EP2385304A2 - Brûleur de prémélange maigre d'un moteur à turbine à gaz doté d'un corps central concentrique et annulaire - Google Patents

Brûleur de prémélange maigre d'un moteur à turbine à gaz doté d'un corps central concentrique et annulaire Download PDF

Info

Publication number: EP2385304A2
Authority: EP; European Patent Office
Prior art keywords: burner; fuel; lean burn; annular; region
Prior art date: 2010-05-07
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

EP11003576A

Other languages

German (de)

English (en)

Other versions

EP2385304A3 (fr

EP2385304B8 (fr

EP2385304B1 (fr

Inventor

Imon-Kalyan Bagchi

Waldemar Lazik

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

Rolls Royce Deutschland Ltd and Co KG

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.)

2010-05-07

Filing date

2011-05-02

Publication date

2011-11-09

2011-05-02 Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG

2011-11-09 Publication of EP2385304A2 publication Critical patent/EP2385304A2/fr

2014-11-19 Publication of EP2385304A3 publication Critical patent/EP2385304A3/fr

2016-04-20 Application granted granted Critical

2016-04-20 Publication of EP2385304B1 publication Critical patent/EP2385304B1/fr

2016-07-13 Publication of EP2385304B8 publication Critical patent/EP2385304B8/fr

Status Not-in-force legal-status Critical Current

2031-05-02 Anticipated expiration legal-status Critical

Links

UHZZMRAGKVHANO-UHFFFAOYSA-M chlormequat chloride Chemical compound [Cl-].C[N+](C)(C)CCCl UHZZMRAGKVHANO-UHFFFAOYSA-M 0.000 title 1
239000000446 fuel Substances 0.000 claims abstract description 53
238000002485 combustion reaction Methods 0.000 claims description 8
MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 6
230000000694 effects Effects 0.000 description 5
238000000889 atomisation Methods 0.000 description 4
230000002349 favourable effect Effects 0.000 description 4
239000007789 gas Substances 0.000 description 4
230000015572 biosynthetic process Effects 0.000 description 3
239000003381 stabilizer Substances 0.000 description 3
230000001133 acceleration Effects 0.000 description 2
239000000203 mixture Substances 0.000 description 2
238000011144 upstream manufacturing Methods 0.000 description 2
230000003111 delayed effect Effects 0.000 description 1
230000001419 dependent effect Effects 0.000 description 1
238000001704 evaporation Methods 0.000 description 1
230000008020 evaporation Effects 0.000 description 1
239000007788 liquid Substances 0.000 description 1
239000003595 mist Substances 0.000 description 1
239000006199 nebulizer Substances 0.000 description 1
230000010355 oscillation Effects 0.000 description 1
238000007788 roughening Methods 0.000 description 1
238000000926 separation method Methods 0.000 description 1
238000004544 sputter deposition Methods 0.000 description 1
230000006641 stabilisation Effects 0.000 description 1
238000011105 stabilization Methods 0.000 description 1
230000003319 supportive effect Effects 0.000 description 1
238000009736 wetting Methods 0.000 description 1

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
- 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

