EP3887720A1 - Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes - Google Patents

Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes

Info

Publication number
EP3887720A1
EP3887720A1 EP19848964.3A EP19848964A EP3887720A1 EP 3887720 A1 EP3887720 A1 EP 3887720A1 EP 19848964 A EP19848964 A EP 19848964A EP 3887720 A1 EP3887720 A1 EP 3887720A1
Authority
EP
European Patent Office
Prior art keywords
injection system
frustoconical portion
longitudinal axis
relative
spin
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.)
Pending
Application number
EP19848964.3A
Other languages
German (de)
French (fr)
Inventor
Sébastien Alain Christophe BOURGOIS
Romain Nicolas Lunel
Haris MUSAEFENDIC
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 EP3887720A1 publication Critical patent/EP3887720A1/en
Pending legal-status Critical Current

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
    • F23R3/28—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
    • F23R3/02—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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to the general technical field of 5 aircraft turbomachines such as turbojets and turbopropellers. It relates to an injection system for a combustion chamber of a turbomachine.
  • An annular combustion chamber for a turbomachine generally comprises a plurality of injection systems which are inserted into openings 10 in a bottom of the combustion chamber.
  • a fuel injector is housed in each of the injection systems.
  • the Snecma patent application FR 2 903 169 relates to an injection system which includes an internal spin, a venturi and a mixing bowl.
  • the mixing bowl includes swirl holes. These mixing bowl vortex holes 15 are located radially outside the venturi and around the venturi. They are located in an upstream portion of the mixing bowl, which is cylindrical with a circular section.
  • the space requirement of the request system FR 2 903 169 is limited, while allowing relatively satisfactory spraying of the fuel into the combustion chamber.
  • the injection system is difficult to manufacture due to its reduced dimensions. Furthermore, the flow inside the venturi is not entirely satisfactory, in particular since a film of air and fuel mixture is likely to be deposited on the internal wall of the venturi. The size and mass of the injection system can be further reduced.
  • the invention aims to at least partially solve the problems encountered in the solutions of the prior art.
  • the invention relates to an injection system for the combustion chamber 5 of a turbomachine.
  • the injection system includes a spin and an air-fuel mixing bowl.
  • the mixing bowl comprises a converging frustoconical portion and a diverging frustoconical portion around a longitudinal axis of the injection system.
  • the converging frustoconical portion is connected to the spin.
  • the diverging frustoconical portion 10 is connected to the converging frustoconical portion, by forming an aerodynamic profile continuity between on the one hand a converging inner face of the converging frustoconical portion and on the other hand an diverging inner face of the diverging frustoconical portion.
  • the divergent frustoconical portion is crossed by swirl holes which each define a channel extending along a main axis 15 comprising an axial component extending along the longitudinal axis of the injection system and a circumferential component around the longitudinal axis of the injection system, the axial component and the tangential component each being non-zero.
  • the injection system can comprise a single spin.
  • the structure of the mixing bowl also makes it possible to remove a venturi which is conventionally located between a spin and the mixing bowl. This results in a reduced overall size and a limitation of the mass of the injection system, while allowing satisfactory spraying of the air-fuel mixture into the combustion chamber. Furthermore, the injection system tends to be easier to manufacture.
  • the injection system Due to the presence of a single spin and the absence of a venturi, the injection system is easier to manufacture.
  • the single spin of the injection system has a larger diameter around the longitudinal axis of the injection system,
  • the invention may optionally include one or more of the following characteristics, whether or not combined.
  • the ratio of an axial length of the converging frustoconical portion to an axial length of the diverging frustoconical portion is less than 1, in particular strictly less than 1.
  • the ratio of an angle of the outer wall of the converging frustoconical portion relative to the longitudinal axis of the injection system over an angle of the outer wall of the diverging frustoconical portion relative to the longitudinal axis of the injection system injection is between 0.8 and 1.2, being notably substantially equal to 1.
  • the injection system comprises a housing sleeve which is configured to accommodate an injector nose movably relative to the spin and the mixing bowl.
  • the housing sleeve is connected to the spin.
  • the swirl holes are all substantially distributed over at least one annular row around the axis
  • the swirl holes are all distributed in a single annular row around the longitudinal axis of the injection system.
  • the vortex holes are axially closer to the outlet of the mixing bowl than a connection zone of the divergent frustoconical portion to the frustoconical convergent portion.
  • the circumferential components of all the swirl holes are oriented in the same direction relative to the longitudinal axis of the injection system.
  • the swirl holes are circumferentially inclined at an angle which is less than or equal to 60 ° relative to the axis
  • all the vortex holes are axially inclined downstream relative to the longitudinal axis of the injection system.
  • all the swirl holes are axially inclined downstream relative to the longitudinal axis of the injection system at an angle which is substantially equal to 45 ° relative to the longitudinal axis of the injection system. .
  • the injection system comprises a single spin.
  • the spin includes a plurality of vanes distributed over substantially a single annular row.
  • the blades of the spin are each oriented circumferentially in a first direction around the longitudinal axis of the injection system.
  • the swirl holes are each oriented circumferentially in a second direction which is opposite to the first direction relative to the longitudinal axis of the injection system.
  • the mixing bowl comprises a collar and a connecting spoiler.
  • the collar is located downstream of the divergent frustoconical portion.
  • the collar extends radially relative to the longitudinal axis of the injection system.
  • the connecting spoiler is configured to connect the mixing bowl to a combustion chamber bottom and / or to a combustion chamber deflector.
  • the connecting spoiler is connected to the diverging frustoconical portion extending upstream.
  • the connecting spoiler is traversed by cooling orifices which are oriented axially towards the flange.
  • the invention also relates to a combustion chamber comprising an injection system as defined above.
  • the combustion chamber 25 comprises a chamber bottom, a deflector, an upstream retaining member, and the injection system.
  • the injection system comprises a radial wall segment which is located axially between the upstream retaining member and the deflector, to limit the axial movement of the injection system relative to the bottom of the combustion chamber.
  • FIG. 5 - Figure 1 a partial schematic representation in longitudinal half section of a combustion chamber for a turbomachine, according to a first embodiment of the invention
  • FIG. 2 is a partial schematic representation in perspective of an injection system for a combustion chamber, according to the first embodiment
  • Figure 3 is a partial schematic perspective view of an upstream portion of the injection system according to the first embodiment
  • FIG. 4 is a plan view upstream from downstream of the injection system according to the first embodiment
  • Figure 5 a partial schematic representation in longitudinal half section of a flow of air and fuel mixture through the injection system according to the first embodiment.
  • FIG. 1 schematically represents a combustion chamber 2 of an aircraft turbomachine.
  • the combustion chamber 2 is annular around a longitudinal axis Y-Y of the turbomachine.
  • It comprises an outer casing wall 22 and an inner casing wall 23, a fairing 24, an outer wall 25 and an inner wall 26 which are joined by a chamber bottom 28.
  • injectors 3 injection systems 4 and a diffuser 10 and upstream retaining members 21 of the injection systems 4.
  • the outer casing wall 22 delimits the combustion chamber 2 radially outward relative to the longitudinal axis Y-Y of the turbomachine.
  • the inner casing wall 23 is located radially inward relative to the outer wall 22 relative to the longitudinal axis Y-Y of the turbomachine.
  • the outer casing wall 22 defines with the outer wall 25 a first passage 11 for air flow.
  • the inner casing wall 23 defines with the inner wall 26 a second passage 12 for air flow.
  • An “upstream” direction and the “downstream” direction are defined by the general direction of flow of air and fuel in the combustion chamber 2. This direction also corresponds substantially to the general direction of flow of gases d exhaust in the turbomachine.
  • the outer wall 25 and the inner wall 26 are walls of revolution 15 which are coaxial around the longitudinal axis of the turbomachine Y-Y. They each include primary orifices 51 for introducing a flow of primary air and dilution orifices 52 for introducing a flow of dilution air into the flame tube of the combustion chamber 2.
  • the fairing 24 extends from the external wall 25 and the internal wall 26 upstream by being located upstream of the chamber bottom 28. It has central openings for housing the injection systems 4 and the corresponding injectors 3 .
  • the chamber bottom 28 has openings 29 for mounting the injection systems 4. These openings 29 are for example circular.
  • the diffuser 10 is configured to supply the combustion chamber 25 2, in particular the injection systems 4, the primary orifices 51 and the dilution orifices
  • Each upstream retaining member 21 is an annular ring which participates with the deflector 27 in the delimitation of a housing for a radial rim 89 of the mixing bowl 8.
  • Each fuel injector 3 is of the aeromechanical type, that is to say that the fuel pressure inside the injector 3 is used to spray the fuel at the outlet of the injector 3.
  • Each injector 3 has a primary fuel circuit and a secondary fuel circuit 5.
  • the primary circuit is intended for example for an ignition phase and of low power.
  • the secondary circuit intervenes in the medium to high power operating phases, in addition to the primary circuit.
  • Each fuel injector 3 comprises an injection nozzle 30, an injector nose 31 and a fixing plate 33.
  • the fixing plate 33 serves to fix the injector 3 to the outer casing wall 22 of the combustion.
  • the injector nose 31 includes the fuel outlet from the injector 3, it is designed to be inserted into a housing socket 6 of the corresponding injection system 4.
  • the injection rod 30 extends between the fixing plate 33 and the injector nose 31, and it supplies the injector nose 31 with fuel.
  • the injection systems 4 are mounted in the openings 29 of the chamber bottom 28, being spaced from one another in a circumferential direction around the longitudinal axis Y-Y of the turbomachine.
  • Each injection system 4 is annular about its longitudinal axis X-X which can be inclined relative to the direction of the longitudinal axis Y-Y of the turbomachine.
  • an axial direction is a direction along the longitudinal axis X-X of an injection system.
  • a circumferential direction C-C or tangential direction is a direction which is substantially locally orthogonal to the direction of the longitudinal axis X-X of an injection system, around the longitudinal axis X-X of the injection system.
  • a radial direction 25 RR is a direction which is substantially locally orthogonal to the direction of the longitudinal axis XX of an injection system and to the circumferential direction CC, being intersecting with the longitudinal axis XX of the injection system .
  • the coordinate system R-R, C-C, X-X forms an orthonormal coordinate system in cylindrical coordinates.
  • each injection system 4 30 comprises from upstream to downstream a housing sleeve 6, a spin 7 and a mixing bowl 8.
  • the housing sleeve 6, the spin 7 and the mixing bowl 8 jointly form air supply means for producing a sheet of air-fuel mixture with the fuel injected by the corresponding injector 3.
