GB1301968A - - Google Patents

Info

Publication number
GB1301968A
GB1301968A GB5354871A GB5354871A GB1301968A GB 1301968 A GB1301968 A GB 1301968A GB 5354871 A GB5354871 A GB 5354871A GB 5354871 A GB5354871 A GB 5354871A GB 1301968 A GB1301968 A GB 1301968A
Authority
GB
United Kingdom
Prior art keywords
air
flame tube
holes
combustion
tube
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
GB5354871A
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 filed Critical
Publication of GB1301968A publication Critical patent/GB1301968A/en
Expired legal-status Critical Current

Links

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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Gas Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

1301968 Gas turbine combustion chambers GENERAL MOTORS CORP 18 Nov 1971 [27 Nov 1970] 53548/71 Heading F1L To reduce formation of nitrogen oxides a gas turbine flame tube 12 is provided with means to introduce primary air mixed with recirculating combustion products into the combustion zone. The means comprises a series of angularly spaced L-shaped tubes 59 secured to the side wall 26 of the flame tube and each having an opening 58 for primary air from a surrounding air space, (11) Fig.1 (not shown). Each tube 59 has a converging outlet 60 opening into the entrance 55 of a recirculation tube 54 so as to induce combustion products into the latter to mix with the primary air, the mixture discharging radially through outlets 56 into the combustion zone. The upstream end wall of the flame tube is formed by a dome 27 comprising outer and inner sheets 36, 38 welded together, sheet 36 having holes 42 for the admission of air which then passes into the combustion zone through rows of oppositely directed swirl vanes 39, 40 in sheet 38 to mix with fuel from injector assembly 28. The periphery of sheets 36, 38 is welded to a ring 43 secured to inwardly deformed brackets 47 on wall 26 by screws passing through holes 44, 48. Film cooling air enters the gap between wall 26 and ring 43. Dilution air enters the flame tube through holes 62. The air-flow into the flame tube is distributed so that of the total discharged by the compressor about 9% flows through swirlers 39, 40, 28% through the gap surrounding ring 43, 5% through inlets 58, and 58% through dilution holes 62. The air may have been pre-heated in a rotary or other regenerator. The ratio of recirculated combustion products to fresh air in tubes 54 is approximately 3:5. Tabs 52 are provided on the downstream end of the flame tube for engagement with a transition duct (14). The construction is applicable also to annular combustion apparatus.
GB5354871A 1970-11-27 1971-11-18 Expired GB1301968A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US9301970A 1970-11-27 1970-11-27

Publications (1)

Publication Number Publication Date
GB1301968A true GB1301968A (en) 1973-01-04

Family

ID=22236381

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5354871A Expired GB1301968A (en) 1970-11-27 1971-11-18

Country Status (4)

Country Link
US (1) US3656298A (en)
AU (1) AU445514B2 (en)
DE (1) DE2158215C3 (en)
GB (1) GB1301968A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10539073B2 (en) 2017-03-20 2020-01-21 Chester L Richards, Jr. Centrifugal gas compressor

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1335134A (en) * 1970-12-05 1973-10-24 Nissan Motor Combustion apparatus of a gas turbine engine
JPS4724483Y1 (en) * 1970-12-22 1972-08-02
US3854503A (en) * 1971-08-05 1974-12-17 Lucas Industries Ltd Flame tubes
US3969892A (en) * 1971-11-26 1976-07-20 General Motors Corporation Combustion system
US3744242A (en) * 1972-01-25 1973-07-10 Gen Motors Corp Recirculating combustor
FR2312654A1 (en) * 1975-05-28 1976-12-24 Snecma COMBUSTION CHAMBERS IMPROVEMENTS FOR GAS TURBINE ENGINES
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
US3990232A (en) * 1975-12-11 1976-11-09 General Electric Company Combustor dome assembly having improved cooling means
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
US4195476A (en) * 1978-04-27 1980-04-01 General Motors Corporation Combustor construction
US4222230A (en) * 1978-08-14 1980-09-16 General Electric Company Combustor dome assembly
US4345426A (en) * 1980-03-27 1982-08-24 Egnell Rolf A Device for burning fuel with air
JP3951909B2 (en) * 2002-12-12 2007-08-01 株式会社日立製作所 Gas turbine combustor
US7260936B2 (en) * 2004-08-27 2007-08-28 Pratt & Whitney Canada Corp. Combustor having means for directing air into the combustion chamber in a spiral pattern
EP2767696A1 (en) * 2013-02-15 2014-08-20 Siemens Aktiengesellschaft Assembly comprising a gas turbine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE550737A (en) *
DE1130958B (en) * 1956-08-25 1962-06-07 Schmidt Sche Heissdampf Large capacity burner for burning liquid fuels, especially heavy oils, for heating steam boilers
US3024608A (en) * 1958-09-24 1962-03-13 Snecma Combustion device
US3498055A (en) * 1968-10-16 1970-03-03 United Aircraft Corp Smoke reduction combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10539073B2 (en) 2017-03-20 2020-01-21 Chester L Richards, Jr. Centrifugal gas compressor

Also Published As

Publication number Publication date
AU3598071A (en) 1973-05-31
DE2158215B2 (en) 1975-04-24
AU445514B2 (en) 1974-02-21
DE2158215A1 (en) 1972-06-08
DE2158215C3 (en) 1975-12-11
US3656298A (en) 1972-04-18

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees