EP0049190A1 - Vorrichtung zur Luftfilmkühlung für das Flammrohr eines Gasturbinentriebwerks - Google Patents

Vorrichtung zur Luftfilmkühlung für das Flammrohr eines Gasturbinentriebwerks Download PDF

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Publication number
EP0049190A1
EP0049190A1 EP19810401447 EP81401447A EP0049190A1 EP 0049190 A1 EP0049190 A1 EP 0049190A1 EP 19810401447 EP19810401447 EP 19810401447 EP 81401447 A EP81401447 A EP 81401447A EP 0049190 A1 EP0049190 A1 EP 0049190A1
Authority
EP
European Patent Office
Prior art keywords
flame tube
wall
slot
downstream
internal
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
EP19810401447
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English (en)
French (fr)
Other versions
EP0049190B1 (de
Inventor
Jean Robert Bedue
Jacques Emile Jules Caruel
Philippe Marc Denis Gastebois
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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.)
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0049190A1 publication Critical patent/EP0049190A1/de
Application granted granted Critical
Publication of EP0049190B1 publication Critical patent/EP0049190B1/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
    • F23R3/04—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

  • the invention relates to an air film cooling device for a flame tube of a gas turbine engine, said device forming an annular connection piece, between a downstream section and an upstream section of the flame tube, comprising an external wall. and an internal wall delimiting between them a chamber fed in the radial direction by at least one row of orifices made in the internal wall, the internal wall delimiting with the external wall an annular outlet slot through which an air film flows cooling and insulation of the internal wall of the downstream section of the flame tube.
  • the flame tube which extends the combustion chamber, is subjected to a significant heat flow since it is there that the combustion phenomenon of the air fuel mixture occurs in the chamber. It is therefore necessary to cool the flame tube and, to do this, air taken from the high pressure flow is introduced into the tube, so as to form an air film or film on the wall of the tube. in order to remove it from the direct action of the flame and to cool it.
  • French patent 1,432,316 describes an annular connection piece between two sections of flame tube.
  • the piece is made up of two spaced concentric rings.
  • the inner ring is connected or is part of the upstream tube portion, while the outer ring is part of the downstream tube portion.
  • the upstream end of the outer ring is connected to the inner ring by an annular flange radial.
  • Axially directed air inlet holes are provided in this rim, others, directed radially, are provided in the outer ring.
  • the free end of the inner ring is inclined towards the outer ring so as to form a slit through which the cooling air flows.
  • French patent 1,510,874 presents a device comprising only radial orifices which have the main function of allowing the adjustment of the flow rate of the cooling fluid.
  • the short, rigid tongue protects the ports against hot interior fluid and generates the desired film of cooling air.
  • One of the essential concerns in the realization of the tongue seems to have been to decrease its length, in order to avoid temperature gradients. Axial slots eventually allow it to expand.
  • the invention aims to achieve impact cooling on the tongue and to obtain a cooling film whose flow rate is perfectly controlled.
  • Cooling is obtained by radial jets which, to be effective, must retain their radial kinetic energy, without this being reduced or even eliminated by excessive axial movement in the area of these jets.
  • the axial speed in the area of the radial jets must therefore be as low as possible.
  • the known devices all have an adjustment at the input of the film feed rate.
  • the invention makes this adjustment in the outlet slot by a judicious staging of the flow velocities, which makes it possible to choose the height of the chamber, arranged upstream of the slot, to obtain a real impact effect on the tongue exposed to hot gases.
  • the mode of formation of the cooling film allows the use of the device according to the invention in flame tubes of constant diameter or not by modification of the position of the upstream wall.
  • the device according to the invention is remarkable in that the external and internal walls each have a cylindrical portion extending longitudinally, said portions being coaxial and spaced from each other, the cylindrical portion of the external wall being connected in downstream by a conical portion to the downstream section of the flame tube, the cylindrical portions of the outer walls. and internal being connected upstream by at least an approximately conical portion to the upstream section of the flame tube.
  • the air film cooling device (Fig. 1,2) according to the invention forms an annular connection piece between a downstream section 1 and an upstream section 2 of the flame tube, to which it is welded in 3 and 4 by through cylindrical connection portions 5, 6 of diameter corresponding to the diameter of the sections of the flame tube.
  • the device also consists of an external wall 7 and an internal wall 8 delimiting between them an annular chamber 9.
  • the external wall carries radial orifices 10 arranged along the guidelines of the wall 7.
  • the wall 7 carries two rows 11, 12 of orifices, but their number can go up to 4. In each row the orifices are equidistant.
  • the orifices are offset peripherally from one row to the next row.
  • the inner wall 8 defines with the outer pardi 7 an annular outlet slot 13 through which the film of cooling air and insulation from the wall of the downstream section 1 of the flame tube flows.
  • the outer wall 7 and the inner wall 8 each have a cylindrical portion 14 'and 15 respectively. These portions are coaxial and are spaced from each other.
  • the cylindrical portion 14 of the outer wall 7 is connected downstream by a conical portion 16 to the downstream section 1 of the flame tube via the cylindrical connection portion 5.
  • FIG. 2 represents three possible positions (in line solid, broken line and dashed line) of the upstream wall 2 depending on whether the other sections to be connected to the flame tube are of the same or different diameters.
  • the internal wall 8 is connected by an approximately conical portion to the section 2.
  • this section is of smaller diameter, it is the external wall which is connected to it by a portion approximately conical.
  • each wall is connected by an approximately conical portion.
  • the internal wall 8, in its cylindrical part 15, is extended to form, with the cylindrical portion 5 of connection to the downstream section 1 of the flame tube, the slot 13, being in the form of an annular channel whose width is less than the length 'L.
  • the chamber 9 is se-. adorned in several sectors by longitudinal reinforcements 20 which make it possible to maintain rigorous dimensions of the chamber and of the annular channel, and in particular the height of the chamber and the width of the channel.
  • FIG. 3 makes it possible to understand the aerodynamic operation of the device.
  • the film 21 is supplied by the air jets which penetrate radially into the chamber 9.
  • the jets which strike the internal surface of the internal wall 8 exposed to hot gases 19, by impact effect promote its cooling.
  • the flow from the jets engages in the converging 22, formed of the conical part 16, whose role is, by accelerating it, to promote its mixing, therefore to attenuate the wakes of the reinforcements.
  • the convergent ends in a slot 13 in the form of an annular channel, the length of which must be sufficient to obtain a correct speed profile at the outlet in the flame tube.
  • the internal wall 8, delimiting the slot has at its downstream part and up to the free edge, an outer bevel portion.
  • This bevel makes it possible to reduce the wake at the outlet of the slot.
  • the thickness e of the free edge of the wall 8 is less than half the width h of the slot.
  • the height H of the chamber 9 is equal to or greater than twice the width h of the slot 13; the projected length c of the conical portion 16 between the cylindrical outer wall 14 and the downstream section of the flame tube 5 is equal to or greater than 1.2 times the height H of the chamber; the length L of the annular channel of the slot 13 is equal to or greater than 2 times the width h of the slot; and the diameter of the orifices 10 is equal to or less than 0.5 times the width h of the slot.
  • the width of the slot can be less than a millimeter.
  • the use of multiple rows of holes provides sufficient supply of the chamber, without weakening the connecting structure.
  • the first row sends radial jets into a chamber where the local axial speed is low since there will be approximately 1/3 of the axial speed at the exit of the converging front chamber. The impact will therefore be better for the first row which corresponds precisely to the part of the internal wall that needs to be best cooled.
  • the device according to the invention provides a solution to the cooling by air film of small diameter flame tubes in which the pressure is high.

