Flow directing assembly for turbomachine

Abstract

The invention relates to a flow guide assembly (6) comprising:-two outer annular shell portions (62) and an inner annular shell portion (64) defining therebetween a first flow channel (V2) for a flow (F2) wherein the shell portions are each divided into outer and inner shell portion regions (620, 640) arranged circumferentially about an axis (A); and-discharge conduits (66) located within the inner shell portion (62) and opening into openings (65) formed in the inner shell portion (62), where the conduits (66) define inner discharge flow paths (F3) intended to be injected through the openings (65) into the first flow channel (V2), and where the discharge conduits (66) are located within the inner shell portion (62) and open into the second flow channel (V2) through the openings (65). Each of the ducts (66) is integrally formed from a composite material with one of the zones (640) of the inner shell portion, the zones of the inner shell portion including an opening (65) to which the duct (66) opens.

Description

Technical Field

[0001] This invention relates to the field of turbines, and more particularly to the field of dual-flow turbines for aircraft. Specifically, the invention relates to a flow guiding assembly for a turbine, which, for example, enables the guiding of one or more flows within the turbine's passageways. The invention also relates to a turbine incorporating such a flow guiding assembly. Background Technology

[0002] Prior art includes, in particular, documents US-A1-2018 / 291841 and FR-A1-3119199.

[0003] A dual-flow turbine, specifically used in aircraft, typically comprises a fan and a gas generator (or engine). The gas generator, from upstream to downstream, includes at least one compressor, a combustion chamber, and at least one turbine, depending on the gas flow within the turbine. This gas generator may be housed within an inner casing (also known as an inter-channel casing (or intermediate casing)). The fan is located upstream of the gas generator and within the outer casing. The air passing through the turbine is divided into a primary flow (or hot air flow) circulating within the gas generator and a secondary flow (or cold air flow) from the fan circulating around the inter-channel casing.

[0004] A two-flow turbine includes a main duct and a secondary duct. The main flow passes through the main duct, and the secondary duct extends around the main duct and through which the secondary flow passes. The main and secondary ducts are separated by an inter-duct casing.

[0005] The turbine is also equipped with a flow guidance system or component, also known as a "kit engine". kit engine The guiding assembly is used to direct the secondary flow and / or so-called discharge flow, specifically originating from the compressor, into the secondary piping of the turbine. To achieve this, the guiding assembly includes a discharge pipe (or valve) known as a Variable Bleed Valve (VBV) or Handling Bleed Valve (HBV). This discharge pipe is located within the inter-channel housing and allows a portion of the mainstream flow compressed by the compressor to be drawn in and injected into the secondary flow in the secondary piping (specifically for discharging from high-pressure compressors), where a portion of the mainstream flow mixes with the secondary flow. The purpose of this discharge is to stabilize compressor operation by limiting turbulence, swirling flow separation, or floating phenomena.

[0006] Figure 1 and Figure 2 An example of such a flow guiding component 6 is shown. The flow guiding component may include: - Two annular shells (outer annular shell 62 and inner annular shell 64) extend around the same axis A, with one annular shell surrounding the other. These two shells 62 and 64 define a first flow channel V2 between them for a first flow F2 (e.g., a secondary flow in a turbine). These shells 62 and 64 are composed of multiple sections and each includes shell sections 620 and 640 arranged circumferentially end-to-end around axis A. - Connecting arms 68, used to connect housings 62 and 64 together, extending radially between and connecting housings 62 and 64, these arms 68 are tubular and can be passed through by auxiliary devices configured to pass through the first flow channel V2, and - Discharge pipes 66, located inside the inner shell 64 and leading to openings 65 formed on the inner shell 64, define an internal passage for discharge flow F3, the discharge flow being configured to be injected into the first flow channel V2 through these openings 65.

[0007] The boot component 6 performs the following functions: - The tertiary flow (e.g., the discharge flow) formed by the main flow entering the discharge duct is guided to the secondary duct (e.g., the first flow channel of the guiding component). - Ensure the aerodynamic continuity of the third-order flow. -Guide and ensure the continuity of the main stream entering the guide assembly and exiting into the discharge pipe. - Ensure the passage and maintenance of auxiliary equipment (such as electrical, mechanical, hydraulic, and gas / oil exchangers) between the gas generator and the surrounding housing (or nacelle) of the gas generator. - Provide a mechanical connection between the gas generator and the nacelle. - Ensure fireproofing between different compartments of the gas generator and secondary piping, and - Enables access to equipment and auxiliary devices for maintenance purposes.

