WO2012156631A1 - Chambre annulaire de combustion pour une turbomachine - Google Patents
Chambre annulaire de combustion pour une turbomachine Download PDFInfo
- Publication number
- WO2012156631A1 WO2012156631A1 PCT/FR2012/051056 FR2012051056W WO2012156631A1 WO 2012156631 A1 WO2012156631 A1 WO 2012156631A1 FR 2012051056 W FR2012051056 W FR 2012051056W WO 2012156631 A1 WO2012156631 A1 WO 2012156631A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- auger
- fuel
- channels
- downstream
- longitudinal axis
- Prior art date
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Classifications
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- 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
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- 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
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- 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
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- 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
Definitions
- the present invention relates to an annular combustion chamber of a turbomachine such as an airplane turbojet or turboprop.
- An annular combustion chamber comprises two coaxial annular walls, respectively internal and external, interconnected at their upstream ends by an annular chamber bottom wall having openings in each of which is mounted a fuel injection system.
- a conventional injection system comprises means for supporting and centering an injector head, and primary and secondary tendrils which are mounted downstream of the support means, coaxially with these means, and which deliver each of the flow streams. radial air downstream of the injector to achieve a mixture of air and fuel to be injected and burned in the combustion chamber. The air exiting the primary swirler is accelerated in a venturi sandwiched between the two tendrils. A frustoconical mixing bowl is mounted downstream of the tendrils for spraying the air / fuel mixture which enters the combustion chamber.
- the tendrils of the injection system each comprise substantially radial channels which deliver a swirling air flow or "swirl" in English terminology.
- these channels have a section in the form of a square or rectangle having a longitudinal axis, their upstream and downstream faces being perpendicular to this longitudinal axis and interconnected by side faces parallel to this axis.
- the combustion chamber is equipped with an annular row of fuel injectors which extends around the longitudinal axis of the bedroom.
- Each injector comprises one or two fuel circuits which each feed a helical channel located in the head of the injector, this helical channel for rotating the fuel around the longitudinal axis of the head and producing a sheet of fuel wherein the velocity vectors of the sprayed fuel drops are all oriented in the same direction (clockwise or anticlockwise) with respect to the longitudinal axis of the injector head and all form the same angle with respect to this longitudinal axis.
- This angle is substantially equal to the helix angle of the aforementioned helical channel, that is to say the angle formed between a tangent line at a point of the helical channel and the longitudinal angle of the injector head.
- each injector is engaged axially in the abovementioned support means of an injection system, these support means comprising axial air purge orifices which open radially inside the primary swirler for ventilation of the injector system. venturi.
- the flow of air exiting these purge orifices disturbs the vortex flow of air delivered by the primary swirler, which causes turbulence and recirculation of the air-fuel mixture in the venturi and results in the deposition of soot and coke on the inner surface of the venturi.
- This deposit can interfere with the injection of the air / fuel mixture into the chamber and locally create hot spots inside the chamber, which notably promotes the emission of harmful gases such as nitrogen oxides (NOx).
- NOx nitrogen oxides
- the invention aims in particular to provide a simple, effective and economical solution to this problem.
- annular combustion chamber for a turbomachine, comprising two coaxial annular walls, respectively internal and external, connected at their upstream ends by an annular wall forming a bottom of the chamber, and an annular row of fuel injectors.
- each injector head having at least one helical fuel passage channel for rotating the fuel around the longitudinal axis of the head, and each injection system comprising at least one twist coaxial with the nozzle head and having substantially radial air passage channels having an elongate section having an axis, characterized in that the longitudinal axes of the sections of said channels are inclined relative to the longitudinal axis of the auger, an angle which is substantially equal to the helix angle of the aforementioned helical channel of the injector head, within +/- 10 °, and are oriented in the same meaning as this channel around the longitudinal axis of the spin.
