Device for distributing fuel flows for a circuit for supplying fuel to a turbomachine combustion chamber

Description

Technical field of the invention

[0001] The present invention relates to a fuel flow distribution device and a fuel supply circuit for a combustion chamber equipped with such a device intended for their mixing. The invention also relates to a turbomachine supplied via this fuel circuit and in particular an aircraft turbomachine. Technical background

[0002] The state of the art includes in particular document US-A1-2012 / 0047900.

[0003] A turbomachine, in particular an aircraft turbomachine, comprises a gas generator including in particular one or more compressors, for example low pressure and high pressure, arranged upstream of a combustion chamber.

[0004] Traditionally, the combustion chamber is supplied with compressed air from the high-pressure compressor, notably via an annular diffuser, and with fuel via a fuel supply circuit comprising injectors distributed angularly around a longitudinal axis of the turbomachine.

[0005] The fuel circuit may include the following elements cited herein in the direction of fuel flow from upstream to downstream: a fuel tank for storing fuel, a low pressure LP pump to supply fuel from the tank, a fuel filtration unit to limit (or even eliminate) contaminating elements in the fuel leaving the LP pump, a high pressure HP pump, a metering unit, usually called FMU (for "Fuel Metering Unit" in English terminology), and a set of injectors delivering the total flow of fuel into the combustion chamber of the turbomachine.

[0006] Generally speaking, the LP and HP pumps can be integral and driven by the same output shaft of an accessory box, of the AGB type (for "Accessory GearBox" in English terminology), of the turbomachine.

[0007] The LP pump allows the fuel to be delivered to the HP pump, which supplies the fuel metering unit with a flow rate greater than the fuel requirement of the combustion chamber.

[0008] There figure 1schematically illustrates the fuel flow rate (or flux) injected by the HP pump of the fuel supply circuit as a function of the turbomachine combustion engine speeds. The linear C 1 curve represents a regular increase in the fuel flow rate supplied by the HP pump between the R 1 and R 2 operating speeds of the turbomachine. The R 1 speed represents the fuel flow rate at the time of start-up or during the auto-rotation phase (or "Windmilling" according to the English terminology) in flight or on the ground of the turbomachine. The R 2 speed represents the fuel flow rate at a maximum normal operating speed of the turbomachine (such as at the time of takeoff of the aircraft). The C 2 curve represents the fuel requirement of the combustion chamber to operate at the R 1 and R 2 speeds.This curve C 2 represents a fuel flow rate meeting the needs of the combustion chamber which is much lower than the fuel flow rate injected by the HP pump of curve C 1 . The excess fuel quantity is represented by an arrow E on the . figure 1 .

[0009] This excess fuel quantity is recirculated in the fuel supply circuit. For this purpose, the circuit also includes a recirculation channel configured to return from the FMU metering unit to an inlet of the HP pump, a second fuel flow corresponding to the excess fuel quantity from the metering unit.

[0010] Thus, the first flow and the second flow of fuel mix before entering the HP pump. The outlet of the recirculation channel is generally close to the fuel inlet of the HP pump, in particular to optimize the size and space in the turbomachine. The main disadvantage of this configuration is that the first and second fuel flows entering the HP pump are not perfectly homogenized. This can generate cavitation (i.e. bubbles) in the fuel flow feeding the HP pump and which can damage the latter. Thus, the performance of the HP pump can be degraded and its service life limited.

[0011] Known from the prior art is a fuel supply circuit for a combustion chamber of an aircraft turbomachine comprising a loop for recirculating an excess quantity of fuel from a metering unit to a fuel tank or a jet pump arranged upstream of an HP pump, as described respectively in documents FR-A1-2999653 and WO-A1-2014 / 096620. When the fuel is returned to the tank, the question of homogenizing the fuel upstream of the HP pump does not arise. As regards the jet pump, it is capable of mixing the first flow of fuel from an LP pump and the second flow from the metering unit to supply fuel to the HP pump. However, the jet pump has the disadvantage of requiring complicated and bulky mounting.

