EP3084308A1 - Chambre de combustion dans une turbomachine - Google Patents
Chambre de combustion dans une turbomachineInfo
- Publication number
- EP3084308A1 EP3084308A1 EP14828233.8A EP14828233A EP3084308A1 EP 3084308 A1 EP3084308 A1 EP 3084308A1 EP 14828233 A EP14828233 A EP 14828233A EP 3084308 A1 EP3084308 A1 EP 3084308A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- revolution
- combustion chamber
- annular
- radial
- 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 abstract description 31
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 41
- 239000000446 fuel Substances 0.000 claims abstract description 13
- 230000014759 maintenance of location Effects 0.000 claims abstract description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000005219 brazing Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the present invention relates to an annular turbomachine combustion chamber and a turbomachine equipped with an annular combustion chamber.
- annular combustion chamber comprises two inner and outer coaxial revolution walls, connected to each other upstream by an annular so-called bottom wall wall having fuel injector head through openings. between the walls of internal and external revolution.
- Each injector is engaged in centering means which are movable radially in support means integral with support means.
- the centering means of each injector are formed by a centering ring in which is engaged an injector and having a radial annular flange extending radially outwardly and slidably mounted in an annular groove means of support.
- the annular groove of the support means allows a radial displacement of the centering ring housing the injector to compensate for manufacturing tolerances as well as differential expansions in operation.
- the annular groove of radial displacement of the ring is defined by retaining means axially upstream and downstream of the radial annular flange of the centering ring.
- the axially downstream retaining means are formed by a downstream radial wall of an annular sheath fixed on the annular chamber bottom, the radial wall being connected to a cylindrical rim extending upstream and on which is attached by welding or brazing a washer attached to the cylindrical rim.
- This washer is therefore fixed releasably on the support means.
- this washer In case it is necessary to replace everything or part of the centering means of an injector during a maintenance operation, it is necessary to destroy this washer, which is a delicate operation because the sleeve which is fixed on the annular wall of the chamber bottom must not be damaged . Furthermore, it has been found breaks welding seams, which is not permissible, and does not ensure a perfect mechanical integrity of the fuel injection systems.
- the invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
- annular combustion chamber in a turbomachine, comprising two internal and external coaxial revolution walls, between which fuel injectors each engage in centering means which are movable in a radial direction in support means.
- the chamber also comprising axial retaining means upstream of the centering means, characterized in that said upstream axial retaining means are removably attached to at least one of the inner and outer walls of revolution.
- the axial retaining means comprising a radial annular ring fixed radially internally and / or externally on at least one of the walls of internal and external revolution and having an annular row of openings for the passage of the injectors, the edge of each opening being shaped to form an axial abutment upstream of a radial annular collar means of Injecting fuel injectors ..
- the axial retaining means upstream of the centering means are fixed on at least one of the internal and external walls of revolution of the combustion chamber and no longer on the support means, which allows easy and fast assembly and disassembly of the upstream axial retaining means for carrying out maintenance operations.
- the removable attachment can be made for example by bolting using the fasteners used to integrally assemble an annular chamber bottom and the inner and outer walls of revolution, which is simple to implement.
- the annular ring will advantageously comprise a plurality of rings regularly spaced circumferentially from each other and delimiting said orifices of passages of the injectors.
- the crown thus comprises free spaces between the rings avoiding a significant increase in the mass of the axial retaining means upstream of the centering means.
- At least some of the rings of the crown are connected to at least one lug extending radially inwards or outwards whose end opposite the ring is connected to a flange. extending axially, preferably downstream, and serving for attachment to the internal or external revolution wall, respectively.
- the crown comprises a unitary pattern whose successive repetition circumferentially forms the annular ring.
- the pattern comprises a ring connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the outer radial tab. being connected externally to an outer rim extending downstream and fixed on the outer wall of revolution.
- the pattern comprises at least three rings whose circumferential end rings of the pattern are connected to at least one radial tab carrying at its end opposite the ring a flange extending downstream and fixed on the inner or outer wall of revolution, the ring or rings circumferentially interposed between the two rings of circumferential ends of the pattern being connected to said end rings by circumferential arms.