  • the housing socket 6 is rigidly secured to the spin 7, being 5 in particular one piece with the spin 7.
  • the housing socket 6 comprises a flared portion 60 for pre-centering the injector nose 31, and a cylindrical portion 62 for centering the injector nose 31.
  • the housing socket 6 is configured to position the injector nose 31, immobilizing it, relative to the spin 7 and to the mixing bowl 8. More generally, the connection socket 6 is configured for mechanically and fluidly connecting an injector nose 31 to the spin 7.
  • the spin 7 is the only spin 7 of the injection system 4. It is rigidly secured to the mixing bowl 8, in particular being in one piece with the mixing bowl 8.
  • the spin 7 has vanes 70, a central duct 71, a radial wall 72 for supporting the vanes, and air inlet orifices 73 which open into the central duct 71.
  • the spin 7 is used to drive the air-fuel mixture which passes through it, in rotation about the longitudinal axis X-X of the injection system.
  • the air which is introduced through the air inlet orifices 73 is rotated in a first direction Ri.
  • the spin 7 has a single stage of blades 70. These blades 70 are distributed in a single annular row 70a on the radial wall 72 of support.
  • the vanes 70 are oriented circumferentially in the same direction, known as the first direction Ri, around the longitudinal axis XX of the injection system. In other words, they each have a circumferential component in the first direction Ri relative to the longitudinal axis XX 25 of the injection system.
  • Each of the blades is inclined with a setting angle bi which has a value greater than 65 °. This wedging angle bi represents the inclination of the lower surface of the vanes 70 relative to a radial direction relative to the longitudinal axis XX of the injection system.
  • the spin 7 comprises a single stage of blades 70, it has a larger diameter than a two-stage spin of blades 70. Furthermore, the pitch angle bi of the blades is greater than with several stages of spin.
  • the mixing bowl 5 8 comprises a converging frustoconical portion 82 and a diverging frustoconical portion 84 which is connected to the converging frustoconical portion 82 by a connection zone 85.
  • the mixing bowl 8 comprises a connecting spoiler 86 and a flange 87 which are connected to the divergent frustoconical portion 84.
  • the mixing bowl 8 is in one piece.
  • the converging frustoconical portion 82 is connected to the spin 7 which it delimits downstream.
  • the outer wall of the converging frustoconical portion 82 is inclined at an angle ai relative to the longitudinal axis X-X of the injection system, for example 45 °.
  • the converging frustoconical portion 82 extends axially over an axial length li. It has an average diameter di.
  • the outer wall of the converging frustoconical portion 15 has a thickness ei which is substantially uniform. The converging frustoconical portion 82 tends to increase the speed of the mixture of air and fuel passing through it.
  • the diverging frustoconical portion 84 is connected to the converging frustoconical portion 82 by the connection zone 85, forming a continuity 20 of aerodynamic profile with the converging frustoconical portion 82. More specifically, the inner face of the frustoconical convergent portion 82 forms a continuity of aerodynamic profile with the inner face of the divergent frustoconical portion 84 for the air-fuel mixture.
  • the diverging frustoconical portion 84 is crossed in its downstream part by swirl holes 81.
  • the outer wall of the divergent frustoconical portion 84 is inclined at an angle ⁇ 3 ⁇ 4 relative to the longitudinal axis X-X of the injection system, for example 45 °.
  • the divergent frustoconical portion 84 extends axially over an axial length. It has an average diameter d2 which is strictly greater than that of the converging frustoconical portion 82.
  • the divergent frustoconical portion 84 tends to increase the static pressure and reduce the speed of the air and fuel mixture passing through it.
  • the ratio of the axial length li of the converging frustoconical portion 82 to the axial length of the diverging frustoconical portion 84 is strictly less than 1.
  • the diverging frustoconical portion 84 has a length axial greater than that of the converging frustoconical portion 82.
  • the ratio of the angle ai of the converging frustoconical portion 82 to the angle ⁇ 2 of the diverging frustoconical portion 84 is for example substantially equal to 1.
  • connection spoiler 86 comprises a cylindrical connection portion 88 and a radial rim 89.
  • the connection spoiler 86 is configured to connect the mixing bowl 8 to the deflector 27, and to connect the
  • the cylindrical connecting portion 88 is cylindrical around the longitudinal axis X-X of the injection system. It is connected to the divergent tapered portion 84 extending axially upstream and radially outward relative to the divergent tapered portion 84. It axially connects the radial flange
  • the cylindrical connection portion 88 is crossed by cooling orifices 83.
  • the cooling orifices are oriented axially downstream and radially outwards, in the direction of the flange 87.
  • the cooling orifices 83 are distributed over a single annular row 83a.
  • the radial rim 89 is intended to be located axially between the upstream retaining member 21 and the deflector 27, in order to limit the axial movement of the injection system 4 relative to the bottom of the combustion chamber 28.
  • the flange 87 is located downstream of the divergent frustoconical portion 84. It serves to cool the deflector 27, by guiding the air which passes through towards the deflector 27
  • the swirl holes 81 are all substantially distributed over at least one annular row 81a around the longitudinal axis X-X of the injection system. In the embodiment shown, the swirl holes 81 are all distributed over a single annular row 81a.
  • the swirl holes 81 are axially closer to the outlet of the mixing bowl 8 than to the connection zone 85 of the divergent tapered portion 84 to the tapered convergent portion 82.
  • each of the swirl holes 81 defines a channel extending along a main axis, through the wall 10 of the divergent frustoconical portion 84. This channel is inclined axially downstream relative to the longitudinal axis XX of the injection system, comprising an axial component along the longitudinal axis XX of the injection system. All the swirl holes 81 are inclined axially downstream relative to the longitudinal axis XX of the injection system at an angle g which is for example equal to 45 ° relative to the longitudinal axis XX 15 of the system d 'injection.
  • each of the swirl holes 81 each comprise a component circumferential to the external wall of the mixing bowl 8 with respect to the longitudinal axis X-X of the injection system.
  • the swirl holes 81 are inclined circumferentially 20 by a setting angle b2 which is for example less than or equal to 60 ° relative to the longitudinal axis X-X of the injection system.
  • the swirl holes 81 are each oriented circumferentially in a second direction R2 which is opposite to the first direction Ri of the blades 70 of the spin 7.
  • the swirl holes 81 are configured to entrain the air which is introduced therein in a counter-rotating flow with that of the air which is introduced into the injection system 4 through the air inlet holes 73 of the spin 7.
  • the pressurized air which feeds the combustion chamber 2 is used for combustion or cooling of the combustion chamber 2. It comes from the diffuser 10.
  • Part of this air is introduced into the flame tube of the combustion chamber 2 at the level of the central opening of the fairing 24, while another part of the air flows towards the passages 11 and 12 of air flow.
  • the air supplying the injection system 4 flows from the central opening of the fairing 24, through 5 in particular the spin 7 of the injection system shown in FIG. 1 and holes 81, 83 which pass through the mixing bowl 8.
  • the air which enters the air inlet orifices 73 of the spin according to arrow 56 imparts a rotational movement according to arrow 57 to the air fuel mixture and contributes to the atomization of the fuel.
  • the mixture of air and fuel at the outlet from the converging portion 82 is confined radially by the air which is introduced into the vortex holes 81 according to arrow 58.
  • the vortex holes 81 also impart to the mixture a rotational movement relative to the longitudinal axis XX of the injection system, according to arrow 59. They contribute to the atomization of the fuel.
  • the deflector 10 is then in particular cooled by a film of cooling air which is directed towards the deflector 10 by the flange 87, after having passed through the cooling holes 83.
  • the air flow in the passages 11 and 12 enters the combustion chamber 2 through the primary orifices 51 and the dilution orifices 52.
  • the injection system 4 can have only one spin 7.
  • the structure of the mixing bowl 8 according to the invention also makes it possible to eliminate the venturi which is conventionally located between a spin and the mixing bowl 8.
  • injection system 4 while allowing a satisfactory spraying of the air-fuel mixture in the combustion chamber 2. Furthermore, the injection system 4 tends to be easier to manufacture.
  • the single spin 7 of the injection system Due to the presence of a single spin and the absence of a venturi, the single spin 7 of the injection system has a larger diameter around the longitudinal axis XX of the injection system, and the diameter of the mixer bowl holes 8 formed by swirl holes 81 is increased.
  • the injection system 4 is easier to manufacture. It has a more limited mass and size.
  • the combustion chamber 2 is a combustion chamber of a turboprop engine or of a turbojet engine, instead of being an annular combustion chamber 2 of a double-body turbojet engine with double flow.
  • the upstream retaining member 21 is a radial wall segment 15 which is rigidly secured to the deflector 27, to delimit the housing of the radial rim 89 of the mixing bowl.
  • the upstream retaining member 21 then forms a single piece with the deflector 27.
  • the combustion chamber 2 is devoid of deflector 27.
  • the injection system 4 is notably devoid of flange 87.
  • the housing sleeve 6 has air supply holes (not shown).
  • the housing socket 6 can be fixed to the spin 7, instead of being integral with the spin 7.
  • the housing socket 6 is connected so
  • the housing sleeve 6 in particular forms a passage sliding.
  • the mixing bowl 8 and the spin 7 are for example fixed to the chamber bottom 28 or to the deflector
  • the number, shape and distribution of the blades 70 of the spin is variable.
  • the wedging angle bi can have variable values.
  • the vanes 70 can also be oriented in the second direction R2.
  • the blades 70 are for example configured to drive the mixture of air and fuel in a corotative flow with that 5 of the air which is introduced into the injection system 4 through the swirl holes 81.
  • the shape of the mixing bowl 8 is variable.
  • the diverging frustoconical portion 84 can be fixed to the converging frustoconical portion 82.
  • the shape and distribution of the swirl holes 81 and the cooling holes 83 is variable.
  • the swirl holes 81 may be located on more than one annular row, for example by being distributed over two annular rows.
  • the swirl holes 81 can be oriented in the first direction Ri, instead of being oriented in the second direction R2.
  • at least some of the holes in the annular row 81a can be devoid of circumferential component 20 relative to the longitudinal axis X-X.
  • the cooling holes 83 may be located on more than one annular row, for example by being distributed over two annular rows.
  • the fuel injector 3 is a multi-point injector.
  • the combustion chamber 2 is in particular devoid of primary orifices 51 and dilution orifices 52 in this case.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

The invention relates to an injection system (4) for a turbomachine combustion chamber. The injection system comprises a swirler (7) and a mixing bowl (8). The mixing bowl (8) comprises a converging frustoconical portion (82) and a diverging frustoconical portion (84). The diverging frustoconical portion (84) is connected to the converging frustoconical portion (82), forming a continuous aerodynamic profile with the converging frustoconical portion (82). The diverging frustoconical portion (84) is passed through by vortex holes (81) which each comprise a circumferential component around a longitudinal axis (X-X) of the injection system and an axial component along the longitudinal axis (X-X) of the injection system.

