Secondary flow guide vanes of a turbine and turbines equipped with secondary flow guide vanes

Abstract

The present invention relates to a secondary flow guide vane (1) for a turbine, comprising a skin (2, 3) having ends (21, 31) defining an opening (5) and a cavity (4) between the ends, the skin branching off from each other in a direction (Y). A filler material (41) is located in the cavity (4) at a distance from the opening (5). A reinforcement (6) having a higher density than the material (41) includes a first reinforcement portion (61) positioned against the material (41) in the cavity (4) and a second reinforcement portion (62) for closing the opening (5) between the portions (21, 31) to form a single piece.

Description

Technical Field

[0001] The present invention relates to a secondary flow guide vane of a turbine, and a turbine provided with the secondary flow guide vane.

[0002] The field of this invention relates to aircraft turbines, particularly turbojet engines or turboprop engines. Background Technology

[0003] An increase in the bypass ratio (the ratio of the main flow velocity to the secondary flow velocity) is a preferred solution for engine manufacturers to improve the performance of aircraft turbine engines and reduce their specific fuel consumption rate. This manifests as an increase in the diameter of the impeller blades (particularly the first inlet blade (fan or propeller blade) and the associated guide blades downstream of that first inlet blade) for a given engine thrust. For structures without rectifiers, this increase in size is even greater.

[0004] However, these increases in size do have the disadvantage of increasing the mass of the guide vanes, which has an adverse effect on engine performance.

[0005] A secondary flow guide vane for a turbine with a rectifier is known from document FR-A-3 063 514. This secondary flow guide vane includes a vane body made of a composite material composed of three-dimensionally woven fiber reinforcements densified with a matrix. The fiber reinforcement has a first portion extending longitudinally from a second end portion, and the second portion includes two segments separated from each other from a junction between the first and second portions to a free end of the fiber reinforcement. The vane also includes an insert with a π-shaped cross-section, comprising a platform portion extending perpendicularly to the longitudinal direction and two longitudinal flanges separated from each other by a space. The platform portion includes a receiving portion defined by a bottom wall and an edge, the bottom wall including an opening communicating with the space between the two flanges. The first portion of the fiber reinforcement of the vane body is held between the two flanges of the insert, and a segment of the second portion of the fiber reinforcement is folded against the bottom wall of the receiving portion of the insert on either side of the first portion. The vane also includes an insert located between the segments of the second portion of the fiber reinforcement, at the junction between the segments. The turbine is rectified by the fact that guide vanes extend radially between an internal platform and two external platforms, the guide vanes being attached to the inner casing of the turbojet engine via the internal platform, and the two external platforms enabling the guide vanes to be attached to the outer casing of the turbojet engine.

[0006] Guide vanes, as known from document FR-A-3 063 514, can indeed limit the increase in mass and can be manufactured using solid composite materials instead of metallic materials (e.g., for hollow titanium or aluminum vanes).

[0007] However, considering the larger size of the guide vanes in turbine structures without rectifiers, it is necessary to improve this mass reduction.

[0008] However, in a structure without a rectifier, the fact that the guide vane is attached to the turbine housing via a single radial end (vane root) has the result of all forces passing through the root region, leading to a high level of stress in the composite part of the guide vane. Summary of the Invention

[0009] The object of the present invention is to obtain a secondary flow guide vane for a turbine, and a turbine equipped with the secondary flow guide vane. The present invention solves the above problems by enabling the reduction of stress while limiting the increase in mass.

[0010] Therefore, the first subject of the present invention is a secondary flow guide vane of a turbine, the secondary flow guide vane comprising a first outer skin and a second outer skin made of a first composite material and connected to each other.

[0011] The first outer skin includes a first end portion, and the second outer skin includes a second end portion located away from the first end portion.

[0012] The first end and the second end are located on the same mounting side of the impeller, an opening is defined between the first end and the second end, and the first end and the second end branch off from each other along the thickness direction.

[0013] Its features are,

[0014] The blades also include:

[0015] A cavity, positioned along the thickness direction between a first outer skin and a second outer skin, and the cavity leading to an opening.

[0016] A filling material having a first density, located within the cavity and at a distance from the opening.

[0017] A reinforcing member having a second density greater than a first density, and comprising a first reinforcing portion and a second reinforcing portion, the first reinforcing portion being located in a cavity and abutting against a filler material, and the second reinforcing portion closing an opening between a first end and a second end.

