EP4065892B1 - Système d'injection d'air et de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée - Google Patents

Système d'injection d'air et de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée Download PDF

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Publication number
EP4065892B1
EP4065892B1 EP20820511.2A EP20820511A EP4065892B1 EP 4065892 B1 EP4065892 B1 EP 4065892B1 EP 20820511 A EP20820511 A EP 20820511A EP 4065892 B1 EP4065892 B1 EP 4065892B1
Authority
EP
European Patent Office
Prior art keywords
injection
mixing device
injector
injection system
air
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.)
Active
Application number
EP20820511.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP4065892A1 (fr
Inventor
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
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4065892A1 publication Critical patent/EP4065892A1/fr
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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
    • F23R3/286—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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Definitions

  • the invention relates to air and fuel injection systems equipping the annular combustion chambers of turbomachines, particularly those of aircraft.
  • FIG 1 illustrates an air and fuel injection system 1 of known type comprising a fuel injector 2 and a mixing device 3 equipping a bottom wall of a combustion chamber (not shown on the figure 1 ).
  • the mixing device 3 comprises, from upstream to downstream in a general direction 4 of fuel flow, a centering member 5 of a head 12 of the injector 2, an intake crown air 7 and a conical wall 8 which is flared downstream called bowl in the following.
  • the bowl 8 is intended to guide at the outlet of the injection system 1 a mixture of air and fuel intended to ignite in the primary zone of the combustion chamber.
  • the centering member 5 (or sliding bushing) is made up of an annular part flared towards the upstream in order to facilitate the introduction of the injection head during its assembly.
  • the air intake crown 7 comprises fins (not shown) to impart to the air passing through this crown a gyrating movement around a longitudinal axis AA' of the mixing device 3.
  • This crown comprises a primary spinner 71 and a secondary spinner 72.
  • the mixing device 3 is equipped with a venturi 9 in order to accelerate the flow of fluids at its level.
  • the head of the injector 12 comprises an injection nose 13 through which the fuel is intended to be supplied.
  • the head 12 is inserted into the mixing device 3 via the centering member 5.
  • the head 12 of the injector is in contact with the internal annular wall 10 of the mixing device 3 according to a spherical part 11 which allows have a swivel connection between the internal annular wall 10 and the head 12.
  • the invention proposes to overcome at least one of these drawbacks.
  • the invention proposes a combustion chamber of a turbomachine comprising an injection system according to the first aspect of the invention.
  • the invention proposes a turbomachine comprising a combustion chamber according to the second aspect of the invention.
  • FIG. 2 illustrates an air and fuel injection system 21 of a turbomachine according to one embodiment of the invention.
  • Such an injection system comprises an injector 22 and a mixing device 25 arranged downstream of the injector 22 in a direction of flow of the fuel in the injection system.
  • upstream and downstream are defined in relation to the direction of fuel flow (from left to right on the figure 2 ).
  • the injector 22 comprises a fuel supply pipe 23 ending in an injection nose 24.
  • This pipe 23 is an extension of an upstream conduit and makes an elbow with the latter.
  • Pipeline 23 extends from upstream to downstream along a longitudinal axis AA' of the air and fuel injection system.
  • the injector 22 further comprises an air injection crown 26, downstream of the pipe 23.
  • the air injection crown 26 comprises a first twist 261 and a second twist 262.
  • the crown 26 surrounds the nose injection 24.
  • the first and second tendrils of the air injection crown 25 include air passages arranged all around.
  • a ring 28 for connecting the injector 22 to the mixing device 25.
  • This ring 28 comprises an annular part 281 which is extended by a divergent part 282 flared downstream.
  • the mixing device 25 is arranged downstream of the injection nose 24.
  • the mixing device 25 is in particular made up of a bowl 27 comprising an annular inlet 30 which is extended by a conical part 33 flared downstream.
  • the annular inlet 30 constitutes the inlet of the mixing device
  • the mixing device 25 defines an annular cavity 29 in which, in operation, the mixture of air and fuel takes place.
  • the injector is partly arranged in this annular cavity 29.
  • the injector must be in fluid communication with the mixing device.
  • connection ring 28 of the injector It is via the ring 28 of the injector that the injector 22 is in communication with the mixing device 25.
  • the connection ring 28 is advantageously arranged around the inlet 30 of the mixing device 25.
  • the connection ring 28 has an internal diameter greater than that of the inlet 30 of the mixing device 25 so that this connection ring 28 encompasses the inlet of the mixing device.
  • this ring 28 is flared downstream in order to facilitate the insertion of the mixing device inlet 25, at the level of the bowl 27, in the connection ring 28 during the assembly of the injector to the mixing device.
  • the inlet 30 of the mixing device 25 comprises an external surface 31 which takes the form of a truncated sphere and the ring 28 is in contact with the inlet of the bowl via this truncated sphere.
  • the injector and the mixing device present at this contact zone a connection which allows movement relative of the injector relative to the mixing device.
  • the injector and the mixing device have a swivel connection at this contact zone.
  • this arrangement makes it possible, during the operation of the injection system, to authorize relative movements of the injector relative to the mixing device without affecting the operation of the injection system. Indeed, as presented in the introduction during the operation of the turbomachine the injection system is subjected to very strong movements which are applied to the different elements constituting the injection system.
  • the injector 22 comprises a venturi 32 located axially in the vicinity of the injection nose 24.
  • the venturi 32 is part of the injector and not of the mixing device.
  • the venturi 32 is arranged between the first and second tendrils of the air injection crown 26 of the injector 22.
  • the injection head is now axially arranged at the level of the venturi 32 and is closer to the inlet 30 of the mixing device. The mixture is therefore better.
  • the conduit 23, the ring 28 and the venturi 32 are formed in one piece, that is to say that all the parts constituting them are machined in the same part.
  • These parts can be obtained by an additive manufacturing process and are preferably in one piece.
  • the air injection crown and the injector connection ring are formed in a single piece, preferably obtained by an additive manufacturing process.
  • the inlet 30 of the mixing device is located in the air passage of the second swirl 262. Indeed, as can be seen in the figure 2 , the air arriving via the second spindle 262 and guided by the venturi will directly arrive in the inlet 30 of the mixing device.
  • the injection nose 24 is arranged relative to the venturi 32 so as to open the fuel spray angle to the maximum without impacting the venturi 32 or the bowl 27 while maintaining a passage section between the nose 24 and the venturi 32. Indeed, when the assembly is in one piece it is easier to position the different elements in relation to each other since in this case we are freed from relative movements between the parts.
  • FIG 3a illustrates the fuel spray S coming from the injection nose 24.
  • the injection system 22 described above is advantageously implemented in a combustion chamber 40 of a turbomachine as illustrated in the Figure 4 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
EP20820511.2A 2019-11-26 2020-11-24 Système d'injection d'air et de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée Active EP4065892B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1913223A FR3103540B1 (fr) 2019-11-26 2019-11-26 Système d'injection de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée
PCT/FR2020/052164 WO2021105607A1 (fr) 2019-11-26 2020-11-24 Système d'injection de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associé