Description

3 64 67 ^ ^ Q - D 3 64 67 ^ ^ Q - D
WO 2020/144416 PCT/FR2019/053163 WO 2020/144416 PCT / FR2019 / 053163
1 1
SYSTEME D'INJECTION POUR TURBOMACHINE, COMPRENANT UNE VRILLE ET DES INJECTION SYSTEM FOR A TURBOMACHINE, INCLUDING A TRUCK AND
TROUS TOURBILLONNAIRES DE BOL MELANGEUR MIXER BOWL WHIRLPOOL HOLES
DESCRIPTION DESCRIPTION
DOMAINE TECHNIQUE TECHNICAL AREA
L'invention se rapporte au domaine technique général des 5 turbomachines d'aéronef telles que les turboréacteurs et les turbopropulseurs. Elle concerne un système d'injection pour une chambre de combustion de turbomachine. The invention relates to the general technical field of 5 aircraft turbomachines such as turbojets and turbopropellers. It relates to an injection system for a combustion chamber of a turbomachine.
ÉTAT DE LA TECHNIQUE ANTÉRIEURE STATE OF THE PRIOR ART
Une chambre de combustion annulaire pour turbomachine comprend généralement une pluralité de systèmes d'injection qui sont insérés dans des ouvertures 10 d'un fond de la chambre de combustion. Un injecteur de carburant est logé dans chacun des systèmes d'injection. An annular combustion chamber for a turbomachine generally comprises a plurality of injection systems which are inserted into openings 10 in a bottom of the combustion chamber. A fuel injector is housed in each of the injection systems.
La demande de brevet Snecma FR 2 903 169 a trait à un système d'injection qui comprend une vrille interne, un venturi et un bol mélangeur. Le bol mélangeur comprend des trous tourbillonnaires. Ces trous tourbillonnaires de bol 15 mélangeur sont situés radialement à l'extérieur du venturi et autour du venturi. Ils sont situés dans une portion amont du bol mélangeur, qui est cylindrique de section circulaire. The Snecma patent application FR 2 903 169 relates to an injection system which includes an internal spin, a venturi and a mixing bowl. The mixing bowl includes swirl holes. These mixing bowl vortex holes 15 are located radially outside the venturi and around the venturi. They are located in an upstream portion of the mixing bowl, which is cylindrical with a circular section.
L'encombrement du système d'injection de la demande FR 2 903 169 est limité, tout en permettant une pulvérisation relativement satisfaisante du carburant dans la chambre de combustion. The space requirement of the request system FR 2 903 169 is limited, while allowing relatively satisfactory spraying of the fuel into the combustion chamber.
20 Le système d'injection est difficile à fabriquer du fait de ses dimensions réduites. Par ailleurs, l'écoulement à l'intérieur du venturi n'est pas entièrement satisfaisant, en particulier puisqu'un film de mélange d'air et de carburant est susceptible de se déposer sur la paroi interne du venturi. L'encombrement et la masse du système d'injection peuvent être davantage réduits. The injection system is difficult to manufacture due to its reduced dimensions. Furthermore, the flow inside the venturi is not entirely satisfactory, in particular since a film of air and fuel mixture is likely to be deposited on the internal wall of the venturi. The size and mass of the injection system can be further reduced.
2 2
EXPOSÉ DE L'INVENTION STATEMENT OF THE INVENTION
L'invention vise à résoudre au moins partiellement les problèmes rencontrés dans les solutions de l'art antérieur. The invention aims to at least partially solve the problems encountered in the solutions of the prior art.
A cet égard, l'invention a pour objet un système d'injection pour chambre 5 de combustion de turbomachine. Le système d'injection comprend une vrille et un bol mélangeur air-carburant. In this regard, the invention relates to an injection system for the combustion chamber 5 of a turbomachine. The injection system includes a spin and an air-fuel mixing bowl.
Selon l'invention, le bol mélangeur comprend une portion tronconique convergente et une portion tronconique divergente autour d'un axe longitudinal du système d'injection. La portion tronconique convergente est raccordée à la vrille. La portion 10 tronconique divergente est raccordée à la portion tronconique convergente, en formant une continuité de profil aérodynamique entre d'une part une face intérieure convergente de la portion tronconique convergente et d'autre part une face intérieure divergente de la portion tronconique divergente. La portion tronconique divergente est traversée par des trous tourbillonnaires qui définissent chacun un canal s'étendant suivant un axe principal 15 comprenant une composante axiale s'étendant suivant l'axe longitudinal du système d'injection et une composante circonférentielle autour de l'axe longitudinal du système d'injection, la composante axiale et la composante tangentielle étant chacune non nulle. According to the invention, the mixing bowl comprises a converging frustoconical portion and a diverging frustoconical portion around a longitudinal axis of the injection system. The converging frustoconical portion is connected to the spin. The diverging frustoconical portion 10 is connected to the converging frustoconical portion, by forming an aerodynamic profile continuity between on the one hand a converging inner face of the converging frustoconical portion and on the other hand an diverging inner face of the diverging frustoconical portion. The divergent frustoconical portion is crossed by swirl holes which each define a channel extending along a main axis 15 comprising an axial component extending along the longitudinal axis of the injection system and a circumferential component around the longitudinal axis of the injection system, the axial component and the tangential component each being non-zero.
Grâce aux trous tourbillonnaires, le système d'injection peut comprendre une seule vrille. La structure du bol mélangeur rend aussi possible la suppression d'un 20 venturi qui est classiquement situé entre une vrille et le bol mélangeur. Il en découle un encombrement réduit et une limitation de la masse du système d'injection, tout en permettant une pulvérisation satisfaisante du mélange air-carburant dans la chambre de combustion. Par ailleurs, le système d'injection tend à être plus facile à fabriquer. Thanks to the swirl holes, the injection system can comprise a single spin. The structure of the mixing bowl also makes it possible to remove a venturi which is conventionally located between a spin and the mixing bowl. This results in a reduced overall size and a limitation of the mass of the injection system, while allowing satisfactory spraying of the air-fuel mixture into the combustion chamber. Furthermore, the injection system tends to be easier to manufacture.
En particulier, l'atomisation du mélange air carburant dans la chambre de 25 combustion est satisfaisante. Il n'y a plus de problèmes d'écoulement du mélange air- carburant au niveau d'un venturi qui a été supprimé. In particular, the atomization of the air fuel mixture in the combustion chamber is satisfactory. There are no longer any problems with the flow of the air-fuel mixture at a venturi which has been removed.
Du fait de la présence d'une seule vrille et de l'absence de venturi, le système d'injection est plus facile à fabriquer. L'unique vrille du système d'injection présente un diamètre plus important autour de l'axe longitudinal du système d'injection, Due to the presence of a single spin and the absence of a venturi, the injection system is easier to manufacture. The single spin of the injection system has a larger diameter around the longitudinal axis of the injection system,
3 et le diamètre des trous de bol mélangeur formant les trous tourbillonnaires est augmenté, ce qui facilite davantage la fabrication du système d'injection. 3 and the diameter of the mixing bowl holes forming the swirl holes is increased, which further facilitates the manufacture of the injection system.
La présence d'une seule vrille et l'absence de venturi tend à réduire la masse et l'encombrement du système d'injection. The presence of a single spin and the absence of a venturi tend to reduce the mass and size of the injection system.
5 L'invention peut comporter de manière facultative une ou plusieurs des caractéristiques suivantes combinées entre elles ou non. The invention may optionally include one or more of the following characteristics, whether or not combined.
Avantageusement, le rapport d'une longueur axiale de la portion tronconique convergente sur une longueur axiale de la portion tronconique divergente est inférieur à 1, notamment strictement inférieur à 1. Advantageously, the ratio of an axial length of the converging frustoconical portion to an axial length of the diverging frustoconical portion is less than 1, in particular strictly less than 1.
10 Avantageusement, le rapport d'un angle de la paroi externe de la portion tronconique convergente relativement à l'axe longitudinal du système d'injection sur un angle de la paroi externe de la portion tronconique divergente relativement à l'axe longitudinal du système d'injection est compris entre 0,8 et 1,2, en étant notamment sensiblement égal à 1. Advantageously, the ratio of an angle of the outer wall of the converging frustoconical portion relative to the longitudinal axis of the injection system over an angle of the outer wall of the diverging frustoconical portion relative to the longitudinal axis of the injection system injection is between 0.8 and 1.2, being notably substantially equal to 1.
15 Selon une particularité de réalisation, le système d'injection comprend une douille de logement qui est configurée pour loger un nez d'injecteur de manière mobile relativement à la vrille et au bol mélangeur. La douille de logement est raccordée à la vrille. According to a particular embodiment, the injection system comprises a housing sleeve which is configured to accommodate an injector nose movably relative to the spin and the mixing bowl. The housing sleeve is connected to the spin.
Selon une autre particularité de réalisation, les trous tourbillonnaires sont tous sensiblement répartis sur au moins une rangée annulaire autour de l'axe According to another particular feature, the swirl holes are all substantially distributed over at least one annular row around the axis
20 longitudinal du système d'injection. De préférence, les trous tourbillonnaires sont tous répartis sur une seule rangée annulaire autour de l'axe longitudinal du système d'injection. 20 longitudinal of the injection system. Preferably, the swirl holes are all distributed in a single annular row around the longitudinal axis of the injection system.
Selon une particularité de réalisation, les trous tourbillonnaires sont axialement plus proches de la sortie du bol mélangeur que d'une zone de raccordement de la portion tronconique divergente à la portion tronconique convergente. According to a particular embodiment, the vortex holes are axially closer to the outlet of the mixing bowl than a connection zone of the divergent frustoconical portion to the frustoconical convergent portion.
25 Selon une particularité de réalisation, les composantes circonférentielles de tous les trous tourbillonnaires sont orientées dans un même sens relativement à l'axe longitudinal du système d'injection. According to a particular embodiment, the circumferential components of all the swirl holes are oriented in the same direction relative to the longitudinal axis of the injection system.