[0008] The guide assembly 6 includes discharge fins (or grids) 666, which are attached to each of the openings 65 in the inner shell section 640. These discharge fins 666 rectify the discharge flow in the secondary duct and prevent any external objects from entering the main duct via the discharge duct 66. The inner shell section 640, the discharge duct 66, and the discharge fins 666 are connected to each other by bolt-type attachments.

[0009] The guide assembly 6 also includes a sealing element 7, which is attached between the inner housing section 640 and the discharge duct 66 to provide protection against fire and air and to provide a seal.

[0010] Typically, the guide assembly 6 includes eight discharge ducts 66 circumferentially distributed on the inner shell 64, eight fins 666, and at least eight sealing elements 7. This arrangement can be cumbersome for the turbine and can also complicate the production and assembly of the guide assembly (e.g., the use of specific tools—such as mounting pins, tools for positioning the discharge ducts relative to the shell section, etc.). This can disrupt and affect the operation of the flow guide assembly, and therefore often disrupt turbine operation.

[0011] In this context, it is of interest to propose a solution that enables the overcoming of at least one of the aforementioned disadvantages, particularly by optimizing and simplifying the production, assembly, and maintenance of flow guiding components in turbines, while simultaneously making them lightweight and compact. Summary of the Invention

[0012] This invention provides a simple, effective, and economical solution to the aforementioned shortcomings of the prior art.

[0013] Therefore, the present invention relates to a flow guiding assembly for a turbine, particularly for aircraft, the assembly comprising: - Two annular shells, an outer annular shell and an inner annular shell, extend about the same axis A, with one annular shell surrounding the other. These outer and inner shells define a first flow channel between them. Each shell is composed of multiple sections, each including an outer shell section and an inner shell section arranged circumferentially end-to-end around said axis A. - Discharge pipes, located inside the inner shell and leading to openings formed in the inner shell, define an internal passage for the discharge flow, which is configured to be injected into the first channel through these openings. According to the invention, each of the discharge pipes is integrally formed from a composite material and a section of an inner shell portion, the inner shell portion including an opening to which the discharge pipe leads.

[0014] The term "integrated" means that each exhaust pipe and associated inner shell section are a single piece and made of the same material (i.e., composite material).

[0015] This construction of the present invention simplifies and facilitates the design of the flow guiding component, thereby improving its performance in guiding flow (e.g., the flow in the first flow channel and / or the discharge flow) within the first flow channel. This ensures a longer service life for the guiding component.

[0016] The integral manufacturing process means that the surfaces of the discharge pipe and the inner shell section are continuous, uniform, and homogeneous within the composite material, enhancing the mechanical resistance and fire resistance of the guiding assembly. In this way, the use of existing bolt-type attachments or sealing elements to assemble the discharge pipe to the inner shell section to form the guiding assembly is eliminated. Therefore, the integral design optimizes the overall dimensions and mass of the guiding assembly. In this manner, the dimensions of the discharge pipe and the inner shell section can be designed to minimize the required mass while maintaining flow guidance and fire resistance functions.

[0017] In this way, the dimensions of the exhaust duct and inner shell section can be designed to minimize the required mass while maintaining flow guidance and fire protection functions. The use of composite materials also helps optimize the performance of the guiding components and the turbine as a whole by reducing the overall weight of the turbine (thereby reducing fuel consumption, which in turn leads to a reduction in harmful emissions (CO, CO2, NOx, etc.)). Therefore, this invention makes a significant contribution to limiting environmental impact.

[0018] Therefore, the advantages of this invention are that it provides very high reliability based on a design that is easy to manufacture and maintain, and has almost no impact on cost, weight and overall size.