- the axes of the sections of the channels of the tendril are thus substantially parallel, within +/- 10 °, to the velocity vectors of the drops of fuel sprayed into the injection system, which allows the air flow delivered by the auger to shearing the fuel layer by limiting recirculations of the air-fuel mixture downstream of the tendril and the risk of coke deposition on the internal surface of the venturi.
- the axes of the sections of the channels of the auger are inclined at an angle which is substantially equal to the helix angle of the helical channel of the injector head.
- the axes of the sections of the channels of the auger are for example inclined at an angle of between 20 and 40 ° approximately with respect to the longitudinal axis of the auger.
- Each fuel injector may comprise a first fuel supply circuit of a helical channel and a second fuel independent supply circuit of another helical channel (outer) of greater diameter than the first helical channel (internal).
- These fuel systems provide two cone-shaped coaxial fuel plies with different opening angles.
- the lower opening fuel level can be optimized at engine start and for the full throttle and the second larger aperture angle can be optimized for the speed range from start to full throttle.
- the axes of the channel sections of the auger are preferably inclined at the same angle and in the same direction as the outer helical channel for producing the larger opening angle of fuel.
- Each channel of the tendril may have a section in the form of a square, rectangle or rhombus.
- the auger is formed in one piece with the support means of the injection system.
- the spin may comprise at its downstream end a cylindrical peripheral retaining rim on a venturi located downstream of the auger.
- the channels of the tendrils are separated from each other by vanes.
- Each of these vanes may comprise at least one through air passage orifice, which is inclined relative to the longitudinal axis of the tendril substantially at the same angle and in the same direction as the axes of the sections of the channels located from on both sides of this blade.
- These orifices communicate with through orifices formed in the venturi for the passage of an air flow intended to flow along the outer surface of the venturi and the inner surface of the bowl.
- each injection system comprises two tendrils, respectively upstream and downstream
- the mixing bowl comprises at least one annular row of air passages for mixing with the fuel
- the axes of the sections channels of the upstream tendon are inclined at the same angle and in the same direction as the helical channel of the injector head
- the axes of the channel sections of the downstream tendon are oriented in the same direction as the helical channel of the injector head.
- the mixing bowl has orifices of the aforementioned type, it is indeed advantageous for the air flows delivered by the tendrils to be co-current with the speed vectors of the drops of the fuel layer.
- the angle between the axes of the downstream swirly channel sections and the longitudinal axis of the swirler may be the same as or different from that between the axis axes of the upstream swirler and the longitudinal axis.
- each injection system comprises two tendrils, respectively upstream and downstream, and a mixing bowl devoid of air passage holes for mixing with the fuel
- the axes of the sections of the channels of the upstream twist are inclined at the same angle and in the same direction as the helical channel of the injector head
- the axis axes of the channels of the downstream swirler are oriented in the opposite direction to the helical channel of the head of injector around the longitudinal axis of the tendril.
- the mixing bowl has no orifices of the aforementioned type, it is indeed advantageous for the air flow delivered by the upstream auger to be co-current with the velocity vectors of the fuel drops and the flow of air delivered by the downstream spin is against the flow of these velocity vectors, so that the air flow delivered by the downstream auger stabilizes the flame in the focus of the combustion chamber.
- the angle between the axes of the downstream swept channel sections and the longitudinal axis of the swirler may be identical to that between the axes of the channel sections of the upstream swirler and this axis.
- the channels of the auger are separated from each other by vanes and may be contained in a radial plane.
- the trailing edges or radially inner ends of the vanes extending advantageously on a frustoconical surface flared downstream about the longitudinal axis of the injection system.
- the swirling airflow delivered by the spin of the injection system is intended to sweep and ventilate the injector head and the venturi and to mix with the fuel injected into the chamber.
- the auger thus provides in addition to its main function a function similar to that of bleeding orifices of the prior art and can therefore be considered as a "purgeuse" auger.
- the injection system is therefore advantageously free of purge orifices of the above-mentioned type, which makes it possible to eliminate the turbulences associated with the interaction of the air flows leaving the purge orifices and the prior art twist, as well as that the risks of deposit of coke on the venturi due to these turbulences.
