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EP3771862A1 - Kraftstoffeinspritzernase für turbomaschine, die eine innen durch einen zapfen begrenzte kammer zur inbetriebsetzung der drehbewegung umfasst - Google Patents

Kraftstoffeinspritzernase für turbomaschine, die eine innen durch einen zapfen begrenzte kammer zur inbetriebsetzung der drehbewegung umfasst Download PDF

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Publication number
EP3771862A1
EP3771862A1 EP20187953.3A EP20187953A EP3771862A1 EP 3771862 A1 EP3771862 A1 EP 3771862A1 EP 20187953 A EP20187953 A EP 20187953A EP 3771862 A1 EP3771862 A1 EP 3771862A1
Authority
EP
European Patent Office
Prior art keywords
fuel
upstream portion
inlet
circumferential
pin
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.)
Withdrawn
Application number
EP20187953.3A
Other languages
English (en)
French (fr)
Inventor
Loïc PORA
Christophe CHABAILLE
Kevin Didier Pierre LE NORMAND
Sébastien Christophe LOVAL
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 EP3771862A1 publication Critical patent/EP3771862A1/de
Withdrawn legal-status Critical Current

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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
    • F23R3/283—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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Definitions

  • the invention relates to the general field of fuel injectors which equip the combustion chamber of a turbomachine, in particular a turbomachine of the type intended for propelling aircraft.
  • the combustion chambers of turbomachines are generally equipped with fuel injectors associated with premixing systems, commonly referred to as “injection systems”, generally comprising one or more spindles (axial and / or radial), also called “swirlers”. » Which use the air coming from a compressor arranged upstream of the combustion chamber to spray the fuel into the combustion chamber.
  • aerodynamic injectors which mainly use the pressure and speed of the air leaving the compressor to rotate the fuel leaving the nozzle of the injector
  • aeromechanical injectors which use mainly the fuel pressure inside the injector nose to rotate and spray the fuel
  • the noses of dual fuel circuit injectors comprise a primary fuel circuit, also called a pilot circuit, comprising a primary fuel swirl supplying a primary injector (also called a pilot injector) arranged on an axis of the injector nose, and a secondary fuel circuit, also called the main circuit, comprising a secondary fuel spiral supplying a secondary injector (also called the main injector) arranged around the primary injector.
  • a primary fuel circuit also called a pilot circuit
  • a secondary fuel circuit also called the main circuit
  • a secondary fuel circuit also called the main circuit
  • secondary injector also called the main injector
  • These may be aeromechanical injectors or a combination of an aeromechanical primary injector and an aerodynamic secondary injector.
  • the primary circuit is generally intended to supply the combustion chamber with fuel at all speeds, in particular during the ignition and winding phases, that is to say when the flame propagates to neighboring sectors.
  • the secondary circuit is intended to supply the engine at speeds ranging from cruising flight to take-off.
  • the injector technology uses low operating clearances, whether at the level of the primary or secondary tendrils, which equip the nose of the injectors. These fuel augers are a critical part of the injector's ability to ensure proper fuel jet atomization and hydraulic characteristic to specification.
  • the nozzles of the injectors must be able to locally ignite the combustion chamber, under various aerodynamic and thermodynamic conditions, via breakdown of one or more spark plugs then propagation of the hot gas core close to the spark plug and then into the different combustion chamber sectors. combustion.
  • the quality of the fuel jet in this transient phase is critical.
  • the engine operates on the primary flow alone, because it is desirable to limit as much as possible the quantity of fuel injected, and therefore burnt, in order to limit the heating of the turbine (s), in particular in the in-flight restart sequences.
  • the invention provides for this purpose a fuel injector nose for a turbomachine, comprising a fuel circuit comprising a rotation chamber which comprises an upstream portion into which at least one inlet channel emerges, and a downstream portion in which opens out at a downstream end of the upstream portion and which ends in a fuel injection nozzle.
  • the fuel injector nose comprises a pin which extends in the direction of the fuel ejection nozzle from a surface delimiting an upstream end of the upstream portion of the rotation chamber. , so that the pin internally delimits the upstream portion of the rotation chamber.
  • said at least one inlet channel consists of a single inlet channel
  • the upstream portion of the rotation chamber comprises a circumferential inlet and a circumferential outlet, a section of the circumferential outlet being smaller than a section of the circumferential inlet, the inlet channel and the circumferential outlet jointly opening into the circumferential inlet so that the upstream portion of the rotating chamber forms a loop around the pawn.