[0018] The first reinforcing part and the second reinforcing part are integrated into one piece.

[0019] The proposed solution enables increased mechanical strength in the root region (mounted end) of the guide vane in turbine structures without rectifiers, while limiting mass gain. This invention allows for reinforcement of the guide vane root, reducing stress and limiting its impact on mass.

[0020] The benefits of this solution are as follows:

[0021] - The stress at the connection radius is reduced in composite skin;

[0022] - Reduced skin displacement in the root region and at the tip of the blades;

[0023] - The frequency of the first resonance mode increases.

[0024] Known blades with a cavity between the two skins also have the following problems: high stress is observed in the composite skin at the blade root; additionally, the skin displacement in this region is too large; this limits the blade's lifespan, prevents proper frequency localization (especially the first resonant mode), and introduces a risk of composite skin buckling. The present invention, by eliminating the significantly mass-bearing spar inserted into the cavity, enables the resolution of these problems caused by known blades with a cavity between the two skins.

[0025] This invention enables a significant reduction in stress at the root of the guide vane at the connection radius.

[0026] According to an embodiment of the present invention, the first reinforcing portion includes a contact surface for contacting the filling material in the cavity.

[0027] The first and second outer skins have leading and trailing edges, which are spaced apart from each other along the width direction of the blade, the width direction being transverse to the thickness direction.

[0028] The mounting side of the impeller is positioned below the airflow line along the height direction of the impeller, which is transverse to the thickness and width directions.

[0029] The airflow lines form the boundary of the turbine's secondary flow on the first and second outer skins.

[0030] The first upstream portion of the contact surface is located on the leading edge side and positioned along the height direction above the second upstream portion of the airflow located on the leading edge side.

[0031] According to an embodiment of the invention, a first downstream portion of the contact surface is located on the trailing edge side and positioned along the height direction below a second downstream portion of the airflow located on the trailing edge side.

[0032] According to an embodiment of the invention, the first upstream portion of the contact surface is positioned along the height direction at a height greater than or equal to 50 mm and less than or equal to 100 mm above the opening.

[0033] According to an embodiment of the present invention, the first upstream portion of the contact surface is positioned along the height direction at a height greater than or equal to 50 mm and less than or equal to 100 mm above the second upstream portion of the airflow.

[0034] According to an embodiment of the present invention, a connection is formed between a first end and a second end, the plate is attached below and abuts against the first end and the second end, and the plate is positioned against an opening and a second reinforcing portion.

[0035] According to an embodiment of the present invention, the second reinforcing portion extends below the first end, below the second end, and below the opening to form a base having a non-zero height.

[0036] According to an embodiment of the invention, the plate is attached below and abuts against the base.

[0037] According to an embodiment of the present invention, the plate is made of a composite material.

[0038] According to an embodiment of the present invention, the reinforcement is made of a first composite material.

[0039] According to an embodiment of the invention, the reinforcement is made of a second nonwoven composite material having fibers embedded in a matrix.

[0040] According to an embodiment of the invention, the reinforcement is made of at least one metal.

[0041] According to an embodiment of the invention, the reinforcement has a Young's modulus greater than or equal to 5 GPa. According to an embodiment of the invention, the reinforcement has a Young's modulus, for example, from about 10 GPa to 20 GPa.

[0042] According to an embodiment of the present invention, the filler material includes a protruding portion at the contact surface, the protruding portion being fitted into the hollow portion of the first reinforcing portion.

[0043] The second subject of the present invention is an aircraft turbine without a rectifier, comprising:

[0044] case,

[0045] The fan has a fan hub and peripheral fan blades fixed to the fan hub.

[0046] The fan hub has a downstream hub portion that is surrounded by the inner surface of the upstream portion of the housing and protrudes from the upstream portion of the housing.

[0047] The fan hub is rotatably mounted relative to the upstream portion of the housing about a rotation axis pointing from upstream to downstream.

[0048] The turbine also includes secondary flow guide vanes as described above, which are positioned adjacent to the outer wall of the upstream portion of the housing via their mounting side and positioned downstream relative to the peripheral fan blades. According to embodiments of the invention, the guide vanes may, for example, have a variable setting, similar to the peripheral fan blades. Attached Figure Description

[0049] The invention will be better understood by reading the following description, which is given by way of non-limiting example only and with reference to the accompanying drawings.

