EP0910776B1 - Bruleur dote d'une buse de pulverisation - Google Patents

Bruleur dote d'une buse de pulverisation Download PDF

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Publication number
EP0910776B1
EP0910776B1 EP97936627A EP97936627A EP0910776B1 EP 0910776 B1 EP0910776 B1 EP 0910776B1 EP 97936627 A EP97936627 A EP 97936627A EP 97936627 A EP97936627 A EP 97936627A EP 0910776 B1 EP0910776 B1 EP 0910776B1
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EP
European Patent Office
Prior art keywords
flow
atomiser
burner
component
fuel
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
EP97936627A
Other languages
German (de)
English (en)
Other versions
EP0910776A1 (fr
Inventor
Nikolaos Zarzalis
Thomas Ripplinger
Bernhard Glaeser
Burkhard Simon
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.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP0910776A1 publication Critical patent/EP0910776A1/fr
Application granted granted Critical
Publication of EP0910776B1 publication Critical patent/EP0910776B1/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
    • F23R3/02—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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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 burner for combustion chambers of gas turbines according to the Preamble of claim 1.
  • a burner is in the German patent application P 44 44 961.
  • the reduction of pollutants in the combustion of kerosene in combustion chambers of aircraft engines is a constant development goal.
  • the pollutant-reduced combustion chamber is a starting point.
  • components of the combustion chamber be optimized. For example, it applies to fuel in all operating areas atomize as finely as possible and mix with the combustion air.
  • This fuel preparation is used in the combustion chambers of modern aircraft gas turbines Air atomizing nozzles accomplished. The fuel flows according to their operating principle on a cylindrical surface to the end where due to air shear forces atomization begins.
  • the mass flow of the secondary air flow must be greater than that of the primary airflow, so in the short distance from the end of the atomizer lip until it enters the combustion chamber, the peripheral pulse of the secondary air flow is not completely broken down and the formation of the recirculation vortex is endangered becomes. This in turn results in the distribution of the air-fuel ratio does not have the desired homogeneity at the nozzle outlet because the primary Airflow that is primarily involved in the mixing process is less than that secondary airflow is.
  • An injection device for a combustion chamber is known from GB 2 272 756 A, which comprises an atomizer, several channels and a premixing section, the First of all, fuel to the guiding elements surrounding the channels with atomizer lips atomized and then in the premixing section with the air streams the channels that open into the premixing section are mixed.
  • the premixing section is convergent-divergent to ensure good mixing of the atomized To ensure fuel with the air flows.
  • GB 1 099 959 and GB 2 094 464 A describe a burner for solid or liquid Fuels disclosed in which the fuel mixes with multiple air streams is, whose channels through concentrically arranged pipes with divergent outlet nozzles be formed. When using liquid fuels, this is in one Pressure atomization at the point of entry into the nozzle area.
  • the object of the invention is a generic burner specify a largely homogeneous distribution of the air-fuel mixture in the combustion chamber.
  • the invention has the advantage that by twisting the two in the same direction Airflows considering mixing them before entering the combustion chamber to a high peripheral speed must not be avoided, so that too Dimensional current ratio can be selected regardless of the swirl of the currents can to make the distribution of the air-fuel mixture homogeneous. Regardless of a mixture of the two streams, the swirl number of the Air flow can be varied to a detached or a wall-to-wall Set the flow state in the combustion chamber. By positioning the atomizer lip narrowest flow cross-section in the atomizer nozzle or shortly before can atomize the fuel in a range of maximum air shear forces take place so that the atomization can take place optimally.
  • the burner 1 shown in FIG. 1 is one of several arranged in a ring Burners of the combustion chamber 2 shown in sections of a not shown Aircraft gas turbine.
  • the burner 1 has an atomizing nozzle 3 with a primary and a secondary Flow channel 4 or 5 and an injection nozzle 15.
  • the two flow channels 4, 5 are in their channel course by ring or sleeve-shaped components 6, 7 determined and limited.
  • the two concentric to the burner axis Z Flow channels 4, 5 each have a radial inlet section E. in order to then be deflected into a substantially axially extending outlet section A. to become.
  • the sleeve-shaped component 6 separates the two channels 4, 5 from one another and has an annular atomizer lip in its downstream portion 8 with a conical taper.
  • the component 6 On its upstream section the component 6 has a radially extending flange 9, the two axially spaced, annular inlet sections E of the channels 4.5 separates.
  • the secondary flow channel running between the two components 6 and 7 5 is in its radially extending inlet section E of two parallel, annular wall sections of the two components 6 and 7 limited.
  • the secondary flow channel 5 In the outlet section A, the secondary flow channel 5 is downstream radially outward from one, seen in the direction of flow, convergent-divergent running inner wall I of component 7 limited.
  • the atomizer lip 8 ends immediately in front of the location with the narrowest flow cross section Q, which through the convergent-divergent course of the component 7 is defined so that downstream the atomizer lip 8, within the divergent section of the component 7 and downstream this results in a homogeneous mixing of the two air flows.
  • the conically tapered inner wall of the atomizer lip 8 is by means of the injector 15 arranged in the primary flow channel 4 fine fuel sprayed in the form of a cone widening downstream like a fan, see above that it is deposited on the inner wall like a film.
  • the same directional twist is responsible for the formation of the rotation vortex W the air flow in the flow channels 4 and 5, which in each case in the Entry sections E of the flow channels 4 and 5 arranged swirl devices 12 is generated.
  • the cross sections of the two flow channels 4, 5 are dimensioned such that a mass flow ratio between primary and secondary air flow of is greater than 0.4. This ensures homogeneous mixing of the combustion chamber guaranteed with air-fuel mixture.
  • the swirl formation in the same direction in the Flow channels 4 and 5 by varying the number of swirl in the two channels 4.5 a detached or wall-mounted combustion chamber flow can be represented, so that on location and formation of the rotary vortex W can be influenced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)

