Device for distributing the fuel flow of a fuel supply circuit of a turbine combustion chamber

Abstract

The invention relates to a device (8) for distributing at least one fuel flow of a fuel supply circuit, in particular of a turbine combustion chamber of an aircraft, the device (8) comprising a rotating body (80) extending around a longitudinal axis (A), said body (80) comprising: an internal flow duct (800) for a first fuel flow, the internal flow duct extending along the axis (A) through the body (80); a first annular portion (81) configured to form an outlet passage for a second fuel flow, and comprising at least one aperture (810) for passing the second fuel flow; and an external annular groove (820) in fluid communication with the at least one aperture (810) in the first portion (81).

Description

Technical Field

[0001] This invention relates to a fuel flow distribution device and a fuel supply circuit for a combustion chamber, the fuel supply circuit being equipped with such a device for mixing fuel flows. A further object of the invention is a turbine supplied via this fuel circuit, particularly an aircraft turbine. Background Technology

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

[0003] A turbine, particularly a turbine for an aircraft, includes a gas generator comprising one or more compressors, such as a low-pressure compressor and a high-pressure compressor, arranged upstream of a combustion chamber.

[0004] Traditionally, compressed air is supplied to the combustion chamber from a high-pressure compressor via an annular diffuser, and fuel is supplied to the combustion chamber via a fuel supply circuit, wherein the fuel supply circuit includes injectors angled around the longitudinal axis of the turbine.

[0005] The fuel circuit may include the following components, which are listed in this document in the direction of fuel flow from upstream to downstream:

[0006] - Fuel tanks used to store fuel.

[0007] - A low-pressure LP pump is used to ensure fuel supply from the tank.

[0008] - Fuel filtration unit, used to limit (or even eliminate) contaminants in the fuel leaving the LP pump.

[0009] - High-pressure HP pump

[0010] - Metering unit, commonly referred to as fuel metering unit (FMU), and

[0011] - A set of injectors used to deliver the entire fuel flow to the turbine's combustion chamber.

[0012] Typically, LP pumps and HP pumps can be mounted on the same output shaft of the turbine's accessory gearbox (AGB) and driven by it.

[0013] The LP pump enables fuel to be delivered to the HP pump, which supplies fuel to the metering unit at a flow rate greater than the combustion chamber's fuel requirements.

[0014] Figure 1This diagram schematically illustrates the fuel flow rate (or velocity) injected by the HP pump in the supply loop, varying with the speed of the turbine internal combustion engine. Linear curve C1 represents a steady increase in the fuel flow rate supplied by the HP pump between turbine operating speeds R1 and R2. Speed ​​R1 represents the fuel flow rate during turbine startup, in flight, or during the windmill phase on the ground. Speed ​​R2 represents the fuel flow rate at the turbine's maximum normal operating speed (e.g., during aircraft takeoff). Curve C2 represents the fuel demand of the combustion chamber operating at speeds R1 and R2. This curve C2 represents the fuel flow rate required to meet the combustion chamber's needs and is significantly lower than the fuel flow rate injected by the HP pump in curve C1. Figure 1 Arrow E in the diagram indicates the amount of excess fuel.

[0015] This excess fuel is recirculated through the fuel supply loop. To this end, the loop also includes a recirculation path configured to return a second fuel flow corresponding to the amount of excess fuel in the metering unit from the metering unit (FMU) toward the inlet of the HP pump.

[0016] Therefore, the first and second fuel streams are mixed before entering the HP pump. The outlet of the recirculation path is typically located near the fuel inlet of the HP pump to optimize the overall size and space of the turbine, in particular. A major drawback of this configuration is that the first and second fuel streams entering the HP pump are not perfectly homogeneous. This can cause cavitation (i.e., bubbles) in the fuel stream supplied to the HP pump, which can damage the pump. Consequently, the performance of the HP pump may degrade, and its service life may be limited.

