EP0841520B1 - Chambre de combustion pour une turbine à gaz - Google Patents

Chambre de combustion pour une turbine à gaz Download PDF

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Publication number
EP0841520B1
EP0841520B1 EP19970308248 EP97308248A EP0841520B1 EP 0841520 B1 EP0841520 B1 EP 0841520B1 EP 19970308248 EP19970308248 EP 19970308248 EP 97308248 A EP97308248 A EP 97308248A EP 0841520 B1 EP0841520 B1 EP 0841520B1
Authority
EP
European Patent Office
Prior art keywords
combustor
flange
heatshield
annular
cylinder
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 - Lifetime
Application number
EP19970308248
Other languages
German (de)
English (en)
Other versions
EP0841520A2 (fr
EP0841520A3 (fr
Inventor
John Guy Allen
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP0841520A2 publication Critical patent/EP0841520A2/fr
Publication of EP0841520A3 publication Critical patent/EP0841520A3/fr
Application granted granted Critical
Publication of EP0841520B1 publication Critical patent/EP0841520B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • This invention relates to a gas turbine engine combustor and is particularly concerned with the thermal protection of the combustor wall or bulkhead by heatshields and specifically the miniflare associated therewith.
  • Modern gas turbine annular combustors are usually provided with a combustor which is of generally annular configuration.
  • a wall or bulkhead is provided at the upstream end of the combustor which is suitably apertured to receive a number of fuel burners.
  • the fuel burners are equally spaced around the combustor and direct fuel into the combustor to support combustion therein.
  • the combustor bulkhead is therefore usually close to the high temperature combustion process taking place within the combustor making it vulnerable to heat damage.
  • each heat shield is associated with a corresponding fuel burner and extends both radially towards the radially inner and outer extents of the bulkhead and circumferentially to abut adjacent heat shields.
  • Each heat shield is spaced apart from the bulkhead so that a narrow space is defined between them. Cooling air is directed into this space in order to provide cooling of the heat shield and so maintain the heat shield and the bulkhead at acceptably low temperatures.
  • miniflares More recently cylinders comprising end flanges, commonly known as miniflares, have been used to direct a film of cooling air across the heatshield thus protecting it from hot combustion gases.
  • US4,914,918 discloses one such prior art miniflare, however, although this miniflare provide a film of cooling air for the heat shield their own cooling is insufficient to prevent overheating, in particular towards its outer edge. Additionally the cooling film produced often ceases to be effective at the outer regions of the heatshield. It is an aim of the present invention, therefore, to provide an improved device for cooling a heatshield which attempts to alleviate the aforementioned problems.
  • a combustor for a gas turbine engine in which a fuel nozzle is located in the upstream end thereof and is positioned within a hollow, annular cylinder, said cylinder comprising at its downstream end an annular flange extending from said cylinder in a generally radial direction and said flange comprising a plurality of apertures extending therethrough.
  • cooling air is directed through 'the apertures in the annular flange thus increasing the outer edge of the cylinder and also provides an effective cooling air film across an adjacent heatshield.
  • FIG 1 With reference to figure 1 there is shown a three shafted ducted fan gas turbine engine of generally conventional configuration. It will be understood however that the present invention may be usefully employed in other engine configurations.
  • the engine of figure 1 comprises in axial flow series a low pressure spool consisting of a fan 2 driven by a low pressure turbine 4 via a first shaft 6, an intermediate pressure turbine 10 through a second shaft 12 and a high pressure compressor 14 driven by a high pressure turbine 16 via a third shaft 18, an annular combustor 20 and a propulsive nozzle 21.
  • the annular combustor 20 is shown in more detail in Figure 2.
  • the combustor chamber inner casing 22 comprises radially spaced inner and outer walls 24, 26 respectively, interconnected at their upstream ends by means of an annular bulkhead 28.
  • the walls 24 and 26 extend upstream of the bulkhead to form a domed combustor head 30.
  • the bulkhead divides the combustor into an upstream cooling air chamber 32 and a downstream combustion region and a downstream combustion region 34.
  • Compressor delivery air from an upstream compressor enters the cooling air chamber 32 through a plurality of circumferentially spaced inlet apertures 36 before entering the combustion chamber 34.
  • Fuel is delivered to the combustion chamber by means of a plurality of air spray type fuel supply nozzles 38.
  • the nozzles are suspended from a combustion chamber outer casing structure 40 and extend into the combustor 20 through a corresponding array of circumferentially spaced apertures 42 is provided in the bulkhead member 28, each to receiver the outlet of an adjacent one of the nozzles.
  • a protective heatshield 44 is mounted on the downstream face of the bulkhead 28 to provide thermal shielding from combustion temperatures.
  • This heatshield has an annular configuration made up of a plurality of abutting heatshield segments 46.
  • the segments which are of substantially identical form, extend both radially towards the inner and outer walls 24, 26 of the combustor and circumferentially towards adjacent segments to define a fully annular shield.
  • Some or all of the heatshield segments may be adapted to receive a fuel nozzle.
  • Those which receive a fuel nozzle comprise an aperture the periphery of which is defined by an axially extending cylindrical flange 48 which locates the heatshield in the corresponding aperture 42 in the bulkhead wall 28.
  • Each heatshield segment receives an airspray burner and a miniflare seal 49.
  • the miniflare seal 49 is in the form of an annular cylinder 50 and is provided with a pair of axially spaced radial flanges 52 and 54 which slidably engage with the heatshield flange extremities.
  • the cylindrical miniflare 49 has an external diameter which is less than the heatshield aperture.
  • the miniflare radial flange 54 extends radially from the downstream end of the cylinder. This flange 54 comprises a further axially extending end flange portion 56.
  • This axially extending flange portion comprises two rows of holes 58, 60 axially spaced from one another.
  • the upstream outer rim of this end flange portion 56 is provided with castellations 62 at its outer edge.
  • the provision of multi rows of holes 58, 60 in the miniflare flange end portion 56 increases the cooling of the outer edge of the miniflare and as such reduces its surface temperature and provides a more effective air film across the heatshield 44 or combustor head face thus increasing the protection from hot combustion gases.

