EP2526341A1 - Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injection - Google Patents
Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injectionInfo
- Publication number
- EP2526341A1 EP2526341A1 EP11706299A EP11706299A EP2526341A1 EP 2526341 A1 EP2526341 A1 EP 2526341A1 EP 11706299 A EP11706299 A EP 11706299A EP 11706299 A EP11706299 A EP 11706299A EP 2526341 A1 EP2526341 A1 EP 2526341A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- injection device
- ducts
- ring
- radial
- retaining ring
- 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 title claims description 10
- 238000003466 welding Methods 0.000 claims abstract description 6
- 238000002347 injection Methods 0.000 claims description 44
- 239000007924 injection Substances 0.000 claims description 44
- 239000000446 fuel Substances 0.000 claims description 16
- 239000000203 mixture Substances 0.000 claims description 5
- 230000001413 cellular effect Effects 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract 1
- 238000011144 upstream manufacturing Methods 0.000 description 7
- 239000011324 bead Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000002245 particle Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
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
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
Definitions
- the invention relates to an injection device adapted to provide a mixture of air and suitable fuel which will then be burned in the combustion chamber of a turbomachine.
- the invention also relates to a combustion chamber equipped with such an injection device.
- each turbomachine combustion chamber at least one injector provides fuel which is mixed with air in an injection device attached to the bottom wall of the chamber.
- the air comes from the last stage of a compressor of the turbomachine and is introduced into the injection device annularly.
- the fuel is introduced upstream by a nozzle, formed at the end of a pipe, and fitted into a centering guide fitted to the injection device. Air and fuel are mixed and then burned in the chamber to generate highly gases.
- the introduction of air is conventionally performed in the injection device 1 through a whirlpool 4 formed of two annular parts, 12 and 14, each having cells 15 of air suction distributed circumferentially.
- a retaining ring or cover 16 makes it possible, by welding to the upstream part 12 - according to the flow of the fuel - to couple a fuel injection pipe 17 to the honeycomb parts.
- the cellular parts 12 and 14 succeed each other axially and are welded to one another.
- the cells form a multitude of slots 15 which extend radially and are disposed on the circumference of each piece.
- Welds 18 and 19 for joining the parts form radial walls for these slots 15.
- Said slots are oriented from one room to another in two directions making opposite angles with respect to any radius centered on the axis. Air vortices in opposite directions form in venturises air layers that overlap, and in which the fuel particles come to mix homogeneously, which promotes air-fuel mixture.
- Such an injection device thus comprises three annular welds: the welds, 18 and 19, solidarisant each annular piece, and a weld 20 between the retaining ring 16 and the first part 12.
- the welds close to the slots 15 require to develop costly specific means for limiting the deformation of the slots during manufacture.
- the welds 18 to 20 of the injection device 1 are difficult to achieve and do not have a reproducible nature.
- the welds 18 and 19 deform the slots, which affects the flow of air.
- the invention aims to remedy these problems, particularly it aims to achieve a significantly lower cost injection device, easier to manufacture and more robust.
- the invention proposes to configure the parts according to a particular interlocking to overcome the welding between the honeycomb parts.
- the subject of the present invention is a device for injecting a fuel-air mixture
- a whirlpool having at least two annular air intake parts, external and internal. , a centering guide and a retaining ring, and wherein the annular parts have ducts opening out into outer and inner coaxial venturis, formed by internal axial walls.
- the parts are mounted coaxially, the inner part being adapted to be self-centered in the outer part by contacting axial and radial walls.
- the retaining ring, the outer part and the inner part are welded together in the same radial plane along opposite radial faces, the retaining ring covering the centering guide to keep it in a radial housing.
- the weld bead then immobilizes the inner part in rotation.
- the air ducts of the outer part are regularly distributed on two crowns orthogonal to the axis, the ducts of a crown can be oriented at an angle opposite to or in the same direction as that of the ducts of the other crown relative to a radius from the axis;
- the ducts of the inner part are arranged in the extension of the ducts of one ring of the outer piece and open into the internal venturi, the ducts of the other ring of the outer piece opening into a space formed between the internal venturis and external;
- the ducts of the inner part are adapted to be made in the extension of the conduits of a ring of the outer part after centering of the inner part in the outer part and welding with the retaining ring;
- the ducts are of substantially the same size in at least two perpendicular directions, in particular the ducts are cylindrical with a circular or square section;
- the number of conduits of the crowns is identical, the ducts of a ring being offset by a half step on the periphery of the outer part;
- the retaining ring has a radial chamfer able to facilitate the positioning of the inner part on the outer part
- the centering guide which receives the injection nozzle is adaptable in position in a radial housing formed between the radial wall of the retaining ring and the radial wall of the inner part by a suitable dimensioning of the retaining ring and / or a flange formed on the centering guide.