[0050] [ Figure 1 A schematic radial-axial cross-sectional view of the secondary flow guide vane of a turbine according to an embodiment of the present invention is shown.

[0051] [ Figure 2 [This shows the path along] Figure 1 A schematic partial view of the radial cross-section of the secondary flow guide vane of a turbine according to an embodiment of the present invention, with section line A.

[0052] [ Figure 3 A schematic partial view of the radial cross-section of a secondary flow guide vane of a turbine according to another embodiment of the present invention is shown.

[0053] [ Figure 4 A schematic partial view of the radial cross-section of a secondary flow guide vane of a turbine according to another embodiment of the present invention is shown.

[0054] [ Figure 5 A schematic partial view of the radial cross-section of a secondary flow guide vane of a turbine according to another embodiment of the present invention is shown.

[0055] [ Figure 6 It shows Figure 2 A schematic partial radial cross-sectional perspective view of the secondary flow guide vanes of a turbine according to an embodiment of the present invention.

[0056] [ Figure 7 It shows Figure 6 A schematic diagram of the axial and radial cross sections of the secondary flow guide vanes of a turbine according to an embodiment of the present invention.

[0057] [ Figure 8 It shows Figures 1 to 7 A top axial view of the secondary flow guide vanes of a turbine according to an embodiment of the present invention.

[0058] [ Figure 9A schematic partial perspective view is shown, illustrating the effect applied in grayscale. Figure 2 The stress value on the mounting side of the secondary flow guide vane of the turbine according to an embodiment of the present invention.

[0059] [ Figure 10 The diagram shows a radial axial cross-section schematic of a comparative example of a secondary flow guide vane of a turbine not equipped with the device according to the invention.

[0060] [ Figure 11 A schematic partial perspective view is shown, in grayscale, illustrating the application of [something] according to [the context]. Figure 10 The comparison example shows the stress values ​​on the mounting side of the secondary flow guide vane of the turbine.

[0061] [ Figure 12 A schematic perspective view of an example turbine without a rectifier is shown, which includes guide vanes according to the invention. Detailed Implementation

[0062] The following is for reference. Figure 12 A more detailed description of an example of turbine 100 is provided, on which one or more secondary flow guide vanes 1 according to the invention may be used.

[0063] As is known, Figure 12 The turbine 100 shown is intended to be mounted on an aircraft (not shown) to propel the aircraft through the air, such as an airplane or a helicopter.

[0064] Gas turbine engines or turbine 100 components are types that do not have rectifiers.

[0065] The gas turbine engine or turbine 100 assembly extends about an axis AX or axial direction AX oriented from upstream to downstream. Therefore, the terms "upstream" and "downstream," "front" and "rear," and "left" and "right" are used along the general direction of the gas flowing through the turbine along the axis AX. The direction from the inside to the outside is the radial direction DR (or the height direction DR as described below, or the spanwise direction DR as described below) starting from the axis AX.

[0066] The turbine 100 includes a housing 101 that supports a fan 200 upstream of the housing 101. The fan has a fan hub 201 and peripheral fan blades 202, the peripheral fan blades being fixed to the fan hub 201 and distributed on the fan hub about a rotation axis AX upstream of the housing 101. The fan hub 201 has a downstream hub portion 203 that is surrounded by the inner surface 102 of the upstream portion 103 of the housing 101 and protrudes beyond the upstream portion 103 of the housing 101. The fan hub 201 is rotatable about itself about the rotation axis AX relative to the upstream portion 103 of the housing 101. Downstream of the fan hub 201 and within the housing 101, the turbine includes an engine assembly 300 that enables the fan hub 201, and thus the peripheral fan blades 202, to rotate about the rotation axis AX.

[0067] The turbine 100 also includes a secondary flow guide vane 1, the mounting side 11 of which is removably mounted or attached to the outer wall 104 of the upstream portion 103 of the housing 101. The mounting side 11 is adjacent to the outer wall 104 of the upstream portion 103 of the housing 101. The secondary flow guide vane 1 is located downstream of the peripheral fan blades 202. Therefore, when the peripheral fan blades 202 are configured to rotate about axis AX, the guide vane 1 is positioned in the secondary airflow FS1, which is generated downstream of the peripheral fan blades 202 around the outer wall 104 of the housing 101.