Abstract

L'invention concerne un brûleur destiné aux chambres de combustion (2) de turbines à gaz et doté d'une buse (3) pour pulvériser le combustible dans l'air de combustion. Ledit brûleur comprend deux canaux (4,5) d'écoulement, un canal primaire et un canal secondaire. L'invention vise à obtenir, pour ce type de brûleurs utilisés essentiellement dans les moteurs d'avion, une répartition largement uniforme du mélange air-combustible dans la chambre de combustion afin de réduire les émissions. Les canaux (4,5) d'écoulement débouchant dans la chambre de combustion (11) sont séparés par un premier élément (6) disposé de façon concentrique par rapport à l'axe (A) du brûleur et doté d'une lèvre (8) de pulvérisation en forme de douille, de profil cylindrique ou conique. Le canal secondaire (4) extérieur est délimité vers l'extérieur et radialement par un deuxième élément (7) concentrique, de forme annulaire, doté d'une paroi (14) intérieure de profil convergent-divergent. Le deuxième élément (7) forme un espace (Q) caractérisé par la plus faible section de passage, sur la hauteur axiale de laquelle ou bien en amont, débouche la lèvre (8) de pulvérisation du premier composant (6) disposé à l'intérieur, de façon radiale. Le flux d'air (L) s'écoulant dans les deux canaux (4,5) présente une torsion similaire. En plaçant la lèvre (8) de pulvérisation au niveau de la plus petite section d'écoulement de la buse de pulvérisation ou juste en deçà, on obtient une pulvérisation du combustible située dans une plage d'efforts de cisaillement maximaux de l'air et donc une pulvérisation optimale.

Claims (5)