[0019] The flow guiding component according to the invention may include one or more of the following features, used independently or in combination with each other: - The flow guiding assembly includes connecting arms for connecting the outer shell and the inner shell together. The connecting arms extend radially between and connect to the outer shell and the inner shell. The arms are tubular and can be passed through by auxiliary devices configured to pass through the first channel. - Each inner shell section extends axially between an upstream edge and a downstream edge, the upstream edge and the downstream edge extending at least partially radially inside the section, and the opening to which the discharge pipe leads is located between these upstream edges and the downstream edge. - At least one of the upstream edge and the downstream edge is L-shaped in axial cross section and includes a radial wall connected to a cylindrical wall that forms a free end of the inner shell section. - The flow bootstrap component also includes: - At least one washer, the at least one washer being disposed against the upstream edge of the inner shell section, and particularly against the cylindrical wall of the inner shell section, and / or - A heat exchanger is arranged against the downstream edge of the inner shell section, and particularly against the cylindrical wall of the inner shell section; - Each inner shell section includes a radially inwardly projecting rib at its downstream edge, for example at its radial wall, and the rib is located between the opening and the downstream edge; - Each inner shell region has an additional thickness at at least one of its upstream and downstream edges; - Each discharge duct is tubular and includes an elongated axis B along the internal passage of the discharge duct, the elongated axis being inclined relative to the section of the inner shell; - Each discharge pipe is connected to the shell via a bent or flexed connection, each of the bent or flexed connections having the same thickness as the minimum thickness of the discharge pipe and / or the minimum thickness of the section of the inner shell. - The flow guiding assembly also includes discharge fins fitted into or formed in each of the openings in the inner shell region; - The thickness of the connector is at least 1.65 mm; - Each discharge duct is inclined at an angle α relative to a section of the inner shell, such that the angle is, for example, between 20° and 70°; -The composite material has an organic or ceramic matrix; - Composite materials include fiber preforms embedded in resin, wherein the fiber preforms are woven or laminated in multiple layers; - The composite material includes fibers selected from carbon fiber, glass fiber, aramid fiber and polyamide fiber, or a mixture of at least two of these fibers; The present invention also relates to a turbine, particularly for use in aircraft, the turbine including a flow guiding component according to one of the features of the invention.

[0020] Specifically, between the low-pressure compressor and the high-pressure compressor of the turbine, each discharge pipe may include a first end and a second end opposite to the first radial end, the first end leading to a first flow passage for flow through the opening, and the second end leading to a second flow passage for another flow of the turbine.

[0021] A turbine can be an aircraft turbojet engine, a turboprop engine, or a turboshaft engine.

[0022] The present invention may also relate to a method for manufacturing a flow guiding component according to one of the above features.

[0023] The method may include the following steps: (a) Provide a female mold including a cavity, (b) Forming a fiber preform in the cavity of the mold, (c) Compacted fiber preforms, (d) The fiber preform is bonded (or densified) with a curing resin to integrally form each discharge duct with one of the inner shell sections. (e) Remove the part obtained in the step from the mold, and (f) Provide the outer casing. Attached Figure Description

[0024] The invention will be better understood through the following description, which is 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, as illustrated in the drawings: Figure 1 This is a schematic perspective view of a flow guiding assembly for a turbine according to the prior art; Figure 2 yes Figure 1 Axial cross-sectional view of the discharge pipe of the guide assembly and the associated inner shell section; Figure 3 This is a schematic half-view of the longitudinal section of a turbine according to the present invention; Figure 4 yes Figure 3 An enlarged schematic half-view of an axial cross-section of a portion of a guide assembly according to the invention in a turbine. Figure 5 yes Figure 3 or Figure 4 A schematic cross-sectional view of the discharge pipe of the guide component and the corresponding inner shell section; Figure 6 yes Figure 4 or Figure 5 A schematic diagram of the discharge pipe of the guide component and the corresponding inner shell section; Figure 7 yes Figure 5 or Figure 6 A half-view of the axial cross-section of the discharge pipe of the guide assembly and the integrated inner shell section; Figure 8 This is a block diagram of a method for manufacturing the flow guiding component of the present invention.

[0025] Elements that have the same function in different embodiments have the same reference numerals in the drawings. Detailed Implementation

[0026] By convention, in the following description, the terms "longitudinal" and "axial" refer to the orientation of a structural element extending along a longitudinal axis (such as the longitudinal axis of a turbine). The terms "radial" or "vertical" refer to the orientation of a structural element extending along a direction perpendicular to the longitudinal axis. The terms "inner" and "outer," as well as "internal" and "external," are used with reference to positioning relative to the longitudinal axis. Thus, a structural element extending along a longitudinal axis includes an inner surface facing the longitudinal axis and an outer surface opposite the inner surface of the structural element. Similarly, the terms "upstream" and "downstream" are defined relative to the direction of gas flow in the turbine.