- the rings of circumferential ends of the pattern are each connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the internal wall of revolution and the outer radial lug being externally connected to an outer flange extending downstream and fixed to the outer wall of revolution.
- the annular ring may be a one-piece piece or comprise a plurality of crown portions which are juxtaposed circumferentially.
- the use of several crown portions, although requiring several independent assembly operations, may make it possible to have to change only one crown portion rather than the entire crown during a maintenance operation.
- the support means comprise axial retaining means downstream of the centering means, said support means being fixed on an annular chamber bottom.
- the upstream axial retaining means are fixed on the inner and outer walls of revolution by means of the same fasteners of said internal and external walls of revolution to an annular chamber bottom, which makes it possible to use pre-existing fixing zones and avoids the modifications of the walls of internal and external revolution.
- the invention also relates to an axial retaining member of a centering piece of an injector in a combustion chamber, comprising a radial annular ring which:
- each opening comprises an annular row of fuel injector passage openings, an edge of each opening being shaped to form an axial stop upstream of a radial annular flange of the centering means of one of the injectors, and an a plurality of rings circumferentially spaced from each other and at least some of which have two tabs extending diametrically opposite each other from the ring, both legs
- FIG. 1 is a schematic axial sectional view of the upstream portion of a combustion chamber according to the prior art
- FIG. 2 is a schematic axial sectional view of the upstream portion of a combustion chamber according to the invention.
- FIG. 3 is a schematic perspective view of the axial retaining means upstream of a centering part of an injector according to a first embodiment of the invention
- - Figure 4 is a schematic perspective view of the axial retaining means upstream of a centering part of an injector according to a second embodiment of the invention
- FIG. 5 is a schematic perspective view of the axial retaining means upstream of a centering part of an injector according to a third embodiment of the invention.
- FIG. 6 is a schematic perspective view of the axial retaining means upstream of a centering part of an injector according to a fourth embodiment of the invention.
- FIG. 1 represents the upstream part of a combustion chamber 10 in a turbomachine according to the known technique comprising two walls of internal revolution 12 and external 14 extending around the axis 16 of the combustion chamber and fixed at their upstream ends on an annular chamber bottom 18 extending between the internal walls of revolution 12 and external 14 and traversed by fuel injectors 19.
- the annular chamber bottom 18 comprises a radial annular wall 20 connected at its outer periphery to an outer cylindrical rim 22 extending upstream and fixed by bolting elements 24 on the upstream end of the outer wall of revolution 14
- the radial wall 20 of the annular chamber bottom 18 is connected at its inner periphery to an internal cylindrical rim 26 extending upstream and fixed by bolting elements 28 to the upstream end of the internal wall of revolution 12 .
- the annular chamber bottom 18 comprises a plurality of openings for the passage of the injector heads 19 for the spraying of fuel between the walls of internal revolution 12 and external 14 and downstream of the chamber bottom 18.
- Each injector 19 is engaged axially in centering means 36 of the injector 19, which centering means 36 are freely movable in the radial direction in support means 38 integral with the annular chamber bottom 18.
- each injector 19 comprise a radial annular wall 40 fixed on the inner periphery and facing upstream of the passage opening of an injector 19.
- the radial annular wall 40 also comprises a cylindrical flange 42 extending upstream.
- a plate 44 or washer is fixed by welding or brazing its outer periphery on the upstream end of the cylindrical rim 42 of the sleeve.
- each injector 19 comprise a cylindrical ring 46 traversed axially by the head and comprising an annular flange 48 extending radially outwards and mounted to slide radially in the groove delimited upstream by the washer 44, downstream. by the radial annular wall 40. The bottom of the groove is delimited by the cylindrical rim 42.
- the weld seams of the washers 44 holding upstream centering means can be weakened and are thus likely to break in operation, which impacts the injection of fuel between the walls of internal revolution 12 and external 14.
- the invention overcomes this problem by removably fixing the axial retaining means on at least one of the inner wall 12 and outer wall 14 so as to facilitate the dismounting of the removable fastening means.
- the axial retaining means comprise an annular ring 50 whose inner periphery is fixed on the internal wall of revolution 12 and whose outer periphery is fixed on the external wall of revolution 14.