De préférence, les trous tourbillonnaires sont inclinés circonférentiellement d'un angle qui est inférieur ou égal à 60° relativement à l'axe Preferably, the swirl holes are circumferentially inclined at an angle which is less than or equal to 60 ° relative to the axis
30 longitudinal du système d'injection. 4 30 longitudinal of the injection system. 4
Selon une particularité de réalisation, tous les trous tourbillonnaires sont inclinés axialement vers l'aval par rapport à l'axe longitudinal du système d'injection. According to a particular embodiment, all the vortex holes are axially inclined downstream relative to the longitudinal axis of the injection system.
De préférence, tous les trous tourbillonnaires sont inclinés axialement vers l'aval par rapport à l'axe longitudinal du système d'injection d'un angle qui est 5 sensiblement égal à 45° par rapport à l'axe longitudinal du système d'injection. Preferably, all the swirl holes are axially inclined downstream relative to the longitudinal axis of the injection system at an angle which is substantially equal to 45 ° relative to the longitudinal axis of the injection system. .
Selon une particularité de réalisation, le système d'injection comprend une unique vrille. La vrille comprend une pluralité d'aubes réparties sur sensiblement une seule rangée annulaire. According to a particular embodiment, the injection system comprises a single spin. The spin includes a plurality of vanes distributed over substantially a single annular row.
Selon une particularité de réalisation, les aubes de la vrille sont chacune 10 orientées circonférentiellement dans un premier sens autour de l'axe longitudinal du système d'injection. Les trous tourbillonnaires sont chacun orientés circonférentiellement dans un deuxième sens qui est opposé au premier sens relativement à l'axe longitudinal du système d'injection. According to a particular embodiment, the blades of the spin are each oriented circumferentially in a first direction around the longitudinal axis of the injection system. The swirl holes are each oriented circumferentially in a second direction which is opposite to the first direction relative to the longitudinal axis of the injection system.
Selon une particularité de réalisation, le bol mélangeur comprend une 15 collerette et un becquet de liaison. La collerette est située en aval de la portion tronconique divergente. La collerette s'étend radialement relativement à l'axe longitudinal du système d'injection. Le becquet de liaison est configuré pour raccorder le bol mélangeur à un fond de chambre de combustion et/ou à un déflecteur de chambre de combustion. Le becquet de liaison est raccordé à la portion tronconique divergente en s'étendant vers l'amont. Le 20 becquet de liaison est traversé par des orifices de refroidissement qui sont orientés axialement vers la collerette. According to a particular embodiment, the mixing bowl comprises a collar and a connecting spoiler. The collar is located downstream of the divergent frustoconical portion. The collar extends radially relative to the longitudinal axis of the injection system. The connecting spoiler is configured to connect the mixing bowl to a combustion chamber bottom and / or to a combustion chamber deflector. The connecting spoiler is connected to the diverging frustoconical portion extending upstream. The connecting spoiler is traversed by cooling orifices which are oriented axially towards the flange.
L'invention porte aussi sur une chambre de combustion comprenant un système d'injection tel que défini ci-dessus. The invention also relates to a combustion chamber comprising an injection system as defined above.
Selon une particularité de réalisation, la chambre de combustion 25 comprend un fond de chambre, un déflecteur, un organe de retenue amont, et le système d'injection. Le système d'injection comprend un segment de paroi radial qui est situé axialement entre l'organe de retenue amont et le déflecteur, pour limiter le déplacement axial du système d'injection relativement au fond de chambre de combustion. According to a particular embodiment, the combustion chamber 25 comprises a chamber bottom, a deflector, an upstream retaining member, and the injection system. The injection system comprises a radial wall segment which is located axially between the upstream retaining member and the deflector, to limit the axial movement of the injection system relative to the bottom of the combustion chamber.
5 5
BRÈVE DESCRIPTION DES DESSINS BRIEF DESCRIPTION OF THE DRAWINGS
La présente invention sera mieux comprise à la lecture de la description d'exemples de réalisation, donnés à titre purement indicatif et nullement limitatif, en faisant référence aux dessins annexés sur lesquels : The present invention will be better understood on reading the description of exemplary embodiments, given for purely indicative and in no way limiting, with reference to the appended drawings in which:
5 - la figure 1 une représentation schématique partielle en demi coupe longitudinale d'une chambre de combustion pour turbomachine, selon un premier mode de réalisation de l'invention ; 5 - Figure 1 a partial schematic representation in longitudinal half section of a combustion chamber for a turbomachine, according to a first embodiment of the invention;
la figure 2 est une représentation schématique partielle en perspective d'un système d'injection pour chambre de combustion, selon le premier mode 10 de réalisation ; FIG. 2 is a partial schematic representation in perspective of an injection system for a combustion chamber, according to the first embodiment;
la figure 3 est une représentation schématique partielle en perspective d'une portion amont du système d'injection selon le premier mode de réalisation ; Figure 3 is a partial schematic perspective view of an upstream portion of the injection system according to the first embodiment;
la figure 4 est une vue plane vers l'amont de l'aval du système 15 d'injection selon le premier mode de réalisation ; FIG. 4 is a plan view upstream from downstream of the injection system according to the first embodiment;
la figure 5 une représentation schématique partielle en demi coupe longitudinale d'un écoulement de mélange d'air et de carburant à travers le système d'injection selon le premier mode de réalisation. Figure 5 a partial schematic representation in longitudinal half section of a flow of air and fuel mixture through the injection system according to the first embodiment.
20 EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERS 20 DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
Des parties identiques, similaires ou équivalentes des différentes figures portent les mêmes références numériques de façon à faciliter le passage d'une figure à l'autre. Identical, similar or equivalent parts of the different figures have the same reference numerals so as to facilitate the passage from one figure to another.
La figure 1 représente de manière schématique une chambre de 25 combustion 2 d'une turbomachine d'aéronef. La chambre de combustion 2 est annulaire autour d'un axe longitudinal Y-Y de la turbomachine. FIG. 1 schematically represents a combustion chamber 2 of an aircraft turbomachine. The combustion chamber 2 is annular around a longitudinal axis Y-Y of the turbomachine.
Elle comporte une paroi de carter extérieure 22 et une paroi de carter intérieure 23, un carénage 24, une paroi externe 25 et une paroi interne 26 qui sont réunies par un fond de chambre 28. It comprises an outer casing wall 22 and an inner casing wall 23, a fairing 24, an outer wall 25 and an inner wall 26 which are joined by a chamber bottom 28.
6 6
Elle comprend également des injecteurs 3, des systèmes d'injection 4 et un diffuseur 10 et des organes de retenue amont 21 des systèmes d'injection 4. It also includes injectors 3, injection systems 4 and a diffuser 10 and upstream retaining members 21 of the injection systems 4.
La paroi de carter extérieure 22 délimite la chambre de combustion 2 radialement vers l'extérieur par rapport à l'axe longitudinal Y-Y de la turbomachine. La 5 paroi de carter intérieure 23 est située radialement vers l'intérieur par rapport à la paroi extérieure 22 relativement à l'axe longitudinal Y-Y de la turbomachine. The outer casing wall 22 delimits the combustion chamber 2 radially outward relative to the longitudinal axis Y-Y of the turbomachine. The inner casing wall 23 is located radially inward relative to the outer wall 22 relative to the longitudinal axis Y-Y of the turbomachine.
La paroi de carter extérieure 22 délimite avec la paroi externe 25 un premier passage 11 d'écoulement d'air. De même, la paroi de carter intérieure 23 définit avec la paroi interne 26 un deuxième passage 12 d'écoulement d'air. The outer casing wall 22 defines with the outer wall 25 a first passage 11 for air flow. Similarly, the inner casing wall 23 defines with the inner wall 26 a second passage 12 for air flow.
10 Une direction « amont » et la direction « aval » sont définies par la direction générale d'écoulement de l'air et du carburant dans la chambre de combustion 2. Cette direction correspond également sensiblement à la direction générale d'écoulement des gaz d'échappement dans la turbomachine. 10 An “upstream” direction and the “downstream” direction are defined by the general direction of flow of air and fuel in the combustion chamber 2. This direction also corresponds substantially to the general direction of flow of gases d exhaust in the turbomachine.
La paroi externe 25 et la paroi interne 26 sont des parois de révolution 15 qui sont coaxiales autour de l'axe longitudinal de turbomachine Y-Y. Elles comprennent chacune des orifices primaires 51 d'introduction d'un flux d'air primaire et des orifices de dilution 52 d'introduction d'un flux d'air de dilution dans le tube à flamme de la chambre de combustion 2. The outer wall 25 and the inner wall 26 are walls of revolution 15 which are coaxial around the longitudinal axis of the turbomachine Y-Y. They each include primary orifices 51 for introducing a flow of primary air and dilution orifices 52 for introducing a flow of dilution air into the flame tube of the combustion chamber 2.
Le carénage 24 s'étend depuis la paroi externe 25 et la paroi interne 26 20 vers l'amont en étant situé en amont du fond de chambre 28. Il comporte des ouvertures centrales de logement des systèmes d'injection 4 et des injecteurs 3 correspondants. The fairing 24 extends from the external wall 25 and the internal wall 26 upstream by being located upstream of the chamber bottom 28. It has central openings for housing the injection systems 4 and the corresponding injectors 3 .
Le fond de chambre 28 comporte des ouvertures 29 de montage des systèmes d'injection 4. Ces ouvertures 29 sont par exemple circulaires. The chamber bottom 28 has openings 29 for mounting the injection systems 4. These openings 29 are for example circular.
Le diffuseur 10 est configuré pour alimenter la chambre de combustion 25 2, notamment les systèmes d'injection 4, les orifices primaires 51 et les orifices de dilution The diffuser 10 is configured to supply the combustion chamber 25 2, in particular the injection systems 4, the primary orifices 51 and the dilution orifices
52, en air. 52, in the air.