[0068] The aircraft turbine 100 does not have a rectifier, which means that the guide vane 1 is attached or mounted only on the outer wall 104 of the upstream portion 103 of the housing 101 via its mounting side 11 (or blade root). The blade tip 12, located at the end of the vane 1 further away from its mounting side 11 in the radial direction DR, is exposed to the secondary airflow and is not mounted or attached to the housing. There is no housing or nacelle surrounding the guide vane 1 and the housing 101.

[0069] The engine assembly 300 includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine in the housing 101 along the gas flow direction from upstream to downstream. These components define the main gas flow through the housing 101 from the air inlet 105, which is located between the upstream portion 103 of the housing 101 and the fan hub 201 and downstream of the peripheral fan blades 202.

[0070] The low-pressure compressor and the high-pressure compressor may each include one or more stages, each stage consisting of a set of fixed blades (or stator blades) and a set of rotating blades (or rotor blades). The fixed blades of the low-pressure compressor are attached to housing 101. The rotating blades of the low-pressure compressor are attached to a first rotary drive shaft extending along axis AX. The fixed blades of the high-pressure compressor are attached to housing 101. The rotating blades of the high-pressure compressor are attached to a second rotary drive shaft extending along axis AX. The high-pressure turbine and the low-pressure turbine may each include one or more stages, each stage consisting of a set of fixed blades (or stator blades) and a set of rotating blades (or rotor blades). The fixed blades of the high-pressure turbine are attached to housing 101. The rotating blades of the high-pressure turbine are attached to a second rotary drive shaft. The fixed blades of the low-pressure turbine are attached to housing 101. The rotating blades of the low-pressure turbine are attached to the first rotary drive shaft.

[0071] The rotating blades of the low-pressure turbine drive the rotating blades of the low-pressure compressor to rotate around axis AX under the thrust of the gas from the combustion chamber. The rotating blades of the high-pressure turbine drive the rotating blades of the high-pressure compressor to rotate around axis AX under the thrust of the gas from the combustion chamber.

[0072] During operation, airflow passes through the rotary fan 200, and the first portion of the airflow, FP1 (mainstream FP1), is guided through the low-pressure compressor and the high-pressure compressor, whereby the mainstream FP1 is compressed and delivered to the combustion chamber. The hot combustion products from the combustion chamber drive the high-pressure turbine and the low-pressure turbine, thus generating thrust for the turbine 100, and are discharged through nozzles 108 located at the downstream end of the downstream portion 107 of the housing 101, downstream of the upstream portion 103 of the housing 101. Secondary airflow FS1 is discharged from the rotary fan 200 from upstream to downstream around the housing 101. The guide vanes 1 are shaped to concentrate the secondary airflow FS1 at the outer surface 106 of the downstream portion 107 of the housing 101, downstream of the outer wall 104 of the upstream portion 103 of the housing 101. An external attachment arm or external attachment device connects the housing 101 to the aircraft.

[0073] The following reference Figures 1 to 9 The secondary flow guide vane 1 of the turbine according to the present invention is described.

[0074] The secondary flow guide vane 1 of the turbine includes a first outer skin 2 and a second outer skin 3 made of a first composite material and connected to each other. As described above, when the turbine is running, these skins 2 and 3 form the outer surface of the guide vane 1 located in the secondary airflow FS1 during turbine operation. The first outer skin 2 and the second outer skin 3 support the leading edge 8 of the guide vane 1, the edge of which is located upstream along the width direction of the vane 1 formed by the axial direction AX. The first outer skin 2 and the second outer skin 3 support the trailing edge 9 of the guide vane 1, the edge of which is located downstream along the width direction AX (or chord direction AX) of the vane 1.

[0075] In the region of the blade root 11 or mounting side 11 of the guide vane 1, the first outer skin 2 includes a first end 21, and the second outer skin 3 includes a second end 31 located away from the first end 21 along the thickness direction Y. The first end 21 and the second end 31 together define the opening 5 and move away from each other along the thickness direction Y, as... Figures 2 to 6 As illustrated by example. The thickness direction Y is perpendicular to the width direction AX and the height direction DR. The height direction DR is perpendicular to the width direction AX. The first outer skin 2 and the second outer skin 3 together define the cavity 4 along the thickness direction Y. The cavity 4 is positioned above the opening 5 and above the first end 21 and the second end 31 along the height direction DR, and opens to the opening 5. The filling material 41 (or filling portion 41) abuts against the skins 2 and 3 in the cavity 4 and is located at a distance from the opening 5.