- each vane of the vortex may comprise a curved surface (concave inward) and inclined from upstream to downstream outward.
- the frustoconical surface on which the trailing edges extend has an opening angle of the order of 45 to 65 ° for example, which corresponds substantially to that of the fuel ply sprayed by the injector into the system.
- the vanishing edges of the vanes therefore extend parallel to the outer peripheral surface of the fuel layer, which facilitates the mixing of air and fuel in the venturi.
- the removal of the purge orifices makes it possible to reduce the number of orifices of the injection system compared with those of the prior art and to increase the diameter of the orifices remaining for a given permeability of the system (equal to the sum effective sections of the orifices and air passage channels of the system), which facilitates their machining and reduces their cost of production, and allows for a small diameter injection system for a small turbine.
- Each injection system may comprise a venturi and a mixing bowl located downstream of the auger, the auger providing ventilation of the venturi, by guiding the airflow exiting the auger along the inner surface of the venturi.
- the spin comprises at its downstream end a cylindrical peripheral rim hooking on the venturi.
- Each injection system may comprise means for supporting and centering an injector head, these support means comprising an internal cylindrical surface which is intended to surround the head of the injector and which is connected to its downstream end. at the upstream end of smaller diameter of the aforementioned frustoconical surface.
- the present invention also relates to a turbomachine, such as an airplane turbojet or turboprop engine, characterized in that it comprises an annular combustion chamber as described above.
- FIG. 1 is a schematic half-view in axial section of a diffuser and an annular turbomachine combustion chamber according to the prior art
- FIG. 2 is a partial diagrammatic view in axial section of a fuel injector for a turbomachine combustion chamber
- FIG. 3 is a view on a larger scale of the injection system of FIG. 1;
- FIG. 4 is a sectional view along the line IV-IV of Figure 3;
- FIG. 5 is a partial schematic perspective view of an injector head and an injection system for a combustion chamber according to the invention.
- FIG. 8 is a diagrammatic view in axial section of an injection system according to the invention.
- FIG. 9 is a schematic perspective view of the injection system of Figure 8, seen from upstream and side;
- FIG. 10 is a diagrammatic perspective view of the twist of the injection system of FIG. 8, seen from downstream and from the side;
- FIG. 1 1 is a view of the downstream face of a swirler according to an alternative embodiment of the injection system according to the invention.
- FIG. 12 is a view corresponding to FIG. 8 and showing the alternative embodiment of the injection system of FIG. 11.
- FIG. 1 represents an annular combustion chamber 10 of a turbomachine, such as an airplane turbojet or turboprop engine, this chamber being arranged at the outlet of a diffuser 12, itself located at the outlet of a compressor (not shown).
- a turbomachine such as an airplane turbojet or turboprop engine
- the chamber 10 comprises a wall of internal revolution 14 and a wall of external revolution 16 which are connected upstream by an annular wall 18 of the chamber bottom.
- An annular shroud 20 is fixed on the upstream ends of the walls 14, 16 of the chamber and comprises openings 22 for air passage aligned with openings 24 of the wall 18 of the chamber bottom in which are mounted systems 26 of fuel injection, the fuel being supplied by injectors 28 regularly distributed around the axis of the chamber.
- a part of the air flow 32 supplied by the compressor and leaving the diffuser 12 enters the annular enclosure defined by the shroud 20, passes into the injection system 26, and is then mixed with the fuel supplied by the injector 28 and sprayed into the combustion chamber 10.
- Each injector 28 comprises a fuel injection head 30 engaged in an injection system 26 and aligned on the axis of an opening 24 of the chamber bottom wall 18.
- Figure 2 shows on a larger scale the head 30 of a fuel injector 28 of the type comprising two fuel circuits, which is described in detail in the application FR-A1 -2 817 016 of the applicant.