Definitions

the invention relates to a lean burn burner of a gas turbine engine according to the features of the preamble of claim 1.
the invention relates to a lean burn burner of a gas turbine engine having an annular central body substantially concentric with a burner central axis which has an annular duct connected to a supply duct and at least one of a film layer flared at a fuel exit side in its radially inward facing region a connected to the annular channel fuel outlet opens.
Combustion chambers of gas turbine engines can be equipped with lean burn burners to burn in the combustion chamber, a fuel-air mixture with high air content and low combustion temperature and correspondingly reduced nitrogen oxide formation.
lean burn burners to burn in the combustion chamber, a fuel-air mixture with high air content and low combustion temperature and correspondingly reduced nitrogen oxide formation.
Such burners can, as in the EP 1 801 504 described, with an annular atomizer lip having a circumferential fuel film. On the film laying surface is - evenly distributed on this opening feed channels - applied a steady fuel film, which is acted upon by a concentric, swirled by swirl elements air flow. In this way, a high atomization effect and an intensive mixing of air and fuel can be achieved.
the invention has the object of providing a lean burn burner of the type mentioned in such a way that on the Filmlege Design a stable, evenly distributed fuel film is produced, which breaks off evenly at the trailing edge and forms a fine droplet mist to quiet and uniform combustion at low temperature , to ensure low nitrogen oxide formation and good burnout.
the film applicator adjacent to the fuel outlet openings, at the area facing the fuel outlet side comprises a step-like, annular projection area pointing radially to the burner center axis.
This projection region may be annular, so that there is a step in the flow, which flows along the film depositor at its fuel outlet side, where the fuel is discharged.
the flow along the surface is influenced so that at this positive stage or this positive projection results in an acceleration of the air flow, so that the fuel comes into contact with air flow areas with increased speed.
This results in more favorable boundary layer effects which lead to a more uniform and stable fuel distribution.
This results according to the invention thus a more homogeneous fuel input and a improved premix.
the invention makes it possible, with increasing diameters of film layers and low fuel mass flows, to apply a continuous fuel film to the film-laying surface.
the resulting better combustion through the burner results in particular at medium thrust settings of the gas turbine engine considerable advantages.
the projecting region is likewise conical and thus preferably has the same cone angle as the remaining conical region of the film applicator upstream of the projecting region.
the step-like projection area is rounded.
the fuel emerging from the fuel outlet opening is thus guided smoothly around the rounded edge of the projection area. This in turn favors film education and downstream atomization.
the surface of the film applicator arranged downstream of the burner outlet opening is provided with a roughened surface.
This roughened surface may be formed by sandblasted areas, by introduced recesses, by grooves or by grooves.
the roughened surface results in an improved contact angle for liquid drops applied to the surface.
the wettability of the surface is thus improved, since more favorable surface tensions result, which are related to the contact angle via the Young's equation and thus make it a measure of the wettability.
the smaller the contact angle the greater the wettability of the surface of the film layer by the fuel. Thanks to these measures, channel formation is counteracted and a continuous fuel film is made possible.
the in Fig. 1 Magervormischbrenner shown has a burner center axis 1, to which the components are arranged substantially concentric.
the lean burn burner has a support burner 11, which is formed according to the prior art and which is supplied with fuel through a fuel line 12.
the support burner 11 is surrounded by swirl elements 13, as is known from the prior art.
a flame stabilizer 14 is provided, which is also formed according to the prior art, so that can be dispensed with a detailed description at this point.
Radially outside the flame stabilizer 14, at least one swirl element 15 is likewise arranged.
the lean burn burner according to the invention has an annular central body 2, in which a supply line 3 for fuel is formed.
the supply line 3 opens into an annular channel 4 through which Fuel can escape through at least one fuel outlet opening 6 (see also Fig. 3 ).
the annular central body 2 forms a film layer 5, which is conical and widens radially outward in the flow direction. Radially pointing inwards, a film-laying surface is formed on the film-laying member 5, which ends in the axial direction at a sputtering lip 16.
At least one swirl element 17 is arranged, which is bounded radially outside by an outer ring 18.
a projection region 7 is formed adjacent to the fuel outlet opening 6 on the film layer 5 (see FIG Fig. 2 and 3 ).
This projection region 7 thus forms at its Anström Scheme, adjacent to the fuel outlet opening 6, rounded stage through which an acceleration of the flow takes place, as indicated by the flow arrows in Fig. 2 is shown.
the projection region 7 thus forms part of a fuel exit side 8 of the film layer 5.
the projection region 7 is also conical, as is the case in particular from FIGS Fig. 2 and 3 results.
the conicity is formed with the same cone angle as the conicity of the fuel exit side 8 of the film layer 5.
an offset 19 is formed, which leads to a reduced diameter.
the Anström Scheme 20 of the formed by the projection portion 7 edge or step is rounded, so that there is an optimized flow.
the Fig. 3 Fig. 11 also shows a cone angle 21 of the projecting portion 7 which is equal to the cone angle upstream of the fuel outlets.
the Fig. 5 shows a modified embodiment, in which downstream of the fuel outlet openings, an additional groove 10 or groove is formed, which is arranged in a plane perpendicular to the burner central axis 1 level and leads to a further fuel film stabilization.
the Fig. 6 shows an enlarged detail of the representation of Fig. 5 ,
the reference numeral 22 shows the groove depth, measured perpendicular to the surface.
Reference numeral 23 denotes the flank angle of the groove 10.
the Fig. 4 shows in the right side of an inventively designed surface 9 of the film layer 5, while in the left half of the Fig. 4 a smooth, the prior art corresponding surface is shown.
the Fig. 5 shows that by roughening the surface 9, an optimized contact angle 24 can be achieved, which leads to a better wetting of the surface of the film layer 5 with fuel. This is a measure which considerably increases the effect of the projection area 7, since the fuel emerging from the burner outlet opening and guided over the rounded edge of the onflow area 20 of the projection area 7 can be guided in a more uniform, thin layer along the surface 9 of the film layer 5 without that it comes to clot currents.