[0027] Figure 1 and Figure 2 As described in the background section of this application, and representing a flow guiding component for a turbine according to the prior art.

[0028] This invention can be applied in a non-limiting manner to turbine 10, particularly to turbines for aircraft. Turbine 10 can be a turbojet engine, a turboprop engine, or a turboshaft engine.

[0029] The turbine 10 can extend along the longitudinal axis X.

[0030] Figure 3 and Figure 4 An example of a turbine 10, referred to as a dual-flow turbine, is shown. The turbine 10 may include a main duct C1 and a secondary duct C2 extending around the main duct C1. The main duct C1 and the secondary duct C2 are separated by an annular shell referred to as an inter-channel shell 4 (or intermediate shell).

[0031] Reference Figure 4 The inter-channel housing 4 may include two annular inner sections 42 and outer sections 44 extending around each other.

[0032] Turbine 10 typically includes a fan 1 and an engine 2 (or gas generator) from upstream to downstream along the direction of gas flow along the longitudinal axis X.

[0033] Figure 3 The fan 1 shown is ducted. To achieve this, the annular housing 5 (especially the annular housing of the nacelle) can extend around the fan 1 and rectifier 3 of the turbine 10.

[0034] Fan 1 draws in the initial airflow into turbine 10, which is divided into a main flow F1 (called the hot air flow) and a secondary flow F2 (called the cold air flow).

[0035] The rectifier 3 may include at least one annular row of blades (particularly stator or stationary blades) referred to as outlet guide vanes (OGVs). These OGV blades are used to rectify the secondary flow at the outlet of the upstream fan 1 to provide maximum thrust at the outlet of the turbine 10. The engine 2 typically includes a low-pressure compressor 2a, a high-pressure compressor 2b, a combustion chamber 2c, a high-pressure turbine 2e, a low-pressure turbine 2f, and possibly gas exhaust nozzles. Figure 3 (Not shown in the image).

[0036] The main stream F1 is compressed in the low-pressure compressor 2a and then in the high-pressure compressor 2b. This compressed air stream is then mixed with fuel and burned in the combustion chamber 2c. The gas formed by combustion passes through the high-pressure turbine 2d and the low-pressure turbine 2e. The gas can then be discharged through a nozzle whose cross-section allows the gas to be accelerated to generate thrust. The secondary stream F2 passes through the rectifier 3, which increases the velocity of the secondary stream F2 to generate thrust.

[0037] Reference Figures 3 to 7 The turbine 10 may include a flow guiding assembly 6, which includes: - Two annular shell sections (outer shell section 62 and inner shell section 64, respectively), and - Discharge pipe 66, the discharge pipe is located inside the inner shell 64 and leads to the opening 65 formed on the inner shell 64.

[0038] During the operation of turbine 10, the guide assembly 6 can be arranged between low-pressure compressor 2a and high-pressure compressor 2b, such as... Figure 3 and Figure 4 As shown. This enables the guide assembly 6 to draw in the main flow F1 from the main pipe C1 to generate the discharge flow F3 (also known as the tertiary flow), which is injected / discharged by the discharge pipe 66 into the secondary pipe C2 and mixed with the secondary flow F2.

[0039] The outer annular shell portion 62 and the inner annular shell portion 64 (hereinafter referred to as the outer shell portion 62 and the inner shell portion 64) extend around each other and around the same axis A. This axis A can roughly correspond to the longitudinal axis X of the turbine 10.

[0040] The outer shell portion 62 and the inner shell portion 64 define a first flow passage V2 between them for the flow F2. When the guide assembly 6 is installed in the turbine, the first flow passage V2 may correspond to at least a section of the secondary pipe C2, and the flow F2 may correspond to the secondary flow of the turbine 10.

[0041] The outer shell portion 62 and the inner shell portion 64 are composed of multiple sections, and each includes an outer shell portion 620 and an inner shell portion 640 arranged circumferentially around axis A end to end. As an example, the inner shell portion 64 may include four to ten inner shell portion sections 640.