[0076] The first portion 61 of the reinforcement 6 is positioned against the filling material 41 in the cavity 4. The first reinforcement portion 61 includes a contact surface 610 for contacting the filling material 41 in the cavity 4. The first portion 61 of the reinforcement can be positioned against the first skin 2 and / or the second skin 3. The second portion 62 of the reinforcement 6 blocks the opening 5 between the first end 21 and the second end 31. The reinforcement 6 has a second density greater than the first density of the filling material 41. The first reinforcement portion 61 and the second reinforcement portion 62 are manufactured as a single integral component.

[0077] The function of the reinforcement 6 is both to block the opening 5 between the first end 21 of the skin 2 and the second end 31 of the skin 3 in the blade root 11, and to provide greater bending stiffness than the filling material 41 in the blade root 11, since the stress is greatest in this region.

[0078] therefore, Figure 9 It shows that the stress applied to the root 11 of the guide vane 1 during operation (including the maximum value FMAX of these stresses located at the connection radius in the root 11 of the vane) is less than that applied during operation. Figure 10 The stress in the root 11' of the comparative example of the guide vane 1' (including) Figure 11The maximum values ​​of these stresses shown are FMAX', and this comparative example excludes reinforcement 6 and includes only skins 2' and 3' and the filling material 41' in cavity 4. Therefore, compared to adding a spar or increasing the thickness of the composite skin, this invention represents a better trade-off between stiffness and mass, thereby improving mechanical strength. Figure 9 and Figure 11 In the figure, stress is shown in grayscale on the same scale ECH with increased grayscale levels.

[0079] Compared to the solutions described in document FR-A-3 063 514, which consist only of foam or are equipped with inserts, the present invention enables reinforcement of the root region of the OGV, resulting in reduced stress in the composite skin. The increased stiffness also allows for limiting the displacement of the tip 12 of the guide vane 1. Another benefit of the invention is the low mass impact, particularly compared to spar solutions.

[0080] According to an embodiment of the invention, the mounting side 11 of the blade, the first end 21 of the skin 2, and the second end 31 of the skin 3 are positioned below the airflow line 7 of the blade 1 along the height direction DR. The airflow line 7 forms the boundary of the turbine secondary flow path FS1 on the first outer skin 2 and the second outer skin 3, and the airflow line 7 represents the point of the skins 2 and 3 closest to the central axis of rotation AX of the turbine 100 and in the secondary flow FS1. The contact surface 610 has a first upstream portion 611 and a second downstream portion 612, the second downstream portion 612 being positioned behind the first upstream portion 611 along the width direction AX. The airflow line 7 includes a second upstream portion 71 and a second downstream portion 72, the second downstream portion 72 being positioned behind the second upstream portion 71 along the width direction AX. The first upstream portion 611 of the contact surface 610 is located on the leading edge 8 side and is positioned above the second upstream portion 71 of the airflow line 7 located on the leading edge 8 side along the height direction DR. This allows for an increase in the stiffness of the guide blade 1 because stress is confined in this region.

[0081] According to an embodiment of the invention, the first downstream portion 611 of the contact surface 610 is located on the trailing edge 9 side and is positioned along the height direction DR below the second downstream portion 72 of the airflow 7 located on the trailing edge 9 side. This also makes it possible to improve the quality of the guide vane 1.

[0082] According to embodiments of the present invention, such as by Figure 2 As shown in the example, the first upstream portion 611 of the contact surface 610 is positioned along the height direction DR at a height H greater than or equal to 50 mm and less than or equal to 100 mm above the opening 5.

[0083] According to an embodiment of the present invention, the first upstream portion 611 of the contact surface 610 is positioned along the height direction DR at a height greater than or equal to 50 mm and less than or equal to 100 mm above the second upstream portion 71 of the air streamline 7.

[0084] According to an embodiment of the present invention, the reinforcement 6 is made of the same first composite material as the first outer skin 2 and the second outer skin 3.