Landscapes

Engineering & Computer Science (AREA)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Spray-Type Burners (AREA)

EP11003576.3A 2010-05-07 2011-05-02 Brûleur de prémélange maigre d'un moteur à turbine à gaz doté d'un corps central concentrique et annulaire Not-in-force EP2385304B8 (fr)

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
DE201010019772 DE102010019772A1 (de)	2010-05-07	2010-05-07	Magervormischbrenner eines Gasturbinentriebwerks mit einem konzentrischen, ringförmigen Zentralkörper

Publications (4)

Publication Number	Publication Date
EP2385304A2 true EP2385304A2 (fr)	2011-11-09
EP2385304A3 EP2385304A3 (fr)	2014-11-19
EP2385304B1 EP2385304B1 (fr)	2016-04-20
EP2385304B8 EP2385304B8 (fr)	2016-07-13

Family

ID=44314098

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP11003576.3A Not-in-force EP2385304B8 (fr)	2010-05-07	2011-05-02	Brûleur de prémélange maigre d'un moteur à turbine à gaz doté d'un corps central concentrique et annulaire

Country Status (3)

Country	Link
US (1)	US8943828B2 (fr)
EP (1)	EP2385304B8 (fr)
DE (1)	DE102010019772A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102012002664A1 (de) *	2012-02-10	2013-08-14	Rolls-Royce Deutschland Ltd & Co Kg	Gasturbinenvormischbrenner
GB201317241D0 (en)	2013-09-30	2013-11-13	Rolls Royce Plc	Airblast Fuel Injector
ITUB20159388A1 (it) *	2015-12-29	2017-06-29	Ge Avio Srl	Gruppo di iniezione perfezionato per un combustore di una turbina a gas
US10808934B2 (en) *	2018-01-09	2020-10-20	General Electric Company	Jet swirl air blast fuel injector for gas turbine engine
WO2020049861A1 (fr)	2018-09-06	2020-03-12	株式会社Ihi	Injecteur de combustible liquide
GB201820206D0 (en) *	2018-12-12	2019-01-23	Rolls Royce Plc	A fuel spray nozzle
US11378275B2 (en) *	2019-12-06	2022-07-05	Raytheon Technologies Corporation	High shear swirler with recessed fuel filmer for a gas turbine engine
DE102020106842A1 (de)	2020-03-12	2021-09-16	Rolls-Royce Deutschland Ltd & Co Kg	Düse mit Strahlerzeugerkanal für in eine Brennkammer eines Triebwerks einzuspritzenden Kraftstoff
JP2024043147A (ja) *	2022-09-16	2024-03-29	三菱重工航空エンジン株式会社	航空エンジン用燃焼器
GB202405296D0 (en) *	2024-04-15	2024-05-29	Rolls Royce Plc	Nozzle body for fuel injector

Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US6560964B2 (en)	1999-05-07	2003-05-13	Parker-Hannifin Corporation	Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
EP1801504A2 (fr)	2005-12-22	2007-06-27	Rolls-Royce Deutschland Ltd & Co KG	Brûleur de prémélange maigre pourvu d'une lèvre de diffuseur

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
GB1380931A (en) *	1971-01-11	1975-01-15	Lefebvre A H	Methods of liquid fuel injection and to airblast atomizers
US5329760A (en) *	1991-10-07	1994-07-19	Fuel Systems Textron, Inc.	Self-sustaining fuel purging fuel injection system
GB0219458D0 (en) *	2002-08-21	2002-09-25	Rolls Royce Plc	Fuel injection apparatus
US6986255B2 (en) *	2002-10-24	2006-01-17	Rolls-Royce Plc	Piloted airblast lean direct fuel injector with modified air splitter
GB0516208D0 (en) *	2005-08-05	2005-09-14	Rolls Royce Plc	Fuel injector
US7878000B2 (en) *	2005-12-20	2011-02-01	General Electric Company	Pilot fuel injector for mixer assembly of a high pressure gas turbine engine
US7506510B2 (en)	2006-01-17	2009-03-24	Delavan Inc	System and method for cooling a staged airblast fuel injector
GB2439097B (en)	2006-06-15	2008-10-29	Rolls Royce Plc	Fuel injector
JP4364911B2 (ja) *	2007-02-15	2009-11-18	川崎重工業株式会社	ガスタービンエンジンの燃焼器
US7926744B2 (en) *	2008-02-21	2011-04-19	Delavan Inc	Radially outward flowing air-blast fuel injector for gas turbine engine

2010
- 2010-05-07 DE DE201010019772 patent/DE102010019772A1/de not_active Withdrawn
2011
- 2011-05-02 US US13/098,610 patent/US8943828B2/en not_active Expired - Fee Related
- 2011-05-02 EP EP11003576.3A patent/EP2385304B8/fr not_active Not-in-force

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US6560964B2 (en)	1999-05-07	2003-05-13	Parker-Hannifin Corporation	Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
EP1801504A2 (fr)	2005-12-22	2007-06-27	Rolls-Royce Deutschland Ltd & Co KG	Brûleur de prémélange maigre pourvu d'une lèvre de diffuseur

Also Published As

Publication number	Publication date
US8943828B2 (en)	2015-02-03
EP2385304A3 (fr)	2014-11-19
EP2385304B8 (fr)	2016-07-13
EP2385304B1 (fr)	2016-04-20
DE102010019772A1 (de)	2011-11-10
US20110271680A1 (en)	2011-11-10

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