  • said at least one input channel consists of a number N of input channels at least equal to 2, the input channels being distributed around an axis of the fuel ejection nozzle, and the upstream portion of the rotating chamber comprises N angular portions having respective circumferential inlets and respective circumferential outlets through which the N angular portions are connected end-to-end circumferentially so that the upstream portion of the rotation chamber forms a loop around the pin, a section of the circumferential outlet of each of the N angular portions being smaller than a section of the circumferential inlet of the latter, each of the N channels d 'inlet opening into the respective circumferential inlet of a corresponding angular portion among the N angular portions, together with the respective circumferential outlet of another angular portion area among the N angular portions.
  • the configuration of the spinning chamber allows good homogeneity of the fuel velocity field in the spinning chamber, and can therefore advantageously play the role conventionally played by a fuel spinner, while offering specific advantages.
  • the pin makes it possible to promote the setting in rotation and the homogenization of the fuel within the setting in rotation chamber.
  • the invention thus makes it possible, at constant fuel flow, to reduce the number of inlet channels necessary to obtain satisfactory rotation and homogeneity of the fuel.
  • the invention makes it possible to achieve low spray rates, while ensuring the manufacturability of the injector nose, or even simplifying the manufacture of the latter.
  • the inlet channel or each inlet channel may have a larger section than each of the channels forming the tendrils in the injector noses of known type, while being, if necessary cumulatively, of section less than or equal to the cumulative section of the channels forming the tendrils in the injector noses of known type.
  • the invention makes it possible to improve the performance of the fuel injector nose in terms of atomization and particle size (drop size in ⁇ m), and therefore to increase the capacities of the combustion chamber in terms of ignition and re-ignition in flight.
  • the fuel injector nose comprises a first surface arranged around and at a distance from the pin, so that the first surface comprises an inlet part delimiting externally the inlet channel, and a main part externally delimiting the upstream portion of the rotating chamber or, where appropriate, externally delimiting a corresponding angular portion of the upstream portion of the rotating chamber.
  • the main part extends from the entry part approaching the pin and / or extends away from the pin from an end of the main part opposite to the part of. entrance.
  • the inlet channel or each inlet channel emerges tangentially into the upstream portion of the rotation chamber.
  • the pin has a cylindrical shape of revolution.
  • said fuel circuit is a primary fuel circuit
  • the fuel injector nose further comprising a secondary fuel circuit arranged around the primary fuel circuit and comprising a fuel ejection end portion arranged around the primary fuel circuit fuel ejection nozzle.
  • the invention also relates to an injection module for a turbomachine, comprising an injection system and a fuel injector nose of the type described above, in which the injection system comprises, from upstream to downstream, a socket in which is mounted the fuel injector nose, at least one air intake swirl opening downstream of the fuel injector nose, and a bowl.
  • the invention also relates to a turbomachine, comprising at least one fuel injector nose of the type described above, or at least one injection module of the type described above.
  • the figure 1 illustrates a turbomachine 10 for an aircraft of a known type, generally comprising a fan 12 intended for the suction of an air flow dividing downstream of the fan into a primary flow circulating in a flow channel of primary flow, hereinafter referred to as the primary stream PF, within a core of the turbomachine, and a secondary flow bypassing this core in a secondary flow channel, hereinafter referred to as the secondary stream SF.
  • a turbomachine 10 for an aircraft of a known type generally comprising a fan 12 intended for the suction of an air flow dividing downstream of the fan into a primary flow circulating in a flow channel of primary flow, hereinafter referred to as the primary stream PF, within a core of the turbomachine, and a secondary flow bypassing this core in a secondary flow channel, hereinafter referred to as the secondary stream SF.
  • the turbomachine is for example of the double-flow and double-body type.
  • the heart of the turbomachine thus generally comprises a low pressure compressor 14, a high pressure compressor 16, a combustion chamber 18, a high pressure turbine 20 and a low pressure turbine 22.
  • the turbomachine is streamlined by a nacelle 24 surrounding the secondary stream SF. Furthermore, the rotors of the turbomachine are mounted to rotate about a longitudinal axis 28 of the turbomachine.
  • the longitudinal direction X is the direction of the longitudinal axis 28
  • the radial direction R is at all points a direction orthogonal to the longitudinal axis 28 and passing through the latter
  • the circumferential direction or tangential C is at all points a direction orthogonal to the radial direction R and to the longitudinal axis 28.
  • the terms “internal” and “external” refer respectively to a relative proximity, and a relative distance, of an element with respect to to the longitudinal axis 28.
  • the “upstream” and “downstream” directions are defined by reference to the general direction of the gas flow in the primary PF and secondary SF streams of the turbomachine.