  1. Brûleur pour chambres de combustion (2), de turbines à gaz, avec une buse de pulvérisation (3) pour pulvériser du carburant dans l'air de combustion, dont l'écoulement traverse un canal d'écoulement primaire et un canal d'écoulement secondaire (4, 5) en amont de l'enceinte de combustion (11) de la chambre à combustion (12), le carburant étant pulvérisé sur une paroi dans la buse de pulvérisation (3) et les canaux d'écoulement (4, 5) débouchant dans l'enceinte de combustion (11) étant séparés par un premier composant (6), disposé concentriquement par rapport à l'axe de brûleur A, ayant une lèvre de pulvérisateur (8) en forme de douille, d'allure cylindrique ou s'effilant de façon conique, et le canal d'écoulement secondaire (5) étant limité radialement vers l'extérieur par un deuxième composant (7) en forme d'anneau disposé concentriquement ayant une paroi intérieure (14) à allure convergente/divergente, caractérisé en ce que le deuxième composant (7) disposé dans la buse de pulvérisateur (3) constitue un site (Q) ayant une aire de section transversale d'écoulement d'étroitesse maximale, à hauteur axiale duquel ou en amont duquel dans la direction de l'écoulement, le premier composant (6) disposé radialement à l'intérieur s'achève par la lèvre de pulvérisateur (8) et l'écoulement d'air (L) traversant les canaux d'écoulement (4, 5) avec une rotation orientée dans le même sens.
  2. Brûleur selon la revendication 1, caractérisé en ce que les deux composants (6, 7) sont disposés concentriquement par rapport à l'axe de brûleur A et constituent entre eux le canal d'écoulement secondaire (5) en forme d'anneau.
  3. Brûleur selon la revendication 1 ou 2, caractérisé en ce que, dans chacun des canaux d'écoulement (4, 5), avant leur tronçon de sortie (A) sont disposés des dispositifs de mise en rotation (12).
  4. Brûleur selon l'une ou plusieurs des revendications précédentes, caractérisé en ce que les canaux d'écoulement (4, 5) sont configurés de manière que le rapport de débit-masse, entre l'écoulement d'air primaire et l'écoulement d'air secondaire, soit supérieur à 0,4.
  5. Brûleur selon l'une des revendications précédentes, caractérisé en ce que le brûleur (1) présente une buse d'injection (15) par laquelle, dans le canal d'écoulement primaire (4), du carburant est injecté sur la paroi intérieure (14) du produit composant (6), en amont de la lèvre de pulvérisateur (6).
EP97936627A 1996-07-10 1997-07-08 Bruleur dote d'une buse de pulverisation Expired - Lifetime EP0910776B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19627760 1996-07-10
DE19627760A DE19627760C2 (de) 1996-07-10 1996-07-10 Brenner mit Zerstäuberdüse
PCT/EP1997/003595 WO1998001706A1 (fr) 1996-07-10 1997-07-08 Bruleur dote d'une buse de pulverisation

Publications (2)

Publication Number Publication Date
EP0910776A1 EP0910776A1 (fr) 1999-04-28
EP0910776B1 true EP0910776B1 (fr) 2001-08-22

Family

ID=7799420

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97936627A Expired - Lifetime EP0910776B1 (fr) 1996-07-10 1997-07-08 Bruleur dote d'une buse de pulverisation

Country Status (5)

Country Link
US (1) US6244051B1 (fr)
EP (1) EP0910776B1 (fr)
DE (2) DE19627760C2 (fr)
ES (1) ES2162683T3 (fr)
WO (1) WO1998001706A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1340940A1 (fr) 2002-02-21 2003-09-03 J. Eberspächer GmbH & Co. KG Buse d'atomisation pour un brûleur, en particulier pour un apparail de chauffage dans une voiture
EP1342950A2 (fr) 2002-02-11 2003-09-10 J. Eberspächer GmbH & Co. KG Buse d'atomisation pour un brûleur
DE10211590B4 (de) * 2002-03-15 2007-11-08 J. Eberspächer GmbH & Co. KG Zerstäuberdüse, insbesondere für ein Fahrzeugheizgerät