[0012] In this context, it is interesting to overcome the drawbacks of the prior art, by proposing a reliable device for distributing several fuel flows which can be integrated into a fuel supply circuit of a combustion chamber, while allowing its simple and rapid assembly in a turbomachine. Summary of the invention

[0013] A fuel supply circuit is proposed for a combustion chamber of a turbomachine, in particular an aircraft, comprising: a supply channel configured for the circulation of a first flow of fuel from a fuel tank; a metering unit configured to provide a predetermined flow rate of fuel into the combustion chamber; at least one supply pump intended to circulate the fuel from the tank to the metering unit; a recirculation channel for a second flow of fuel, corresponding to an excess quantity of fuel from the metering unit, upstream of the supply pump; the supply and recirculation channels opening in different directions upstream of the supply pump.

[0014] According to the invention, the circuit comprises a device for distributing at least one of the fuel flows according to claim 1.

[0015] Thus, this solution makes it possible to achieve the aforementioned objective. Indeed, such a configuration makes it possible to separate at least two fuel flows coming from different directions and to direct them in the same direction via the distribution device of the invention. This makes it possible to achieve a homogeneous and optimal mixture of these flows to end up in the feed pump of the fuel supply circuit for a combustion chamber.

[0016] In particular, the fuel flows entering the distribution device have different flow rates and therefore come from separate and intersecting channels upstream of the device (and consequently upstream of the feed pump). These flows entering the device are regulated by coaxial flow conduits (namely the internal flow conduit of the first flow and the at least one passage orifice of the second flow), so that the flows do not interfere with each other to form turbulence and / or cavitations. Thus, the flows leaving the distribution device have the advantage of having a stable flow rate and therefore of being in a state of rest. In this way, the flows with a stable flow rate mix at the outlet of the distribution device to emerge in the feed pump by a homogeneous mixture and without cavitation.The feed pump of the circuit of the invention is therefore not damaged by the fuel flows coming from the feed and recirculation channels of the circuit. Thus, the service life and performance of the feed pump are greatly improved.

[0017] The invention thus has the advantage of proposing a simple design, offering very high reliability, and with little penalty in terms of cost and size of the turbomachine.

[0018] The fuel supply circuit according to the invention also comprises one or more of the following features, taken alone or in combination: the supply channel opens downstream into the internal flow duct of the distribution device and the recirculation channel opens into the annular groove of the distribution device; the device is mounted in a housing arranged upstream of the supply pump, and in which said at least one orifice and said internal duct open into a mixing zone of the housing; the supply and recirculation channels are configured to open in a secant manner into the housing, in which a downstream end of the supply channel opens into the internal duct and an upstream end of the recirculation channel opens into the external annular groove; the downstream end of the supply channel opening into the internal flow duct extends substantially axially or inclined relative to the axis A;the upstream end of the recirculation channel opening into the annular groove, extends substantially perpendicular or inclined relative to the axis A; the distribution device comprises a main body of revolution extending around a longitudinal axis and comprising: ▪ the internal flow duct of the first fuel flow which extends through the main body along the axis A, and ▪ a first annular portion configured to form an outlet passage for the second fuel flow, and the first annular portion comprising said at least one orifice for the passage of the second fuel flow which is distributed according to an annular row of orifices around the axis; said at least one orifice extends along an axis parallel to the axis of the internal duct; said internal flow duct and said at least one orifice are configured to open transversely to an axis around which the feed pump extends;the main body further comprises a second annular portion configured to form an inlet passage for the first fuel flow through the internal duct, the second portion is connected to the first portion via an intermediate portion at least partially delimiting the central opening; the second portion further comprises at least one annular sealing and fixing groove configured for mounting a sealing element; the fuel circuit feed pump comprises a low pressure pump (for example of the rotodynamic type) and / or a high pressure pump (for example of the volumetric gear type); the housing and the mixing zone are arranged upstream of the high pressure pump; the internal flow duct for the first fuel flow is formed by a central opening.;

[0019] The present application further relates to a turbomachine, in particular for an aircraft, comprising a fuel supply circuit according to one of the particularities of the invention, for a combustion chamber of the turbomachine.

[0020] The invention also proposes a device for distributing at least one fuel flow for a fuel supply circuit of a combustion chamber of a turbomachine, in particular of an aircraft, the device being defined in claim 1

[0021] The distribution device according to the invention has the advantage of ensuring several functions within the fuel supply circuit, namely: guiding the first flow of fuel coming from a supply channel of the circuit (for example from a first filtration unit with reference to the example described below or from a low pressure pump); guiding the second flow of fuel coming from a recirculation channel of the circuit; directing the first and second flows in the same direction (in particular by the coaxial flow conduits); sealing the housing arranged in at least one of the casings of the components of the fuel circuit (for example between the casings of the first filtration unit and a high pressure pump with reference to the example described below).

