Diverter comprising channels with dual ejection angles

Abstract

The invention relates to a deflector (21) for a compressor of a double-flow turbine engine (1) having a longitudinal axis, comprising a wall (25) provided with a plurality of injection channels (29) capable of discharging an exhaust air flow into a flow path of the turbine engine in which the air flow circulates, injection channels having axes (C) are arranged in a plurality of rows and are configured to inject a flow of exhaust air in a flow direction of the flow of air, the axes (C) each being oriented in a first direction forming a first angle (alpha) with respect to an axis (B) parallel to an axis of revolution of the exhaust deflector. According to the invention, the projection of the axis of the injection channels (29) of each row in a projection plane (PP) perpendicular to the median plane (PM) forms a second angle (beta) with a straight line parallel to the median plane.

Description

Field of the Invention

[0001] The present invention relates to the field of turbomotors, and more particularly to a dual-flow turbomotor for an aircraft. In particular, the object of the present invention is to provide a deflector that can discharge a part of the air flow flowing through the compressor into the flow path of the turbomotor. The present invention also relates to a turbomotor including such a deflector. Background Art

[0002] Known dual-flow turbomotors are equipped with one or more air discharge systems for the compressor assembly. These systems are called: "Handling Bleed Valve" (HBV) or "Transient Bleed Valve" (TBV), the handling bleed valve or the transient bleed valve takes a part of the main stream from the high-pressure compressor; or "Variable Bleed Valve" (VBV), the variable bleed valve takes a part of the main stream from the low-pressure compressor. The obtained air flow is injected into the secondary flow or downstream of the main stream. The purpose of this discharge is to stabilize the operation of the low-pressure compressor and / or the high-pressure compressor and to limit certain phenomena that may impede the operation of the low-pressure compressor and / or the high-pressure compressor, such as pumping, rotational separation or floating.

[0003] The HBV-type discharge system includes a plurality of holes leading to the secondary flow path, and the secondary flow circulates in this secondary flow path. The jet of the air flow injected into the secondary flow path by the discharge system can impact the components around the holes, such as the inner wall (referred to as IFD (Inner Fan Duct)) that partially defines the secondary flow path or the outer wall (referred to as OFD (Outer Fan Duct)) that partially defines the secondary flow path, as well as possible other components in the wake of the air flow. The holes can be oriented in the direction of the secondary flow or in a direction transverse to the air flow to increase the mixing of the discharged main stream and the secondary flow and to limit the thermal stress on adjacent structures and / or elements that cannot withstand high temperatures. Examples of such discharge systems are described in documents FR-A1-3057026, FR-A1-3057028 and US-B2-6588195.

[0004] However, for such known discharge systems, there is still a risk that certain components (especially the OFD and the thrust reverser) around the injection area of the air inhaled into the compressor may still be significantly affected.

[0005] It is necessary to solve some or all of the above disadvantages. Summary of the Invention

[0006] The object of the present invention is to provide a deflector that enables a better distribution of the air flow at its outlet, while avoiding thermal stresses, and that is economically and simply manufactured.

[0007] According to the invention, this object is achieved by a deflector for an exhaust system of a compressor of a dual-flow turbomachine having a longitudinal axis, the deflector comprising a wall provided with a plurality of injection channels that are able to discharge an exhaust air flow from the compressor into the flow path of the turbomachine, in which the air flow circulates in a flow direction, the injection channels having axes that are arranged in a plurality of rows in an alignment direction that is substantially parallel to a median plane of the deflector, the median plane being substantially parallel to the flow direction, and the injection channels being configured to inject the exhaust air flow in the flow direction, the axes each being oriented in a first direction that forms a first angle with an axis parallel to the axis of rotation of the deflector, and the projection of the axes of the injection channels of each row in a projection plane perpendicular to the median plane forming a second angle with a straight line parallel to the median plane.

[0008] Thus, this solution makes it possible to achieve the above object. In particular, the orientation of each injection channel at two angles, in particular at the second angle (axial and tangential orientation), makes it possible to direct the jets of the air flow leaving the deflector so as to rapidly homogenize the mixture and reduce the thermal shock on thermosensitive components, without affecting the acoustics of the deflector. The arrangement of the second angle makes it possible to reduce the temperature of the jets leaving the deflector, which provides greater protection for the walls (such as the radial inner wall and the radial outer wall that delimit the flow path of the turbomachine) and for the surrounding components (such as a thrust reverser that can be carried by one of the walls of the flow path), and the arrangement of the second angle also makes it possible to expand the flow of the exhaust air.