[0017] A fuel supply circuit for the combustion chamber of an aircraft turbine is known in the prior art, comprising a recirculation circuit in which excess fuel flows from a metering unit to a fuel tank or injector pump located upstream of the HP pump, as described in documents FR-A1-2999653 and WO-A1-2014 / 096620, respectively. When fuel is returned to the tank, the problem of fuel homogenization upstream of the HP pump is avoided. The injector pump is capable of mixing a first fuel stream from the LP pump and a second fuel stream from the metering unit to supply fuel to the HP pump. However, a disadvantage of the injector pump is that it requires complex and cumbersome installation.

[0018] In this context, it is of interest to overcome the shortcomings of the prior art by proposing a reliable multi-fuel flow distribution device that can be integrated into the fuel supply circuit of the combustion chamber while enabling its simple and rapid assembly in the turbine. Summary of the Invention

[0019] This invention proposes a fuel supply circuit, particularly for the combustion chamber of a turbine in an aircraft, comprising:

[0020] - A supply passage configured to allow a first fuel flow from the fuel tank;

[0021] - A metering unit configured to supply fuel at a predetermined flow rate to the combustion chamber;

[0022] - At least one supply pump, said at least one supply pump being used to flow the fuel from the tank to the metering unit;

[0023] - A recirculation path for a second fuel stream, corresponding to the amount of excess fuel from the metering unit, the recirculation path being located upstream of the supply pump;

[0024] The supply passage and the recirculation passage open in different directions upstream of the supply pump.

[0025] According to the present invention, the circuit includes at least one fuel flow distribution device, the distribution device including an internal conduit for the flow of the first fuel flow, an external annular valley for the flow of the second fuel flow, and at least one orifice for the passage of the second flow, the at least one orifice being in fluid communication with the annular valley.

[0026] According to the invention, the at least one hole and the internal pipe are coaxial and open upstream of the supply pump, respectively.

[0027] Therefore, this solution enables the achievement of the aforementioned objectives. In fact, this configuration allows for the separation of at least two fuel streams from different directions using the distribution device of the present invention, and directs them in the same direction. This enables optimal and uniform mixing of these streams for use in the fuel supply pump of the fuel supply circuit for the combustion chamber.

[0028] Specifically, the fuel flows entering the distribution device have different flow rates and therefore originate from a separation and secant passage upstream of the device (and thus upstream of the supply pump). These flows entering the device are regulated by coaxial flow channels (i.e., an internal flow channel for the first flow and at least one orifice for the passage of the second flow) so that the flows do not interfere with each other, thus preventing turbulence and / or cavitation. Therefore, the flows leaving the distribution device have the advantage of having a stable flow rate and thus being in a quiescent state. In this way, the stable flow rates are mixed at the outlet of the distribution device, thus being fed into the supply pump in a uniformly mixed manner without cavitation. Therefore, the supply pump of the loop of the present invention is not damaged by fuel flows from the supply passage and recirculation passage of the loop. This significantly improves the service life and performance of the supply pump.

[0029] Therefore, the advantages of this invention are that it proposes a simple design, provides very high reliability, and suffers almost no loss in terms of turbine cost and overall size requirements.

[0030] The fuel supply circuit according to the invention further includes one or more of the following features, used individually or in combination:

[0031] - The supply passage leads downstream to the internal conduit for flow of the distribution device, and the recirculation passage leads to the annular valley of the distribution device;

[0032] - The device is installed in a housing arranged upstream of the supply pump, and in the device, the at least one hole and the internal conduit lead to the mixing area of ​​the housing;

[0033] - The supply passage and the recirculation passage are configured to secantly lead to the housing, wherein the downstream end of the supply passage leads to the internal conduit, and the upstream end of the recirculation passage leads to the external annular valley;

[0034] - The downstream end of the internal conduit leading to the supply passage for flow extends generally axially or obliquely relative to the axis A;

[0035] - The upstream end of the recirculation path leading to the annular valley extends substantially perpendicularly or obliquely relative to the axis A;

[0036] - The dispensing device includes a rotating body extending about a longitudinal axis and comprising:

[0037] - An internal conduit for the flow of the first fuel stream, the internal conduit extending along axis A through the body, and

[0038] - A first annular portion, configured to form an outlet channel for the second fuel flow, and the first annular portion including at least one hole for the passage of the second fuel flow, the at least one hole being distributed around the axis in the form of an annular row of holes;