Publications (2)

Publication Number Publication Date
EP4065892A1 EP4065892A1 (fr) 2022-10-05
EP4065892B1 true EP4065892B1 (fr) 2023-11-08

Family

ID=70738604

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20820511.2A Active EP4065892B1 (fr) 2019-11-26 2020-11-24 Système d'injection d'air et de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée

Country Status (5)

Country Link
US (1) US11933497B2 (zh)
EP (1) EP4065892B1 (zh)
CN (1) CN114746699B (zh)
FR (1) FR3103540B1 (zh)
WO (1) WO2021105607A1 (zh)

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6314739B1 (en) * 2000-01-13 2001-11-13 General Electric Company Brazeless combustor dome assembly
FR2859272B1 (fr) * 2003-09-02 2005-10-14 Snecma Moteurs Systeme d'injection air/carburant, dans une chambre de combustion de turbomachine, ayant des moyens de generation de plasmas froids
FR2875584B1 (fr) * 2004-09-23 2009-10-30 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
FR2886714B1 (fr) * 2005-06-07 2007-09-07 Snecma Moteurs Sa Systeme d'injection anti-rotatif pour turbo-reacteur
FR2899314B1 (fr) 2006-03-30 2008-05-09 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2903170B1 (fr) * 2006-06-29 2011-12-23 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2903172B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette
FR2941288B1 (fr) * 2009-01-16 2011-02-18 Snecma Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
US9951955B2 (en) * 2011-05-17 2018-04-24 Snecma Annular combustion chamber for a turbine engine
FR2988813B1 (fr) * 2012-03-29 2017-09-01 Snecma Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
FR3001283A1 (fr) * 2013-01-18 2014-07-25 Snecma Traversee coulissante d'axe d'inclinaison variable relativement a l'axe d'un bol melangeur
FR3029271B1 (fr) * 2014-11-28 2019-06-21 Safran Aircraft Engines Paroi annulaire de deflection pour systeme d'injection de chambre de combustion de turbomachine offrant une zone etendue d'atomisation de carburant
FR3033030B1 (fr) * 2015-02-20 2018-04-13 Safran Aircraft Engines Systeme d'injection d'un melange air-carburant dans une chambre de combustion de turbomachine d'aeronef, comprenant un venturi perfore de trous d'injection d'air
FR3040765B1 (fr) * 2015-09-09 2017-09-29 Snecma Element d'appui pour amortir des deplacements axiaux de traversee coulissante de systeme d'injection pour turbomachine
FR3081539B1 (fr) * 2018-05-23 2021-06-04 Safran Aircraft Engines Fond de chambre de combustion de turbomachine
FR3082284B1 (fr) * 2018-06-07 2020-12-11 Safran Aircraft Engines Chambre de combustion pour une turbomachine

Also Published As

Publication number Publication date
FR3103540A1 (fr) 2021-05-28
CN114746699A (zh) 2022-07-12
CN114746699B (zh) 2023-08-25
WO2021105607A1 (fr) 2021-06-03
FR3103540B1 (fr) 2022-01-28
EP4065892A1 (fr) 2022-10-05
US11933497B2 (en) 2024-03-19
US20230003386A1 (en) 2023-01-05

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