WO1998001706A1 - Brenner mit zerstäuberdüse - Google Patents
Brenner mit zerstäuberdüse Download PDFInfo
- Publication number
- WO1998001706A1 WO1998001706A1 PCT/EP1997/003595 EP9703595W WO9801706A1 WO 1998001706 A1 WO1998001706 A1 WO 1998001706A1 EP 9703595 W EP9703595 W EP 9703595W WO 9801706 A1 WO9801706 A1 WO 9801706A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flow
- burner
- component
- air
- lip
- Prior art date
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
- 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 described in German patent application P 4444 961.
- the pollutant-reduced combustion chamber is a starting point.
- Components of the combustion chamber have to be optimized in order to implement the pollutant-reduced combustion concepts.
- the fuel must be atomized as finely as possible in all operating areas and mixed with the combustion air. This fuel preparation is carried out in the combustion chambers of modern aircraft gas turbines with air atomizing nozzles. According to their functional principle, the fuel flows on a cylindrical surface to the end where, due to the air Shear forces that atomize.
- the air flow through the atomizer nozzle is divided into a primary and secondary flow channel and swirled in opposite directions, so that counter-rotating vortices are generated in the combustion chamber Flow channel assigned to a radially inflated swirl device A high swirl number of the air Electricity also leads to a recirculation vortex on the rear wall of the combustion chamber, which is to achieve homogeneous combustion.
- the atomizer lip which separates the primary from the secondary air stream, is extended as far as possible to the mouth of the atomizer nozzle on the combustion chamber side. In the case of convergent-divergent flow channels, however, this has the consequence that the atomization does not take place in the region of the maximum air shear forces and, for this reason, the atomization does not reach the possible optimum.
- the mass flow of the secondary air flow must be greater than that of the primary air flow, so that the peripheral impulse of the secondary air flow is not completely reduced in the short distance from the end of the atomizer lip to the entry into the combustion chamber and the formation of the recirculation vortex is endangered.
- the invention has the advantage that the twisting of the two air streams in the same direction causes them to mix before entering the combustion chamber 3 does not have to be avoided to a high peripheral speed, so that the mass flow ratio can be selected independently of the swirl of the currents in order to be able to make the distribution of the air-fuel mixture homogeneous. Regardless of a mixture of the two currents, the swirl number of the
- Air flow can be varied to set a detached or wall-mounted flow state in the combustion chamber.
- the atomizer lip By positioning the atomizer lip at the narrowest flow cross section in the atomizer nozzle or shortly before, the atomization of the fuel can take place in a range of the maximum air shear forces, so that the atomization can take place optimally.
- FIG. 1 shows a half section of a front combustion chamber section with a burner
- Fig. 2a in half section the flow state in the combustion chamber and in the
- Fig. 2b in half section the flow state in the combustion chamber and in the atomizer nozzle with wall-flowing flow.
- the burner 1 shown in FIG. 1 is one of several annularly arranged burners of the combustion chamber 2, which is shown in sections, of an aircraft gas turbine (not shown further).
- 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 channel flow of the two flow channels 4, 5 is determined and limited by annular or sleeve-shaped components 6, 7.
- the two led concentrically to the Btenner axis Z.
- Flow channels 4, 5 each have a radially extending inlet section E, in order then to be deflected into an essentially axially extending outlet section A.
- the sleeve-shaped component 6 separates the two channels 4, 5 from one another and has an annular atomizer lip 8 with a conically tapering course in its downstream section. At its upstream section, the component 6 has a radially extending flange 9, which separates the two axially spaced, annular inlet sections E of the channels 4, 5.
- the secondary flow channel 5 running between the two components 6 and 7 is, in its radially extending inlet section E, of two annular wall sections of the two components running parallel to one another
- the secondary flow channel 5 is delimited radially outwards by an inner wall I of the component 7, which is convergent-divergent, viewed in the flow direction.
- the atomizer lip 8 ends immediately before the location with the narrowest flow cross section Q, which is defined by the convergent-divergent profile of the component 7, so that downstream of the atomizer lip 8, within the divergent portion of the component 7 and downstream thereof, a homogeneous mixing of the two air streams he follows.
- Fuel is finely atomized onto the conically tapered inner wall of the atomizer lip 8 by means of the injection nozzle 15 arranged in the primary flow channel 4 in the form of a cone which widens downstream in the manner of a fan, so that it deposits on the inner wall like a film.
- the fuel film tears off in the form of a shear flow, so that the fuel is introduced into the rotary vortex W forming in the combustion chamber 11 of the combustion chamber 2 in a mist-like and partly vaporous manner and evenly distributed.
- the swirl of the air flow in the flow channels 4 and 5, which is generated by swirl devices 12 arranged in the inlet sections E of the flow channels 4 and 5, is responsible for the formation of the rotation vortex W.
- the cross sections of the two flow channels 4, 5 are dimensioned in such a way that a mass flow ratio between primary and secondary air flow of greater than 0.4 results. This ensures homogeneous mixing of the combustion chamber with the air / fuel mixture.
- the air flow opens downstream of the divergent section of the component 7 into the combustion chamber and flows parallel to the radially extending rear wall 13 of the combustion chamber 11, in order to then flow centrally in a recirculation vortex W approximately parallel to the burner axis Z in the direction of Stream 1 burner.