Chaque organe de retenue amont 21 est une bague annulaire qui participe avec le déflecteur 27 à la délimitation d'un logement pour un rebord radial 89 de bol mélangeur 8. Each upstream retaining member 21 is an annular ring which participates with the deflector 27 in the delimitation of a housing for a radial rim 89 of the mixing bowl 8.
7 7
Chaque injecteur 3 de carburant est de type aéromécanique, c'est-à-dire que la pression du carburant à l'intérieur de l'injecteur 3 est utilisée pour pulvériser le carburant en sortie de l'injecteur 3. Each fuel injector 3 is of the aeromechanical type, that is to say that the fuel pressure inside the injector 3 is used to spray the fuel at the outlet of the injector 3.
Chaque injecteur 3 comporte un circuit primaire de carburant et un circuit 5 secondaire de carburant. Le circuit primaire est destiné par exemple à une phase d'allumage et de faible puissance. Le circuit secondaire intervient dans les phases de fonctionnement de moyenne à forte puissance, en complément du circuit primaire. Each injector 3 has a primary fuel circuit and a secondary fuel circuit 5. The primary circuit is intended for example for an ignition phase and of low power. The secondary circuit intervenes in the medium to high power operating phases, in addition to the primary circuit.
Chaque injecteur 3 de carburant comprend une canne d'injection 30, un nez d'injecteur 31 et une platine de fixation 33. La platine de fixation 33 sert à fixer 10 l'injecteur 3 à la paroi de carter extérieure 22 de la chambre de combustion. Le nez d'injecteur 31 comprend la sortie de carburant de l'injecteur 3, il est conçu pour être inséré dans une douille de logement 6 du système d'injection 4 correspondant. La canne d'injection 30 s'étend entre la platine de fixation 33 et le nez d'injecteur 31, et elle alimente le nez d'injecteur 31 en carburant. Each fuel injector 3 comprises an injection nozzle 30, an injector nose 31 and a fixing plate 33. The fixing plate 33 serves to fix the injector 3 to the outer casing wall 22 of the combustion. The injector nose 31 includes the fuel outlet from the injector 3, it is designed to be inserted into a housing socket 6 of the corresponding injection system 4. The injection rod 30 extends between the fixing plate 33 and the injector nose 31, and it supplies the injector nose 31 with fuel.
15 Les systèmes d'injection 4 sont montés dans les ouvertures 29 du fond de chambre 28, en étant espacés les uns des autres selon une direction circonférentielle autour de l'axe longitudinal Y-Y de la turbomachine. Chaque système d'injection 4 est annulaire autour de son axe longitudinal X-X qui peut être incliné par rapport à la direction de l'axe longitudinal Y-Y de la turbomachine. The injection systems 4 are mounted in the openings 29 of the chamber bottom 28, being spaced from one another in a circumferential direction around the longitudinal axis Y-Y of the turbomachine. Each injection system 4 is annular about its longitudinal axis X-X which can be inclined relative to the direction of the longitudinal axis Y-Y of the turbomachine.
20 Dans la suite de l'exposé et en référence notamment à la figure 5, une direction axiale est une direction selon l'axe longitudinal X-X d'un système d'injection. Une direction circonférentielle C-C ou direction tangentielle est une direction qui est sensiblement localement orthogonale à la direction de l'axe longitudinal X-X d'un système d'injection, autour de l'axe longitudinal X-X du système d'injection. Une direction radiale 25 R-R est une direction qui est sensiblement localement orthogonale à la direction de l'axe longitudinal X-X d'un système d'injection et à la direction circonférentielle C-C, en étant sécante avec l'axe longitudinal X-X du système d'injection. Le repère R-R, C-C, X-X forme un repère orthonormé en coordonnées cylindriques. In the rest of the description and with particular reference to FIG. 5, an axial direction is a direction along the longitudinal axis X-X of an injection system. A circumferential direction C-C or tangential direction is a direction which is substantially locally orthogonal to the direction of the longitudinal axis X-X of an injection system, around the longitudinal axis X-X of the injection system. A radial direction 25 RR is a direction which is substantially locally orthogonal to the direction of the longitudinal axis XX of an injection system and to the circumferential direction CC, being intersecting with the longitudinal axis XX of the injection system . The coordinate system R-R, C-C, X-X forms an orthonormal coordinate system in cylindrical coordinates.
En référence conjointe aux figures 1 à 5, chaque système d'injection 4 30 comprend d'amont en aval une douille de logement 6, une vrille 7 et un bol mélangeur 8. With reference to FIGS. 1 to 5, each injection system 4 30 comprises from upstream to downstream a housing sleeve 6, a spin 7 and a mixing bowl 8.
8 8
La douille de logement 6, la vrille 7 et le bol mélangeur 8 forment conjointement des moyens d'alimentation en air pour produire une nappe de mélange air- carburant avec le carburant injecté par l'injecteur 3 correspondant. The housing sleeve 6, the spin 7 and the mixing bowl 8 jointly form air supply means for producing a sheet of air-fuel mixture with the fuel injected by the corresponding injector 3.
La douille de logement 6 est rigidement solidaire de la vrille 7, en étant 5 notamment monobloc avec la vrille 7. La douille de logement 6 comprend une portion évasée 60 de précentrage du nez d'injecteur 31, et une portion cylindrique 62 de centrage du nez d'injecteur 31. La douille de logement 6 est configurée pour positionner le nez d'injecteur 31, en l'immobilisant, relativement à la vrille 7 et au bol mélangeur 8. De manière plus générale, la douille de raccordement 6 est configurée pour raccorder 10 mécaniquement et fluidiquement un nez d'injecteur 31 à la vrille 7. The housing socket 6 is rigidly secured to the spin 7, being 5 in particular one piece with the spin 7. The housing socket 6 comprises a flared portion 60 for pre-centering the injector nose 31, and a cylindrical portion 62 for centering the injector nose 31. The housing socket 6 is configured to position the injector nose 31, immobilizing it, relative to the spin 7 and to the mixing bowl 8. More generally, the connection socket 6 is configured for mechanically and fluidly connecting an injector nose 31 to the spin 7.
En référence plus spécifiquement aux figures 2, 3 et 5, la vrille 7 est la seule vrille 7 du système d'injection 4. Elle est rigidement solidaire du bol mélangeur 8, en étant notamment monobloc avec le bol mélangeur 8. La vrille 7 comporte des aubes 70, un conduit central 71, une paroi radiale 72 de support des aubes, et des orifices d'entrée d'air 15 73 qui débouchent dans le conduit central 71. With more specific reference to Figures 2, 3 and 5, the spin 7 is the only spin 7 of the injection system 4. It is rigidly secured to the mixing bowl 8, in particular being in one piece with the mixing bowl 8. The spin 7 has vanes 70, a central duct 71, a radial wall 72 for supporting the vanes, and air inlet orifices 73 which open into the central duct 71.
La vrille 7 sert à entraîner le mélange air-carburant qui la traverse, en rotation autour de l'axe longitudinal X-X du système d'injection. Dans le mode de réalisation représenté, l'air qui est introduit par les orifices d'entrée d'air 73 est entraîné en rotation selon un premier sens Ri. The spin 7 is used to drive the air-fuel mixture which passes through it, in rotation about the longitudinal axis X-X of the injection system. In the embodiment shown, the air which is introduced through the air inlet orifices 73 is rotated in a first direction Ri.
20 La vrille 7 comporte un unique étage d'aubes 70. Ces aubes 70 sont réparties sur une seule rangée annulaire 70a sur la paroi radiale 72 de support. Les aubes 70 sont orientées circonférentiellement dans le même sens, dit premier sens Ri, autour de l'axe longitudinal X-X du système d'injection. Autrement dit, elles ont chacune une composante circonférentielle selon le premier sens Ri relativement à l'axe longitudinal X-X 25 du système d'injection. Chacune des aubes est inclinée avec un angle de calage bi qui a une valeur supérieure à 65°. Cet angle de calage bi représente l'inclinaison de la paroi d'intrados des aubes 70 relativement à une direction radiale par rapport à l'axe longitudinal X-X du système d'injection. The spin 7 has a single stage of blades 70. These blades 70 are distributed in a single annular row 70a on the radial wall 72 of support. The vanes 70 are oriented circumferentially in the same direction, known as the first direction Ri, around the longitudinal axis XX of the injection system. In other words, they each have a circumferential component in the first direction Ri relative to the longitudinal axis XX 25 of the injection system. Each of the blades is inclined with a setting angle bi which has a value greater than 65 °. This wedging angle bi represents the inclination of the lower surface of the vanes 70 relative to a radial direction relative to the longitudinal axis XX of the injection system.
9 9
Étant donné que la vrille 7 comprend un seul étage d'aubes 70, elle présente un diamètre plus important qu'une vrille à deux étages d'aubes 70. Par ailleurs, l'angle de calage bi des aubes est plus important qu'avec plusieurs étages de vrille. Since the spin 7 comprises a single stage of blades 70, it has a larger diameter than a two-stage spin of blades 70. Furthermore, the pitch angle bi of the blades is greater than with several stages of spin.
En référence plus spécifiquement aux figures 1, 2, 4 et 5, le bol mélangeur 5 8 comprend une portion tronconique convergente 82 et une portion tronconique divergente 84 qui est raccordée à la portion tronconique convergente 82 par une zone de raccordement 85. Le bol mélangeur 8 comprend un becquet de liaison 86 et une collerette 87 qui sont raccordés à la portion tronconique divergente 84. Le bol mélangeur 8 est monobloc. With more specific reference to FIGS. 1, 2, 4 and 5, the mixing bowl 5 8 comprises a converging frustoconical portion 82 and a diverging frustoconical portion 84 which is connected to the converging frustoconical portion 82 by a connection zone 85. The mixing bowl 8 comprises a connecting spoiler 86 and a flange 87 which are connected to the divergent frustoconical portion 84. The mixing bowl 8 is in one piece.
10 La portion tronconique convergente 82 est raccordée à la vrille 7 qu'elle délimite vers l'aval. La paroi externe de la portion tronconique convergente 82 est inclinée selon un angle ai relativement à l'axe longitudinal X-X du système d'injection, par exemple de 45°. La portion tronconique convergente 82 s'étend axialement sur une longueur axiale li. Elle présente un diamètre moyen di. La paroi externe de la portion tronconique 15 convergente 82 présente une épaisseur ei qui est sensiblement uniforme. La portion tronconique convergente 82 tend à accroître la vitesse du mélange d'air et de carburant qui la traverse. The converging frustoconical portion 82 is connected to the spin 7 which it delimits downstream. The outer wall of the converging frustoconical portion 82 is inclined at an angle ai relative to the longitudinal axis X-X of the injection system, for example 45 °. The converging frustoconical portion 82 extends axially over an axial length li. It has an average diameter di. The outer wall of the converging frustoconical portion 15 has a thickness ei which is substantially uniform. The converging frustoconical portion 82 tends to increase the speed of the mixture of air and fuel passing through it.
