EP3201531A1 - Brennkammer einer turbomaschine - Google Patents

Brennkammer einer turbomaschine

Info

Publication number
EP3201531A1
EP3201531A1 EP15785163.5A EP15785163A EP3201531A1 EP 3201531 A1 EP3201531 A1 EP 3201531A1 EP 15785163 A EP15785163 A EP 15785163A EP 3201531 A1 EP3201531 A1 EP 3201531A1
Authority
EP
European Patent Office
Prior art keywords
annular
deflector
chamber
combustion chamber
chamber bottom
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
Application number
EP15785163.5A
Other languages
English (en)
French (fr)
Other versions
EP3201531B1 (de
Inventor
Romain Nicolas Lunel
Thomas Olivier Marie Noel
Matthieu François RULLAUD
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3201531A1 publication Critical patent/EP3201531A1/de
Application granted granted Critical
Publication of EP3201531B1 publication Critical patent/EP3201531B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/42—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
    • F23R3/28—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
    • F23R3/42—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
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • 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
    • 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

Definitions

  • the present invention relates to a combustion chamber in a turbomachine, and a turbomachine equipped with a combustion chamber.
  • annular combustion chamber comprises two inner and outer coaxial annular shrouds, connected to each other at their upstream ends by an annular so-called bottom wall having injector head passage openings.
  • Each injector is engaged in a centering sleeve which is movable radially in support means integral with the chamber bottom.
  • the sleeve carries at its downstream end an annular flange extending radially outward and slidably mounted in an annular groove formed in support means integral with the annular wall of the chamber bottom.
  • the annular groove allows a radial and circumferential displacement of the sleeve housing the injector to compensate for manufacturing tolerances that can lead to misalignment of the injector with the fuel injection axis between the inner and outer rings of the combustion chamber. It also makes it possible to compensate for differential expansions in operation between the injector and the chamber.
  • the annular groove of radial displacement of the sleeve is defined by means of retaining axially upstream and downstream of the radial annular collar.
  • the axially downstream retaining means are formed by a downstream radial annular wall of an annular sheath fixed on the annular chamber bottom, the radial annular wall being connected to a cylindrical flange extending upstream. and on which is fixed by welding or brazing a washer attached to the cylindrical rim and delimiting with the radial annular wall the aforementioned groove. This washer is thus fixed releasably on the sheath.
  • the invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
  • a combustion chamber for a turbomachine such as a turbojet or an airplane turboprop, comprising an inner annular shell and an outer annular shell connected at their upstream ends by an annular bottom wall of a chamber, said chamber comprising deflectors mounted downstream of the annular bottom wall of the chamber, injectors being mounted in sleeves, at least one of which comprises a radial annular flange which is arranged to slide radially between the chamber bottom and the deflector and which is blocked axially between the chamber bottom and the deflector.
  • the invention makes it possible to eliminate the fixing sleeve of each injector and thus to reduce the mass of the combustion chamber.
  • the axial spacing between the baffle and the annular wall of the chamber bottom serves to accommodate the flange of the sleeve which can slide radially freely, which also reduces the axial size of the combustion chamber by using said spacing that was not used in the prior art.
  • the combustion chamber comprises first means for rotating the sleeve on the deflector and second means for rotating the deflector against the chamber bottom.
  • the anti-rotation of the sleeve with respect to the axis of the injector is thus achieved by means of the deflector itself locked in rotation on the annular wall of the chamber bottom.
  • the collar carries at least one member projecting radially outwardly.
  • This member may be arranged axially between the annular chamber bottom and the deflector so as to ensure the axial locking of the sleeve on the chamber bottom and the deflector.
  • the first rotational abutment means comprise a radial groove formed on the upstream face of the deflector and in which said member is engaged.
  • the deflector comprises a central annular wall of axis that of the injector and extending axially upstream and passing through a passage opening of an injector of the bottom annular wall. chamber, said annular wall of the baffle comprising a mounting slot axially sliding the flange into said groove of the baffle.
  • the second rotational locking means comprise a lug formed on the inner peripheral edge of said opening of the chamber bottom and projecting radially inwards in said notch.