  • the figure 2 represents the combustion chamber 18 of the turbomachine of the figure 1 and its immediate environment.
  • this combustion chamber which is for example of annular type, comprises two coaxial annular walls, respectively radially internal 32 and radially external 34, which extend from upstream to downstream, in the direction 36 d 'flow of the primary gas flow in the turbomachine, around the longitudinal axis 28 of the turbomachine.
  • These internal 32 and external 34 annular walls are interconnected at their upstream end by an annular chamber bottom wall 40 which extends substantially radially around the longitudinal axis 28.
  • This chamber bottom annular wall 40 is equipped with injection systems 42 distributed around the longitudinal axis 28, one of which is visible on the figure 2 , each receiving an injector nose 43 mounted at the end of an injector rod 45, to allow the injection of a premix of air and fuel centered along a respective injection axis 44.
  • each injection system 42 comprises a sleeve 46, commonly referred to as a “sliding bushing”, in which the corresponding injector nose 43 is mounted with the ability to slide to allow differential thermal expansions in operation.
  • the sleeve 46 internally delimits a single air intake swirl 48, for example of the axial type, formed within the injection system 42.
  • Each injection system 42 further comprises a divergent bowl 49 arranged at the outlet of the air intake swirl 48 and opening into the combustion chamber 18.
  • the assembly formed of an injection system 42 and the corresponding injector nose 43 constitutes an injection module, in the terminology of the present invention.
  • part 50 of an air flow 52 coming from a diffuser 54 and coming from the compressor 16 feeds the injection systems 42, while another part 56 of the air flow 52 feeds the orifices of 'air inlet 58 formed in the walls 32 and 34 of the combustion chamber, in a well known manner.
  • the longitudinal direction X ' is the direction of the injection axis 44
  • the radial direction R' is at all points a direction orthogonal to the injection axis 44 and passing through the latter
  • the circumferential or tangential direction It is at all points a direction orthogonal to the radial direction R 'and to the injection axis 44.
  • the terms “internal” and “external” refer respectively to a relative proximity, and a relative distance, of a element with respect to the injection axis 44.
  • upstream and downstream directions are defined with reference to the general direction of the flow of air and fuel in the injector nose 43
  • a transverse plane is defined as a plane orthogonal to the injection axis 44
  • an axial plane is defined as a plane containing the injection axis 44.
  • the figure 3 illustrates in more detail a fuel injector nose 143 of a known type.
  • This comprises a primary fuel circuit 162 which occupies a central position relative to the injection axis 44, a secondary fuel circuit 164 arranged around the primary fuel circuit 162, as well as a peripheral cooling circuit 166 arranged around the secondary fuel circuit 164.
  • the primary circuit 162 is intended for the emission of a primary fuel cone 168, while the secondary circuit 164 is intended for the emission of a secondary fuel layer 169 of frustoconical annular shape, surrounding the cone. primary fuel 168.
  • the secondary fuel circuit 164 comprises an annular fuel supply channel 170 opening into a secondary fuel swirler 172 which itself opens into a secondary rotation chamber 174, of annular shape, which forms an end part of fuel ejection opening at the free end 176 of the injector nose 143.
  • the primary fuel circuit 162 comprises a central fuel supply channel 180, an annular distribution chamber 182 connected to the central channel 180 by radial channels 184, a primary fuel swirler 186 connected to the annular distribution chamber 182 and opening out. in a primary rotation chamber 187 leading to a fuel ejection nozzle 188, i.e. a throttle from which fuel is ejected in the form of a divergent spray, i.e. - say in general in the form of a hollow conical sheet.
  • This fuel ejection nozzle 188 has an axis which merges with the injection axis 44.
  • the figure 4 shows the space occupied, in operation, by the fuel within an end part of the primary circuit 162, corresponding to the primary fuel swirler 186, the primary rotation chamber 187 and the fuel ejection nozzle 188 , and by the primary cone 168.
  • the figure 5 is a sectional view along the VV plan of the figure 3 , showing the flow of fuel within the primary spinner 186.
  • the primary swirler 186 is formed of channels 190 opening into the primary rotation chamber 187. These channels 190 are orthogonal to the injection axis 44 but not intersecting with the latter, and therefore not parallel to the radial direction R '. As a result, the fuel C1 coming from these channels 90 is naturally rotated C2 in the primary rotation chamber 187.
  • a primary spinner of this type requires several channels 190 distributed around the injection axis 44, typically three or four channels for fuel injector noses of common dimensions, otherwise the fuel cannot be rotated. This is not performed satisfactorily and the homogeneity of the fuel velocity field at the fuel ejection nozzle 188 may be insufficient.
  • the channels must also have a sufficiently large passage section to allow correct flow of the fuel, and also due to constraints inherent in the manufacturing processes. However, this goes against the need to be able to have very low fuel flow rates in certain operating phases, in particular when the combustion chamber is ignited.