[0039] - The at least one hole extends along an axis parallel to the axis of the internal conduit;

[0040] - The internal conduit and the at least one orifice for flow are configured to open transversely to the axis around which the supply pump extends;

[0041] - The body also includes a second annular portion configured to form an inlet passage for the first fuel flow through the internal conduit, the second portion being connected to the first portion via an intermediate portion that at least partially defines the central opening;

[0042] - The second part also includes at least one annular seal and attachment groove, the at least one annular seal and attachment groove being configured for mounting a sealing element;

[0043] - The supply pump of the fuel circuit includes a low-pressure pump (e.g., rotary power type) and / or a high-pressure pump (e.g., positive gear type);

[0044] - The housing and the mixing region are arranged upstream of the high-pressure pump;

[0045] - The internal conduit for the flow of the first fuel stream is formed by the central opening.

[0046] This application also relates to a turbine, particularly an aircraft turbine, including a fuel supply circuit for the combustion chamber of the turbine according to one of the features of the invention.

[0047] The present invention also proposes a fuel flow distribution device for at least one fuel flow in a fuel supply circuit of a combustion chamber, particularly for an aircraft turbine, the device comprising a rotating body extending about a longitudinal axis A. The body includes:

[0048] - An internal conduit, the internal conduit being used for the flow of the first fuel stream and extending along axis A through the body, and

[0049] - A first annular portion, configured to form an outlet channel for the second fuel flow, and the first annular portion includes at least one hole for the passage of the second fuel flow.

[0050] The dispensing device according to the invention has the advantage of ensuring multiple functions within the fuel supply circuit, namely:

[0051] - To direct the first fuel flow from the supply path of the loop (e.g., from the first filter unit, or from the low-pressure pump, as described in the examples below);

[0052] -Guide the second fuel flow from the recirculation path in the loop;

[0053] - Direct the first and second flows in the same direction (e.g., particularly via coaxial flow channels);

[0054] - Seal the housing in at least one housing of the components arranged in the fuel circuit (e.g., between the housing of the first filter unit and the housing of the high-pressure pump, as described in the example below).

[0055] Furthermore, as described above, the distribution device for the fuel circuit thus enables the separation of the first and second flows from different directions and allows the first and second flows to be directed in the same direction at the outlet of the device. This slows down the flow rate of each fuel flow, thereby limiting (or even eliminating) turbulence and / or cavitation in the fuel leaving the device. In this way, the fuel flow entering the supply pump of the circuit is optimally homogenized, especially after passing through the mixing zone located between the supply pump and the device.

[0056] The dispensing device according to the invention further includes one or more of the following features, used individually or in combination:

[0057] - The device includes an outer annular valley that is in fluid communication with at least one orifice of the first portion;

[0058] - The at least one hole for the passage of the second fuel flow is distributed in the form of an annular row of holes;

[0059] - Each of the holes in the annular row extends along an axis parallel to axis A;

[0060] - The main body also includes a second annular portion configured to form an inlet passage for the first fuel flow through the internal conduit;

[0061] - The second part is connected to the first part via an intermediate portion of the dispensing device, the intermediate portion at least partially defining the internal conduit;

[0062] - The second part includes an annular collar extending radially around the axis A;

[0063] - The annular valley is at least partially defined by the wing side of the collar and the wall of the first portion;

[0064] - The second part also includes at least one annular seal and attachment groove, the at least one annular seal and attachment groove being configured for mounting a sealing element;

[0065] - The outer diameter of the first annular portion is smaller than the outer diameter of the annular collar of the second annular portion;

[0066] - The diameter of each hole in the annular row of holes is between 3 mm and 10 mm, preferably between 5 mm and 7 mm, and more preferably about 5.5 mm;

[0067] - The annular row of holes includes five to twenty holes, preferably fifteen to twenty holes, and more preferably about seventeen holes.