[0042] The flow guiding assembly 6 may include a connecting arm 68 for connecting the outer shell portion 62 and the inner shell portion 64 together.

[0043] Connecting arms 68 (hereinafter referred to as arms 68) extend radially (relative to axis A) between the outer shell portion 62 and the inner shell portion 64, and are connected to these outer shell portions 62 and the inner shell portion 64. These arms 68 are tubular and can be passed through by auxiliary devices configured to pass through the first flow channel V2.

[0044] The discharge duct 66 defines an internal passage 660 for the discharge flow F3, which is configured to be injected into the first flow channel V2 through these openings 65.

[0045] like Figure 4 and Figure 7 As shown, each discharge pipe 66 can connect, on the one hand, through an opening 65 to a first flow passage V2 for flow F2, and on the other hand, to a second flow passage V1 for another flow F1 in the turbine 10. Specifically, the second flow passage V1 is located between the low-pressure compressor 2a and the high-pressure compressor 2b of the turbine 10. When the guide assembly 6 is installed in the turbine 10, this second flow passage V1 can correspond to at least a section of the main pipe C1, and the other flow F1 can correspond to the main flow F1.

[0046] A feature of the invention is that each of the discharge conduits 66 is integrally formed from a composite material with a section of an inner shell 640, and the inner shell section 640 includes an opening 65 to which the discharge conduit 66 opens. As mentioned above, this construction allows for a simplified design of the flow guiding assembly by reducing mass and overall size, while maintaining flow guiding, mechanical strength, and fire resistance. Figure 5 , Figure 6 and Figure 7 Examples of an integrally formed (or as a single component) exhaust pipe 66 and inner shell section 640 are shown above in a non-limiting manner.

[0047] Each inner shell section 640 may have a first minimum thickness E 640 The first minimum thickness E 640 Measured relative to a plane perpendicular to axis A. First minimum thickness E 640 It can be at least 1.65mm. This provides fire protection, or in other words, forms a fire barrier.

[0048] Each inner shell section 640 may extend axially between an upstream edge 642 and a downstream edge 644, the upstream and downstream edges extending at least partially radially inward (relative to axis A) of the inner shell section 640. An opening 65 to which the discharge conduit 66 leads may be located between these upstream edges 642 and downstream edges 644. Specifically, the upstream edge 642 allows the outer shell 5 to be positioned on the inner shell section 640 (and thus on the flow guiding assembly 6). The downstream edge 644 allows the heat exchanger 9 to be positioned on the inner shell section 640.

[0049] At least one of the upstream edge 642 and the downstream edge 644 may be L-shaped in axial cross-section and may include radial walls 642a and 644a connected to cylindrical walls 642b and 644b, the cylindrical walls forming the free ends of the inner shell portion 640.

[0050] The upstream edge 642 may have a second thickness E, measured in a plane perpendicular to axis A. 642 The second thickness E 642 It can be greater than or equal to the first minimum thickness E 640 .

[0051] The downstream edge 644 may have a third thickness E measured in a plane perpendicular to axis A. 644 The third thickness E 644 It can be greater than or equal to the first minimum thickness E 640 Third thickness E 644 It can be equal to the second thickness E 642 .

[0052] exist Figure 7 In the example shown, the inner shell region 640 has an additional thickness E at at least one of the upstream edge 642 and the downstream edge 644. 642 E 644 In other words, the second thickness E 642 and the third thickness E 644 One of them can be greater than the first minimum thickness E 640 The additional thickness E 642 E 644 This allows rigid support areas to be formed at the upstream edge 642 and the downstream edge 644, so as to position and support the gasket 8 and the heat exchanger 9 respectively.

[0053] Bootstrap component 6 may also include: - At least one washer 8, at least one washer arranged against the upstream edge 642, particularly against the cylindrical wall 642b, and / or - Heat exchanger 9, the heat exchanger is arranged against the downstream edge 644, and specifically against the cylindrical wall 644b.

[0054] Gasket 8 provides a fluid and fire-resistant seal between guide assembly 6 and housing 5 (or nacelle), housing 5 which can be mounted and supported on upstream edge 642.

