EP0841520A2 - Chambre de combustion pour une turbine à gaz - Google Patents

Chambre de combustion pour une turbine à gaz Download PDF

Info

Publication number
EP0841520A2
EP0841520A2 EP97308248A EP97308248A EP0841520A2 EP 0841520 A2 EP0841520 A2 EP 0841520A2 EP 97308248 A EP97308248 A EP 97308248A EP 97308248 A EP97308248 A EP 97308248A EP 0841520 A2 EP0841520 A2 EP 0841520A2
Authority
EP
European Patent Office
Prior art keywords
flange
heatshield
combustor
cylinder
combustor according
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
EP97308248A
Other languages
German (de)
English (en)
Other versions
EP0841520A3 (fr
EP0841520B1 (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

Links

Images

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 an 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.
  • miniflares 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.
  • Advantageously 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.
  • Figure 1 is a schematic diagram of a ducted fan gas turbine engine having an annular combustor.
  • Figure 2 is a partially sectioned side view of a combustor in accordance with the present invention.
  • Figure 3 is view of a cylinder and flange in accordance with the present invention.
  • Figure 4 is a cross sectional view of a portion of the cylinder and flange (apertures not shown) of figure 3.
  • 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.

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)
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 true EP0841520A2 (fr) 1998-05-13
EP0841520A3 EP0841520A3 (fr) 1999-11-03
EP0841520B1 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)

Cited By (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
EP1510760A1 (fr) * 2003-08-28 2005-03-02 General Electric Company Calotte de chambre de combustion pour diminuer la dynamique de la combustion
CN101206037B (zh) * 2006-12-22 2011-08-24 通用电气公司 用于修复燃烧器衬里的方法
FR3033028A1 (fr) * 2015-02-25 2016-08-26 Turbomeca Chambre de combustion de turbomachine comportant une piece penetrante avec ouverture
US10704517B2 (en) 2016-12-20 2020-07-07 Rolls-Royce Plc 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (11)

* 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
US6679063B2 (en) 2000-10-02 2004-01-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head for a gas turbine
EP1510760A1 (fr) * 2003-08-28 2005-03-02 General Electric Company Calotte de chambre de combustion pour diminuer la dynamique de la combustion
US6923002B2 (en) 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
CN101206037B (zh) * 2006-12-22 2011-08-24 通用电气公司 用于修复燃烧器衬里的方法
FR3033028A1 (fr) * 2015-02-25 2016-08-26 Turbomeca Chambre de combustion de turbomachine comportant une piece penetrante avec ouverture
WO2016135409A1 (fr) * 2015-02-25 2016-09-01 Turbomeca Chambre de combustion de turbomachine comportant une pièce pénétrante avec ouverture
CN107257904A (zh) * 2015-02-25 2017-10-17 赛峰直升机发动机公司 涡轮发动机的包括具有开口的贯通部件的燃烧室
RU2704440C2 (ru) * 2015-02-25 2019-10-29 Сафран Хеликоптер Энджинз Камера сгорания газотурбинного двигателя, содержащая заходящую деталь с отверстием
CN107257904B (zh) * 2015-02-25 2020-05-26 赛峰直升机发动机公司 涡轮发动机的包括具有开口的贯通部件的燃烧室
US10704517B2 (en) 2016-12-20 2020-07-07 Rolls-Royce Plc Combustion chamber and a combustion chamber fuel injector seal

Also Published As

Publication number Publication date
DE69719671D1 (de) 2003-04-17
EP0841520A3 (fr) 1999-11-03
DE69719671T2 (de) 2003-08-14
GB9623195D0 (en) 1997-01-08
EP0841520B1 (fr) 2003-03-12

Similar Documents

Publication Publication Date Title
US5974805A (en) Heat shielding for a turbine combustor
US5509270A (en) Gas turbine engine combustor heatshield
US5271219A (en) Gas turbine engine combustor
EP0471438B1 (fr) Chambre de combustion pour turbine à gaz
EP0471437B1 (fr) Chambre de combustion pour turbine à gaz
US4843825A (en) Combustor dome heat shield
EP1001222B1 (fr) Chemise de chambre de combustion avec refroidissement par couche d'air
EP2864707B1 (fr) Paroi de chambre de combustion de moteur à turbine avec distribution non uniforme d'ouvertures d'effusion
US3899876A (en) Flame tube for a gas turbine combustion equipment
US8205336B2 (en) Method for manufacturing a combustor heat shield
CA2641195C (fr) Dispositif combustor de turbine a gaz et methode d'application de gaz de purge dans une chambre de combustion du dispositif combustor
GB2298266A (en) A cooling arrangement for heat resistant tiles in a gas turbine engine combustor
US5353599A (en) Fuel nozzle swirler for combustors
US10753283B2 (en) Combustor heat shield cooling hole arrangement
US8387395B2 (en) Annular combustion chamber for a turbomachine
EP3026343B1 (fr) Structure d'orifice auto-refroidi
EP3315866B1 (fr) Ensemble de chambre de combustion comportant un composant auxiliaire monté
JP2004003835A (ja) ガスタービンエンジンの燃焼器ライナ用の多孔パッチ
US9599344B2 (en) Combustion chamber for a turbine engine
US6220015B1 (en) Gas-turbine engine combustion system
EP1241413B1 (fr) Bouclier thermique remplaçable pour injecteur de post-combustion
US4222230A (en) Combustor dome assembly
EP3130855B1 (fr) Paroi de chambre de combustion de turbine à gaz comprenant une agencement de perforations
US6705088B2 (en) Advanced crossfire tube cooling scheme for gas turbine combustors
EP0841520B1 (fr) Chambre de combustion pour une turbine à gaz

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;RO;SI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;RO;SI

17P Request for examination filed

Effective date: 19991012

AKX Designation fees paid

Free format text: DE FR GB

17Q First examination report despatched

Effective date: 20011218

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 69719671

Country of ref document: DE

Date of ref document: 20030417

Kind code of ref document: P

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20031215

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20121029

Year of fee payment: 16

Ref country code: FR

Payment date: 20121107

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20121025

Year of fee payment: 16

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20131017

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69719671

Country of ref document: DE

Effective date: 20140501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20131017

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20131031

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140501