[0068] This application also relates to a turbine, particularly an aircraft turbine, comprising at least one distribution device for at least one fuel flow to the combustion chamber of the turbine, according to one of the features of the invention. Attached Figure Description

[0069] The invention will be better understood from the following description by way of non-limiting example and with reference to the accompanying drawings, and other details, features and advantages of the invention will become clearer, in which:

[0070] [ Figure 1 ] Figure 1 This is a schematic diagram showing the fuel flow rate supplied by the high-pressure pump in the fuel supply circuit and the fuel flow rate required by the combustion chamber;

[0071] [ Figure 2 ] Figure 2 This is a very schematic view of the fuel supply circuit for a turbine combustion chamber according to the present invention;

[0072] [ Figure 3 ] Figure 3 It is used for allocation Figure 2 A schematic perspective view of the upstream side of a device for at least one fuel flow in a circuit;

[0073] [ Figure 4 ] Figure 4 yes Figure 3 A schematic perspective view of the downstream side of the distribution device;

[0074] [ Figure 5 ] Figure 5 yes Figure 4 A schematic cross-sectional view of the dispensing device; and

[0075] [ Figure 6 ] Figure 6 yes Figures 3 to 5 The dispensing device in Figure 2 An enlarged schematic cross-sectional view of the layout in the supply loop. Detailed Implementation

[0076] By convention, in the following description, the terms "longitudinal" and "axial" refer to the orientation of a structural element extending in the direction of a longitudinal axis X. This axis X may coincide with the rotational axis of the turbine rotor. The terms "radial" or "vertical" refer to the orientation of a structural element extending in a direction perpendicular to axis X. The terms "inner" and "outer," as well as "internal" and "external," refer to positioning relative to axis X. Thus, a structural element extending along axis X includes an inner surface oriented toward axis X and an outer surface opposite to it. In this application, the terms "upstream" and "downstream" are defined relative to the direction of gas flow in the turbine.

[0077] The above has already been discussed. Figure 1 It has been described.

[0078] This invention applies to turbine 100, and particularly to turbines for aircraft, which include a gas generator or engine. Such a turbine can be a turboprop engine, a turbojet engine, or a turboshaft engine. The gas generator of the turbine typically includes one or more compressors, such as a low-pressure compressor and a high-pressure compressor, arranged upstream of the combustion chamber 9.

[0079] In particular, compressed air is supplied from the high-pressure compressor to the combustion chamber 9 via an annular diffuser, and fuel is supplied to the combustion chamber via a fuel supply circuit 1, wherein the fuel supply circuit 1 includes injectors angled around the longitudinal axis X of the turbine.

[0080] Figure 2 The fuel supply circuit 1 (or fuel circuit 1 in this application) may include the following elements, which are listed in this application in the direction of fuel flow from upstream to downstream:

[0081] - Fuel tank 2, used for storing fuel

[0082] - Low-pressure LP pump 3, such as a rotary-powered low-pressure pump (e.g., a centrifugal pump that allows fluid to be pumped and emptied by the rotation of a rotor or impeller), to ensure the fuel supply from tank 2.

[0083] - First fuel filter unit 4a, used to limit (or even eliminate) contaminants in the fuel leaving LP pump 3.

[0084] - High-pressure HP pump 5, such as a positive displacement gear type high-pressure pump,

[0085] - Second fuel filter unit 4b, used to limit (or even eliminate) contaminants in the fuel leaving HP pump 5.

[0086] - Metering unit 6, used to deliver the entire distributed fuel flow to combustion chamber 9 at the outlet, and

[0087] - A set of injectors 7 for delivering the entire fuel flow to the combustion chamber 9 of the turbine 100.

[0088] LP pump 3 and HP pump 4 can be mounted on and driven by the same output shaft of the turbine 100's (e.g., AGB type) accessory gearbox (not shown). This, in particular, allows the flow rate delivered by LP pump 3 and HP pump 5 to be adapted to the needs of combustion chamber 9.

[0089] LP pump 3 supplies a first fuel flow F1 from tank 2 to first filter unit 4a and HP pump 5 via supply passage 20. HP pump 5 supplies fuel, for example, to second filter unit 4b and metering unit 6 via supply passage 20 at a flow rate higher than the fuel demand of combustion chamber 9.