[0009] The deflector further comprises one or more of the following features, taken alone or in combination:

[0010] - The injection channels in each row have a circular cross-section.

[0011] - The value of the second angle is symmetric with respect to the median plane.

[0012] - The second angle increases in a direction perpendicular to the median plane from the median plane towards the edge of the deflector.

[0013] - The variation of the second angle is gradual.

[0014] - The second angle is constant in the same row on both sides of the median plane.

[0015] - The injection channels are arranged to form curves that are parallel to each other, transverse to the median plane, and symmetric with respect to the median plane.

[0016] - The first angle of each row is constant.

[0017] - Each first angle in the same row varies in a decreasing manner between the upstream edge and the downstream edge of the wall in the flow direction of the air flow.

[0018] The invention also relates to a turbomachine comprising at least one deflector having any of the foregoing features. When the deflector is installed in the turbomachine, the second angle significantly improves the protection of the turbomachine structure at the radial outer wall (OFD).

[0019] The invention also relates to an aircraft comprising a turbomachine as described above. Description of the Drawings

[0020] With reference to the attached schematic diagrams, the present invention will be better understood by reading the following detailed explanatory description of embodiments of the present invention given as a purely illustrative and non - limiting example, and other objects, details, features, and advantages of the present invention will become clearer. In the attached schematic diagrams:

[0021] - Figure 1 A partial axial cross - section of an example of a turbomachine to which the present invention is applicable is shown;

[0022] - Figure 2 Is a schematic diagram of an axial cross - section of a flow path in which an example of an exhaust system according to the present invention is arranged;

[0023] - Figure 3 A cross - sectional view of an example of an exhaust system according to the present invention is shown;

[0024] - Figure 4 Is Figure 3 A top view of the exhaust system shown. Detailed Description of the Embodiments

[0025] Figure 1 A turbomachine for an aircraft according to the present invention is schematically shown. The turbomachine 1 shown is a twin - flow and twin - body turbofan engine extending along a longitudinal axis X.

[0026] The turbomachine 1 generally includes a gas generator 2. The gas generator generally includes a low - pressure compressor 3, a high - pressure compressor 4, a combustion chamber (not shown), a low - pressure turbine (not shown), and a high - pressure turbine (not shown) from upstream to downstream.

[0027] The terms "upstream" and "downstream" are defined with respect to the flow of gas in the turbomachine (under normal operating conditions) along the longitudinal axis X. Similarly, the terms "radial", "inner", and "outer" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X.

[0028] The low-pressure compressor 3 and the low-pressure turbine are connected by a low-pressure shaft (not shown) and together form a low-pressure (BP) body. The high-pressure compressor 4 and the high-pressure turbine are connected by a high-pressure shaft (not shown) and together form a high-pressure (HP) body. The low-pressure shaft and the high-pressure shaft are centered on the longitudinal axis.

[0029] The turbomachine includes a fan 5 arranged upstream of the gas generator 2. The fan 5 is directly driven by the low-pressure shaft or via a speed reducer (not shown) to rotate. The fan 5 includes a row of fan blades 6 that extend radially outward and are evenly spaced around the longitudinal axis. The fan blades 6 are surrounded by an outer casing 7, and the outer casing 7 is supported by a fan casing 8. The outer casing 7 is centered on the longitudinal axis X.

[0030] In one embodiment, the fan blades 6 can be variable pitch.

[0031] Referring to Figure 1 , the turbomachine 1 includes a first annular flow path called the main flow path 9 and a second annular flow path called the secondary flow path 10. The main (or hot) flow circulates in the main flow path 9, and the secondary flow (or cold flow) circulates in the secondary flow path 10. The secondary flow path 10 advantageously surrounds the main flow path 9. The main flow path 9 and the secondary flow path 10 are separated by an annular inter-flow-path casing 11 located between the outer casing 7 and the inner casing 11. The inner casing partially encloses the gas generator 2.

[0032] Advantageously, the main flow path 9 is defined by the radial inner wall of the inter-flow-path casing 11 and the radial outer wall of the inner casing. The main flow path 9 is coaxial with the inter-flow-path casing 11 and is surrounded by the inter-flow-path casing 11. Advantageously, the secondary flow path 10 is defined by the radial outer wall 12 of the inter-flow-path casing 11 and the radial inner wall 13 of the outer casing 7.

