10-04 1984-10-04
US657554 1984-10-04

Publications (1)

Publication Number Publication Date
EP0178820A1 true EP0178820A1 (fr) 1986-04-23

Family

ID=24637675

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85307034A Withdrawn EP0178820A1 (fr) 1984-10-04 1985-10-02 Chambre de combustion de turbine à gaz refroidie par jet heurtant la paroi et avec refroidissement interne par film

Country Status (6)

Country Link
EP (1) EP0178820A1 (fr)
JP (1) JPS6186519A (fr)
KR (1) KR860003469A (fr)
CN (1) CN85107191A (fr)
IT (1) IT1185959B (fr)
MX (1) MX161443A (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19547703A1 (de) * 1995-12-20 1997-07-03 Mtu Muenchen Gmbh Brennkammer, insbesondere Ringbrennkammer, für Gasturbinentriebwerke
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
US7975487B2 (en) 2006-09-21 2011-07-12 Solar Turbines Inc. Combustor assembly for gas turbine engine
CN105042640A (zh) * 2015-08-11 2015-11-11 南京航空航天大学 航空发动机燃烧室火焰筒的冷却结构
EP3037726A1 (fr) * 2014-12-22 2016-06-29 Alstom Technology Ltd Alimentations séparées de l'air de refroidissement et de dilution
EP2989389B1 (fr) * 2013-04-25 2018-08-01 Ansaldo Energia Switzerland AG Combustion séquentielle avec gaz de dilution
US10502423B2 (en) 2012-10-24 2019-12-10 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100395643B1 (ko) * 2000-10-04 2003-08-21 한국기계연구원 가스터빈 연소기
US8448443B2 (en) * 2007-10-11 2013-05-28 General Electric Company Combustion liner thimble insert and related method
JP2011102669A (ja) 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及びガスタービン
US8707673B1 (en) * 2013-01-04 2014-04-29 General Electric Company Articulated transition duct in turbomachine
FR3037107B1 (fr) * 2015-06-03 2019-11-15 Safran Aircraft Engines Paroi annulaire de chambre de combustion a refroidissement optimise
EP3478941B1 (fr) * 2016-08-30 2021-02-24 Siemens Energy Global GmbH & Co. KG Élement de refroissement par impact d'une turbine à gaz
CN110185554B (zh) * 2019-03-08 2021-09-10 西北工业大学 一种用于喷气发动机矢量喷管的双层壁冷却结构
CN110107914A (zh) * 2019-04-10 2019-08-09 南京航空航天大学 一种基于三角形截面导流板（环）的冲击-气膜冷却结构
CN113464283B (zh) * 2021-08-10 2022-10-21 南京航空航天大学 一种旋转爆震发动机复合主动冷却结构及旋转爆震发动机
CN113739208B (zh) * 2021-09-09 2022-08-26 成都中科翼能科技有限公司 一种用于低污染燃气轮机的混合冷却火焰筒

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US4109459A (en) * 1974-07-19 1978-08-29 General Electric Company Double walled impingement cooled combustor
GB2095816A (en) * 1981-03-27 1982-10-06 Westinghouse Electric Corp Gas turbine combustor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US4109459A (en) * 1974-07-19 1978-08-29 General Electric Company Double walled impingement cooled combustor
GB2095816A (en) * 1981-03-27 1982-10-06 Westinghouse Electric Corp Gas turbine combustor

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19547703A1 (de) * 1995-12-20 1997-07-03 Mtu Muenchen Gmbh Brennkammer, insbesondere Ringbrennkammer, für Gasturbinentriebwerke
DE19547703C2 (de) * 1995-12-20 1999-02-18 Mtu Muenchen Gmbh Brennkammer, insbesondere Ringbrennkammer, für Gasturbinentriebwerke
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
US7975487B2 (en) 2006-09-21 2011-07-12 Solar Turbines Inc. Combustor assembly for gas turbine engine
US10502423B2 (en) 2012-10-24 2019-12-10 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas
EP2989389B1 (fr) * 2013-04-25 2018-08-01 Ansaldo Energia Switzerland AG Combustion séquentielle avec gaz de dilution
EP3037726A1 (fr) * 2014-12-22 2016-06-29 Alstom Technology Ltd Alimentations séparées de l'air de refroidissement et de dilution
US10443849B2 (en) 2014-12-22 2019-10-15 Ansaldo Energia Switzerland AG Separate feedings of cooling and dilution air
CN105042640A (zh) * 2015-08-11 2015-11-11 南京航空航天大学 航空发动机燃烧室火焰筒的冷却结构
CN105042640B (zh) * 2015-08-11 2018-05-08 南京航空航天大学 航空发动机燃烧室火焰筒的冷却结构

Also Published As

Publication number Publication date
JPH0317045B2 (fr) 1991-03-07
MX161443A (es) 1990-09-27
JPS6186519A (ja) 1986-05-02
CN85107191A (zh) 1986-09-24
KR860003469A (ko) 1986-05-26
IT1185959B (it) 1987-11-18
IT8522315A0 (it) 1985-09-30

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Inventor name: TOBERY, EDWARD WAYNE

Inventor name: KUZNAR, RONALD JOSEPH