La portion tronconique divergente 84 est raccordée à la portion tronconique convergente 82 par la zone de raccordement 85, en formant une continuité 20 de profil aérodynamique avec la portion tronconique convergente 82. Plus précisément, la face intérieure de la portion tronconique convergente 82 forme une continuité de profil aérodynamique avec la face intérieure de la portion tronconique divergente 84 pour le mélange air-carburant. La portion tronconique divergente 84 est traversée dans sa partie aval par des trous tourbillonnaires 81. The diverging frustoconical portion 84 is connected to the converging frustoconical portion 82 by the connection zone 85, forming a continuity 20 of aerodynamic profile with the converging frustoconical portion 82. More specifically, the inner face of the frustoconical convergent portion 82 forms a continuity of aerodynamic profile with the inner face of the divergent frustoconical portion 84 for the air-fuel mixture. The diverging frustoconical portion 84 is crossed in its downstream part by swirl holes 81.
25 La paroi externe de la portion tronconique divergente 84 est inclinée selon un angle <¾ relativement à l'axe longitudinal X-X du système d'injection, par exemple 45°. La portion tronconique divergente 84 s'étend axialement sur une longueur axiale . Elle présente un diamètre moyen d2 qui est strictement supérieur à celui de la portion tronconique convergente 82. La paroi externe de la portion tronconique divergente 84 The outer wall of the divergent frustoconical portion 84 is inclined at an angle <¾ relative to the longitudinal axis X-X of the injection system, for example 45 °. The divergent frustoconical portion 84 extends axially over an axial length. It has an average diameter d2 which is strictly greater than that of the converging frustoconical portion 82. The outer wall of the diverging frustoconical portion 84
30 présente une surépaisseur e2 au niveau des trous tourbillonnaires 81 qui la traversent, 30 has an additional thickness e2 at the level of the swirl holes 81 which pass through it,
10 notamment par rapport à l'épaisseur el de la paroi externe de la portion tronconique convergente 82 et/ou à l'épaisseur moyenne de la paroi externe de la portion tronconique divergente 84. La portion tronconique divergente 84 tend à accroître la pression statique et réduire la vitesse du mélange d'air et de carburant qui la traverse. 10 in particular with respect to the thickness el of the external wall of the converging frustoconical portion 82 and / or to the average thickness of the external wall of the divergent frustoconical portion 84. The divergent frustoconical portion 84 tends to increase the static pressure and reduce the speed of the air and fuel mixture passing through it.
5 En référence plus spécifiquement à la figure 5, le rapport de la longueur axiale li de la portion tronconique convergente 82 sur la longueur axiale de la portion tronconique divergente 84 est strictement inférieur à 1. Autrement dit, la portion tronconique divergente 84 a une longueur axiale plus importante que celle de la portion tronconique convergente 82. 5 With more specific reference to FIG. 5, the ratio of the axial length li of the converging frustoconical portion 82 to the axial length of the diverging frustoconical portion 84 is strictly less than 1. In other words, the diverging frustoconical portion 84 has a length axial greater than that of the converging frustoconical portion 82.
10 Le rapport de l'angle ai de la portion tronconique convergente 82 sur l'angle Œ2 de la portion tronconique divergente 84 est par exemple sensiblement égal à 1. The ratio of the angle ai of the converging frustoconical portion 82 to the angle Œ2 of the diverging frustoconical portion 84 is for example substantially equal to 1.
En référence plus spécifiquement à la figure 5, le becquet de liaison 86 comprend une portion cylindrique de liaison 88 et un rebord radial 89. Le becquet de liaison 86 est configuré pour raccorder le bol mélangeur 8 au déflecteur 27, et pour raccorder le With more specific reference to FIG. 5, the connection spoiler 86 comprises a cylindrical connection portion 88 and a radial rim 89. The connection spoiler 86 is configured to connect the mixing bowl 8 to the deflector 27, and to connect the
15 bol mélangeur 8 au fond de chambre 28. 15 mixing bowl 8 at the bottom of the chamber 28.
La portion cylindrique de liaison 88 est cylindrique autour de l'axe longitudinal X-X du système d'injection. Elle est raccordée à la portion tronconique divergente 84 en s'étendant axialement vers l'amont et radialement vers l'extérieur par rapport à la portion tronconique divergente 84. Elle raccorde axialement le rebord radial The cylindrical connecting portion 88 is cylindrical around the longitudinal axis X-X of the injection system. It is connected to the divergent tapered portion 84 extending axially upstream and radially outward relative to the divergent tapered portion 84. It axially connects the radial flange
20 89 à la collerette 87. 20 89 on the flange 87.
La portion cylindrique de liaison 88 est traversée par des orifices de refroidissement 83. Les orifices de refroidissement sont orientés axialement vers l'aval et radialement vers l'extérieur, en direction de la collerette 87. Les orifices de refroidissement 83 sont répartis sur une seule rangée annulaire 83a. The cylindrical connection portion 88 is crossed by cooling orifices 83. The cooling orifices are oriented axially downstream and radially outwards, in the direction of the flange 87. The cooling orifices 83 are distributed over a single annular row 83a.
25 Le rebord radial 89 est destiné à être situé axialement entre l'organe de retenue amont 21 et le déflecteur 27, pour limiter le déplacement axial du système d'injection 4 relativement au fond de chambre 28 de combustion. The radial rim 89 is intended to be located axially between the upstream retaining member 21 and the deflector 27, in order to limit the axial movement of the injection system 4 relative to the bottom of the combustion chamber 28.
La collerette 87 est située en aval de la portion tronconique divergente 84. Elle sert à refroidir le déflecteur 27, en guidant vers le déflecteur 27 l'air qui traverse The flange 87 is located downstream of the divergent frustoconical portion 84. It serves to cool the deflector 27, by guiding the air which passes through towards the deflector 27
30 les trous de refroidissement 83 en direction de la collerette 87. 30 the cooling holes 83 in the direction of the flange 87.
1 1 1 1
De manière générale, les trous tourbillonnaires 81 sont tous sensiblement répartis sur au moins une rangée annulaire 81a autour de l'axe longitudinal X-X du système d'injection. Dans le mode de réalisation représenté, les trous tourbillonnaires 81 sont tous répartis sur une seule rangée annulaire 81a. In general, the swirl holes 81 are all substantially distributed over at least one annular row 81a around the longitudinal axis X-X of the injection system. In the embodiment shown, the swirl holes 81 are all distributed over a single annular row 81a.
5 Les trous tourbillonnaires 81 sont axialement plus proches de la sortie du bol mélangeur 8 que de la zone de raccordement 85 de la portion tronconique divergente 84 à la portion tronconique convergente 82. 5 The swirl holes 81 are axially closer to the outlet of the mixing bowl 8 than to the connection zone 85 of the divergent tapered portion 84 to the tapered convergent portion 82.
En référence plus spécifiquement à la figure 5, chacun des trous tourbillonnaires 81 définit un canal s'étendant suivant un axe principal, à travers la paroi 10 de la portion tronconique divergente 84. Ce canal est incliné axialement vers l'aval par rapport à l'axe longitudinal X-X du système d'injection, en comprenant une composante axiale suivant l'axe longitudinal X-X du système d'injection. Tous les trous tourbillonnaires 81 sont inclinés axialement vers l'aval par rapport à l'axe longitudinal X-X du système d'injection d'un angle g qui est par exemple égal à 45° par rapport à l'axe longitudinal X-X 15 du système d'injection. With more specific reference to FIG. 5, each of the swirl holes 81 defines a channel extending along a main axis, through the wall 10 of the divergent frustoconical portion 84. This channel is inclined axially downstream relative to the longitudinal axis XX of the injection system, comprising an axial component along the longitudinal axis XX of the injection system. All the swirl holes 81 are inclined axially downstream relative to the longitudinal axis XX of the injection system at an angle g which is for example equal to 45 ° relative to the longitudinal axis XX 15 of the system d 'injection.
En référence plus spécifiquement à la figure 4, les canaux définis par chacun des trous tourbillonnaires 81 comprennent chacun une composante circonférentielle à la paroi externe du bol mélangeur 8 par rapport à l'axe longitudinal X-X du système d'injection. Les trous tourbillonnaires 81 sont inclinés circonférentiellement 20 d'un angle de calage b2 qui est par exemple inférieur ou égal à 60° relativement à l'axe longitudinal X-X du système d'injection. With more specific reference to FIG. 4, the channels defined by each of the swirl holes 81 each comprise a component circumferential to the external wall of the mixing bowl 8 with respect to the longitudinal axis X-X of the injection system. The swirl holes 81 are inclined circumferentially 20 by a setting angle b2 which is for example less than or equal to 60 ° relative to the longitudinal axis X-X of the injection system.
En référence plus spécifiquement aux figures 1, 2, 4 et 5, les trous tourbillonnaires 81 sont chacun orientés circonférentiellement dans un deuxième sens R2 qui est opposé au premier sens Ri des aubes 70 de la vrille 7. Autrement dit, les trous 25 tourbillonnaires 81 sont configurés pour entraîner l'air qui y est introduit selon un écoulement contrarotatif avec celui de l'air qui est introduit dans le système d'injection 4 par les trous d'entrée d'air 73 de la vrille 7. With more specific reference to FIGS. 1, 2, 4 and 5, the swirl holes 81 are each oriented circumferentially in a second direction R2 which is opposite to the first direction Ri of the blades 70 of the spin 7. In other words, the swirl holes 81 are configured to entrain the air which is introduced therein in a counter-rotating flow with that of the air which is introduced into the injection system 4 through the air inlet holes 73 of the spin 7.
En référence à la figure 5, l'air sous pression qui alimente la chambre de combustion 2 sert à la combustion ou au refroidissement de la chambre de combustion 2. 30 II provient du diffuseur 10. With reference to FIG. 5, the pressurized air which feeds the combustion chamber 2 is used for combustion or cooling of the combustion chamber 2. It comes from the diffuser 10.
12 12