[0022] Furthermore, as described above, the distribution device equipping the fuel circuit therefore makes it possible to separate the first flow and the second flow coming from channels of different directions, and to orient them in the same direction at the outlet of the device. This makes it possible to slow down the flow rate of each of the fuel flows, so as to limit (or even eliminate) turbulence and / or cavitation in the fuel leaving the device. In this way, the flow of fuel entering a feed pump of the circuit is optimally homogenized, in particular after passing through a mixing zone located between the feed pump and the device.

[0023] The dispensing device according to the invention also comprises one or more of the following characteristics, taken alone or in combination: the device comprises an external annular groove which is in fluid communication with the at least one orifice of the first portion; said at least one orifice for the passage of the second fuel flow is distributed according to an annular row of orifices; the annular row of orifices each extends along an axis parallel to the axis A; the second portion is connected to the first portion via an intermediate portion of the distribution device delimiting at least in part the internal conduit; the annular groove is delimited at least in part by a flank of the collar and a wall of the first portion; the second portion further comprises at least one annular sealing and fixing groove configured for mounting a sealing element; the first annular portion has an external diameter smaller than the external diameter of the annular collar of the second annular portion;each orifice of the annular row of orifices has a diameter of between 3 and 10 mm, preferably between 5 and 7 mm, and more preferably of approximately 5.5 mm; the annular row of orifices comprises between five to twenty orifices, preferably between fifteen and twenty orifices, and more preferably of approximately seventeen orifices.;

[0024] The present application further relates to a turbomachine, in particular for an aircraft, comprising at least one device for distributing at least one fuel flow according to one of the particularities of the invention, for a combustion chamber of the turbomachine. Brief description of the figures

[0025] The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which: [ Fig. 1 ] there figure 1is a schematic diagram illustrating the fuel flow rate supplied by a high pressure pump in a fuel system and the fuel flow rate required by a combustion chamber; [ Fig. 2 ] there figure 2 is a very schematic view of a fuel supply circuit for a combustion chamber of a turbomachine according to the invention; [ Fig. 3 ] there figure 3 is a schematic perspective view of the upstream side of a device for distributing at least one fuel flow from the circuit of the figure 2 ; [ Fig. 4 ] there figure 4 is a schematic perspective view of the downstream side of the distribution device of the figure 3 ; [ Fig. 5 ] there Figure 5 is a schematic sectional view of the distribution device of the figure 4 ; And [ Fig. 6 ] there figure 6 is an enlarged schematic sectional view of the arrangement of the distribution device figures 3 to 5 in the power supply circuit of the figure 2 . Detailed description of the invention

[0026] By convention, in the description below, the terms "longitudinal" and "axial" qualify the orientation of structural elements extending in the direction of a longitudinal axis X. This axis X can be confused with an axis of rotation of a rotor of a turbomachine. The terms "radial" or "vertical" qualify an orientation of structural elements extending in a direction perpendicular to the axis X. The terms "inner" and "outer", and "internal" and "external" are used in reference to a positioning relative to the axis X. Thus, a structural element extending along the axis X comprises an inner face facing the axis X and an outer surface, opposite its inner surface. In the present application, the terms "upstream" and "downstream" are defined relative to the direction of circulation of the gases in the turbomachine.

[0027] There figure 1has been described in the above.

[0028] The invention applies to a turbomachine 100, in particular an aircraft turbomachine, comprising a gas generator or engine. Such a turbomachine may be a turboprop, a turbojet or a turboshaft engine. The gas generator of the turbomachine typically comprises one or more compressors, for example low pressure and high pressure, arranged upstream of a combustion chamber 9.

[0029] The combustion chamber 9 is supplied with compressed air from the high-pressure compressor via, in particular, an annular diffuser, and with fuel via a fuel supply circuit 1 comprising injectors distributed angularly around a longitudinal axis X of the turbomachine.