[0055] Each inner shell section 640 may include a radially inward (relative to axis A) projecting rib 646. This rib 646 is located at the downstream edge 644, and for example, at the radial wall 644a. Specifically, in Figure 7 In the example shown, rib 646 is located between opening 65 and downstream edge 644. Rib 646 is configured to provide mechanical rigidity to inner shell section 640 and improve the installation space between inner shell section 640 and heat exchanger 9.

[0056] Each inner shell section 640 may include a shoulder 648 projecting radially inward (relative to axis A). This shoulder 648 is located at the upstream edge 642, for example, at the radial wall 642a. Specifically, in Figure 7 In the example shown, shoulder 648 is located between opening 65 and upstream edge 642. Shoulder 648 forms a second thickness E at upstream edge 642. 642 Additional thickness.

[0057] Each discharge conduit 66 may be tubular. Each discharge conduit 66 may include a first end 662 and a second end 664 opposite to the first end 662. The first end 662 leads to a first flow channel V2 for flow F2. The second end 664 may lead to a second channel V1 for another flow F1.

[0058] like Figure 4 and Figure 7 As shown, the first end 662 can be connected to the first channel V2 through the opening 65 (referred to as the discharge or outlet orifice for the discharge flow F3), and the second end 664 can be connected to the second channel V1 through the hole 67 (referred to as the inlet hole for the discharge flow F3), the hole 67 being specifically formed on the downstream neck 48 of the inter-channel housing 4.

[0059] exist Figure 4In the example shown, the interchannel housing 4 may include an intermediate space 40 configured to receive another flow F1, specifically from the low-pressure compressor 2a. This intermediate space 40 is defined from upstream to downstream by an upstream neck 46 and a downstream neck 48 of the interchannel housing 4. These upstream necks 46 and downstream necks 48 may connect an inner annular section 42 and an outer annular section 44 to each other, thereby defining the intermediate space 40. The inner annular section 42 may include an orifice 47 configured to be selectively opened or closed by a tongue 470 according to the flight stage of the turbine 10. Preferably, the tongue 470 is movable between a closed position and an open position, in which the tongue 470 closes the orifice 47 and in which the tongue 470 releases the orifice 47 to allow the other flow F1 to enter the intermediate space 40. The other flow F1 entering the intermediate space 40 can generate and form an exhaust flow F3, which enters the exhaust pipe 66 through the hole 67 to reach the first channel V1 and mixes with the flow F2 through the opening 65.

[0060] The discharge duct 66 may include an elongation axis B along its internal passage 660, which may be inclined relative to a portion of the corresponding inner housing 640. For example, the discharge duct 66 may be inclined at an angle α between 20° and 70° relative to a plane passing through the inner housing portion 640.

[0061] Each discharge pipe 66 can have a fourth minimum thickness E 66 The fourth minimum thickness is specifically measured along a plane inclined relative to axis A. The first minimum thickness E 6540 and the fourth minimum thickness E 66 They can be the same.

[0062] Each discharge pipe 66 can be connected to the inner shell section 640 via a curved or bent connector 665. These connectors 665 may each have a fifth thickness E. 655 This fifth thickness is specifically measured along a plane inclined relative to axis A. Fifth thickness E 655 The first minimum thickness E of the section of the inner shell 640 can be equal to the minimum thickness of the inner shell section 640. 640 and / or the fourth minimum thickness E of the discharge pipe 66 66 For example, the fifth thickness E 665 It can be at least 1.65mm. This provides fire protection, or in other words, forms a fire barrier.

[0063] The composite material forming the inner shell section 640 and the discharge duct 66 may include a fiber preform embedded in the resin. The fiber preform may be woven (e.g., three-dimensionally woven) or laminated in multiple layers.

[0064] Composite materials (or fiber preforms) may include fibers selected from carbon fibers, glass fibers, aramid fibers and polyamide fibers, or mixtures of at least two of these fibers.

[0065] The resin can be thermosetting or thermoplastic. For example, the resin can be based on epoxy resin, polyoxide, polyimide, polybismaleimide, polyurethane, polyester, or vinyl ester.

[0066] The guide assembly 6 may also include exhaust fins 666 fitted or formed in each of the openings 65 in the inner shell section 640. As an example, each opening 65 may include between two and six exhaust fins 666. These exhaust fins 666 may be made of composite materials, particularly by thermoforming (such as deep drawing). These exhaust fins 666 can therefore be directly mounted to the inner shell section 640 and / or the exhaust duct 66, for example, by riveting.