- the first fuel circuit of the injector 28 comprises a feed tube 34, one end of which is engaged and fixed in a cylindrical bore 36 of a cylindrical piece 38 which is itself mounted inside a sleeve 40
- the fuel is fed through the tube into the bore 36 of the piece 38 and then circulates in helical channels 42 opening at the free downstream end of the piece 38 to rotate the fuel around the longitudinal axis XX of the injector head.
- the free downstream end of the sleeve 40 is located downstream of the cylindrical piece 38 and comprises a fuel ejection orifice 43 whose downstream end portion has a frustoconical section to form a cone shaped fuel sheet having a aperture angle A predetermined.
- the second fuel circuit of the injector 28 comprises a supply tube 44, coaxial with the tube 34 and of greater diameter, one end of which is engaged and fixed in a cylindrical bore 46 of the cylindrical piece 38, this bore 46 being in fluidic communication with helical channels 48 of the aforementioned sleeve 40.
- These channels 48 are formed by external helical grooves formed on an outer cylindrical surface of the sleeve 40 and closed by a cylindrical tip 50 surrounding the cylindrical piece 38, the sleeve 40 and the downstream end portions of the tubes 34, 44.
- the fuel is rotated about the longitudinal axis XX during its passage in the channels 48 which open at the downstream end of the sleeve 40.
- the free downstream end of the endpiece 50 is located downstream of the sleeve 40 and comprises a fuel discharge orifice 52 coaxial with the orifice 42 and whose downstream end portion has a frustoconical section to form a cone-shaped fuel sheet having a predetermined opening angle B (B being greater than AT).
- B being greater than AT.
- Each sheet of fuel produced by an injector 28 is formed of a multitude of drops whose velocity vectors are substantially all oriented in the same way with respect to the longitudinal axis XX of the injector head.
- the velocity vectors of these drops form an angle ⁇ (beta) with the axis XX, this angle ⁇ being substantially equal to the helix angle of the helical channels 42 or 48 above which deliver the fuel layer.
- the fuel drops have a size of between 10 and 100 microns approximately.
- An injection system 26 of the prior art comprises two coaxial tendrils, an upstream or internal swirler 54 and a downstream or external swirler 56, which are separated from one another by a venturi 58. and which are connected upstream to means 60 for supporting the head 30 of an injector 28, and downstream to a mixing bowl 62 which is mounted axially in the opening 24 of the wall 18 of the chamber bottom.
- the tendrils 54, 56 each comprise a plurality of vanes extending substantially radially around the axis XX of the tendrils and regularly distributed around this axis to deliver swirling air flows downstream of the injection head 30.
- the vanes delimit between them channels of air passage, which are inclined or curved around the axis XX of the tendrils.
- the means 60 for supporting the injection head 30 comprise a ring 64 traversed axially by the injection head 30 and slidably mounted in a bushing 66 fixed to the internal swirler 54.
- the ring 64 comprises an annular rim 68 extending radially outwardly and housed in an annular groove of the sleeve 66, the internal diameter of the groove of the sleeve 66 being greater than the outside diameter of the flange 68 of the ring 64.
- the rim 68 of the ring 64 has purge holes 70 substantially axial for the passage of an air flow intended to sweep the head 30 of the injector to prevent flashback to the injector in operation.
- the mixing bowl 62 has a substantially frustoconical wall flared downstream and connected at its downstream end to a cylindrical flange 72, extending upstream and axially mounted in the opening 24 of the wall 18 of the chamber bottom. The upstream end of the frustoconical wall of the bowl 62 is connected to an intermediate annular piece 74 fixed to the external swirler 56.
- the frustoconical wall of the bowl 62 comprises an annular row of orifices 76 of air passage, extending around the axis XX.
- the bowl 62 further comprises, in the vicinity of its rim 72, a second annular row of orifices 78 for air passage, this air being intended to impact an annular flange extending radially outwardly from the end downstream of the frustoconical wall of the bowl.