- the ring gear 50 may be a one-piece piece comprising a plurality of rings 52 each formed of a radial annular wall forming a passage opening 53 of an injector 19 intended to come face to face axially. an annular flange 48 of a centering ring 36 of an injector 19 so as to form an axial abutment upstream of said annular flange 48.
- Each ring 52 is connected to two tabs, one of which extends radially inwards and the other 56 extends radially outwards.
- the radially outer ends of the outer tabs 56 are connected to an outer cylindrical rim 58 extending axially downstream.
- the radially inner ends of the inner tabs 54 are connected to an inner cylindrical rim 60 extending axially downstream.
- the annular ring 50 is thus formed of a plurality of unitary patterns repeating successively in the circumferential direction and integral with each other. Each pattern is then formed of a ring 52, two inner radial tabs 54 and outer 56 and inner cylindrical rim portions 62 and outer 64.
- Each inner cylindrical rim 60 and outer 58 comprises orifices 66 for the passage of a fixing screw, these orifices 66 being regularly distributed around the axis 16 of the combustion chamber.
- Each pattern thus comprises two orifices 66 whose centers are aligned with the center of the ring 50 and located in the same radial plane containing the axis 16 of the combustion chamber.
- the outer cylindrical rim 58 of the ring 50 is attached to the outer cylindrical rim 22 of the chamber bottom 18 and is fixed to the outer wall of revolution 14 by means of the fixing screws 24.
- the internal cylindrical rim 60 of the ring 50 is attached to the inner cylindrical rim 26 of the chamber bottom 18 and is fixed to the upstream end of the internal wall of revolution 12 by means of the fixing screws 28.
- the assembly and disassembly of the crown 50 are thus simple and easy to perform when a maintenance operation is necessary.
- the double internal and external fixation of the ring 50 on the inner and outer walls 12 of revolution 14 ensures good mechanical strength to the crown and ensures its integrity in operation.
- a ring 68 In a second embodiment of a ring 68 according to the invention, it is formed of a plurality of independent patterns 70 juxtaposed circumferentially to form the annular ring 68.
- Each portion of internal cylindrical rim 72 or outer 74 of a pattern at its circumferential ends which are arranged with clearance vis-a-vis the circumferential ends of the inner cylindrical rim portions 72 or outer 74, respectively, adjacent patterns.
- FIG. 5 shows a third embodiment of an annular ring 76 according to the invention, formed of a circumferential repetition of several H-shaped patterns 78 integral with each other and each comprising three successive rings 80, 82.
- Each pattern 78 thus comprises two circumferential end rings 82, each connected to two tabs extending radially inward 84 and outward 86.
- the outer radial tabs 86 of the circumferential end rings 82 of each pattern 78 are connected to an outer cylindrical rim 88 extending downstream and the inner radial lugs 84 of the circumferential end rings 82 of each pattern 78 are connected to an inner cylindrical rim 90 extending downstream.
- Ring 80 of each pattern 78 which is interspaced circumferentially between two circumferential end rings 82 is devoid of radial tabs and is connected to the circumferential end rings 82 by circumferential joining arms 92.
- FIG. 6 represents a fourth embodiment of an annular ring 94 according to the invention, formed of a circumferential repetition of several units 96 independent of one another and juxtaposed circumferentially without contact.
- Each pattern 96 includes an inner cylindrical rim portion 98 and an outer cylindrical rim portion 100 for attachment of each pattern 96 to the internal and external 12 and outer revolution walls 14.
- the crown may comprise only one cylindrical fixing flange on one of the walls of internal or external revolution.