[0033] The main flow passes through the compressor, the combustion chamber, and the turbine, and then is discharged into the atmosphere through a nozzle (not shown).

[0034] Referring to Figure 2 , an exhaust system 20 is arranged in the turbomachine to be able to extract a portion of the air flow at one or more components of the turbomachine and inject this portion of the air flow into another air flow of the turbomachine.

[0035] Advantageously, the exhaust system 20 is configured to extract a portion of the air from the high-pressure compressor 4. This extracted portion of the air is part of the main flow.

[0036] The discharge system 20 is arranged between the main flow path 9 and the secondary flow path 10. More specifically, the discharge system 20 is mounted on the radially outer wall 12 of the inter-flow-path housing 11. Advantageously but not limited to, the discharge system 20 is mounted in line with the high-pressure compressor 4 to reduce the overall size. This part of the main flow is injected into the secondary flow path 10.

[0037] In an example of the embodiment, the discharge system 20 includes at least one deflector 21 and a duct 24.

[0038] The deflector 21 includes a wall 25 from which a peripheral skirt 26 extends. Advantageously but not restrictively, the wall 25 is circular and the peripheral skirt 26 is cylindrical with a circular cross-section having a rotational axis A. Of course, the shapes of the wall 25 and the skirt 26 can be different, such as rectangular.

[0039] The deflector 21 includes an air inlet 27 and an air outlet 28. Advantageously, the air inlet 27 is formed by the free edge of the peripheral skirt 26. Advantageously, the air outlet 28 is formed by an injection channel 29 arranged in the wall 25 (specifically shown in Figure 3 .

[0040] Referring to Figures 2 to 4 , the deflector 21 includes a collar 35 fixed to the peripheral skirt 26. In this example, the collar 35 extends from the free end of the peripheral skirt 26 and surrounds the air inlet 27. The collar 35 enables the deflector 21 to be attached to the duct 24. The collar 35 includes holes 36 passing through its wall on both sides. The holes 36 are configured to receive removable attachment means 37, such as screws.

[0041] According to Figure 2 the example shown, the collar 35 is advantageously but not exclusively mounted opposite the radially inner surface 14 of the radially outer wall 12 of the inter-flow-path housing 11.

[0042] Advantageously, the duct 24 is located in the inter-flow-path housing 11 (or in the core compartment of the turbomachine). A part of the wall 25 and the peripheral skirt 26 is arranged in the secondary flow path 10 such that the main flow received from the compressor via the air inlet is directly injected into the secondary flow path 10 via the injection channel 29. The peripheral skirt 26 defines the air flow passage between the air inlet 27 and the injection channel 29.

[0043] The duct 24 includes an air inlet (not shown) configured to be in fluid communication with the main flow path 9 and receive a part of the main flow from the high-pressure compressor 4. The duct 24 also includes an air outlet 32 that is connected to the air inlet 27 of the deflector 21. The duct 24 enables a hot air flow to flow from the compressor towards the deflector 21.

[0044] The regulating device 22 and the actuator 23 can be located in the duct 24 or upstream of the duct 24, close to the main flow path 9.

[0045] In Figure 3 and Figure 4 a wall 25 is provided with a plurality of injection channels 29 which are capable of discharging a part of the main air flow into the secondary flow path 10, and a secondary air flow circulates in the secondary flow path 10. The injection channels 29 are configured to inject a discharged air flow Fc which does not come into direct contact with the walls 12 (IFD), 13 (OFD) of the secondary flow path 10 and does not interfere with the flow or circulation of the secondary flow.

[0046] The wall 25 of the deflector is arched or dome-shaped. The wall 25 has a substantially constant thickness between 1 mm and 5 mm. In particular, the wall 25 has a concave inner surface 30 facing the regulating device 22 of the discharge system 20 and a convex outer surface 31 opposite to the inner surface 30. In this example, the convex outer surface 31 faces the secondary flow path 10. In this case, the wall 25 has a circular periphery as described above.

[0047] Referring to Figure 3 an injection channel 29 is formed in the wall 25 of the deflector 21. Each injection channel 29 extends on either side between the inner surface 30 and the outer surface 31. In the example shown, the injection channels 29 occupy almost the entire surface of the wall 25. Each injection channel 29 has an inlet orifice 33 defined in the inner surface 30 and in fluid communication with the passage of the deflector 21. Each injection channel 29 includes an outlet orifice 34 defined in the outer surface 31 and in fluid communication with the secondary flow path 10.