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)
  • Shaping By String And By Release Of Stress In Plastics And The Like (AREA)
EP19810401447 1980-09-25 1981-09-17 Vorrichtung zur Luftfilmkühlung für das Flammrohr eines Gasturbinentriebwerks Expired EP0049190B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8020558 1980-09-25
FR8020558A FR2490728A1 (fr) 1980-09-25 1980-09-25 Dispositif de refroidissement par film d'air pour tube a flamme de moteur a turbine a gaz

Publications (2)

Publication Number Publication Date
EP0049190A1 true EP0049190A1 (de) 1982-04-07
EP0049190B1 EP0049190B1 (de) 1984-03-28

Family

ID=9246269

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810401447 Expired EP0049190B1 (de) 1980-09-25 1981-09-17 Vorrichtung zur Luftfilmkühlung für das Flammrohr eines Gasturbinentriebwerks

Country Status (4)

Country Link
EP (1) EP0049190B1 (de)
JP (1) JPS5781130A (de)
DE (1) DE3162895D1 (de)
FR (1) FR2490728A1 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526083A1 (fr) * 1982-05-03 1983-11-04 Gen Electric Moteur a bouts d'aubes de turbine refroidis
US4566280A (en) * 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US4723413A (en) * 1985-11-19 1988-02-09 MTU Munuch, GmbH Reverse flow combustion chamber, especially reverse flow ring combustion chamber, for gas turbine propulsion units, with at least one flame tube wall film-cooling arrangement
FR2604509A1 (fr) * 1986-09-25 1988-04-01 Snecma Procede de realisation d'un film de refroidissement pour chambre de combustion de turbomachine, film ainsi realise et chambre de combustion le comportant
EP1104872A1 (de) * 1999-12-03 2001-06-06 General Electric Company Verfahren zur Verminderung der Wärmebelastung einer Brennkammerwand
US6675582B2 (en) * 2001-05-23 2004-01-13 General Electric Company Slot cooled combustor line
EP2189723A1 (de) * 2008-11-25 2010-05-26 Alstom Technology Ltd Brennkammeranordnung zum Betrieb einer Gasturbine
CN109340824A (zh) * 2018-09-19 2019-02-15 西北工业大学 一种具有凹形冷却槽结构的燃烧室火焰筒壁面
CN113154453A (zh) * 2021-05-06 2021-07-23 中国航发湖南动力机械研究所 一种切向倾斜式环膜发散冷却结构
CN113266849A (zh) * 2021-05-18 2021-08-17 中国航发湖南动力机械研究所 气膜冷却结构及涡轮发动机燃烧室火焰筒

