EP0433868A1 - Chambre de combustion pour une turbine à gaz avec des atomisateurs de carburant assistés par air - Google Patents

Chambre de combustion pour une turbine à gaz avec des atomisateurs de carburant assistés par air Download PDF

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Publication number
EP0433868A1
EP0433868A1 EP90123970A EP90123970A EP0433868A1 EP 0433868 A1 EP0433868 A1 EP 0433868A1 EP 90123970 A EP90123970 A EP 90123970A EP 90123970 A EP90123970 A EP 90123970A EP 0433868 A1 EP0433868 A1 EP 0433868A1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustion chamber
air
gas turbine
nozzles
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.)
Withdrawn
Application number
EP90123970A
Other languages
German (de)
English (en)
Inventor
Karl-Heinz Collin
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 Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0433868A1 publication Critical patent/EP0433868A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the invention relates to a combustion chamber according to the preamble of claim 1.
  • Small gas turbines are often built with a radial compressor in which air is compressed and then fed to a combustion chamber.
  • the air in the combustion chamber is heated up due to the combustion of fuel.
  • the resulting combustion gas expands in a turbine arranged behind the combustion chamber.
  • the invention has for its object to provide a combustion chamber with air-assisted fuel atomizing nozzles for a gas turbine, with which sufficient fuel atomization is ensured in the entire operating range.
  • this is achieved in that the atomizer nozzles are arranged directly behind the stator outlet of the compressor. This measure ensures sufficient atomization of the fuel in the entire operating range of the gas turbine and thus good fuel preparation, which leads to better exhaust gas emission values.
  • start atomizing nozzles are no longer necessary, thereby saving weight and space. This is of great advantage particularly in the case of small gas turbines.
  • the atomizer nozzles advantageously have a honing chamber which tapers in the direction of flow and in which an atomizer member is arranged. Good atomization of the fuel can be achieved with these atomizing nozzles.
  • the atomizer member advantageously has a fuel supply line, a fuel channel and a tear-off edge, the fuel channel merging into the tear-off edge. Furthermore, the end of the atomizer member facing the stator has a rounded shape.
  • the reference numeral 1 denotes a radial compressor which conveys combustion air into a combustion chamber 3 via guide wheels 2.
  • a turbine 12 is arranged in the flow direction behind the combustion chamber 3.
  • the fuel is atomized via atomizing nozzles 4.
  • the atomizer nozzles 4 are arranged immediately behind the stator outlet 5 of the compressor 1.
  • the shape of the atomizing nozzles 4 can be seen from FIG.
  • the atomizer nozzles 4 have a cavity 6 which tapers in the direction of flow and in which an atomizer member 7 is arranged.
  • This atomizer member 7 includes a fuel supply line 8, a fuel channel 9 and a tear-off edge 10, the fuel channel 9 extending from the fuel supply line 8 and passing into the tear-off edge 10.
  • the atomizer nozzles 4 are arranged directly behind the stator outlet 5 of the compressor 1. As a result, there is sufficient flow energy for atomizing fuel even when the gas turbine is started.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP90123970A 1989-12-20 1990-12-12 Chambre de combustion pour une turbine à gaz avec des atomisateurs de carburant assistés par air Withdrawn EP0433868A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3942042 1989-12-20
DE19893942042 DE3942042A1 (de) 1989-12-20 1989-12-20 Brennkammer fuer eine gasturbine mit luftunterstuetzten brennstoffzerstaeuberduesen

Publications (1)

Publication Number Publication Date
EP0433868A1 true EP0433868A1 (fr) 1991-06-26

Family

ID=6395873

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90123970A Withdrawn EP0433868A1 (fr) 1989-12-20 1990-12-12 Chambre de combustion pour une turbine à gaz avec des atomisateurs de carburant assistés par air

Country Status (2)

Country Link
EP (1) EP0433868A1 (fr)
DE (1) DE3942042A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0540162A1 (fr) * 1991-09-23 1993-05-05 General Electric Company Système d'injection pour chambre de combustion
US5265425A (en) * 1991-09-23 1993-11-30 General Electric Company Aero-slinger combustor

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19860583A1 (de) * 1998-12-29 2000-07-06 Abb Alstom Power Ch Ag Brennkammer für eine Gasturbine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
EP1825113B1 (fr) 2004-12-01 2012-10-24 United Technologies Corporation Boîte de vitesses contre-rotative pour moteur à turbine en bout
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006059977A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine de bout et procede de mise en oeuvre correspondant
WO2006060000A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Ensemble aubes de guidage d'admission de soufflante variable, turbomachine dotee d'un tel ensemble et procede de commande correspondant
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
EP1828591B1 (fr) 2004-12-01 2010-07-21 United Technologies Corporation Foyer peripherique pour moteur a turbine de bout
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2223093A1 (de) * 1972-05-12 1973-11-22 Gen Electric Brenner und brennstoffinjektor
FR2363001A2 (fr) * 1976-08-30 1978-03-24 Snecma Chambre de combustion antipollution

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
GB1139004A (en) * 1966-02-28 1969-01-08 Mini Of Technology Improvements in or relating to combustion devices
US4081957A (en) * 1976-05-03 1978-04-04 United Technologies Corporation Premixed combustor
GB2161914B (en) * 1980-12-10 1986-06-11 Rolls Royce Combustion equipment for a gas turbine engine
DE3819899C1 (en) * 1988-06-11 1989-11-30 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Apparatus for generating a homogeneous mixture from a first and second medium

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2223093A1 (de) * 1972-05-12 1973-11-22 Gen Electric Brenner und brennstoffinjektor
FR2363001A2 (fr) * 1976-08-30 1978-03-24 Snecma Chambre de combustion antipollution

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN, Band 9, Nr. 226 (M-412)[1949], 12. September 1985; & JP-A-60 82 724 (KOGYO GIJUTSUIN) 10-05-1985 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0540162A1 (fr) * 1991-09-23 1993-05-05 General Electric Company Système d'injection pour chambre de combustion
US5265425A (en) * 1991-09-23 1993-11-30 General Electric Company Aero-slinger combustor

Also Published As

Publication number Publication date
DE3942042A1 (de) 1991-06-27

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