- the invention also relates to a combustion chamber equipped with an injection device as defined above.
- the chamber comprises an annular wall and a bottom wall, means for fixing the injection device being arranged in the bottom wall of the chamber which has a passage opening of the fuel injection nozzle coupled to the centering guide.
- FIG. 2 is a perspective view of an exemplary embodiment of an injection device according to the present invention.
- FIG. 3 a view in longitudinal section of the previous embodiment, and
- the second alveolar part 24 of the whirlpool 40 - said internal part - is coaxial with the first and form, on the side facing the combustion chamber 100, an internal venturi 26, located in the opening 29 of the outer venturi 28 formed by the inner wall of the first piece 22.
- the cells of the piece 22 are cylindrical ducts 25a and 25a 'of circular section, regularly distributed along two annular rings C1 and C2, and respectively oriented in two directions forming two angles of opposite direction relative to any radius perpendicular to the axis of symmetry X'X of the injection device 2.
- the number of ducts of each ring is identical and the ducts are shifted by half a step on the outer periphery of the piece 22.
- the longitudinal sectional view of Figure 3 illustrates the assembly between the various component elements.
- This injection device 2 The longitudinal wall 220 of the outer part 22 has an outer face 22e, parallel to the axis X'X, and an inner face 22i parallel - upstream - to the axis X'X and which narrows - downstream - towards the opening 29, in the direction of the combustion chamber 100.
- This part which is tightened forms the external venturi 28.
- the inner 22i and outer 22e faces of the outer piece 22 are connected upstream by a radial face 22p perpendicular to the axis X'X.
- the second part 24 or inner part, coaxial and concentric with the outer part 22, has a so-called radial wall 241, perpendicular to the axis X'X, and a so-called longitudinal wall 240 extending along this axis of symmetry.
- the radial wall 241 has a downstream face 24a and the longitudinal wall 240 an outer face 24e disposed respectively against the faces 22p and 22i of the part 22.
- the ducts 25a of the first ring of the part 22 are extended by conduits 25b formed in the extension of the first conduits 25a. The ducts are made after assembly, once the two parts 22 and 24 of the swirler nested one into the other by their facing faces and welded to the retaining ring 21, which ensures perfect alignment.
- the outer face 24e of the wall 240 of the inner part 24 remains against the inner face 22i of the outer part only in their upstream portion.
- the wall 240 does not remain parallel to the axis X'X but narrows towards this axis to form, on its internal face 24i, the internal venturi 26 and form, from its outer face 24e, a space venturi E between the two venturis 26 and 28. In this space E, open the ducts 25a 'of the second ring of the part 22.
- the radial wall 241 is capped by the retaining ring 21 whose outer annular face 21 C comes in extension of the outer annular surface 22 of the outer part 22, parallel to the axis of symmetry X'X .
- the ring 21 has an annular wall 210 and a radial wall 21 1.
- a radial recess L is defined between the radial walls 21 1 and 241 for the flange 27c of the centering guide 27.
- the radial recess L is oversized relative to the flange 27c by appropriate dimensioning of the radial and annular walls 21 1 and 210 of the ring, so that the guide 27 adapts in position by displacement in the plane of the housing L.
- an appropriate dimensioning of the flange 27c of the centering guide 27 also allows to offer a double degree of freedom to this guide.
- the annular wall 210 advantageously has a chamfer 21 C on the inside to position the workpiece 24 on the workpiece 22.
- the workpiece 22 is welded to the ring 21 and to the inner workpiece 24 by the bead 30 deposited in the same radial plane P between the radial face 22p of the outer piece 22, on the one hand, and the radial faces 21a of the ring 21 and 24a of the inner piece 24 facing each other, 'somewhere else.
- At least one of the walls to be welded is advantageously bevelled to perform this welding.
- the inner part 24 is then self-centered on two perpendicular walls by interlocking in the first part 22, and the weld bead 30 immobilizes it in rotation.
- the sections of the injection device 2 according to Figures 4a and 4b illustrate the opposite direction of the two sets of ducts 25a and 25b on the one hand and 25a 'on the other hand ,. On these cuts, also appear external and internal parts, 22 and 24, the internal venturi 26 and the inter vent space E (FIG. 4b).