[0030] The fuel supply circuit 1 (or fuel circuit 1 in the present application) of the figure 2may include the following elements cited herein in the direction of fuel flow from upstream to downstream: a fuel tank 2 for storing the fuel, a low pressure pump LP 3, for example of the rotodynamic type (such as a centrifugal pump for pumping and discharging a fluid by rotation of a rotor or a propeller wheel) to ensure the supply of fuel from the tank 2, a first fuel filtration unit 4a for limiting (or even eliminating) the contaminating elements of the fuel at the outlet of the pump LP 3, a high pressure pump HP 5, for example of the volumetric gear type, a second fuel filtration unit 4b for limiting (or even eliminating) the contaminating elements of the fuel at the outlet of the pump HP 5, a metering unit 6 for delivering at the outlet a total flow of fuel distributed towards the combustion chamber 9, and a set of injectors 7 delivering a total flow of fuel into the combustion chamber 9 of the turbomachine 100.

[0031] The BP 3 and HP 4 pumps can be integral and driven by the same output shaft of an accessory box (not shown in the figure), for example of the AGB type, of the turbomachine 100. This makes it possible in particular to adapt the flow rate sent by the BP 3 and HP 5 pumps to the needs of the combustion chamber 9.

[0032] The LP pump 3 supplies the first filtration unit 4a and the HP pump 5 with a first fuel flow F1 coming from the tank 2 via a supply channel 20. The HP pump 5 supplies the second filtration unit 4b and the metering unit 6 with fuel, for example via the supply channel 20, with a flow rate greater than the fuel requirement of the combustion chamber 9.

[0033] As described above, an excess quantity of fuel is recirculated in the fuel circuit 1 via a recirculation channel 60. This recirculation channel 60 is configured to return upstream of the HP pump 5, a second fuel flow F2 corresponding to the excess quantity of fuel from the metering unit 6.

[0034] Thus, the first flow F1 and the second flow F2 of fuel mix before entering the HP pump 5.

[0035] On the example of the figure 2 , channels 20, 60 open out along directions D1, D2 (illustrated on the figure 6 ) different upstream of the HP 5 pump.

[0036] One of the particularities of the invention lies in the fact that the fuel circuit 1 also comprises a fuel distribution device 8. This distribution device 8 can be removably assembled upstream of the HP pump 5.

[0037] On the figure 2 and in a non-limiting manner, the distribution device 8 is located in a housing 10 of the circuit 1. The device 8 and the housing 10 are located downstream of the first filtration unit 4a and upstream of the HP pump 5. The housing 10 may have a general shape at least partly complementary to the general shape of the distribution device 8.

[0038] In the case of the fuel circuit 1, the distribution device 8 is configured to channel and ensure a homogeneous mixture of the first F1 and second F2 fuel flows coming, respectively, from the supply channel 20 and the recirculation channel 60.

[0039] The channels 20, 60 are configured to open in a secant manner into the housing 10 (and consequently into the device 8).

[0040] Furthermore, the housing 10 comprises a mixing zone 12 for the fuel flows F1, F2 leaving the distribution device 8. On the figure 2 , the mixing zone 12 is located downstream of the distribution device 8 and upstream of the HP pump 5.

[0041] In reference to the figures 3 to 5 , we will now describe the fuel distribution device 8 equipping the fuel circuit 1.

[0042] The distribution device 8 has a shape of revolution extending around a longitudinal axis A. The axis A may be substantially parallel or inclined relative to the axis X of the turbomachine 100. The distribution device 8 comprises a main body 80 of generally elongated shape and extending around the axis A.

[0043] In the example of the figures 3 to 5, the main body 80 comprises a first annular portion 81, a second annular portion 83 which is opposite (along the axis A) to the first portion 81, and an intermediate portion 82 which connects the annular portions 81, 83 together. Advantageously, the portions 81, 82, 83 are formed from a single piece (made from the same material).

[0044] The main body 80 further comprises an internal flow duct 800 extending along the axis A. This internal duct 800 may have a cylindrical shape. The internal duct 800 may be formed by a central and through opening. In the example, the opening of the internal duct 800 has a circular cross-section. The opening of the internal duct 800 may have a diameter D 800 of between 10 and 50 mm, preferably between 20 and 30 mm. Even more preferably, the diameter D 800 is approximately 26 mm. In the figure 3, the central opening 800 has a length L1 of substantially between 20 and 50 mm. Advantageously, the length L1 is between 25 and 30 mm.