[0090] As described above, excess fuel is recirculated in fuel circuit 1 through recirculation passage 60. This recirculation passage 60 is configured to return a second fuel flow F2 corresponding to the excess fuel amount of metering unit 6 to the upstream of HP pump 5.

[0091] Therefore, the first fuel stream F1 and the second fuel stream F2 are mixed before entering the HP pump 5.

[0092] exist Figure 2 In the example shown, passages 20 and 60 are upstream of HP pump 5 along different directions D1 and D2 (e.g., Figure 6 (As shown) Open.

[0093] One of the special features of this invention is that the fuel circuit 1 also includes a fuel distribution device 8. This distribution device 8 can be releasably assembled upstream of the HP pump 5.

[0094] exist Figure 2 In, and not limited to, the dispensing device 8 is located within the housing 10 of the circuit 1. The device 8 and the housing 10 are located downstream of the first filter unit 4a and upstream of the HP pump 5. The overall shape of the housing 10 may be at least partially complementary to the overall shape of the dispensing device 8.

[0095] In the case of fuel circuit 1, the distribution device 8 is configured to guide and ensure uniform mixing of the first fuel flow F1 and the second fuel flow F2 from the supply passage 20 and the recirculation passage 60, respectively.

[0096] The passages 20 and 60 are configured to secant into the housing 10 (and thus into the device 8).

[0097] Furthermore, the housing 10 includes a mixing zone 12 for the fuel flows F1 and F2 exiting the distribution device 8. Figure 2 In the middle, the mixing zone 12 is located downstream of the dispensing device 8 and upstream of the HP pump 5.

[0098] Reference Figures 3 to 5 We will now describe the fuel distribution device 8 that equips the fuel circuit 1.

[0099] The dispensing device 8 has a rotatable form extending about a longitudinal axis A. The axis A may be substantially parallel or inclined relative to the axis X of the turbine 100. The dispensing device 8 includes a generally elongated body 80 extending about the axis A.

[0100] exist Figures 3 to 5 In the example, the main body 80 includes a first annular portion 81, a second annular portion 83 opposite to the first portion 81 (along axis A), and an intermediate portion 82 connecting the annular portions 81 and 83 to each other. Advantageously, portions 81, 82, and 83 are formed as a single piece (integral).

[0101] The main body 80 also includes an internal flow conduit 800 extending along axis A. This internal conduit 800 may have a cylindrical shape. The internal conduit 800 may be formed by a central through opening. In this example, the opening of the internal conduit 800 has a circular cross-section. The diameter D of the opening of the internal conduit 800 is... 800 The diameter can be between 10mm and 50mm, preferably between 20mm and 30mm. More preferably, the diameter D... 800 Approximately 26mm. In Figure 3 In the case of the central opening 800, the length L1 is between 20mm and 50mm. Advantageously, the length L1 is between 25mm and 30mm.

[0102] In this example, the opening of the internal conduit 800 forms a fuel inlet passage on one side of the second portion 83 and a fuel outlet passage on one side of the first portion 81. More specifically, the opening of the internal conduit 800 leads to the front wall 812 of the first portion 81 and the rear wall 832 of the rear end 830 of the second portion 83.

[0103] The first part 81 includes a front wall 812 and a rear wall 814 that are generally transverse to axis A. The front wall 81 generally passes through plane P1, and the rear wall 814 generally passes through plane P2. Figure 3 and Figure 4 In this example, planes P1 and P2 are approximately perpendicular to axis A. Furthermore, the first portion 81 has an annular outer surface that narrows toward plane P2.

[0104] The first part 81 also includes at least one orifice 810. The orifice 810 is configured to allow fuel to pass through. Figures 3 to 5 In the example shown, the first portion 81 includes an annular row of holes 810 extending circumferentially around axis A. Each hole 810 in this annular row is through and extends axially between planes P1 and P2. Figure 4Furthermore, and without limitation, the length L2 between planes P1 and P2 (approximately corresponding to the distance between the front wall 812 and the rear wall 814, respectively) is between 5 mm and 15 mm, preferably approximately 8 mm. Each hole 810 may also extend approximately parallel to the central opening of the internal conduit 800. The annular row of holes comprises five to twenty holes, preferably fifteen to twenty holes. More preferably, approximately seventeen holes. The diameter D of each hole 810 in the annular row of holes... 810 The diameter is between 3mm and 10mm, preferably between 5mm and 7mm, and even more preferably about 5.5mm. The opening and hole 810 of the internal conduit 800 are coaxial, particularly coaxial with respect to axis A.