- this type of embodiment is less reliable than those shown in the figures of fact of the double internal and external fixation of the annular ring.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1363348A FR3015639B1 (fr) | 2013-12-20 | 2013-12-20 | Chambre de combustion dans une turbomachine |
PCT/FR2014/053401 WO2015092284A1 (fr) | 2013-12-20 | 2014-12-17 | Chambre de combustion dans une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3084308A1 true EP3084308A1 (fr) | 2016-10-26 |
EP3084308B1 EP3084308B1 (fr) | 2019-09-11 |
Family
ID=51014329
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14828233.8A Active EP3084308B1 (fr) | 2013-12-20 | 2014-12-17 | Chambre de combustion dans une turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US10458654B2 (fr) |
EP (1) | EP3084308B1 (fr) |
FR (1) | FR3015639B1 (fr) |
WO (1) | WO2015092284A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11131458B2 (en) * | 2018-04-10 | 2021-09-28 | Delavan Inc. | Fuel injectors for turbomachines |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4454711A (en) * | 1981-10-29 | 1984-06-19 | Avco Corporation | Self-aligning fuel nozzle assembly |
US4686823A (en) * | 1986-04-28 | 1987-08-18 | United Technologies Corporation | Sliding joint for an annular combustor |
DE19515537A1 (de) * | 1995-04-27 | 1996-10-31 | Bmw Rolls Royce Gmbh | Kopfteil einer Gasturbinen-Ringbrennkammer |
US6412272B1 (en) * | 1998-12-29 | 2002-07-02 | United Technologies Corporation | Fuel nozzle guide for gas turbine engine and method of assembly/disassembly |
US7062920B2 (en) * | 2003-08-11 | 2006-06-20 | General Electric Company | Combustor dome assembly of a gas turbine engine having a free floating swirler |
US7121095B2 (en) * | 2003-08-11 | 2006-10-17 | General Electric Company | Combustor dome assembly of a gas turbine engine having improved deflector plates |
US7628019B2 (en) * | 2005-03-21 | 2009-12-08 | United Technologies Corporation | Fuel injector bearing plate assembly and swirler assembly |
US7546739B2 (en) * | 2005-07-05 | 2009-06-16 | General Electric Company | Igniter tube and method of assembling same |
FR2897145B1 (fr) * | 2006-02-08 | 2013-01-18 | Snecma | Chambre de combustion annulaire de turbomachine a fixations alternees. |
FR2897144B1 (fr) * | 2006-02-08 | 2008-05-02 | Snecma Sa | Chambre de combustion de turbomachine a fentes tangentielles |
US7975487B2 (en) * | 2006-09-21 | 2011-07-12 | Solar Turbines Inc. | Combustor assembly for gas turbine engine |
US7765809B2 (en) * | 2006-11-10 | 2010-08-03 | General Electric Company | Combustor dome and methods of assembling such |
FR2911668B1 (fr) * | 2007-01-18 | 2009-03-20 | Snecma Sa | Chambre de combustion d'une turbomachine |
US7926280B2 (en) * | 2007-05-16 | 2011-04-19 | Pratt & Whitney Canada Corp. | Interface between a combustor and fuel nozzle |
DE102011014972A1 (de) * | 2011-03-24 | 2012-09-27 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammerkopf mit Halterungen für Dichtungen an Brennern in Gasturbinen |
GB201107095D0 (en) * | 2011-04-28 | 2011-06-08 | Rolls Royce Plc | A head part of an annular combustion chamber |
US8745988B2 (en) * | 2011-09-06 | 2014-06-10 | Pratt & Whitney Canada Corp. | Pin fin arrangement for heat shield of gas turbine engine |
US8893382B2 (en) * | 2011-09-30 | 2014-11-25 | General Electric Company | Combustion system and method of assembling the same |
US10378775B2 (en) * | 2012-03-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Combustor heat shield |
-
2013
- 2013-12-20 FR FR1363348A patent/FR3015639B1/fr active Active
-
2014
- 2014-12-17 EP EP14828233.8A patent/EP3084308B1/fr active Active
- 2014-12-17 US US15/104,835 patent/US10458654B2/en active Active
- 2014-12-17 WO PCT/FR2014/053401 patent/WO2015092284A1/fr active Application Filing
Also Published As
Publication number | Publication date |
---|---|
FR3015639A1 (fr) | 2015-06-26 |
FR3015639B1 (fr) | 2018-08-31 |
EP3084308B1 (fr) | 2019-09-11 |
WO2015092284A1 (fr) | 2015-06-25 |
US20180163965A1 (en) | 2018-06-14 |
US10458654B2 (en) | 2019-10-29 |
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