- the venturi 58 has a substantially L-shaped cross section and comprises at its upstream end an outer annular flange 80 extending radially outwardly and interposed axially between the two swirlers 54, 56.
- the venturi 58 extends axially towards the outside. downstream inside the external swirler 56 and separates the air flows from the internal 54 and external 56 tendrils.
- the venturi 58 internally delimits a premix chamber in which a portion of the injected fuel mixes with the air flow delivered by the internal swirler 54, this air / fuel premix then being mixed downstream of the venturi with the flow of air coming from the external swirler 56 to form a sprayed fuel cone within the chamber.
- the number of vanes of the internal swirler 54 is different from that of the purge orifices 70 and the angular positions of the orifices and vanes around the axis XX are defined randomly.
- the channels of the tendrils 54, 56 each have a square-shaped or rectangle-shaped section and comprise an upstream face 86 and a downstream face 88, which are interconnected by lateral faces 90 extending parallel to each other.
- the air flow 82 delivered by the swirler and the outflow of the purge orifices 70 intersect, which creates recirculations 84 and azimuthal heterogeneities of the air supply flow of the venturi 58, the shearing of the fuel ply. by the air flow 68 is not optimal.
- the invention makes it possible to remedy these problems by means of an injection system 126 as represented in FIG. 5, the channels 100 of the auger 154 (upstream in the case of a two-auger system) having elongate sections presenting a longitudinal axis parallel to the side faces 190 of the channels and which are inclined at an angle ⁇ 'relative to the axis XX of the twist, this angle ⁇ ' being substantially equal (+/- 10 "near) to the angle helical ⁇ helical channels 48 above the injection head 30 and the fuel drop velocity vectors of the web produced by these channels.
- the air flow delivered by the swirler 154 is parallel and co-current with the velocity vectors of the drops of fuel of the web, which allows this air flow to shear the web by limiting the risks of recirculation of the air-mixture.
- fuel and coke deposit on the venturi (not shown) located downstream of the spin.
- the support means 160 of the injector head 30 are formed in one piece with the swirler 154 which has at its downstream end an outer peripheral flange 102 hooking on the venturi.
- each channel 100 of the auger 154 is interconnected at their upstream ends by an upstream wall perpendicular to the axis XX.
- the channels 100 are closed downstream by an upstream radial face of the venturi which defines the downstream walls of the channels 100, these downstream walls of the channels being perpendicular to the axis XX.
- the channels 100 of the auger 154 are separated from each other by substantially radial vanes which are pierced with bleed holes 104 passing through the auger over its entire axial dimension.
- These bleed holes 104 open at their upstream ends on an upstream radial face of the swirler 154 and their downstream ends communicate with corresponding orifices of the venturi for the passage of a purge air flow on the outer surface of the venturi and the internal frustoconical surface of the bowl mixer downstream of the venturi, the venturi and the mixing bowl of the injection system according to the invention being similar to those shown in Figure 3.
- the bleed holes 104 are inclined at the same angle ⁇ 'around the axis XX.
- the axes of the sections of the channels of the tendrils can be oriented in the same direction or in opposite directions about the axis XX, as shown schematically in Figures 6 and 7.
- the axes of the channel sections of the upstream and downstream swirlers 254 and 256 are oriented in the same direction and deliver co-current air flows to the drop velocity vectors of the fuel ply.
- the angle ⁇ 1 between the axes of the channel sections of the upstream swirler 254 and the angle XX is substantially equal to +/- 10 "near the aforementioned angle between the velocity vectors of the drops and the axis XX, and the angle ⁇ 2 between the axes of the channel sections of the downstream swirler 256 and the angle XX is equal to ⁇ 1 or different from ⁇ 1
- This embodiment of the invention is particularly suitable for an injection system whose mixing bowl has air passages for mixing with the fuel in operation, that is to say the orifices of the type referenced 76 in Figure 3.
- the axes of the channel sections of the upstream and downstream tendons 354 and 356 are oriented in opposite directions and respectively deliver co-current and countercurrent air flows to the vectors. speeds of the drops of the water table.