  • a ring is screwed onto the outer periphery of the central annular wall and applied on the periphery of the upstream face of the opening of the chamber bottom.
  • This assembly ensures an axial locking of the deflector on the annular wall of the chamber bottom.
  • the ring can be welded to the annular wall of the baffle to prevent unscrewing during operation of the ring.
  • the sleeve may comprise two members each forming a tab extending radially outwardly, preferably diametrically opposite to each other.
  • the annular bottom wall of the chamber and the deflector advantageously comprise ventilation air passage bores.
  • the annular collar comprises an annular row of orifices whose axes open towards a radial annular rim of the sleeve which is arranged downstream.
  • the orifices of the collar make it possible to cool the radial annular flange efficiently because of the orientation of the axes of the orifices perpendicular to the radial flange and the reduced distance between the flange and the radial annular flange.
  • the invention also relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising a combustion chamber as above.
  • 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 from upstream in section along a plane passing containing the axis of an injector and the axis of the combustion chamber;
  • FIG. 4 is a schematic perspective view from upstream of an injection device in a combustion chamber according to the invention.
  • FIG. 5 is a schematic perspective view of a deflector alone
  • FIG. 6 is a schematic perspective view of a centering sleeve of an injector and an associated deflector
  • FIG. 7 is a schematic perspective view similar to Figure 4 without the clamping ring;
  • FIG. 1 represents the upstream portion of a turbomachine combustion chamber 10 according to the known technique comprising two inner and outer annular rings 12 extending around the axis 16 of the chamber 10 and fixed at their upstream ends on an annular chamber bottom wall 18 extending between the inner and outer walls of revolution 14 and traversed by fuel injectors 19 axis 21.
  • the annular chamber bottom 18 comprises a radial annular wall 20 connected at its radially external periphery to an external cylindrical rim 22 extending upstream and fixed on the upstream end of the outer shell 14.
  • the radial annular wall 20 of the chamber bottom 18 is connected at its radially inner periphery to an inner cylindrical rim 26 extending upstream and fixed on the upstream end of the inner shell 12.
  • the radial annular wall of the chamber bottom 18 comprises a plurality of openings each aligned with an opening of a deflector 28 arranged downstream of the radial annular wall 20 of the chamber bottom 1 8.
  • the deflectors 28 are intended to protect the bottom chamber 18 of the flame formed downstream between the inner and outer shells 12 and 14.
  • Each injector 19 is engaged axially in freely radially displaceable centering means in support means 32 integral with the annular chamber bottom 18.
  • each injector 19 comprise a sleeve formed of a radial annular wall 34 fixed around the passage opening of the injector 19 and on the upstream face of the radial annular wall 20 of the chamber bottom 18.
  • the radial annular wall 34 is connected at its radially outer end to a cylindrical rim 36 extending upstream.
  • each injector 19 for each injection system, a washer 38 is fixed by welding or brazing its radially outer periphery on the upstream end of the cylindrical rim 36 of the sleeve.
  • the centering means of each injector 19 comprise a cylindrical portion 40 traversed axially by the head of the injector 19 and connected downstream to an annular flange 42 extending radially outwardly and mounted with radial sliding in the annular groove delimited upstream by the washer 38 and downstream by the radial annular wall 34. The bottom of the groove is delimited externally by the cylindrical rim 36.
  • weld beads that hold the washers 38 can be weakened and are thus likely to break in operation, which impacts the injection of fuel between the inner and outer walls of revolution 12 and 14.
  • each injector is engaged in a sleeve 44 which is engaged in radial sliding between the radial annular wall 46 of the chamber bottom 48 and the deflector 50 and which is also locked axially towards the end of the chamber. upstream by the radial annular wall 46 of the chamber bottom 48 and axially downstream by the deflector 50.
  • Each deflector 50 has a generally angular sector shape and comprises a central cylindrical annular wall 52 extending upstream, an inner peripheral edge 54 and an outer peripheral edge 56 connected by radial lateral edges 58 ( Figure 4).
  • the deflectors 50 are disposed circumferentially adjacent to form a radial annular ring thermally protecting the annular bottom wall of the chamber 48.
  • the central annular wall 52 of each deflector 50 comprises on its outer surface a thread for receiving by screwing a ring 60 as shown in Figures 3 and 4.
  • each baffle 50 comprises two radial notches 62 diametrically opposite one another and opening at the upstream end of the central annular wall 52.
  • Each notch 62 opens downstream in a radial groove 64 formed on the upstream face of the sector of the deflector 50. As shown in Figure 5, each groove 64 is open at its radially inner and outer ends.