Une partie de cet air est introduit dans le tube à flamme de la chambre de combustion 2 au niveau de l'ouverture centrale du carénage 24, tandis qu'une autre partie de l'air s'écoule vers les passages 11 et 12 d'écoulement d'air. L'air alimentant le système d'injection 4 s'écoule depuis l'ouverture centrale du carénage 24, à travers 5 notamment la vrille 7 du système d'injection représenté à la figure 1 et des trous 81, 83 qui traversent le bol mélangeur 8. Part of this air is introduced into the flame tube of the combustion chamber 2 at the level of the central opening of the fairing 24, while another part of the air flows towards the passages 11 and 12 of air flow. The air supplying the injection system 4 flows from the central opening of the fairing 24, through 5 in particular the spin 7 of the injection system shown in FIG. 1 and holes 81, 83 which pass through the mixing bowl 8.
L'air qui entre dans les orifices d'entrée d'air 73 de la vrille selon la flèche 56 imprime un mouvement de rotation selon la flèche 57 au mélange air carburant et contribue à l'atomisation du carburant. The air which enters the air inlet orifices 73 of the spin according to arrow 56 imparts a rotational movement according to arrow 57 to the air fuel mixture and contributes to the atomization of the fuel.
10 Le mélange d'air et de carburant en sortie de portion convergente 82 est confiné radialement par l'air qui est introduit dans les trous tourbillonnaires 81 selon la flèche 58. Les trous tourbillonnaires 81 impriment également au mélange un mouvement de rotation relativement à l'axe longitudinal X-X du système d'injection, selon la flèche 59. Ils contribuent à l'atomisation du carburant. The mixture of air and fuel at the outlet from the converging portion 82 is confined radially by the air which is introduced into the vortex holes 81 according to arrow 58. The vortex holes 81 also impart to the mixture a rotational movement relative to the longitudinal axis XX of the injection system, according to arrow 59. They contribute to the atomization of the fuel.
15 Le déflecteur 10 est alors notamment refroidi par un film d'air de refroidissement qui est dirigé vers le déflecteur 10 par la collerette 87, après avoir traversé les trous de refroidissement 83. The deflector 10 is then in particular cooled by a film of cooling air which is directed towards the deflector 10 by the flange 87, after having passed through the cooling holes 83.
L'écoulement d'air dans les passages 11 et 12 pénètre dans la chambre de combustion 2 par les orifices primaires 51 et les orifices de dilution 52. The air flow in the passages 11 and 12 enters the combustion chamber 2 through the primary orifices 51 and the dilution orifices 52.
20 Grâce aux trous tourbillonnaires 81, le système d'injection 4 peut ne comporter qu'une seule vrille 7. La structure du bol mélangeur 8 selon l'invention permet aussi de supprimer le venturi qui est classiquement situé entre une vrille et le bol mélangeur 8. Thanks to the swirl holes 81, the injection system 4 can have only one spin 7. The structure of the mixing bowl 8 according to the invention also makes it possible to eliminate the venturi which is conventionally located between a spin and the mixing bowl 8.
Il en découle un encombrement réduit et une limitation de la masse du This results in a reduced overall size and a limitation of the mass of the
25 système d'injection 4, tout en permettant une pulvérisation satisfaisante du mélange air- carburant dans la chambre de combustion 2. Par ailleurs, le système d'injection 4 tend à être plus facile à fabriquer. 25 injection system 4, while allowing a satisfactory spraying of the air-fuel mixture in the combustion chamber 2. Furthermore, the injection system 4 tends to be easier to manufacture.
En particulier, l'atomisation du mélange air carburant dans la chambre de combustion 2 est satisfaisante. Il n'y a plus de problèmes d'écoulement du mélange air- In particular, the atomization of the air fuel mixture in the combustion chamber 2 is satisfactory. There are no more flow problems with the air-
13 carburant au niveau d'un venturi qui a été supprimé, notamment de problèmes de film liquide sur la paroi interne du venturi. 13 fuel at a venturi that has been removed, including liquid film problems on the inner wall of the venturi.
Du fait de la présence d'une seule vrille et de l'absence de venturi, la vrille unique 7 du système d'injection présente un diamètre plus important autour de l'axe 5 longitudinal X-X du système d'injection, et le diamètre des trous de bol mélangeur 8 formés par les trous tourbillonnaires 81 est augmenté. Le système d'injection 4 est plus facile à fabriquer. Il présente une masse et un encombrement plus limités. Due to the presence of a single spin and the absence of a venturi, the single spin 7 of the injection system has a larger diameter around the longitudinal axis XX of the injection system, and the diameter of the mixer bowl holes 8 formed by swirl holes 81 is increased. The injection system 4 is easier to manufacture. It has a more limited mass and size.
Bien entendu, diverses modifications peuvent être apportées par l'homme du métier à l'invention qui vient d'être décrite sans sortir du cadre de l'exposé de 10 l'invention. Of course, various modifications can be made by those skilled in the art to the invention which has just been described without departing from the scope of the description of the invention.
En variante, la chambre de combustion 2 est une chambre de combustion d'un turbopropulseur ou d'un turboréacteur, au lieu d'être une chambre de combustion 2 annulaire d'un turboréacteur à double corps et à double flux. As a variant, the combustion chamber 2 is a combustion chamber of a turboprop engine or of a turbojet engine, instead of being an annular combustion chamber 2 of a double-body turbojet engine with double flow.
En variante, l'organe de retenue amont 21 est un segment de paroi radial 15 qui est rigidement solidaire du déflecteur 27, pour délimiter le logement du rebord radial 89 du bol mélangeur. L'organe de retenue amont 21 forme alors une seule pièce avec le déflecteur 27. Alternatively, the upstream retaining member 21 is a radial wall segment 15 which is rigidly secured to the deflector 27, to delimit the housing of the radial rim 89 of the mixing bowl. The upstream retaining member 21 then forms a single piece with the deflector 27.
En variante, la chambre de combustion 2 est dépourvue de déflecteur 27. Dans ce cas, le système d'injection 4 est notamment dépourvu de collerette 87. As a variant, the combustion chamber 2 is devoid of deflector 27. In this case, the injection system 4 is notably devoid of flange 87.
20 En variante, la douille de logement 6 comporte des trous d'alimentation en air (non représentés). Alternatively, the housing sleeve 6 has air supply holes (not shown).
En variante, la douille de logement 6 peut être fixée à la vrille 7, au lieu d'être monobloc avec la vrille 7. As a variant, the housing socket 6 can be fixed to the spin 7, instead of being integral with the spin 7.
En variante encore, la douille de logement 6 est raccordée de manière In another variant, the housing socket 6 is connected so
25 mobile par rapport à la vrille 7 et au bol mélangeur 8, pour raccorder le nez d'injecteur 31 de manière mobile par rapport à la vrille 7 et au bol mélangeur 8. Dans ce cas, la douille de logement 6 forme notamment une traversée coulissante. 25 movable relative to the spin 7 and to the mixing bowl 8, for connecting the injector nose 31 movably relative to the spin 7 and to the mixing bowl 8. In this case, the housing sleeve 6 in particular forms a passage sliding.
Lorsque la douille de logement 6 est une traversée coulissante, le bol mélangeur 8 et la vrille 7 sont par exemple fixés au fond de chambre 28 ou au déflecteur When the housing sleeve 6 is a sliding bushing, the mixing bowl 8 and the spin 7 are for example fixed to the chamber bottom 28 or to the deflector
30 27. 30 27.
14 14
Le nombre, la forme et la répartition des aubes 70 de la vrille est variable. En particulier, l'angle de calage bi peut avoir des valeurs variables. Les aubes 70 peuvent aussi être orientées selon le deuxième sens R2. Les aubes 70 sont par exemple configurées pour entraîner le mélange d'air et de carburant selon un écoulement corotatif avec celui 5 de l'air qui est introduit dans le système d'injection 4 par les trous tourbillonnaires 81. The number, shape and distribution of the blades 70 of the spin is variable. In particular, the wedging angle bi can have variable values. The vanes 70 can also be oriented in the second direction R2. The blades 70 are for example configured to drive the mixture of air and fuel in a corotative flow with that 5 of the air which is introduced into the injection system 4 through the swirl holes 81.
La forme du bol mélangeur 8 est variable. Par exemple, les valeurs du rapport de la longueur axiale li de la portion tronconique convergente 82 sur la longueur axiale b, du rapport de l'angle ai de la portion tronconique convergente 82 sur l'angle 02 de la portion tronconique divergente 84, et/ou du rapport de l'épaisseur moyenne ei de la 10 paroi externe de la portion tronconique convergente 82 sur l'épaisseur e2 de la paroi externe de la portion tronconique divergente 84 à proximité des trous tourbillonnaires 81, peuvent varier. La portion tronconique divergente 84 peut être fixée à la portion tronconique convergente 82. The shape of the mixing bowl 8 is variable. For example, the values of the ratio of the axial length li of the converging tapered portion 82 to the axial length b, of the ratio of the angle ai of the converging tapered portion 82 to the angle 02 of the diverging tapered portion 84, and / or of the ratio of the average thickness ei of the external wall of the converging frustoconical portion 82 to the thickness e2 of the external wall of the diverging frustoconical portion 84 near the swirl holes 81, may vary. The diverging frustoconical portion 84 can be fixed to the converging frustoconical portion 82.
La forme et la répartition des trous tourbillonnaires 81 et des trous de 15 refroidissement 83 est variable. En particulier, les trous tourbillonnaires 81 peuvent être situés sur plus d'une rangée annulaire, par exemple en étant répartis sur deux rangées annulaires. Les trous tourbillonnaires 81 peuvent être orientés selon le premier sens Ri, au lieu d'être orientés selon le deuxième sens R2. Par ailleurs, au moins certains des trous de la rangée annulaire 81a peuvent être dépourvue de composante circonférentielle 20 relativement à l'axe longitudinal X-X. Les trous de refroidissement 83 peuvent être situés sur plus d'une rangée annulaire, par exemple en étant répartis sur deux rangées annulaires. The shape and distribution of the swirl holes 81 and the cooling holes 83 is variable. In particular, the swirl holes 81 may be located on more than one annular row, for example by being distributed over two annular rows. The swirl holes 81 can be oriented in the first direction Ri, instead of being oriented in the second direction R2. Furthermore, at least some of the holes in the annular row 81a can be devoid of circumferential component 20 relative to the longitudinal axis X-X. The cooling holes 83 may be located on more than one annular row, for example by being distributed over two annular rows.
En variante, l'injecteur de carburant 3 est un injecteur multipoint. La chambre de combustion 2 est notamment dépourvue d'orifices primaires 51 et d'orifices de dilution 52 dans ce cas. Alternatively, the fuel injector 3 is a multi-point injector. The combustion chamber 2 is in particular devoid of primary orifices 51 and dilution orifices 52 in this case.
25 25

