EP0049190B1 - 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
EP0049190B1
EP0049190B1 EP19810401447 EP81401447A EP0049190B1 EP 0049190 B1 EP0049190 B1 EP 0049190B1 EP 19810401447 EP19810401447 EP 19810401447 EP 81401447 A EP81401447 A EP 81401447A EP 0049190 B1 EP0049190 B1 EP 0049190B1
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EP
European Patent Office
Prior art keywords
flame tube
wall
slot
internal wall
chamber
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.)
Expired
Application number
EP19810401447
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English (en)
French (fr)
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EP0049190A1 (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
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Publication of EP0049190A1 publication Critical patent/EP0049190A1/de
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    • 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, according to the first part of claim 1.
  • the flame tube which extends the combustion chamber, is subjected to a significant heat flow since it is in this that the phenomenon of combustion of the air / fuel mixture produced in the chamber occurs. 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 No 1432316 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 a radial annular flange.
  • Axially directed air inlet orifices 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.
  • the problems that such a device attempts to solve are mainly the detachment of the air film from the wall of the tube and the cooling of the inner ring, in its part between the rim and its free end and which will be referred to hereinafter as tongue.
  • tongue To prevent the film from coming off and to ensure adequate insulation of the wall, its flow must be non-turbulent and its speed must be approximately equal to the speed of the gas flow in the flame tube.
  • French patent No. 1510874 presents a device comprising only radial orifices which have the main function of allowing the flow rate of the cooling fluid to be adjusted.
  • the short, rigid tongue protects the ports against hot interior fluid and creates 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 the 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 conserve their radial kinetic energy, without this being reduced or even eliminated by too rapid 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.
  • Known devices all have a setting at the input of the film supply 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, disposed upstream of the slot, in order 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 for the technical characteristics defined in the characterizing part of claim 1.
  • 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 via 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 internal wall 8 defines, with the external wall 7, an annular outlet slot 13 through which the film of cooling and insulating air flows from the wall of the downstream section 1 of the flame tube.
  • 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 (solid line, 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 diameters or of 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 h is less than the length L.
  • the chamber 9 is separated into several sectors by longitudinal reinforcements 20 which make it possible to maintain strict 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 the hot gases 19, favor its impact by cooling effect.
  • the flow from the jets engages in the convergent 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 beveled portion. This bevel reduces the wake at the mouth of the slit.
  • 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 2 times 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% of the axial speed at the exit of the chamber before converging. 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.

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  • 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)

Claims (4)

1. Vorrichtung zur Luftfilmkühlung für das Flammrohr eines Gasturbinentriebwerkes in Form eines ringförmigen Verbindungsstückes zwischen einem niederdruckseitigen Abschnitt (1) und einem hochdruckseitigen Abschnitt (2) des Flammrohres mit einer äusseren Wandung (7) und einer inneren Wandung (8), die zwischen sich eine in radialer Richtung durch wenigstens eine Reihe von in der äusseren Wandung angebrachten Öffnungen (10) gespeiste Kammer (9) begrenzen, wobei die innere Wandung zusammen mit der äusseren Wandung einen ringförmigen Auslassschlitz (13) bestimmt, durch welchen ein Luftfilm zur Kühlung und zur Isolierung der Innenwandung des niederdruckseitigen Abschnittes des Flammrohres ausströmt, und wobei die genannte äussere Wandung (7) und die innere Wandung (8) jeweils einen sich in axialer Richtung erstreckenden zylindrischen Teil (14 bzw. 15) beinhalten und diese zylindrischen Teile koaxial und im Abstand voneinander angeordnet und auf der Hochdruckseite durch wenigstens einen näherungsweise konischen Teil (17) mit dem hochdruckseitigen Abschnitt (2) des Flammrohres verbunden sind, dadurch gekennzeichnet, dass der zylindrische Teil (14) der äusseren Wandung (7) niederdruckseitig durch ein konisches Stück (16) mit dem niederdruckseitigen Abschnitt (1) des Flammrohres derart verbunden ist, dass die Abmessungen der Kammer (9) durch folgende Werte bestimmt sind:
Figure imgb0002
wobei
h die Breite des Schlitzes,
H die Höhe der Kammer,
c die projizierte Länge des konischen Teiles zwischen der äusseren Wandung und dem niederdruckseitigen Abschnitt des Flammrohres,
L die Länge des ringförmigen Kanals des Schlitzes, und
d der Durchmesser der Öffnungen

bedeuten.
2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Dicke des freien Randes der den Schlitz (13) begrenzenden inneren Wandung kleiner ist als die halbe Breite des Schlitzes.
3. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die innere Wandung (8) in ihrem niederdruckseitigen Teil eine äussere Abschrägung aufweist.
4. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Anzahl der Reihen von Öffnungen in der Folge {2, 3, 4} gewählt ist.
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
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
FR8020558 1980-09-25

Publications (2)

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

Family

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Family Applications (1)

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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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3248439A1 (de) * 1982-05-03 1983-11-03 General Electric Co., Schenectady, N.Y. Gasturbinentriebwerk mit gekuehlten schaufelspitzen
DE3540942A1 (de) * 1985-11-19 1987-05-21 Mtu Muenchen Gmbh Umkehrbrennkammer, insbesondere umkehrringbrennkammer, fuer gasturbinentriebwerke, mit mindestens einer flammrohrwandfilmkuehleinrichtung

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4566280A (en) * 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
FR2604509B1 (fr) * 1986-09-25 1988-11-18 Snecma Procede de realisation d'un film de refroidissement pour chambre de combustion de turbomachine, film ainsi realise et chambre de combustion le comportant
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
US6250082B1 (en) 1999-12-03 2001-06-26 General Electric Company Combustor rear facing step hot side contour method and apparatus
US6675582B2 (en) * 2001-05-23 2004-01-13 General Electric Company Slot cooled combustor line
CH699997A1 (de) * 2008-11-25 2010-05-31 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
CN113154453B (zh) * 2021-05-06 2022-07-08 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
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
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

Family Cites Families (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
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
CH529916A (de) * 1970-10-01 1972-10-31 Bbc Sulzer Turbomaschinen Brennkammer für eine Gasturbinenanlage
US3845620A (en) * 1973-02-12 1974-11-05 Gen Electric Cooling film promoter for combustion chambers
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
US4050241A (en) * 1975-12-22 1977-09-27 General Electric Company Stabilizing dimple for combustion liner cooling slot
CH634128A5 (de) * 1978-06-13 1983-01-14 Bbc Brown Boveri & Cie Kuehlvorrichtung an einer wand.
US4259842A (en) * 1978-12-11 1981-04-07 General Electric Company Combustor liner slot with cooled props

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3248439A1 (de) * 1982-05-03 1983-11-03 General Electric Co., Schenectady, N.Y. Gasturbinentriebwerk mit gekuehlten schaufelspitzen
DE3540942A1 (de) * 1985-11-19 1987-05-21 Mtu Muenchen Gmbh Umkehrbrennkammer, insbesondere umkehrringbrennkammer, fuer gasturbinentriebwerke, mit mindestens einer flammrohrwandfilmkuehleinrichtung
DE3540942C2 (de) * 1985-11-19 1988-08-04 Mtu Muenchen Gmbh

Also Published As

Publication number Publication date
JPS5781130A (en) 1982-05-21
FR2490728A1 (fr) 1982-03-26
DE3162895D1 (en) 1984-05-03
EP0049190A1 (de) 1982-04-07

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