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
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/214,833 US6244051B1 (en) | 1996-07-10 | 1997-07-08 | Burner with atomizer nozzle |
EP97936627A EP0910776B1 (de) | 1996-07-10 | 1997-07-08 | Brenner mit zerstäuberdüse |
DE59704382T DE59704382D1 (de) | 1996-07-10 | 1997-07-08 | Brenner mit zerstäuberdüse |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19627760.4 | 1996-07-10 | ||
DE19627760A DE19627760C2 (de) | 1996-07-10 | 1996-07-10 | Brenner mit Zerstäuberdüse |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998001706A1 true WO1998001706A1 (de) | 1998-01-15 |
Family
ID=7799420
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP1997/003595 WO1998001706A1 (de) | 1996-07-10 | 1997-07-08 | Brenner mit zerstäuberdüse |
Country Status (5)
Country | Link |
---|---|
US (1) | US6244051B1 (de) |
EP (1) | EP0910776B1 (de) |
DE (2) | DE19627760C2 (de) |
ES (1) | ES2162683T3 (de) |
WO (1) | WO1998001706A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100375051B1 (ko) * | 2000-01-25 | 2003-03-08 | (주) 젠터닷컴 | 실시간 홈쇼핑 구매시스템 및 방법과 그 프로그램 소스를 저장한 기록매체 |
EP1344978A1 (de) * | 2002-03-15 | 2003-09-17 | J. Eberspächer GmbH & Co. KG | Zerstäuberdüse, insbesondere für ein Fahrzeugheizgerät |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19803879C1 (de) * | 1998-01-31 | 1999-08-26 | Mtu Muenchen Gmbh | Zweistoffbrenner |
DE10205573B4 (de) * | 2002-02-11 | 2005-10-06 | J. Eberspächer GmbH & Co. KG | Zerstäuberdüse für einen Brenner |
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 |
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 (de) * | 2015-05-29 | 2016-11-30 | Siemens Aktiengesellschaft | Brennkammer |
FR3057648B1 (fr) * | 2016-10-18 | 2021-06-11 | Safran Helicopter Engines | Systeme d'injection pauvre de chambre de combustion de turbomachine |
EP4202305A1 (de) * | 2021-12-21 | 2023-06-28 | General Electric Company | Brennstoffdüse und verwirbler |
DE102022002113A1 (de) | 2022-06-13 | 2023-12-14 | Mercedes-Benz Group AG | Brenner für ein Kraftfahrzeug, Verfahren zum Betreiben eines solchen Brenners sowie Kraftfahrzeug |
US12007115B1 (en) | 2023-02-28 | 2024-06-11 | Rtx Corporation | High shear swirler for gas turbine engine |
Citations (5)
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 |
GB2094464A (en) * | 1981-02-27 | 1982-09-15 | Westinghouse Electric Corp | Gas turbine combustor |
US5285631A (en) * | 1990-02-05 | 1994-02-15 | General Electric Company | Low NOx emission in gas turbine system |
GB2272756A (en) * | 1992-11-24 | 1994-05-25 | 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 |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4180974A (en) * | 1977-10-31 | 1980-01-01 | General Electric Company | Combustor dome sleeve |
GB2150277B (en) * | 1983-11-26 | 1987-01-28 | Rolls Royce | Combustion apparatus for a gas turbine engine |
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 |
GB9326367D0 (en) * | 1993-12-23 | 1994-02-23 | Rolls Royce Plc | Fuel injection apparatus |
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 |
-
1996
- 1996-07-10 DE DE19627760A patent/DE19627760C2/de not_active Expired - Fee Related
-
1997
- 1997-07-08 US US09/214,833 patent/US6244051B1/en not_active Expired - Lifetime
- 1997-07-08 WO PCT/EP1997/003595 patent/WO1998001706A1/de active IP Right Grant
- 1997-07-08 ES ES97936627T patent/ES2162683T3/es not_active Expired - Lifetime
- 1997-07-08 DE DE59704382T patent/DE59704382D1/de not_active Expired - Lifetime
- 1997-07-08 EP EP97936627A patent/EP0910776B1/de not_active Expired - Lifetime
Patent Citations (5)
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 |
GB2094464A (en) * | 1981-02-27 | 1982-09-15 | Westinghouse Electric Corp | Gas turbine combustor |
US5285631A (en) * | 1990-02-05 | 1994-02-15 | General Electric Company | Low NOx emission in gas turbine system |
GB2272756A (en) * | 1992-11-24 | 1994-05-25 | 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 |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100375051B1 (ko) * | 2000-01-25 | 2003-03-08 | (주) 젠터닷컴 | 실시간 홈쇼핑 구매시스템 및 방법과 그 프로그램 소스를 저장한 기록매체 |
EP1344978A1 (de) * | 2002-03-15 | 2003-09-17 | J. Eberspächer GmbH & Co. KG | Zerstäuberdüse, insbesondere für ein Fahrzeugheizgerät |
Also Published As
Publication number | Publication date |
---|---|
DE59704382D1 (de) | 2001-09-27 |
US6244051B1 (en) | 2001-06-12 |
DE19627760A1 (de) | 1998-01-15 |
ES2162683T3 (es) | 2002-01-01 |
DE19627760C2 (de) | 2001-05-03 |
EP0910776B1 (de) | 2001-08-22 |
EP0910776A1 (de) | 1999-04-28 |
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