- the angle ⁇ 1 'between the axes of the channel sections of the upstream swirler 354 and the angle XX is substantially equal to +/- 10 "near the aforementioned angle between the velocity vectors of the drops and the axis XX
- the angle ⁇ 2 'between the lateral faces 390 of the channels of the downstream swirler 256 and the angle XX is substantially equal to ⁇ 1'
- This embodiment of the invention is particularly suitable for an injection system whose mixing bowl does not have air passage holes for mixing with the fuel in operation, that is to say the orifices of the type referenced 76 in Figure 3. The air flow delivered by the downstream swirler is then intended to stabilize the flame in the combustion chamber.
- the aforementioned injection system may comprise a purging auger for both sweeping the injector head and the internal surface of the venturi (and thus providing a purge function) and mixing with the fuel supplied by the injector .
- the purging auger according to the invention comprises substantially radial vanes whose radially inner trailing edges are inclined from upstream to downstream outwards and extend over a frustoconical surface flared downstream about the axis A of the injection system.
- the channels of the auger have upstream and downstream radial faces which are substantially parallel to one another and to a transverse plane perpendicular to the axis A of the injection system.
- the means 140 for supporting the head 130 of the injector and the upstream twist 134 or internal are formed in one piece.
- the support means 140 comprises an internal cylindrical surface 174 whose downstream end is connected to the upstream end of the frustoconical surface 176 defined by the trailing edges 178 of the vanes 180 of the auger 134.
- the trailing edge 178 each blade 180 comprises an inwardly concave curved surface and inclined from upstream to downstream outwardly.
- the support means 140 comprise a cylindrical wall 184 internally defining the aforementioned cylindrical surface 174 and connected at its upstream end to a frustoconical wall 182 flared upstream, and at its downstream end to a radial wall 186 extending towards the outside.
- the vanes 180 of the auger 134 are connected at their upstream ends to the radial wall 186 of the support means 140.
- the channels 188 delimited by the vanes 180 of the auger are formed by slots opening axially downstream and closed by a radial upstream face of a venturi 138 separating the spin 134 of the bowl 142.
- each blade 180 of the twist 134 has an outer peripheral rim portion cylinder ( Figures 9 and 10)
- the trailing edges 178 of the vanes of the auger 134 extend parallel to the outer peripheral surface of the fuel ply 191 which is delivered as a cone by the injector.
- the injector can provide two coaxial fuel plies, a first cone-shaped fuel ply 192 having an opening angle a1 and a second fuel ply 191 coaxial with cone shape having an aperture angle a2 (greater than a1).
- the first fuel ply 192 can be optimized at engine start and for the full throttle and the second ply 191 can be optimized for the rpm range from start to full throttle.
- the trailing edges 178 of the vanes 180 of the auger 134 are parallel to the outer peripheral surface of the second fuel ply 191, and therefore forms an angle a2 with the axis A, a2 being for example between 45 and 65 °.
- the trailing edges 178 of the vanes 180 are located at the same distance from the outer peripheral surface of the sheet 191.
- the amount of movement of the air flow delivered by the auger 134 is constant over the entire axial dimension of the auger. This air flow shears the fuel ply 191 in an identical manner over the entire axial dimension of the tendril.
- the portion 194 of the outgoing airflow at the upstream end portions of the trailing edges 178 of the vanes 180 is intended to purge the end of the head 130 of the injector and to shear the fuel web. 191 without disturbance.
- the channels 188 of the auger 134 have a square section which is constant over the entire radial dimension of the auger.
- an axial air passage orifice 196 is formed in each blade 180 and communicates with an axial air passage orifice 197 of the venturi 138.
- the orifices 196 open at their upstream ends on the upstream radial face of the radial wall 186 of the centering means, and the orifices 197 open at their downstream ends radially outside the venturi 138.