  • the invention generally proposes to remedy these drawbacks by means of a pin internally delimiting an upstream portion of the rotation chamber, as will appear more clearly in what follows.
  • the invention is not limited to its application to the primary circuit of a dual-circuit injector, the principle of the invention also being applicable in other contexts, for example in the case of a single circuit injector.
  • the application of the invention is also not limited to the specific examples of an injection system, of a combustion chamber, and of a turbomachine, described above with reference to figures 1 and 2 .
  • the figure 6 illustrates a fuel injector nose 243 capable of equipping the turbomachine with figures 1 and 2 and in accordance with a preferred embodiment of the invention.
  • This injector nose 243 has a configuration similar to that of the injector nose 143 of known type described above, except in that it comprises a pin 254 internally delimiting an upstream portion 270 of the rotation chamber 252. .
  • the figures 7 to 10 more particularly illustrate the pawn 254 and its close environment.
  • the figure 8 shows in particular the circulation of fuel C3 in operation.
  • the pin 254 which is preferably centered on the injection axis 44, extends in the direction of the fuel ejection nozzle 188 from a surface 272 defining an upstream end of the upstream portion 270 of the rotation chamber 252.
  • the fuel injector nose 243 has a single inlet channel 250, and the upstream portion 270 of the rotation chamber 252 substantially forms a loop around the pin 254.
  • the inlet channel 250 opens into a part of the upstream portion 270, hereinafter referred to as the circumferential inlet 274, together with another part of the upstream portion 270, hereinafter referred to as the circumferential outlet 276.
  • the circumferential outlet 276 has a section S1 which is smaller than a section S2 of the circumferential inlet 274 ( figure 10 ).
  • the sections S1 and S2, and any other section of the upstream portion 270 defined between the sections S1 and S2 are defined in the radial direction with respect to the axis 44.
  • the upstream portion 270 preferably has a section which gradually decreases from the circumferential inlet 274 to the circumferential outlet 276.
  • the fuel injector nose 243 comprises a first surface 256 arranged around and at a distance from the pin 254, so that the first surface 256 comprises a main part 256A externally delimiting the upstream portion 270 of the rotation chamber 252, and an input portion 256B externally delimiting the input channel 250 ( figures 7, 8 and 10 ).
  • the first surface 256 is for example in the form of a spiral staircase. It should be understood, by “spiral shape”, that the first surface 256 has, in its main part 256A, a first end, called the output end 258, directly opposite the pin 254, and that the first surface 256 extends to from its outlet end 258 by rotating about the injection axis 44, while moving away from said axis ( figures 7 and 10 ), up to a second opposite end, called the end inlet 262, formed at the end of the inlet portion 256B. In the example illustrated, the distance is continuous from the outlet end 258 to the inlet end 262.
  • the distance may concern only one or more parts of the first surface 256 while that one or more other parts of this first surface 256 extend at a constant distance from the injection axis 44.
  • the circumferential inlet 274 and the circumferential outlet 276 are defined in a radial plane intercepting the outlet end 258 of the first surface 256.
  • the main part 256A of the first surface 256 extends directly opposite the pin 254 so that the pin 254 and the main part 256A define between them the upstream portion 270 of the rotation chamber 252.
  • the entry part 256B of the first surface 256 is masked by the main part 256A with respect to the pin 254.
  • the exit end 258 of the first surface 256 is arranged radially between the entry part 256B and pawn 254.
  • the fuel injector nose 243 further comprises a second surface 278 arranged facing the inlet part 256B of the first surface 256 and internally delimiting the inlet channel 250.
  • the second surface 278 is arranged between the part d The inlet 256B of the first surface 256 and an end portion 256AA of the main portion 256A of the first surface 256 defined from the outlet end 258 thereof.
  • the inlet channel 250 opens out tangentially into the upstream portion 270 of the rotation chamber 252. It should be understood by this that, in a view in cross section to the injection axis 44 ( figure 10 ), an output axis 280 of the input channel 250 ( figure 10 ), tangent to an average line 282 of the inlet channel 250 at the level of the circumferential inlet 274 of the upstream portion 270 of the rotation chamber 252, does not intercept the pin 254.
  • the inlet part 256B of the first surface 256 is for example with a rectilinear cross section tangent to the end of the main part 256A from which the inlet part 256B extends
  • the second surface 278 is for example with a rectilinear cross section parallel to the inlet portion 256B and connected to the outlet end 258 of the first surface 256.
  • the figure 11 illustrates a variant in which the inlet portion 256B of the first surface 256 and the second surface 278 are curved.