  • Each sleeve 44 comprises an upstream upstream frustoconical wall 76 flaring connected at its downstream end to a cylindrical wall 78 which is itself connected at its downstream end to an annularly radially inward convexly curved wall 80 whose end downstream is extended by a radial annular flange 82 arranged downstream of a radial annular flange 66 which carries two members or rectangular tabs elongate radially from its peripheral edge.
  • the annular flange 66 is thus arranged substantially downstream of the sleeve 44 and extends annularly around the curved wall 80.
  • the annular flange 66 and the radial annular flange 82 are internally connected to the same cylindrical wall 84.
  • the collar 66 comprises holes 86 or orifices (FIG. 3). These bores 86 are preferably arranged to form an annular row. The axes of the bores are parallel to the axis 21 of the injector and are directed towards the radial annular flange 82. Thus, the air flowing from upstream to downstream in the bores 86 impacts perpendicularly the annular rim 82 which allows to cool it well.
  • the arrangement of the annular flange 66 between the chamber bottom 48 and a deflector 50 makes it possible to reduce the axial distance (along the axis of the injector) between each piercing 86 and the annular flange 82 with respect to the prior art, thereby limiting the dispersions of the airflow and increasing the cooling of the radial flange 82 exposed to the combustion flame.
  • the sleeve 44 is engaged from upstream so that the tabs 68 slide in the notches 62 and each become housed in a groove 64 of the deflector 50.
  • Each groove 64 thus forms first means for rotating the sleeve 44 on the deflector 50.
  • the inner peripheral edge of the opening of the radial annular wall 46 of the chamber bottom 48 which is aligned with the opening of the deflector 50 comprises a lug 70 projecting radially inwards.
  • the lug 70 is arranged in the notch 62 and forms second abutment means intended to block the rotation of the deflector 50 on the radial annular wall 46 of the chamber bottom 48.
  • the sleeve 44 is locked in rotation about the axis 21 of the injector 19 via the deflector 50 itself locked in rotation on the chamber bottom 48.
  • the assembly is carried out by inserting from the downstream assembly formed by the deflector 50 and the sleeve 44 in the opening of the chamber bottom 48. Thereafter the ring 60 is screwed from upstream to the outer periphery of the wall. central annular 52 of the deflector 50 so as to be applied on the upstream face of the radial annular wall 46 of the chamber bottom 48.
  • One or more weld seams are made at the contact zone between the ring 60 and the central annular wall 52 of the deflector 50 so as to avoid loosening in operation of the ring 60.
  • the sleeve 44 is guided in a radial direction by means of the radial tabs 68 which slide in the grooves 64 of the deflector 50.
  • the tabs 68 of the sleeve 44 provide axial locking of the sleeve 44 between the annular wall radial 46 of the chamber bottom 48 and the deflector 50.
  • the invention eliminates the sheath of the prior art and reduces the axial size of the upstream portion of the combustion chamber.
  • the inner peripheral rims 72 and outer 74 of the chamber bottom 48 are oriented downstream and not upstream. It will be understood, however, that these peripheral inner rims 72 and outer 74 may also be directed upstream without this affecting the definition of the invention.
  • the radial annular wall 46 of the chamber bottom 48 and the deflector 50 may comprise ventilation air passages.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Fuel-Injection Apparatus (AREA)
EP15785163.5A 2014-10-01 2015-09-29 Brennkammer einer turbomaschine Active EP3201531B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1459362A FR3026827B1 (fr) 2014-10-01 2014-10-01 Chambre de combustion de turbomachine
PCT/FR2015/052588 WO2016051067A1 (fr) 2014-10-01 2015-09-29 Chambre de combustion de turbomachine

Publications (2)

Publication Number Publication Date
EP3201531A1 true EP3201531A1 (de) 2017-08-09
EP3201531B1 EP3201531B1 (de) 2019-02-27

Family

ID=53008570

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15785163.5A Active EP3201531B1 (de) 2014-10-01 2015-09-29 Brennkammer einer turbomaschine

Country Status (4)

Country Link
US (1) US10488049B2 (de)
EP (1) EP3201531B1 (de)
FR (1) FR3026827B1 (de)
WO (1) WO2016051067A1 (de)

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US10317085B2 (en) 2016-02-25 2019-06-11 General Electric Company Combustor assembly
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
GB201802251D0 (en) 2018-02-12 2018-03-28 Rolls Royce Plc An air swirler arrangement for a fuel injector of a combustion chamber
US12011734B2 (en) 2020-09-15 2024-06-18 Rtx Corporation Fuel nozzle air swirler
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

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Also Published As

Publication number Publication date
FR3026827A1 (fr) 2016-04-08
US20170299192A1 (en) 2017-10-19
WO2016051067A1 (fr) 2016-04-07
EP3201531B1 (de) 2019-02-27
US10488049B2 (en) 2019-11-26
FR3026827B1 (fr) 2019-06-07

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