[0085] The first composite material of skins 2 and 3, and, where applicable, the first composite material of reinforcement 6, may comprise a set of fibers impregnated with a matrix. According to a non-limiting embodiment, skin 2 may be integral and made as a single piece. According to a non-limiting embodiment, skin 3 may be integral and made as a single piece, separate from skin 2. According to a non-limiting embodiment, reinforcement 6 may be integral and made as a single piece, separate from skins 2 and 3. The fibers may comprise at least one of the following materials: carbon, glass, aramid, polypropylene, and / or ceramic. The fiber assembly may comprise a woven (two-dimensional or three-dimensional), braided, knitted, or laminated fiber arrangement. The matrix typically comprises an organic material (thermosetting, thermoplastic, or elastomer) or a carbon matrix. For example, the matrix comprises a plastic, typically a polymer such as epoxy, bismaleimide, or polyimide. The fiber assembly may be manufactured by three-dimensional weaving on a jacquard loom. During weaving, warp bundles (or warp threads) are arranged in several layers. The injection of the plastic may be performed using an injection technique of the RTM or VARRTM type. The injected plastic is, for example, a thermosetting liquid composition containing an organic precursor of a matrix material. The organic precursor is typically in the form of a polymer (such as a resin), diluted in a solvent where applicable. The plastic is heated in a manner known per se to induce polymerization, for example, through crosslinking. The fibers of reinforcement 6 may be made of the same or different materials as the fibers of skins 3 and 2. When manufactured in the manner described above, skins 2 and 3 can be formed as a single integral part. Preferably, skins 2 and 3, as well as reinforcement 6, are made of a composite material comprising fiber assemblies woven by three-dimensional weaving and impregnated with a matrix.

[0086] According to embodiments of the present invention, the reinforcement 6 is made of at least one metal and is formed as a single integral component. The one or more metallic materials of the reinforcement 6 may include at least one of the following: steel, titanium, titanium alloys (particularly TA6V, which comprises titanium, aluminum, vanadium, and trace amounts of carbon, iron, oxygen, and nitrogen), nickel-based superalloys (such as Inconel), or aluminum alloys. The manufacture of the metal reinforcement 6 may involve several specific processes, such as machining, forging, forming, casting, or additive manufacturing (3D printing).

[0087] According to an embodiment of the invention, the reinforcement 6 is made of a second nonwoven composite material having fibers embedded in a matrix. These fibers can be long fibers or short fibers.

[0088] According to an embodiment of the present invention, the reinforcement 6 is made of a composite material (the first composite material or the second composite material described above), the composite material comprising a set of fibers impregnated with a matrix, the fibers of the reinforcement 6 being oriented along the height direction DR (or radial direction DR or spanwise direction DR) of the guide vane 1. Therefore, the material of the reinforcement 6 is structural in the entire radial direction relative to the engine shaft AX to reduce stress in the composite skins 3 and 2.

[0089] According to an embodiment of the invention, the Young's modulus of the reinforcing member 6 is greater than or equal to 5 GPa, particularly greater than 10 GPa, for example greater than or equal to 15 GPa. This Young's modulus is greater than that of the component using a braided fabric, the fibers of which are generally oriented along the chord direction AX (along the width direction Y) of the blade 1.

[0090] According to an embodiment of the invention, the filler material 41 is lighter than the first material of the skins 2 and 3. The filler material 41 may be or include foam or other materials.

[0091] According to embodiments of the present invention, such as Figure 2 , Figure 5 and Figure 6 As shown, plate 10 is attached to and abuts against the first end 21 and the second end 31, and is positioned against the opening 5 and the second end 31. Plate 10 forms a connection between the first end 21 and the second end 31.

[0092] According to embodiments of the present invention, such as Figure 2 , Figure 5 and Figure 6 As shown, the plate 10 includes a flat upper surface 13, which is located below and abuts against the first end 21 and the second end 31, and the plate 10 is positioned against the opening 5 and the second reinforcing portion 62.

[0093] According to embodiments of the present invention, such as Figure 3 and Figure 4 As shown, the second reinforcing portion 62 extends in a base 63 with a non-zero height H3, below the first end 21, below the second end 31, and below the opening 5. Therefore, the reinforcing member 6 has an inverted T-shape. The lower surface 631 of the base 63 can be flat.

[0094] According to embodiments of the present invention, such as Figure 3As shown, plate 10 is attached below and abuts against base 63. Plate 10 may include a flat upper surface 13, which is located below and abuts against the flat lower surface 631 of base 63.