  • the rotation chamber 252 extends axially from the upstream portion 270 thereof, presenting a downstream portion 266 which terminates in the ejection nozzle 188.
  • downstream portion 266 is of convergent shape up to the ejection nozzle 188 ( figures 8 and 9 ).
  • the pin 254 is of cylindrical shape of revolution and has a solid downstream end surface 268 oriented transversely to the injection axis 44 ( figures 7 and 9 ).
  • the presence of the pin 254 within the fuel injector nose 243 according to the invention makes it possible to promote the rotation and the homogenization of the fuel within the rotation chamber 252.
  • L The invention thus makes it possible, at constant fuel flow, to reduce the number of inlet channels necessary to obtain satisfactory rotation and homogeneity of the fuel.
  • the invention makes it possible, in general, to improve the performance of the injector nose in terms of atomization and particle size (drop size in ⁇ m), and therefore to increase the capacities of the combustion chamber in terms of ignition and re-ignition in flight.
  • the invention makes possible a fuel injector nose configuration comprising only a single inlet channel 250.
  • the fuel injector nose 243 comprises several inlet channels, for example the number of of them ( figure 12 ) or three ( figure 13 ), or more generally N input channels 250-i, N being an integer greater than or equal to 2 and i being an integer taking the values ranging from 1 to N.
  • the upstream portion 270 of the rotation chamber 252 is formed of N angular portions 270-i comprising respective circumferential inlets 274-i and respective circumferential outlets 276-i through which the N angular portions 270-i are connected end-to-end circumferentially so that the upstream portion 270 of the rotation chamber 252 forms a loop around the pin 254.
  • the inlet channels 250-i are distributed, preferably evenly, around the axis of the fuel ejection nozzle 188, that is to say the 'injection axis 44.
  • the inlet channels 250-1 to 250-N and the angular portions 270-1 to 270-N are arranged in this order around the injection axis 44, for example clockwise in the figures.
  • each of the N angular portions 270-i has a section S1-i at its circumferential outlet 276-i which is smaller than a section S2-i at its circumferential inlet 274-i.
  • each of the N inlet channels 250-i opens into the respective circumferential inlet 274-i of a corresponding angular portion 270-i among the N angular portions, together with the respective circumferential outlet 276-k of another angular portion 270-k among the N angular portions which precede the angular portion 270-i, k therefore being an integer equal to (i + N-2) mod (N) +1, where "mod" denotes the mathematical operation modulo.
  • Each of the N input channels 250-i is preferably the image of an input channel 250-k which precedes the latter, by a rotation of angle 2Pi / N radiating.
  • each of the N angular portions 270-i is preferably the image of an angular portion 270-k which precedes the latter, by a rotation of angle 2Pi / N radiating.
  • the fuel injector nose 243 comprises N first surfaces 256-i arranged at a distance from the pin 254, so that each first surface 256-i comprises a main part 256A-i outwardly delimiting a corresponding angular portion 270-i, and an input portion 256B-i externally delimiting an input channel 250-i corresponding.
  • Each main part 256A-i has for example a cross section in the form of an arc of a circle eccentric with respect to the injection axis 44 so as to approach the pin 254 from the circumferential entry 274-i to the circumferential outlet 276-i of the corresponding angular portion 270-i.
  • Each inlet part 256B-i has for example a rectilinear cross section tangent to the end of the main part 256A-i from which the inlet part 256B-i extends.
  • the fuel injector nose 243 further comprises an N second surfaces 278-i arranged respectively facing the respective inlet portions 256B-i of the first surfaces 256-i and internally delimiting the inlet channels 250-i respectively.
  • Each second surface 278-i is advantageously tangent to the main part 256A-k of the first surface 256-k delimiting the aforementioned angular part 270-k.
  • each inlet channel 250-i opens out tangentially into the corresponding angular portion 270-i. It should be understood by this that, in a view in cross section to the injection axis 44, an output axis 280-i of the input channel 250-i, tangent to a mean line 282-i of the channel d The entry 250-i at the level of the circumferential entry 274-i of the angular portion 270-i, does not intercept the pin 254.
  • the invention makes it possible to limit the number of inlet channels necessary to obtain satisfactory rotation and homogeneity of the fuel.
  • the pin 254 has a solid shape.
  • the pin 254 may have a central recess 284 ( figure 14 ) opening into the downstream end surface 268 of the pin 254. In certain cases, it is indeed desirable to provide such a central recess so as to reduce the tangential speed of the fuel near the downstream end surface 268.
  • downstream portion 266 of the rotation chamber 252 may not converge downstream but be of constant section ( figure 15 ), so that a Sudden section change takes place between the downstream portion 266 and the fuel ejection nozzle 188.
  • downstream end surface 268 of the pin 254 extends transversely at a downstream surface 286 ( figures 14 and 15 ) delimiting the input channel 250 or each input channel 250-i on the downstream side.
  • the pin 254 may extend downstream beyond the downstream surface 286 ( figure 16 ).