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19803879C1 (de) * 1998-01-31 1999-08-26 Mtu Muenchen Gmbh Zweistoffbrenner
KR100375051B1 (ko) * 2000-01-25 2003-03-08 (주) 젠터닷컴 실시간 홈쇼핑 구매시스템 및 방법과 그 프로그램 소스를 저장한 기록매체
DE102004002246A1 (de) * 2004-01-15 2005-08-11 J. Eberspächer GmbH & Co. KG Vorrichtung zur Erzeugung eines Luft/Kohlenwasserstoff-Gemischs
DE102005022772A1 (de) * 2005-05-12 2007-01-11 Universität Karlsruhe Brenner mit Teilvormischung und -vorverdampfung des flüssigen Brennstoffs
FR2903170B1 (fr) * 2006-06-29 2011-12-23 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
GB2444737B (en) * 2006-12-13 2009-03-04 Siemens Ag Improvements in or relating to burners for a gas turbine engine
US20130067923A1 (en) * 2011-09-20 2013-03-21 General Electric Company Combustor and method for conditioning flow through a combustor
US9423137B2 (en) * 2011-12-29 2016-08-23 Rolls-Royce Corporation Fuel injector with first and second converging fuel-air passages
EP3098514A1 (fr) * 2015-05-29 2016-11-30 Siemens Aktiengesellschaft Agencement de chambre de combustion
FR3057648B1 (fr) * 2016-10-18 2021-06-11 Safran Helicopter Engines Systeme d'injection pauvre de chambre de combustion de turbomachine
EP4202305A1 (fr) * 2021-12-21 2023-06-28 General Electric Company Buse de carburant et tourbillonneur
DE102022002113A1 (de) 2022-06-13 2023-12-14 Mercedes-Benz Group AG Brenner für ein Kraftfahrzeug, Verfahren zum Betreiben eines solchen Brenners sowie Kraftfahrzeug

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
GB1099959A (en) 1965-10-28 1968-01-17 Janos Miklos Beer Improvements in or relating to burners for pulverised coal or like solid fuel or for liquid or gaseous fuel
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
IN155686B (fr) 1981-02-27 1985-02-23 Westinghouse Electric Corp
GB2150277B (en) * 1983-11-26 1987-01-28 Rolls Royce Combustion apparatus for a gas turbine engine
US5285631A (en) 1990-02-05 1994-02-15 General Electric Company Low NOx emission in gas turbine system
DE4220060C2 (de) * 1992-06-19 1996-10-17 Mtu Muenchen Gmbh Einrichtung zur Betätigung einer den Durchsatz von Verbrennungsluft steuernden Dralleinrichtung eines Brenners für Gasturbinentriebwerke
DE4228816C2 (de) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke
GB2272756B (en) 1992-11-24 1995-05-31 Rolls Royce Plc Fuel injection apparatus
GB9326367D0 (en) * 1993-12-23 1994-02-23 Rolls Royce Plc Fuel injection apparatus
DE4444961A1 (de) * 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
US5836163A (en) * 1996-11-13 1998-11-17 Solar Turbines Incorporated Liquid pilot fuel injection method and apparatus for a gas turbine engine dual fuel injector

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342950A2 (fr) 2002-02-11 2003-09-10 J. Eberspächer GmbH & Co. KG Buse d'atomisation pour un brûleur
US6883730B2 (en) 2002-02-11 2005-04-26 J. Eberspächer GmbH & Co. KG Atomizing nozzle for a burner
DE10205573B4 (de) * 2002-02-11 2005-10-06 J. Eberspächer GmbH & Co. KG Zerstäuberdüse für einen Brenner
EP1340940A1 (fr) 2002-02-21 2003-09-03 J. Eberspächer GmbH & Co. KG Buse d'atomisation pour un brûleur, en particulier pour un apparail de chauffage dans une voiture
US6764302B2 (en) 2002-02-21 2004-07-20 J. Eberspacher Gmbh & Co. Kg Atomizing nozzle for a burner, especially for a heater that can be used on a vehicle
DE10207311B4 (de) * 2002-02-21 2005-06-09 J. Eberspächer GmbH & Co. KG Zerstäuberdüse für einen Brenner, insbesondere für ein an einem Fahrzeug einsetzbares Heizgerät
DE10211590B4 (de) * 2002-03-15 2007-11-08 J. Eberspächer GmbH & Co. KG Zerstäuberdüse, insbesondere für ein Fahrzeugheizgerät

Also Published As

Publication number Publication date
DE19627760A1 (de) 1998-01-15
ES2162683T3 (es) 2002-01-01
WO1998001706A1 (fr) 1998-01-15
US6244051B1 (en) 2001-06-12
DE59704382D1 (de) 2001-09-27
EP0910776A1 (fr) 1999-04-28
DE19627760C2 (de) 2001-05-03

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