- the angles A and A 'of opposite direction formed by these ducts with respect to radii R and R' passing through the axis of symmetry X'X and through the center of the ducts 25a and 25a 'at the periphery of the injection device 2 are between +/- 20 to 40 °.
- the injection device is then fixed in a chamber which has an annular wall and a bottom wall.
- the attachment means of the injection device are arranged in the bottom wall of the chamber which has a passage opening for the fuel injection nozzle to be coupled to the centering guide.
- the fuel is injected into each injection device by a nozzle engaged on the centering guide 27 ( Figure 3) and the air by the annular conduits.
- the air penetrates at the speed of 25g / s, about 245 m / s, and the fuel at 5g / s, about 50 m / s.
- the air vortices form in the internal venturi 26 and in the inter venturi space E opposite air plies that will overlap at the entrance of the combustion chamber.
- the fuel particles injected come to mix fluidly and uniformly, which achieves a powerful air-fuel mixture.
- the invention is not limited to the embodiment described and shown. It is for example possible to form more than two crowns of conduits, for example four crowns, two of which open on the inter-venturi space and two others in the internal venturi.
- the gyration effect produced by the venturis is balanced in the various duct crowns by adapting the angles of inclination of the ducts.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Gas Burners (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL11706299T PL2526341T3 (pl) | 2010-01-18 | 2011-01-18 | Urządzenie do wtryskiwania i komora spalania maszyny wirowej wyposażona w takie urządzenie do wtryskiwania |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1050286A FR2955375B1 (fr) | 2010-01-18 | 2010-01-18 | Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injection |
PCT/FR2011/050085 WO2011086336A1 (fr) | 2010-01-18 | 2011-01-18 | Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injection |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2526341A1 true EP2526341A1 (fr) | 2012-11-28 |
EP2526341B1 EP2526341B1 (fr) | 2013-11-13 |
Family
ID=42740371
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11706299.2A Active EP2526341B1 (fr) | 2010-01-18 | 2011-01-18 | Dispositif d'injection et chambre de combustion de turbomachine équipée d'un tel dispositif d'injection |
Country Status (11)
Country | Link |
---|---|
US (1) | US9188338B2 (fr) |
EP (1) | EP2526341B1 (fr) |
JP (1) | JP5676647B2 (fr) |
KR (1) | KR101729362B1 (fr) |
CN (1) | CN102713440B (fr) |
CA (1) | CA2786541C (fr) |
ES (1) | ES2443031T3 (fr) |
FR (1) | FR2955375B1 (fr) |
PL (1) | PL2526341T3 (fr) |
RU (1) | RU2549378C2 (fr) |
WO (1) | WO2011086336A1 (fr) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102665009A (zh) * | 2012-05-17 | 2012-09-12 | 江苏经贸职业技术学院 | 一种高效绿色通信办公桌 |
FR2994713B1 (fr) * | 2012-08-21 | 2018-06-29 | Snecma | Injecteur pour tete d'injection d'une chambre de combustion |
KR101631891B1 (ko) * | 2014-12-18 | 2016-06-20 | 한국항공우주연구원 | 핀틀-스월 혼합형 추진제 분사장치 |
KR101709446B1 (ko) * | 2016-10-04 | 2017-02-22 | 유세권 | 알루미늄 합금 용탕의 붕화물 교반 장치 |
CN106545887A (zh) * | 2016-10-09 | 2017-03-29 | 上海交通大学 | 一种沼气旋流预混喷嘴装置 |
US20190056108A1 (en) * | 2017-08-21 | 2019-02-21 | General Electric Company | Non-uniform mixer for combustion dynamics attenuation |
JP2019158276A (ja) * | 2018-03-15 | 2019-09-19 | 株式会社ハーマン | ブンゼン式ガスバーナのガス噴射ノズル装置 |
US11073114B2 (en) | 2018-12-12 | 2021-07-27 | General Electric Company | Fuel injector assembly for a heat engine |
CN113074899B (zh) * | 2021-06-08 | 2021-08-13 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种低压文氏管组平面分布结构及安装方法 |