- the air 198 which leaves the orifices 197 is intended to circulate on the outer surface of the venturi and forming a purge air film of the radially inner surface of the bowl 142, to prevent the deposition of coke on this surface.
- the mixing bowl 142 of the injection system is mounted downstream of the swirler 136 and comprises, as in the prior art, a substantially frustoconical wall flared downstream and connected at its downstream end to a cylindrical rim 152, extending upstream.
- the frustoconical wall comprises an annular row of orifices 156 for air passage, extending around the axis A.
- the flange 152 comprises an annular row of orifices 158 for air passage, this air being intended to come impact on a annular flange 159 extending radially outwardly from the downstream end of the frustoconical wall of the bowl.
- the rows of orifices 156, 158 are located on circumferences whose diameters are substantially equal to or greater than the maximum external diameter of the support means 140 and the auger 134.
- the air flow 161 which feeds these orifices does not bypass the injection system which limits the disturbances of this flow and optimizes the supply of the orifices 156, 158.
- the invention makes it possible (by eliminating the purge orifices), for a given permeability of the injection system, to optimize with precision the diameter of the orifices 156, 158 of the mixing bowl and the dimensions of the channels of the tendrils 134, 136.
- the cumulative sections of the orifices 158 of the mixing bowl and the channels of the external swirler 136 represent 20 to 30% of the total permeability of the system, the accumulated sections of the orifices 156 of the mixing bowl and channels 188 of the internal swirler 134 representing 70 to 80% of this permeability. 70 to 80% of the air flow supplying the injection system is therefore intended to mix with the fuel supplied by the injector.
- the injection system differs from that previously described in that the channels 288 of its internal swirler 234 have a section which decreases radially from the outside towards the inside.
- each channel 288 at the downstream ends of the trailing edges 276 of the vanes 280 extending on either side of this channel is greater than that of the same channel at the upstream ends of the channels. aforementioned trailing edges ( Figure 1 1).
- the air outlet section at the trailing edges 276 of the vanes 280 is therefore greater at the downstream ends of the trailing edges than at their upstream ends. Because this section is calibrating, the amount of air movement is greater at the downstream end of the swirler at its upstream end (arrows 294) and increases steadily between its upstream end and its downstream end due to the increase in the output width of the channels between these ends.
- the channel section of the internal swirl of the injection system may have a rectangular or trapezoidal shape, and not square as in the examples described above.
- each blade of the spin can have its side faces converging from downstream to upstream.
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
- Fuel-Injection Apparatus (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
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Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201280023894.5A CN103562641B (zh) | 2011-05-17 | 2012-05-11 | 用于涡轮机的环形燃烧室 |
CA2835361A CA2835361C (fr) | 2011-05-17 | 2012-05-11 | Chambre annulaire de combustion pour une turbomachine |
US14/118,393 US9951955B2 (en) | 2011-05-17 | 2012-05-11 | Annular combustion chamber for a turbine engine |
EP12728666.4A EP2710298B1 (fr) | 2011-05-17 | 2012-05-11 | Chambre annulaire de combustion pour une turbomachine |
RU2013155913/06A RU2604260C2 (ru) | 2011-05-17 | 2012-05-11 | Кольцевая камера сгорания для турбомашины |
BR112013028196-0A BR112013028196B1 (pt) | 2011-05-17 | 2012-05-11 | Câmara anular de combustão para uma turbomáquina e turbomáquina |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