[0105] The first part 81 is configured to form a fuel outlet channel. The holes in the annular row are configured to form a fuel inlet channel and a fuel outlet channel.

[0106] The intermediate portion 82 defines an annular valley 820 between the first portion 81 and the second portion 83. Therefore, in this example, the annular valley 820 extends from front to back between plane P2 and plane P3. Plane P3 is generally parallel to planes P1 and P2. Figure 3 Furthermore, and without limitation, the length L3 between planes P1 and P3 (approximately corresponding to the front wall 812 of the first portion 81 and the ends of the intermediate portion 82 opposite to wall 812, respectively) is between 15 mm and 30 mm, preferably about 21 mm. The annular valley 820 is in fluid communication with the orifice 810 of the first portion 81. The annular valley 820 is configured to form a fuel inlet passage.

[0107] The second part 83 includes an annular collar 84 extending radially outward and about axis A. The annular collar 84 is located on one side of the intermediate part 82. The annular collar 84 has a front wing side 842 and a rear wing side 844 axially opposite to the front wing side 842. The wing sides 842 and 844 are connected by a peripheral annular surface 843. In this example, the front wing side 842 is generally defined in plane P3.

[0108] The second part 83 also includes at least one annular groove 85 extending about axis A, referred to as an annular sealing and attachment groove. This annular sealing and attachment groove 85 is configured for mounting a sealing element 850. Specifically, in this example, the annular sealing and attachment groove 85 has a U-shaped axial cross-section and opens to an annular peripheral surface 843. Advantageously, the sealing element 850 is an O-ring (such as...). Figure 6 (As shown). Similarly, in this example, the rear end portion 830 may also include an annular groove 85, which may be U-shaped in axial cross-section and leads to the annular peripheral surface of the rear end portion 830. Figure 5In the middle, the second part 83 includes two annular grooves 85, which are respectively disposed on the annular collar 84 and the rear end 830 opposite to the annular collar 84 (along axis A).

[0109] In this example, the outer diameter D of the annular collar 84 84 (defined by the outer peripheral surface 843) is larger than the outer diameter of the rear end portion 830 of the second part 83.

[0110] Part 83 is configured to form a fuel inlet passage.

[0111] In this example, the outer diameter D of the annular collar 84 84 The outer diameter D of the first part 81 is greater than that of the first part. 81 The outer diameter D of Part 1, 81 81 The outer diameter D of the annular valley is greater than 820. 820 .

[0112] We will now describe the distribution device 8 equipped in the fuel circuit 1 of the present invention.

[0113] Reference Figure 2 and Figure 6 Furthermore, the dispensing device 8 is assembled in a housing 10 located downstream of the first filter unit 4a and upstream of the HP pump 5.

[0114] The HP5 pump can be of the positive displacement gear type. In this case, the HP pump 5 may include one or more toothed gears 52. Figure 6 As shown, the toothed wheel 52 has a rotation axis B. This axis B is approximately perpendicular to the axis A of the device 8.

[0115] The housing 10 has a generally cylindrical shape extending along the axis of rotation. Figure 6 In this configuration, the axis of rotation of housing 10 is approximately coincident with the axis A of the dispensing device 8. Housing 10 may be formed by the wall of at least one of housings 40, 50 and / or at least one of the passages 20, 60 of fuel circuit 1. In this example and not in a limiting sense, housing 10 is at least partially located between housing 40 of the first filter unit 4a and housing 50 of the HP pump 5.

[0116] exist Figure 6 In this configuration, the casing 10 extends radially into the recirculation passage 60 in at least a portion. Additionally, the casing 10 extends upstream into the supply passage 20 and downstream into the mixing region 12 of the fuel circuit 1.