[0045] In the example, the opening of the internal conduit 800 forms a fuel inlet passage which is located on the side of the second portion 83 and a fuel outlet passage which is located on the side of the first portion 81. More particularly, the opening of the internal conduit 800 opens onto a front wall 812 of the first portion 81 and a rear wall 832 of a rear end 830 of the second portion 83.

[0046] The first portion 81 comprises the front wall 812 and a rear wall 814 which are substantially transverse to the axis A. The front wall 812 passes substantially through a plane P1 and the rear wall 814 passes substantially through a plane P2. On the figures 3 And 4, the planes P1 and P2 are substantially perpendicular to the axis A. Furthermore, in the example, the first portion 81 has an annular external surface which is narrowed in the direction of the plane P2.

[0047] The first portion 81 further comprises at least one orifice 810. This orifice 810 is configured for the passage of fuel. In the example of figures 3 to 5 and in a non-limiting manner, the first portion 81 comprises an annular row of orifices 810 extending circumferentially around the axis A. Each of the orifices 810 of the annular row of orifices is through and extends axially between the planes P1 and P2. On the figure 4and in a non-limiting manner, the length L2 between the planes P1 and P2 (corresponding substantially respectively between the front wall 812 and the rear wall 814) is between 5 and 15 mm, preferably approximately 8 mm. Each of the orifices 810 may also extend substantially parallel to the central opening of the internal conduit 800. The annular row of orifices comprises between five to twenty orifices, preferably between fifteen and twenty orifices. More preferably, there are approximately seventeen orifices. Each orifice 810 of the annular row of orifices has a diameter D 810 of between 3 and 10 mm, preferably between 5 and 7 mm, and more preferably approximately 5.5 mm. The opening of the internal conduit 800 and the orifices 810 are coaxial, in particular with respect to the axis A. The first portion 81 is configured to form a fuel outlet passage.The annular row of orifices is configured to form both a fuel inlet passage and a fuel outlet passage.

[0048] The intermediate portion 82 delimits between the first 81 and second 83 portions an annular groove 820. Thus, in the example, the annular groove 820 extends from front to back between the plane P2 and a plane P3. The plane P3 is substantially parallel to the planes P1 and P2. In the figure 3 and in a non-limiting manner, the length L3 between the planes P1 and P3 (corresponding substantially respectively between the front wall 812 of the first portion 81 and one end of the intermediate portion 82 which is opposite the wall 812) is between 15 and 30 mm, preferably approximately 21 mm. This annular groove 820 is in fluid communication with the orifices 810 of the first portion 81. The annular groove 820 is configured to form a fuel inlet passage.

[0049] The second portion 83 comprises an annular collar 84 extending radially outwards and around the axis A. The annular collar 84 is located on the side of the intermediate portion 82. The annular collar 84 has a front flank 842 and a rear flank 844 which is axially opposite the front flank 842. The flanks 842, 844 are connected by a peripheral annular surface 843. In the example, the front flank 842 is defined substantially in the plane P3.

[0050] The second portion 83 also comprises at least one annular groove 85, called a sealing and fixing groove, extending around the axis A. The annular sealing and fixing groove 85 is configured for mounting a sealing element 850. In particular, in the example, it has a U-shaped axial section and opens onto the annular peripheral surface 843. Advantageously, this sealing element 850 is an O-ring (illustrated in the figure 6). Similarly, in the example, the rear end 830 may also comprise the annular groove 85 which may have a U-shaped axial section and open onto an annular peripheral surface of the rear end 830. In the Figure 5 , the second portion 83 comprises two annular grooves 85 arranged, respectively, on the annular collar 84 and on the rear end 830 which is opposite (along the axis A) to the annular collar 84.

[0051] In the example, the annular collar 84 has an external diameter D 84 (delimited by the external peripheral surface 843) greater than the external diameter of the rear end 830 of the second portion 83.

[0052] The second portion 83 is configured to form a fuel inlet passage. In the example, the outer diameter D 84 of the annular collar 84 is greater than the outer diameter D 81 of the first portion 81. The outer diameter D 81 of the first portion 81 is greater than the outer diameter D 820 of the annular groove 820.

[0053] We will now describe the distribution device 8 equipped in the fuel circuit 1 of the invention.