[0048] The injection channels 29 have a substantially constant circular cross-section. Of course, the cross-section of the channels 29 can be any other shape. Here, the diameter of the channels 29 is between 2 mm and 3 mm (preferably about 2.5 mm) in order to facilitate the manufacture of the deflector, regulate the flow rate of the discharged flow to be discharged and limit the noise pollution. The length of these channels 29 is preferably between 1 mm and 6 mm. The dimensions of the channels 29 will depend on the dimensions of the deflector (especially the thickness of the wall) and the flow rate of the discharged flow to be discharged into the secondary flow path 10.

[0049] The injection channels 29 are arranged in a plurality of rows R1, R20, etc. Each row R1, R20 extends in an alignment direction (B) parallel or substantially parallel to (plus or minus 5°) the median plane PM of the deflector 21. In other words, these rows are parallel to each other. The median plane PM is parallel to the flow direction of the air flow (in this case the secondary flow in the installed situation). The median plane PM is in Figure 3 the plane shown and includes the axis of rotation A of the deflector 21.

[0050] Advantageously, each of the rows R1, R20 forms an exhaust flow vane.

[0051] Each row R1, R20 includes from 1 to 30 injection channels 29. The channels 29 are spaced apart from each other by a distance, for example, between 0.5 mm and 3 mm, to maintain the mechanical strength of the wall 25 of the deflector. It should be understood that the number of rows and the number of injection channels 29 per row depend on the dimensions of the deflector 21 and the injection channels 29 on the one hand, and on the required flow rate through the deflector 21 when the valve is open on the other hand.

[0052] As Figure 3 and Figure 4 shown, the injection channels 29 are arranged to form lines L parallel to each other. The lines L are advantageously arranged transversely to the intermediate plane PM. In particular, the lines L are oriented towards the lateral edges of the deflector 21. The lateral edges are arranged on either side of the intermediate plane PM.

[0053] In the example of this embodiment, the lines L are curved. The spherical shape of the wall 25 accentuates the circular shape of the lines L.

[0054] Another advantageous but non - limiting feature is that the lines L are symmetric with respect to the intermediate plane. These lines L are substantially V - shaped, with the tip of the V - shape located on the intermediate plane PM.

[0055] The channels 29 are configured to discharge air jets in the flow direction of the secondary air flow.

[0056] Each injection channel 29 has a central axis C. In this example, the central axis C of each injection channel 29 is oriented in a direction forming a first angle α with respect to an axis B parallel to the axis of rotation A of the deflector. In this example, the axis B is vertical in the Figure 3 plane shown. Each first angle α is measured in a vertical plane parallel to the intermediate plane PM or the longitudinal axis X (when installed in a turbine engine).

[0057] Advantageously, each first angle α is between 0° and 90°. This ensures that the main air flow leaving the deflector 21 avoids the radial inner wall 12 and the radial outer wall 13 of the secondary flow path 10.

[0058] Advantageously, the first angle α of each row decreases from upstream to downstream along the flow direction (or along the longitudinal axis X when the exhaust system 21 is installed in a turbine engine). In other words, the injection channels 29 in the same row are oriented at a first angle α that decreases between the first channel in a row and the last channel in that row. Thus, the first angle α is different. This variation is defined between the upstream edge and the downstream edge of the wall.

[0059] An advantageous but non-limiting feature is that the variation is gradual so as not to disturb the secondary flow. In this way, the discharge air flow Fc through the injection channels 29 is directed along a direction towards the direction of the secondary flow circulation.

[0060] In one embodiment, the injection channels 29 in each row are oriented at the same angle α to form the discharge air flow Fc blades. In other words, the injection channels 29 in the same row are oriented at the same angle α. This configuration prevents the discharge flow Fc blades from contacting the radial inner wall 13 and / or the thrust reverser including the turbomachine.

[0061] According to an example of the embodiment and as Figure 4 shown, the projection of the axis C of the injection channels 29 of each row in the projection plane PP perpendicular to the intermediate plane PM forms a second angle β with a line parallel to the intermediate plane. This configuration maximizes the frontal mixing surface between the flow jets leaving the deflector and the secondary flow to improve mixing.