[0117] The mixing region 12 is generally annular or cylindrical in shape. In this example, the mixing region 12 may also extend along a longitudinal axis that coincides with the axis of rotation of the housing 10 and the axis A of the dispensing device 8.

[0118] exist Figure 6 In this process, the mixing region 12 thus leads upstream to the housing 10 (and the first part 81 of the dispensing device 8 installed in the housing 10) and downstream to the HP pump 5 (e.g., to the gear of the toothed wheel 52 leading to the HP pump 5).

[0119] exist Figure 6 In this example, the front wall 812 of the first portion 81 of the dispensing device 8 abuts against the upstream wall 102 of the housing 10. In this example, the housing 10 may correspond to the wall of the housing 50 of the HP pump 5. The front wing side 842 of the annular collar 84 of the dispensing device 8 abuts against the downstream wall 104 of the housing 10. In this example, the housing 40 of the first filter unit 4a carries the downstream wall 104.

[0120] In this example, O-rings 850 are installed between the groove 85 of the dispensing device 8 and the inner annular surfaces of the housings 40 and 50. These O-rings are sufficient to securely and tightly hold the dispensing device 8 within the housing 10.

[0121] The supply passage 20 of loop 1 includes an upstream outlet 22 that leads upstream of the dispensing device 8 to the central opening 800 located on one side of the second part 83. The upstream outlet 22 is oriented in a direction that is generally inclined or extends axially relative to axis A.

[0122] The recirculation path 60 of loop 1 includes an upstream outlet 62 that leads to the housing 10, particularly to the annular valley 820 of the intermediate portion 82. The downstream outlet 62 is oriented in a direction that extends generally laterally relative to axis A. In particular, the outlet direction is perpendicular or inclined relative to axis A (at an angle between 20° and 50°).

[0123] Reference Figure 6 The first fuel flow F1 originates from the supply passage 20 along the first direction D1, and the second fuel flow F2 originates from the recirculation passage 60 along the second direction D2.

[0124] The first fuel flow F1 flows through the central opening of the pipe 800 of the distribution device 8 to the mixing zone 12, and then into the HP pump 5. This causes the first flow F1 to flow into and out of the distribution device 8 along a third direction D3. This third direction D3 is coaxial with axis A and also with the rotation axis of the mixing zone 12 and the housing 10. When the upstream outlet 22 is opened at an angle relative to axis A (e.g.) Figure 6 As shown), the flow direction D3 of the first flow F1 can be different from the first direction D1, or when the upstream outlet 22 is axially opened relative to the axis A, the flow direction D3 of the first flow F1 is coaxial with the direction D1.

[0125] Advantageously, the first flow F1 along the third direction D3 flows approximately perpendicular to the axis B of the toothed wheel 52 of the HP pump 5.

[0126] An annular chamber 826 is formed within the housing 10 by the walls formed by the upstream end 62 and the annular valley 820. The second fuel flow F2 enters the distribution device 8 through this annular chamber. The second flow F2 then passes through the orifice 810 of the first portion 81 to enter the mixing region 12, and then into the HP pump 5. This allows the second flow F2 to flow into and out of the distribution device 8 along the third direction D3. In this example, the flow direction D3 of the second flow F2 is different from the second direction D2.

[0127] In the annular chamber 826, the second flow F2 is slowed down relative to its velocity in the recirculation passage 60. This causes the second flow F2 to change from a turbulent state in the recirculation passage 60 to a laminar state in the orifice 810 and subsequently in the mixing region 12.

[0128] It is understood that the dispensing device of the present invention is located at the intersection of the outlet of the first stream F1 and the outlet of the second stream F2, and these streams are mixed at the outlet of the dispensing device.

[0129] This means that the fuel streams F1 and F2 entering the mixing zone 12 have little or no cavitation before entering the HP pump 5. In the mixing zone 12, the fuel streams F1 and F2 are homogenized so that they flow into the HP pump 5.