US11815269B2 (en) | 2021-12-29 | 2023-11-14 | General Electric Company | Fuel-air mixing assembly in a turbine engine |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2044431B (en) * | 1979-03-20 | 1983-03-16 | Rolls Royce | Gas turbine |
US4854127A (en) * | 1988-01-14 | 1989-08-08 | General Electric Company | Bimodal swirler injector for a gas turbine combustor |
US4930703A (en) * | 1988-12-22 | 1990-06-05 | General Electric Company | Integral fuel nozzle cover for gas turbine combustor |
RU2083926C1 (ru) * | 1993-04-13 | 1997-07-10 | Виноградов Евгений Дмитриевич | Фронтовое устройство камеры сгорания |
RU2157954C2 (ru) * | 1995-09-05 | 2000-10-20 | Открытое акционерное общество "Самарский научно-технический комплекс им. Н.Д.Кузнецова" | Топливовоздушная горелка |
US6550251B1 (en) * | 1997-12-18 | 2003-04-22 | General Electric Company | Venturiless swirl cup |
RU2183798C2 (ru) * | 1999-09-23 | 2002-06-20 | Открытое акционерное общество Уральский завод тяжелого машиностроения | Горелочное устройство |
US6279323B1 (en) * | 1999-11-01 | 2001-08-28 | General Electric Company | Low emissions combustor |
JP3584289B2 (ja) * | 2002-01-21 | 2004-11-04 | 独立行政法人 宇宙航空研究開発機構 | 液体微粒化ノズル |
US6863228B2 (en) * | 2002-09-30 | 2005-03-08 | Delavan Inc. | Discrete jet atomizer |
US6834505B2 (en) * | 2002-10-07 | 2004-12-28 | General Electric Company | Hybrid swirler |
US7013649B2 (en) * | 2004-05-25 | 2006-03-21 | General Electric Company | Gas turbine engine combustor mixer |
FR2875584B1 (fr) * | 2004-09-23 | 2009-10-30 | Snecma Moteurs Sa | Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine |
US7246494B2 (en) * | 2004-09-29 | 2007-07-24 | General Electric Company | Methods and apparatus for fabricating gas turbine engine combustors |
FR2888631B1 (fr) * | 2005-07-18 | 2010-12-10 | Snecma | Turbomachine a distribution angulaire de l'air |
FR2903169B1 (fr) * | 2006-06-29 | 2011-11-11 | Snecma | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
US20090249789A1 (en) * | 2008-04-08 | 2009-10-08 | Baifang Zuo | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
-
2010
- 2010-01-18 FR FR1050286A patent/FR2955375B1/fr not_active Expired - Fee Related
-
2011
- 2011-01-18 KR KR1020127021426A patent/KR101729362B1/ko active IP Right Grant
- 2011-01-18 PL PL11706299T patent/PL2526341T3/pl unknown
- 2011-01-18 CN CN201180006474.1A patent/CN102713440B/zh active Active
- 2011-01-18 WO PCT/FR2011/050085 patent/WO2011086336A1/fr active Application Filing
- 2011-01-18 ES ES11706299.2T patent/ES2443031T3/es active Active
- 2011-01-18 EP EP11706299.2A patent/EP2526341B1/fr active Active
- 2011-01-18 JP JP2012548469A patent/JP5676647B2/ja not_active Expired - Fee Related
- 2011-01-18 US US13/522,511 patent/US9188338B2/en active Active
- 2011-01-18 RU RU2012135559/06A patent/RU2549378C2/ru active
- 2011-01-18 CA CA2786541A patent/CA2786541C/fr active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2011086336A1 * |
Also Published As
Publication number | Publication date |
---|---|
ES2443031T3 (es) | 2014-02-17 |
EP2526341B1 (fr) | 2013-11-13 |
US9188338B2 (en) | 2015-11-17 |
CA2786541C (fr) | 2018-01-09 |
CN102713440B (zh) | 2015-09-30 |
US20120291441A1 (en) | 2012-11-22 |
CA2786541A1 (fr) | 2011-08-21 |
FR2955375A1 (fr) | 2011-07-22 |
JP2013517446A (ja) | 2013-05-16 |
CN102713440A (zh) | 2012-10-03 |
RU2012135559A (ru) | 2014-02-27 |
JP5676647B2 (ja) | 2015-02-25 |
KR20120112798A (ko) | 2012-10-11 |
KR101729362B1 (ko) | 2017-04-21 |
FR2955375B1 (fr) | 2012-06-15 |
RU2549378C2 (ru) | 2015-04-27 |
PL2526341T3 (pl) | 2014-03-31 |
WO2011086336A1 (fr) | 2011-07-21 |
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