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)
  • Spray-Type Burners (AREA)

Claims (9)

  1. Chambre de combustion (20) pour un moteur à turbine à gaz dans lequel une buse de combustible (38) est située dans l'extrémité amont de la chambre et est positionnée à l'intérieur d'un cylindre annulaire (50) qui s'étend coaxialement à la buse de combustible (38), le cylindre annulaire (50) comprenant au niveau de son extrémité aval une bride annulaire (54) s'étendant à partir du cylindre annulaire (50) dans une direction généralement radiale, la bride annulaire (50) comprenant en outre une partie de bride (56), la partie de bride (56) définissant plusieurs crénelures (62) dans un bord amont de celle-ci, caractérisé en ce que ladite partie de bride (56) s'étend axialement et définit plusieurs ouvertures de refroidissement de fluide (58) qui s'étendent radialement à travers.
  2. Chambre de combustion (20) selon la revendication 1, caractérisée en ce que le cylindre annulaire (50) est monobloc.
  3. Chambre de combustion (20) selon l'une quelconque des revendications 1 et 2, caractérisée en ce que la partie de bride (56) s'étend axialement dans la direction amont.
  4. Chambre de combustion (20) selon l'une quelconque des revendications précédentes, caractérisée en ce que les ouvertures (58, 60) sont prévues en deux rangées espacées axialement (58, 60) à l'intérieur de la partie de bride (56).
  5. Chambre de combustion (20) selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit cylindre annulaire (50) comprend également une seconde bride (52) positionnée axialement en amont de ladite bride (54) de la revendication 1.
  6. Chambre de combustion (20) selon l'une quelconque des revendications précédentes, caractérisée en ce qu'un écran thermique (44) est prévu à l'intérieur d'une ouverture pour recevoir ladite buse de combustible (38).
  7. Chambre de combustion (20) selon la revendication 6, caractérisée en ce que ladite ouverture à écran thermique (44) comprend une bride cylindrique (48) qui s'étend axialement et qui positionne l'écran thermique (44) dans une ouverture correspondante dans le cadre (28) de la chambre de combustion (20).
  8. Chambre de combustion (20) selon la revendication 7, caractérisée en ce que la bride à écran thermique (48) est pourvue de fentes (64) pour diriger un fluide de refroidissement vers une région annulaire (66) située entre la bride à écran thermique (48) et le cylindre (50).
  9. Chambre de combustion (20) selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit air de refroidissement est dirigé radialement par ledit cylindre (50) et la bride associée (54) sous la forme d'un film d'air à travers l'écran thermique (44).
EP19970308248 1996-11-07 1997-10-17 Chambre de combustion pour une turbine à gaz Expired - Lifetime EP0841520B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9623195 1996-11-07
GBGB9623195.6A GB9623195D0 (en) 1996-11-07 1996-11-07 Gas turbine engine combustor

Publications (3)

Publication Number Publication Date
EP0841520A2 EP0841520A2 (fr) 1998-05-13
EP0841520A3 EP0841520A3 (fr) 1999-11-03
EP0841520B1 true EP0841520B1 (fr) 2003-03-12

Family

ID=10802586

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970308248 Expired - Lifetime EP0841520B1 (fr) 1996-11-07 1997-10-17 Chambre de combustion pour une turbine à gaz

Country Status (3)

Country Link
EP (1) EP0841520B1 (fr)
DE (1) DE69719671T2 (fr)
GB (1) GB9623195D0 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10048864A1 (de) 2000-10-02 2002-04-11 Rolls Royce Deutschland Brennkammerkopf für eine Gasturbine
US6923002B2 (en) 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
US8312627B2 (en) * 2006-12-22 2012-11-20 General Electric Company Methods for repairing combustor liners
FR3033028B1 (fr) * 2015-02-25 2019-12-27 Safran Helicopter Engines Chambre de combustion de turbomachine comportant une piece penetrante avec ouverture
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer

Also Published As

Publication number Publication date
DE69719671D1 (de) 2003-04-17
EP0841520A2 (fr) 1998-05-13
EP0841520A3 (fr) 1999-11-03
DE69719671T2 (de) 2003-08-14
GB9623195D0 (en) 1997-01-08

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