Claims

15 REVENDICATIONS 15 CLAIMS
1. Système d'injection (4) pour chambre de combustion (2) de turbomachine, comprenant une vrille (7) et un bol mélangeur (8) air-carburant, la vrille1. Injection system (4) for combustion chamber (2) of a turbomachine, comprising a spin (7) and an air-fuel mixing bowl (8), the spin
5 (7) comprenant une pluralité d'aubes (70) qui sont réparties sur au moins une rangée annulaire (70a), 5 (7) comprising a plurality of vanes (70) which are distributed over at least one annular row (70a),
caractérisé en ce que le bol mélangeur (8) comprend une portion tronconique convergente (82) et une portion tronconique divergente (84) autour d'un axe longitudinal (X-X) du système d'injection, la portion tronconique convergente (82) étant raccordée à la 10 vrille (7), la portion tronconique divergente (84) étant raccordée à la portion tronconique convergente (82) en formant une continuité de profil aérodynamique entre d'une part une face intérieure convergente de la portion tronconique convergente (82) et d'autre part une face intérieure divergente de la portion tronconique divergente (84), characterized in that the mixing bowl (8) comprises a convergent frustoconical portion (82) and a divergent frustoconical portion (84) around a longitudinal axis (XX) of the injection system, the frustoconical convergent portion (82) being connected at the twist (7), the diverging frustoconical portion (84) being connected to the converging frustoconical portion (82) by forming a continuity of aerodynamic profile between on the one hand a converging inner face of the converging frustoconical portion (82) and on the other hand, a divergent interior face of the divergent frustoconical portion (84),
la portion tronconique divergente (84) étant traversée par des trous 15 tourbillonnaires (81) définissant chacun un canal s'étendant suivant un axe principal comprenant une composante axiale s'étendant suivant l'axe longitudinal (X-X) du système d'injection et une composante circonférentielle autour de l'axe longitudinal (X-X) du système d'injection, la composante axiale et la composante circonférentielle étant chacune non nulle. the divergent frustoconical portion (84) being traversed by swirling holes (81) each defining a channel extending along a main axis comprising an axial component extending along the longitudinal axis (XX) of the injection system and a circumferential component around the longitudinal axis (XX) of the injection system, the axial component and the circumferential component each being non-zero.
20 20
2. Système d'injection (4) selon la revendication précédente, dans lequel le rapport d'une longueur axiale (li) de la portion tronconique convergente (82) sur une longueur axiale (b) de la portion tronconique divergente (84) est inférieur à 1, et/ou dans lequel 2. An injection system (4) according to the preceding claim, in which the ratio of an axial length (li) of the converging frustoconical portion (82) to an axial length (b) of the diverging frustoconical portion (84) is less than 1, and / or in which
25 le rapport d'un angle (ai) de la paroi externe de la portion tronconique convergente (82) relativement à l'axe longitudinal (X-X) du système d'injection sur un angle (02) de la paroi externe de la portion tronconique divergente (84) relativement à l'axe longitudinal (X-X) du système d'injection est compris entre 0,8 et 1,2, en étant notamment sensiblement égal à 1. The ratio of an angle (ai) of the outer wall of the converging frustoconical portion (82) relative to the longitudinal axis (XX) of the injection system over an angle (02) of the outer wall of the frustoconical portion divergent (84) relative to the longitudinal axis (XX) of the injection system is between 0.8 and 1.2, in particular being substantially equal to 1.
30 30
1 6 1 6
3. Système d'injection (4) selon l'une quelconque des revendications précédentes, comprenant une douille de logement (6) configurée pour loger un nez d'injecteur (31) de manière mobile relativement à la vrille (7) et au bol mélangeur (8), la douille de logement (6) étant raccordée à la vrille (7). 3. Injection system (4) according to any one of the preceding claims, comprising a housing sleeve (6) configured to accommodate an injector nose (31) movably relative to the spin (7) and the bowl mixer (8), the housing sleeve (6) being connected to the spin (7).
5 5
4. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel les trous tourbillonnaires (81) sont tous sensiblement répartis sur au moins une rangée annulaire (81a) autour de l'axe longitudinal (X-X) du système d'injection, de préférence sur une seule rangée annulaire (81a). 4. Injection system (4) according to any one of the preceding claims, in which the swirl holes (81) are all substantially distributed over at least one annular row (81a) around the longitudinal axis (XX) of the system injection, preferably on a single annular row (81a).
10 10
5. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel les trous tourbillonnaires (81) sont axialement plus proches de la sortie du bol mélangeur (8) que d'une zone de raccordement (85) de la portion tronconique divergente (84) à la portion tronconique convergente (82). 5. Injection system (4) according to any one of the preceding claims, in which the swirl holes (81) are axially closer to the outlet of the mixing bowl (8) than to a connection zone (85) of the diverging frustoconical portion (84) to the converging frustoconical portion (82).
15 15
6. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel les composantes circonférentielles de tous les trous tourbillonnaires (81) sont orientées dans un même sens (R2) relativement à l'axe longitudinal (X-X) du système d'injection, 6. An injection system (4) according to any one of the preceding claims, in which the circumferential components of all the swirl holes (81) are oriented in the same direction (R2) relative to the longitudinal axis (XX) of the injection system,
20 les trous tourbillonnaires (81) sont inclinés circonférentiellement d'un angle (b2) qui est inférieur ou égal à 60° relativement à l'axe longitudinal (X-X) du système d'injection. The vortex holes (81) are inclined circumferentially by an angle (b2) which is less than or equal to 60 ° relative to the longitudinal axis (X-X) of the injection system.
7. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel tous les trous tourbillonnaires (81) sont inclinés axialement vers7. Injection system (4) according to any one of the preceding claims, in which all the swirl holes (81) are inclined axially towards
25 l'aval par rapport à l'axe longitudinal (X-X) du système d'injection d'un angle (y) qui est sensiblement égal à 45° par rapport à l'axe longitudinal (X-X) du système d'injection. 25 downstream from the longitudinal axis (X-X) of the injection system an angle (y) which is substantially equal to 45 ° relative to the longitudinal axis (X-X) of the injection system.
8. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel le système d'injection (4) comprend une unique vrille (7), la vrille 17 8. Injection system (4) according to any one of the preceding claims, in which the injection system (4) comprises a single twist (7), the twist 17
(7) comprenant une pluralité d'aubes (70) réparties sur sensiblement une seule rangée annulaire (70a). (7) comprising a plurality of blades (70) distributed over substantially a single annular row (70a).
9. Système d'injection (4) selon l'une quelconque des revendications 5 précédentes, dans lequel la vrille (7) comprend des aubes qui sont chacune orientées circonférentiellement dans un premier sens (Ri) autour de l'axe longitudinal (X-X) du système d'injection, 9. Injection system (4) according to any one of the preceding claims, in which the spin (7) comprises vanes which are each oriented circumferentially in a first direction (Ri) around the longitudinal axis (XX) the injection system,
les trous tourbillonnaires (81) étant chacun orientés circonférentiellement dans un deuxième sens (R2) qui est opposé au premier sens relativement à l'axe longitudinal (X- 10 X) du système d'injection. the swirl holes (81) each being oriented circumferentially in a second direction (R2) which is opposite to the first direction relative to the longitudinal axis (X-10 X) of the injection system.
10. Système d'injection (4) selon l'une quelconque des revendications précédentes, dans lequel le bol mélangeur (8) comprend une collerette (87) et un becquet de liaison (86), 10. Injection system (4) according to any one of the preceding claims, in which the mixing bowl (8) comprises a collar (87) and a connecting spoiler (86),
15 la collerette (87) s'étendant de façon radiale relativement à l'axe longitudinal (X- The collar (87) extending radially relative to the longitudinal axis (X-
X) et étant située en aval de la portion tronconique divergente (84), X) and being located downstream of the divergent frustoconical portion (84),
le becquet de liaison (86) étant configuré pour raccorder le bol mélangeur (8) à un fond de chambre (28) de combustion et/ou à un déflecteur (27) de chambre de combustion (2), le becquet de liaison (86) étant raccordé à la portion tronconique divergente (84) en the connection spoiler (86) being configured to connect the mixing bowl (8) to a combustion chamber bottom (28) and / or to a combustion chamber deflector (27), the connection spoiler (86 ) being connected to the divergent frustoconical portion (84) in
20 s'étendant vers l'amont, le becquet de liaison (86) étant traversé par des orifices de refroidissement (83) qui sont orientés axialement vers la collerette (87). 20 extending upstream, the connecting spoiler (86) being traversed by cooling orifices (83) which are oriented axially towards the flange (87).
11. Chambre de combustion (2) pour turbomachine, comprenant un système d'injection (4) selon l'une quelconque des revendications précédentes. 11. Combustion chamber (2) for a turbomachine, comprising an injection system (4) according to any one of the preceding claims.
25 25
12. Chambre de combustion (2) selon la revendication précédente, comprenant un fond de chambre (28), un déflecteur (27), un organe de retenue amont (21), et le système d'injection (4), 12. Combustion chamber (2) according to the preceding claim, comprising a chamber bottom (28), a deflector (27), an upstream retaining member (21), and the injection system (4),
le système d'injection (4) comprenant un segment de paroi radial (89) qui est situé the injection system (4) comprising a radial wall segment (89) which is located
30 axialement entre l'organe de retenue amont (21) et le déflecteur (27), pour limiter le 30 axially between the upstream retaining member (21) and the deflector (27), to limit the
18 déplacement axial du système d'injection (4) relativement au fond de chambre (28) de combustion. 18 axial displacement of the injection system (4) relative to the bottom of the combustion chamber (28).
EP19848964.3A 2019-01-08 2019-12-18 Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes Pending EP3887720A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1900169A FR3091574B1 (en) 2019-01-08 2019-01-08 TURBOMACHINE INJECTION SYSTEM, INCLUDING A MIXER BOWL AND SWIRL HOLES
PCT/FR2019/053163 WO2020144416A1 (en) 2019-01-08 2019-12-18 Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes

Publications (1)

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EP3887720A1 true EP3887720A1 (en) 2021-10-06

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EP19848964.3A Pending EP3887720A1 (en) 2019-01-08 2019-12-18 Injection system for turbomachine, comprising a swirler and mixing bowl vortex holes

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EP (1) EP3887720A1 (en)
CN (1) CN113366263A (en)
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WO (1) WO2020144416A1 (en)

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US11739936B2 (en) 2023-08-29
CN113366263A (en) 2021-09-07
WO2020144416A1 (en) 2020-07-16
FR3091574B1 (en) 2020-12-11
US20220082259A1 (en) 2022-03-17
FR3091574A1 (en) 2020-07-10

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