[0130] This application describes a fuel distribution device for distributing or guiding fuel in a fuel supply circuit, particularly for a turbine combustion chamber in an aircraft. The distribution device of this invention can also be applied to any type of fluid and to the hydrodynamic systems of turbines outside the aerospace field.

[0131] The fuel distribution device equipped with a fuel supply circuit according to the present invention offers several advantages, which are particularly applicable to:

[0132] - Optimize the mixing and homogenization of fuel flows from the upstream secant and non-coaxial supply and recirculation paths of the supply pump.

[0133] - Provide a distribution and mixing device within the overall dimensions and available space of the fuel circuit.

[0134] - Optimize the lifespan of the supply pump by preventing fuel cavitation.

[0135] -Easy to attach to and detach from the supply circuit

[0136] - The maintenance costs of the fuel supply pump in the limiting fuel circuit, and

[0137] -Easy to adapt to existing gas generators.

[0138] Overall, the proposed solution is simple, effective, and economical to implement and assemble on turbines, while providing optimal fuel supply to the turbine's combustion chamber and improving the service life of at least one component of the fuel supply circuit.

Claims

1. A fuel flow distribution device (8) for at least one fuel flow in a fuel supply circuit (1) of a combustion chamber (9) of a turbine (100), the distribution device (8) comprising a rotating body (80) extending about a longitudinal axis (A), the rotating body (80) comprising: - An internal conduit (800) for the flow of a first fuel stream (F1) and extending along the longitudinal axis (A) through the rotating body (80). - A first annular portion (81) is configured to form an outlet channel for a second fuel flow (F2), and the first annular portion includes at least one through hole (810) for the second fuel flow (F2). - An outer annular valley (820), said outer annular valley being in fluid communication with at least one through-hole (810) of the first annular 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). The second annular portion (83) is characterized in that it includes an annular collar (84) extending radially around the longitudinal axis (A).

2. The dispensing device (8) according to claim 1, characterized in that, The at least one through hole (810) for the second fuel flow (F2) is distributed in the form of an annular row of holes.

3. The dispensing device (8) according to claim 2, characterized in that, The holes (810) in the annular row each extend along an axis parallel to the longitudinal axis (A).

4. The dispensing device (8) according to any one of claims 1 to 3, characterized in that, The second annular portion (83) is connected to the first annular portion (81) via the middle portion (82) of the dispensing device (8), the middle portion (82) at least partially defining the internal conduit (800).

5. The dispensing device (8) according to any one of claims 1 to 3, characterized in that, The outer annular valley (820) is at least partially defined by the wing side (842) of the annular collar (84) and the wall (814) of the first annular portion (81).

6. The dispensing device (8) according to any one of claims 1 to 3, characterized in that, The second annular portion (83) further includes at least one annular seal and attachment groove (85) configured for mounting a sealing element (850).

7. The dispensing device (8) according to any one of claims 1 to 3, characterized in that, The outer diameter (D) of the first annular portion (81) 81 The outer diameter (D) of the annular collar (84) of the second annular portion (83) is smaller than that of the annular portion (83). 84 ).

8. The dispensing device (8) according to claim 2 or 3, characterized in that, The diameter (D) of each hole (810) in the annular row of holes 810 The diameter is between 3mm and 10mm.

9. The dispensing device (8) according to claim 2 or 3, characterized in that, The annular row of holes includes five to twenty holes.

10. The dispensing device (8) according to claim 8, characterized in that, The diameter (D) of each hole (810) in the annular row of holes 810 The diameter is between 5mm and 7mm.

11. The dispensing device (8) according to claim 10, characterized in that, The diameter (D) of each hole (810) in the annular row of holes 810 The diameter is 5.5mm.

12. The dispensing device (8) according to claim 9, characterized in that, The annular row of holes includes fifteen to twenty holes.

13. The dispensing device (8) according to claim 12, characterized in that, The annular row of holes comprises seventeen holes.

14. A turbine (100) comprising at least one fuel flow distribution device for a fuel supply circuit (1) for a combustion chamber (9) of the turbine (100) according to any one of claims 1 to 13.

15. The turbine according to claim 14, wherein the turbine (100) is an aircraft turbine.

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