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2519193B2 (ja) * 1990-07-17 1996-07-31 シーメンス アクチエンゲゼルシヤフト 高温ガス誘導用の内側領域を備えた管材、特に炎管
CN113421394B (zh) * 2021-05-31 2022-05-17 义乌市吉龙科技有限公司 一种智能家用燃气全程检测控制系统

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR63025E (fr) * 1951-09-28 1955-07-13 Thomson Houston Comp Francaise Appareils à combustion, brûleurs ou appareils analogues perfectionnés, notamment pour l'alimentation de turbines à gaz
FR1510874A (fr) * 1966-01-19 1968-01-26 Gen Electric Structure de refroidissement, notamment pour chambre de combustion de moteurs à turbines à gaz
FR2112220A3 (de) * 1970-10-01 1972-06-16 Bbc Sulzer Turbomaschinen
FR2217548A1 (de) * 1973-02-12 1974-09-06 Gen Electric
DE2622234A1 (de) * 1975-05-21 1976-12-02 Gen Electric Brennkammerverkleidung
FR2336634A1 (fr) * 1975-12-22 1977-07-22 Gen Electric Fente de refroidissement par film pour chemise de chambre de combustion
GB2023232A (en) * 1978-06-13 1979-12-28 Bbc Brown Boveri & Cie Cooling-air nottle arrangement
GB2036945A (en) * 1978-12-11 1980-07-02 Gen Electric Combustion liner

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR63025E (fr) * 1951-09-28 1955-07-13 Thomson Houston Comp Francaise Appareils à combustion, brûleurs ou appareils analogues perfectionnés, notamment pour l'alimentation de turbines à gaz
FR1510874A (fr) * 1966-01-19 1968-01-26 Gen Electric Structure de refroidissement, notamment pour chambre de combustion de moteurs à turbines à gaz
FR2112220A3 (de) * 1970-10-01 1972-06-16 Bbc Sulzer Turbomaschinen
FR2217548A1 (de) * 1973-02-12 1974-09-06 Gen Electric
DE2622234A1 (de) * 1975-05-21 1976-12-02 Gen Electric Brennkammerverkleidung
FR2336634A1 (fr) * 1975-12-22 1977-07-22 Gen Electric Fente de refroidissement par film pour chemise de chambre de combustion
GB2023232A (en) * 1978-06-13 1979-12-28 Bbc Brown Boveri & Cie Cooling-air nottle arrangement
GB2036945A (en) * 1978-12-11 1980-07-02 Gen Electric Combustion liner

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526083A1 (fr) * 1982-05-03 1983-11-04 Gen Electric Moteur a bouts d'aubes de turbine refroidis
US4566280A (en) * 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US4723413A (en) * 1985-11-19 1988-02-09 MTU Munuch, GmbH Reverse flow combustion chamber, especially reverse flow ring combustion chamber, for gas turbine propulsion units, with at least one flame tube wall film-cooling arrangement
FR2604509A1 (fr) * 1986-09-25 1988-04-01 Snecma Procede de realisation d'un film de refroidissement pour chambre de combustion de turbomachine, film ainsi realise et chambre de combustion le comportant
EP0268505A1 (de) * 1986-09-25 1988-05-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Herstellungsweise für einen Verbrennungskammerring, der einen Kühlfilm erzeugt
EP1104872A1 (de) * 1999-12-03 2001-06-06 General Electric Company Verfahren zur Verminderung der Wärmebelastung einer Brennkammerwand
US6250082B1 (en) 1999-12-03 2001-06-26 General Electric Company Combustor rear facing step hot side contour method and apparatus
US6389792B1 (en) 1999-12-03 2002-05-21 General Electric Company Combustor rear facing step hot side contour method
US6675582B2 (en) * 2001-05-23 2004-01-13 General Electric Company Slot cooled combustor line
EP2189723A1 (de) * 2008-11-25 2010-05-26 Alstom Technology Ltd Brennkammeranordnung zum Betrieb einer Gasturbine
CH699997A1 (de) * 2008-11-25 2010-05-31 Alstom Technology Ltd Brennkammeranordnung zum Betrieb einer Gasturbine.
US8479524B2 (en) 2008-11-25 2013-07-09 Alstom Technology Ltd. Combustion chamber arrangement for operating a gas turbine
CN109340824A (zh) * 2018-09-19 2019-02-15 西北工业大学 一种具有凹形冷却槽结构的燃烧室火焰筒壁面
CN113154453A (zh) * 2021-05-06 2021-07-23 中国航发湖南动力机械研究所 一种切向倾斜式环膜发散冷却结构
CN113266849A (zh) * 2021-05-18 2021-08-17 中国航发湖南动力机械研究所 气膜冷却结构及涡轮发动机燃烧室火焰筒
CN113266849B (zh) * 2021-05-18 2022-08-05 中国航发湖南动力机械研究所 气膜冷却结构及涡轮发动机燃烧室火焰筒

Also Published As

Publication number Publication date
FR2490728A1 (fr) 1982-03-26
JPS5781130A (en) 1982-05-21
EP0049190B1 (de) 1984-03-28
DE3162895D1 (en) 1984-05-03

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