[0054] In reference to the figures 2 And 6 and non-limitingly, the distribution device 8 is assembled in the housing 10 arranged downstream of the first filtering unit 4a and upstream of the HP pump 5.

[0055] The HP pump 5 may be of the volumetric gear type. In this case, the HP pump 5 may comprise one or more toothed wheels 52. The toothed wheel 52 has an axis of rotation B, as illustrated in the figure 6This axis B is substantially perpendicular to the axis A of the device 8.

[0056] The housing 10 has a generally cylindrical shape extending along an axis of revolution. On the figure 6 , this axis of revolution of the housing 10 substantially coincides with the axis A of the distribution device 8. The housing 10 may be formed by the walls of at least one of the casings 40, 50 and / or of at least one of the channels 20, 60 of the fuel circuit 1. In the example and in a non-limiting manner, the housing 10 is located at least partly between the casings 40, 50 of the first filtering unit 4a and of the HP pump 5. In the figure 6 , the housing 10 opens at least partly radially into the recirculation channel 60. In addition, the housing 10 opens upstream into the supply channel 20 and downstream into the mixing zone 12 of the fuel circuit 1.

[0057] The mixing zone 12 has a generally annular or cylindrical shape. In the example, this mixing zone 12 can also extend along a longitudinal axis which coincides with the axis of revolution of the housing 10 and the axis A of the distribution device 8.

[0058] On the figure 6 , the mixing zone 12 thus opens upstream into the housing 10 (and also the first portion 81 of the distribution device 8 installed in the housing 10), and downstream into the HP pump 5 (for example into the gears of the toothed wheel 52 of the HP pump 5).

[0059] On the figure 6, the front wall 812 of the first portion 81 of the distribution device 8 bears against an upstream wall 102 of the housing 10. In the example, the housing 10 may correspond to a wall of the casing 50 of the HP pump 5. The front flank 842 of the annular collar 84 of the distribution device 8 bears against a downstream wall 104 of the housing 10. In the example, the casing 40 of the first filtering unit 4a carries the downstream wall 104.

[0060] In the example, O-rings 850 are installed between the grooves 85 of the distribution device 8 and the internal annular surfaces of the housings 40, 50. These O-rings are sufficient to hold the distribution device 8 in a fixed and sealed manner in the housing 10.

[0061] The supply channel 20 of the circuit 1 comprises an upstream outlet 22 which opens into the central opening 800 on the side of the second portion 83, upstream of the distribution device 8. The upstream outlet 22 is oriented in a direction extending substantially in an inclined or axial manner relative to the axis A.

[0062] The recirculation channel 60 of the circuit 1 comprises an upstream outlet 62 opening into the housing 10, in particular into the annular groove 820 of the intermediate portion 82. The downstream outlet 62 is oriented in a direction extending substantially transversely relative to the axis A. In particular, the outlet direction is perpendicular or inclined (with an angle of between 20 and 50°) relative to the axis A.

[0063] In reference to the figure 6, the first fuel flow F1 comes from the supply channel 20 in a first direction D1, and the second fuel flow F2 comes from the recirculation channel 60 in a second direction D2.

[0064] The first fuel flow F1 passes through the central opening of the conduit 800 of the distribution device 8 to open into the mixing zone 12 and then into the HP pump 5. This allows the first flow F1 to flow inside and out of the distribution device 8 in a third direction D3. This third direction D3 is coaxial with the axis A and also with the axes of revolution of the mixing zone 12 and the housing 10. The flow direction D3 of the first flow F1 may be different from the first direction D1 when the upstream outlet 22 opens in an inclined manner relative to the axis A (as illustrated in the figure 6 ), or coaxial with direction D1 when the upstream outlet 22 opens axially to axis A.

[0065] Advantageously, the first flow F1 in the third direction D3 emerges substantially perpendicular to the axis B of the toothed wheel 52 of the HP pump 5.

[0066] The walls formed in the housing 10, by the upstream end 62 and the annular groove 820, form an annular chamber 826 in which the second fuel flow F2 enters the distribution device 8. The second flow F2 then passes through the orifices 810 of the first portion 81 to open into the mixing zone 12 then into the HP pump 5. This allows the second flow F2 to flow inside and out of the distribution device 8 in the third direction D3 as well. In the example, this direction D3 of flow of the second flow F2 is different from the second direction D2.