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FR1154302 | 2011-05-17 | ||
FR1154303 | 2011-05-17 | ||
FR1154303A FR2975467B1 (fr) | 2011-05-17 | 2011-05-17 | Systeme d'injection de carburant pour une chambre de combustion de turbomachine |
FR1154302A FR2975466B1 (fr) | 2011-05-17 | 2011-05-17 | Chambre annulaire de combustion pour une turbomachine |
Publications (1)
Publication Number | Publication Date |
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WO2012156631A1 true WO2012156631A1 (fr) | 2012-11-22 |
Family
ID=46321091
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/051056 WO2012156631A1 (fr) | 2011-05-17 | 2012-05-11 | Chambre annulaire de combustion pour une turbomachine |
Country Status (7)
Country | Link |
---|---|
US (1) | US9951955B2 (fr) |
EP (1) | EP2710298B1 (fr) |
CN (1) | CN103562641B (fr) |
BR (1) | BR112013028196B1 (fr) |
CA (1) | CA2835361C (fr) |
RU (1) | RU2604260C2 (fr) |
WO (1) | WO2012156631A1 (fr) |
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EP2735797A1 (fr) * | 2012-11-23 | 2014-05-28 | Niigata Power Systems Co., Ltd. | Chambre de combustion de turbine à gaz |
US8943834B2 (en) | 2012-11-20 | 2015-02-03 | Niigata Power Systems Co., Ltd. | Pre-mixing injector with bladeless swirler |
US10712008B2 (en) | 2016-10-13 | 2020-07-14 | Rolls-Royce Plc | Combustion chamber and a combustion chamber fuel injector seal |
FR3105984A1 (fr) | 2020-01-03 | 2021-07-09 | Safran Aircraft Engines | Système d’injection de carburant antirotatif |
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CN115013839A (zh) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | 加力燃烧室燃油喷杆结构 |
US20240263788A1 (en) * | 2023-02-02 | 2024-08-08 | Pratt & Whitney Canada Corp. | Combustor with central fuel injection and downstream air mixing |
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-
2012
- 2012-05-11 WO PCT/FR2012/051056 patent/WO2012156631A1/fr active Application Filing
- 2012-05-11 EP EP12728666.4A patent/EP2710298B1/fr active Active
- 2012-05-11 US US14/118,393 patent/US9951955B2/en active Active
- 2012-05-11 CN CN201280023894.5A patent/CN103562641B/zh active Active
- 2012-05-11 RU RU2013155913/06A patent/RU2604260C2/ru active
- 2012-05-11 BR BR112013028196-0A patent/BR112013028196B1/pt active IP Right Grant
- 2012-05-11 CA CA2835361A patent/CA2835361C/fr active Active
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US20070068164A1 (en) * | 2005-09-28 | 2007-03-29 | Snecma | Anti-coking injector arm |
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EP1985924A1 (fr) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Dispositif de tourbillonnement |
FR2918716A1 (fr) | 2007-07-12 | 2009-01-16 | Snecma Sa | Optimisation d'un film anti-coke dans un systeme d'injection |
FR2925146A1 (fr) | 2007-12-14 | 2009-06-19 | Snecma Sa | Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8943834B2 (en) | 2012-11-20 | 2015-02-03 | Niigata Power Systems Co., Ltd. | Pre-mixing injector with bladeless swirler |
EP2735797A1 (fr) * | 2012-11-23 | 2014-05-28 | Niigata Power Systems Co., Ltd. | Chambre de combustion de turbine à gaz |
US10712008B2 (en) | 2016-10-13 | 2020-07-14 | Rolls-Royce Plc | Combustion chamber and a combustion chamber fuel injector seal |
FR3105984A1 (fr) | 2020-01-03 | 2021-07-09 | Safran Aircraft Engines | Système d’injection de carburant antirotatif |
Also Published As
Publication number | Publication date |
---|---|
RU2604260C2 (ru) | 2016-12-10 |
BR112013028196B1 (pt) | 2021-06-22 |
US9951955B2 (en) | 2018-04-24 |
EP2710298A1 (fr) | 2014-03-26 |
BR112013028196A2 (pt) | 2017-01-17 |
CN103562641B (zh) | 2015-11-25 |
EP2710298B1 (fr) | 2020-09-23 |
CA2835361C (fr) | 2019-03-26 |
CN103562641A (zh) | 2014-02-05 |
CA2835361A1 (fr) | 2012-11-22 |
US20140090382A1 (en) | 2014-04-03 |
RU2013155913A (ru) | 2015-06-27 |
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