[0067] This application will now describe an example of a manufacturing method for producing the flow guiding component 6 as described above, the successive steps of which are as follows: Figure 8 As shown in the figure. The method may include the following steps: (a) Provide a female mold including a cavity, (b) Forming a fiber preform in the cavity of the mold, (c) Compacted fiber preforms, (d) The fiber preform is bonded (or densified) with a curing resin to integrally form each discharge pipe 66 with one of the inner shell sections 640. (e) Remove the part obtained in step (d) from the mold, and (f) Provide housing 64.

[0068] In step (a), the cavity may be a hollow section in which the fiber preform is formed. This hollow section may have a shape similar to that of one of the discharge pipes in discharge pipe 66 (one of the discharge pipes connects to one of the inner shell sections in inner shell section 640) (e.g., Figure 5 or Figure 7 (The shape shown) is a complementary shape.

[0069] In step (b), the fiber preform can be configured to form each discharge duct 66 integrally with one of the inner shell sections 640.

[0070] Fiber preforms can be woven (e.g., three-dimensional weaving) or layered into multiple layers.

[0071] For example, folds in a composite material can be deposited in the cavity of a mold by lay-up (or stacking folds) to form a fiber preform.

[0072] The fibers constituting the fiber preform may be selected from carbon fiber, glass fiber, aramid fiber and polyamide fiber, or a mixture of at least two of these fibers.

[0073] In step (c), the components (i.e., the fiber preform and mold obtained in step (b)) can be arranged in a vacuum bag (particularly in an autoclave) for compaction. By compacting the fiber preform, a good volume ratio of fibers in the fiber preform is ensured during polymerization.

[0074] In step (d), the fiber preform can be solidified by heating in an autoclave to polymerize the resin.

[0075] The resin can be thermosetting or thermoplastic. For example, the resin can be based on epoxy resin, polyoxide, polyimide, polybismaleimide, polyurethane, polyester, or vinyl ester.

[0076] Steps (a) through (d) can be repeated multiple times to obtain the required number of discharge pipes 66 and inner shell sections 640 forming the guide assembly 6.

[0077] In step (e), the part obtained in step (d) can be demolded after cooling.

[0078] In an alternative embodiment of the method, the method may include an additional step between step (e) and step (f), the additional step including adding an upstream edge 642 and a downstream edge 644 to the inner shell region 640 of the component obtained in step (e). Adding the upstream edge 642 and the downstream edge 644 may be achieved by machining, particularly when these upstream edges 642 and the downstream edge 644 are made of a metallic material.

[0079] In step (f), a connecting arm 68 may also be provided to assemble the connecting arm 68 between the outer shell portion 64 and the inner shell portion 62. The outer shell portion 62 may be made of a composite material. The connecting arm 68 may be made of a metallic material (such as titanium), particularly by casting.

[0080] In the preceding description, specific reference was made to Figures 3 to 7 The invention is described in the context of an application to a dual-flow turbine 10 for an aircraft. Generally, the invention can be applied to other types of turbines that include such a flow guide assembly 6.

[0081] The flow guiding component according to the present invention provides several advantages, in particular: -Simplify the design and integration of the exhaust pipe and inner shell section to reduce costs and improve the manufacturing of the guide assembly. - Simplify component and assembly time, especially avoiding the use of special tools (such as mounting pins, positioning tools, etc.). - Limit the number of connecting parts (such as bolts, washers, etc.). - Ensure optimal connection between the exhaust pipe and the inner shell. -Optimize the lifespan of the bootloader components, and - Easily adaptable to existing turbine gas generators.

[0082] In summary, the proposed solution is simple, efficient, and economical to manufacture and assemble in turbines, while ensuring optimal and uniform flow guidance within the turbine.