[0062] Advantageously, the second angle β of each row is constant. Each row has the same angle on each side of the intermediate plane. Alternatively, the second angle β of each row is not constant.

[0063] An advantageous feature is that the second angle β increases from the intermediate plane PM towards the lateral edges opposite the intermediate plane. The direction of this increasing variation is perpendicular to the intermediate plane PM. In other words, the second angle β varies in the same curve towards the edges of the wall 25. Between the injection channels in one row and the injection channels in an adjacent row, the second angle β increases from the intermediate plane. This configuration achieves a better distribution of the discharge air flow in the flow of the air flow.

[0064] As can be seen in Figure 4 and in a non-limiting manner, the curves L symmetric on both sides form a V shape, where the tip of the V shape passes through the intermediate plane. This highlights the tangential component of the channels and favors the distribution of the discharge air flow towards the edges of the deflector.

[0065] Advantageously, the variation of the second angle β is gradual, for example, to improve the distribution of the thermal jets.

[0066] The value of the second angle β is symmetric with respect to the intermediate plane PM. This makes it possible to ensure a uniform distribution of the air flow. This distribution can be asymmetric.

[0067] The second angle β is between 0° and 90°, inclusive of 0° and 90°. The variation range of the second angle β can be defined according to the need to dilute the discharge air flow in the secondary flow. The greater the variation of the second angle β, the greater the dilution. On both sides of the intermediate plane, a variation range of + / - 30° between the intermediate plane and the row furthest from the intermediate plane can still provide sufficient dilution in some configurations.

[0068] Thus, when the exhaust air stream Fc is injected into the secondary flow path 10, the exhaust air stream Fc is guided along a plurality of vanes having a substantially parabolic shape, which avoids thermal shock to the environment of the exhaust system 20. The circulation and flow of the cold air stream F are not disturbed. The second angle β enables the flow to be better distributed in the azimuthal (or tangential) direction of the grid.

Claims

1. A deflector (21) for an exhaust system (20) of a compressor (4, 5) of a twin-flow turbine engine (1) having a longitudinal axis (X), said deflector (21) comprising a wall (25) provided with a plurality of injection channels (29) capable of discharging an exhaust air flow from said compressor into a flow path (9, 10) of said turbine engine (1), the air flow flowing in said flow path in a flow direction, the injection channels (29) having an axis (C) being arranged in a plurality of rows (R1, R20) in an alignment direction (B) substantially parallel to an intermediate plane (PM) of said deflector (21), said intermediate plane being substantially parallel to said flow direction, and said injection channels being configured to inject said exhaust air flow in said flow direction, said axes (C) being each oriented in a first direction forming a first angle (α) with respect to an axis (B) parallel to the axis of rotation of said deflector, characterized in that, The projection of the axis of the injection channels (29) in each row in a projection plane (PP) perpendicular to the intermediate plane (PM) forms a second angle (β) with a line parallel to the intermediate plane (PM), the second angle (β) increasing from the intermediate plane (PM) towards the edge of the deflector in a direction perpendicular to the intermediate plane (PM).

2. The deflector (21) according to claim 1, characterized in that, The injection channels (29) in each row have a circular cross-section.

3. The flow deflector (21) according to claim 1 or 2, characterized in that, The value of the second angle (β) is symmetric about the intermediate plane.

4. The deflector (21) according to any one of the preceding claims, characterized in that The variation of the second angle (β) is gradual.

5. The deflector (21) according to any one of the preceding claims, characterized in that, The second angle (β) is constant in the same row on both sides of the intermediate plane.

6. The flow deflector (21) according to any one of the preceding claims, characterized in that The injection channels (29) are arranged to form curves (L) that are substantially parallel to each other, transverse to the intermediate plane (PM) and symmetric about the intermediate plane (PM).

7. The deflector (21) according to any one of the preceding claims, characterized in that, The first angle (α) of each row is constant.

8. The deflector (21) according to any one of claims 1 to 6, characterized in that, Each first angle (α) of the same row varies in a decreasing manner between the upstream edge and the downstream edge of the wall (25) in the flow direction of the air flow (F).

9. The deflector (21) according to any one of claims 1 to 8, characterized in that The second angle (β) is between 0° and 90°, inclusive of 0° and 90°.

10. A twin-spool turbomachine (1) comprising at least one deflector according to any one of the preceding claims.

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