[0067] In the annular chamber 826, the second flow F2 is slowed down relative to its speed in the recirculation channel 60. This allows the second flow F2 to pass from a turbulent state in the recirculation channel 60 to a laminar state in the orifices 810, then in the mixing zone 12.

[0068] We understand that the distribution device of the invention is located at the confluence of the outlets of the first and second flows F1, F2 and that the flows mix at the outlet of the distribution device.

[0069] Thus, the fuel flows F1, F2 opening into the mixing zone 12 have no or very little cavitation before entering the HP pump 5. In the mixing zone 12, the fuel flows F1, F2 are made homogeneous for their flows in the HP pump 5.

[0070] In the present application, the distribution device is described for the distribution or channeling of fuel for a fuel supply circuit of a combustion chamber of a turbomachine, in particular of an aircraft. The distribution device of the invention can also be adapted for any type of fluid and for hydromechanical systems of a turbomachine other than the aeronautical field.

[0071] The fuel distribution device equipping the fuel supply circuit according to the invention provides several advantages which are in particular: optimize the mixing and homogenization of fuel flows from the intersecting and non-coaxial feed and recirculation channels, upstream of the feed pump, provide a distribution and mixing device within the available footprint and space of the fuel circuit, optimize the life of the feed pump by preventing the formation of cavitations in the fuel, easily attach and detach from the feed circuit, limit the maintenance cost of a feed pump from the fuel circuit, and easily adapt to existing gas generators.

[0072] Overall, this proposed solution is simple, efficient and economical to produce and assemble on a turbomachine, while ensuring optimal fuel supply and improved service life of at least one of the components of a fuel supply circuit for a combustion chamber of a turbomachine.

Claims

1. A distribution device (8) of at least one fuel flow (F1, F2) for a fuel supply circuit (1) of a combustion chamber (9) of a turbomachine (100), in particular an aircraft, the device (8) comprising a main body (80) of revolution extending about a longitudinal axis (A), the main body (80) comprising : - an internal conduit (800) for the flow of a first fuel flow (F1) and extending through the main body (80) along the axis (A), - a first annular portion (81) configured to form an outlet passage for a second fuel flow (F2), and comprising at least one passage orifice (810) for the second fuel flow (F2), - an external annular gorge (820) in fluid communication with said at least one orifice (810) of the first portion (81), and - a second annular portion (83) configured to form an inlet passage for the first fuel flow (F1) through the internal conduit (800) characterized in that the second portion (83) comprises an annular collar (84) extending radially about the axis (A).

2. The device (8) according to claim 1, characterized in that said at least one passage orifice (810) of the second fuel flow (F2) is distributed in an annular row of orifices.

3. The device (8) according to claim 2, characterised in that the annular row of orifices (810) each extend along an axis parallel to the axis (A).

4. The device (8) according to any one of claims 1 to 3, characterised in that the second portion (83) is connected to the first portion (81) via an intermediate portion (82) of the distribution device (8) delimiting at least partly the internal conduit (800).

5. The device (8) according to any one of claims 1 to 4, characterised in that the annular gorge (820) is delimited at least partly by a flank (842) of the collar (84) and a wall (814) of the first portion (81).

6. The device (8) according to any one of claims 1 to 5, characterised in that the second portion (83) further comprises at least one annular sealing and attaching groove (85) configured for mounting a sealing element (850).

7. The device (8) according to any one of claims 1 to 6, characterised in that the first annular portion (81) has an external diameter (D81) smaller than an external diameter (D84) of the annular collar (84) of the second annular portion (83).

8. The device (8) according to any one of claims 2 to 7, characterised in that each orifice (810) in the annular row of orifices has a diameter (D810) of between 3 and 10 mm, preferably between 5 and 7 mm, and still more preferably of about 5.5 mm.

9. The device (8) according to any one of claims 2 to 8, characterised in that the annular row of orifices comprises between five and twenty orifices, preferably between fifteen and twenty orifices, and even more preferably about seventeen orifices.

10. A turbomachine (100), in particular an aircraft turbomachine, comprising a distribution device of at least one fuel flow according to any one of claims 1 to 9, for a fuel supply circuit (1) of a combustion chamber (9) of the turbomachine (100).