Claims

1. A flow guiding assembly (6) for a turbine (10), particularly for aircraft, the assembly (6) comprising: - Two annular shells, namely an outer annular shell (62) and an inner annular shell (64), extend around the same axis (A) with one annular shell surrounding the other. These outer and inner shells (62, 64) define a first flow channel (V2) for the flow (F2) between them. The outer and inner shells (62, 64) are composed of multiple sections and each includes an outer shell section and an inner shell section (620, 640) arranged circumferentially end-to-end around the axis (A). - Discharge pipes (66), which are located inside the inner shell (62) and lead to openings (65) formed on the inner shell (62), define an internal passage (660) for a discharge stream (F3) configured to be injected into the first channel (V2) through these openings (65). The characteristic feature is that each of the discharge pipes (66) is integrally formed of a composite material with a section of the inner shell (640), the inner shell section (640) including an opening (65) to which the discharge pipe (66) leads.

2. The flow guiding component according to claim 1, characterized in that, Each inner shell section (640) extends axially between an upstream edge and a downstream edge (642, 644), the upstream edge and the downstream edge extending at least partially radially inside the section (640), and the opening (65) to which the discharge pipe (66) leads is located between these upstream edges and downstream edges (642, 644).

3. The flow guiding component according to claim 2, characterized in that, At least one of the upstream and downstream edges (642, 644) is L-shaped in axial cross-section and includes a radial wall (642a, 644a) connected to a cylindrical wall (642b, 644b) that forms the free end of the inner shell section (640).

4. The flow guiding assembly according to claim 2 or 3, characterized in that, The flow guiding component also includes: - At least one washer (8), said at least one washer being disposed against the upstream edge (642) of the inner shell section, and particularly against the cylindrical wall (642b) of the inner shell section (640), and / or - A heat exchanger (9) is arranged against the downstream edge (644) of the inner shell section (640), and particularly against the cylindrical wall (644b) of the inner shell section (640).

5. The flow guiding assembly according to any one of claims 2 to 4, characterized in that, Each inner shell section (640) includes a radially inwardly projecting rib (646) at its downstream edge (644), for example at its radial wall (644a), and the rib is located between the opening (65) and the downstream edge (644).

6. The flow guiding assembly according to any one of claims 2 to 5, characterized in that, Each inner shell section (640) has an additional thickness (E) at at least one of the upstream and downstream edges (642, 644). 642 E 644 ).

7. The flow guiding component according to any one of the preceding claims, characterized in that, Each discharge duct (66) is tubular and includes an elongation axis (B) along an internal passage (660) of the discharge duct, the elongation axis being inclined relative to a portion of the inner shell (640).

8. The flow guiding component according to any one of the preceding claims, characterized in that, Each discharge pipe (66) is connected to the housing via a bent or flexed connector (665), each of the bent or flexed connectors having a minimum thickness (E) of the discharge pipe (66). 66 ) and / or the minimum thickness (E) of the portion of the inner shell (640) 640 The same thickness (E) 665 ).

9. The flow guiding component according to any one of the preceding claims, characterized in that, The flow guiding assembly also includes discharge fins (666) assembled or formed in each of the openings (65) in the inner shell region (640).

10. The flow guiding component according to any one of the preceding claims, characterized in that, The component (6) includes connecting arms (68) for connecting the outer shell portion (62) and the inner shell portion (64) together. The connecting arms extend radially between and connect the outer shell portion (62) and the inner shell portion (64). The arms (68) are tubular and can be passed through by an auxiliary device configured to pass through the first channel (V2).

11. The flow guiding component according to any one of the preceding claims, characterized in that, The composite material has an organic or ceramic matrix.

12. The flow guiding component according to any one of the preceding claims, characterized in that, The composite material includes fibers selected from carbon fiber, glass fiber, aramid fiber and polyamide fiber, or a mixture of at least two of these fibers.

13. The flow guiding component according to any one of claims, characterized in that, Each discharge duct (66) is inclined at an angle (α) relative to a portion of the inner shell (640), the angle being, for example, between 20° and 70°.

14. A turbine (10), particularly for an aircraft, said turbine comprising a flow guiding assembly (6) according to any one of the preceding claims.

15. A method for manufacturing a flow guiding assembly (6) according to any one of claims 1 to 13, characterized in that, The method includes the following steps: (a) Provide a female mold including a cavity, (b) A fiber preform is formed in the cavity of the mold. (c) Compact the fiber preform. (d) The fiber preform is bonded with a curing resin to integrally form each discharge pipe (66) with one of the inner shell sections (640). (e) Remove the part obtained in step (d) from the mold, and (f) Provide the outer casing (64).

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