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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)
EP20187953.3A 2019-07-29 2020-07-27 Kraftstoffeinspritzernase für turbomaschine, die eine innen durch einen zapfen begrenzte kammer zur inbetriebsetzung der drehbewegung umfasst Withdrawn EP3771862A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1908615A FR3099547B1 (fr) 2019-07-29 2019-07-29 Nez d'injecteur de carburant pour turbomachine comprenant une chambre de mise en rotation intérieurement délimitée par un pion

Publications (1)

Publication Number Publication Date
EP3771862A1 true EP3771862A1 (de) 2021-02-03

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EP20187953.3A Withdrawn EP3771862A1 (de) 2019-07-29 2020-07-27 Kraftstoffeinspritzernase für turbomaschine, die eine innen durch einen zapfen begrenzte kammer zur inbetriebsetzung der drehbewegung umfasst

Country Status (3)

Country Link
EP (1) EP3771862A1 (de)
CN (1) CN112303663B (de)
FR (1) FR3099547B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115682032A (zh) * 2022-11-03 2023-02-03 西北工业大学 一种新型多环式燃料支板喷注器

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US8567198B2 (en) * 2010-01-29 2013-10-29 Alstom Technology Ltd. Injection nozzle having constant diameter pin and method for operating the injection nozzle
FR3015638A1 (fr) * 2013-12-23 2015-06-26 Snecma Segment d'obturation de traversee coulissante de systeme d'injection pour turbomachine

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FR3099547A1 (fr) 2021-02-05

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