[0095] According to embodiments of the present invention, such as Figure 2 , Figure 3 , Figure 5 and Figure 6 As shown, plate 10 may include a flat lower surface 14.

[0096] According to embodiments of the present invention, such as Figure 2 , Figure 3 , Figure 5 and Figure 6 As shown, plate 10 may be made of a material different from the material of the first end 21, the second end 31 and the reinforcement 6, and plate 10 forms a connection between the first end 21 and the second end 31.

[0097] According to embodiments of the present invention, such as Figure 2 , Figure 3 , Figure 5 and Figure 6 As shown, plate 10 is made of composite material.

[0098] According to embodiments of the present invention, such as Figure 4 As shown, the lower surface 631 of the base 63 of the guide vane 1 is exposed. The lower surface 631 may be flat.

[0099] According to embodiments of the present invention, such as Figure 5 As shown, the filler material 41 includes a protrusion 42 on the contact surface 610, the protrusion 42 fitting into the hollow portion 64 of the first reinforcement 61, the contact surface 610 located on the protrusion 42 and the hollow portion 64. The protrusion 42 extends, for example, along the direction Y over the entire width of the cavity between skin 3 and skin 2. The hollow portion 64 extends, for example, along the direction Y over the entire width of the cavity between skin 1 and skin 2. This allows for a gradual transition between the filler material 41 and the reinforcement 6. This reduces abrupt changes in stiffness between the filler material 41 and the reinforcement 6 and avoids localized stress concentrations in the composite skins 2 and 3.

[0100] The attachment side 11, the first end 21, and the second end 31 can be used to mount or attach the guide vane 1 against the outer surface 104 of the upstream portion 103 of the turbine housing 100 via a mounting or attachment device, which may, for example, include holes through the first end 21 and the second end 31. Figure 6The through holes 210 and 310 are shown along the height direction DR, and the mounting or attachment device may include bolts or rivets in the holes, or other devices.

[0101] Of course, the above embodiments, features, possibilities, and examples can be combined with each other or selected independently of each other.

Claims

1. A secondary flow guide vane (1) of a turbine, said secondary flow guide vane comprising a first outer skin (2) and a second outer skin (3) made of a first composite material and connected to each other. The first outer skin (2) includes a first end (21), and the second outer skin (3) includes a second end (31) located away from the first end (21). The first end (21) and the second end (31) are located on the same mounting side (11) of the blade (1), an opening (5) is defined between the first end and the second end, and the first end and the second end branch off from each other along the thickness direction (Y). Its features are, The blade (1) also includes: A cavity (4) is positioned along the thickness direction (Y) between the first outer skin (2) and the second outer skin (3), and the cavity leads to the opening (5). A filling material (41) having a first density, and the filling material being located in the cavity (4) at a distance from the opening (5). The reinforcing member (6) has a second density greater than the first density, and includes a first reinforcing portion (61) and a second reinforcing portion (62), the first reinforcing portion being located in the cavity (4) and abutting against the filling material (41), and the second reinforcing portion closing the opening (5) between the first end (21) and the second end (31). The first reinforcing portion (61) and the second reinforcing portion (62) form an integral part.

2. The guide vane according to claim 1, characterized in that, The first reinforcing portion (61) includes a contact surface (610) for contacting the filling material (41) in the cavity (4). The first outer skin (2) and the second outer skin (3) have a leading edge (8) and a trailing edge (9), the leading edge and the trailing edge being far apart from each other along the width direction (AX) of the blade (1), the width direction being transverse to the thickness direction (Y). The mounting side (11) of the blade (1) is positioned below the airflow line (7) along the height direction (DR) of the blade (1), the height direction being transverse to the thickness direction (Y) and the width direction (AX). The airflow lines (7) form the boundaries of the secondary flow of the turbine on the first outer skin (2) and the second outer skin (3). The first upstream portion (611) of the contact surface (610) is located on the leading edge (8) side and positioned along the height direction (DR) above the second upstream portion (71) of the airflow (7) located on the leading edge (8) side.

3. The guide vane according to claim 2, characterized in that, The first downstream portion (612) of the contact surface (610) is located on the trailing edge (9) side and is positioned along the height direction (DR) below the second downstream portion (72) of the airflow (7) located on the trailing edge (9) side.

4. The guide vane according to claim 2 or 3, characterized in that, The first upstream portion (611) of the contact surface (610) is positioned at a height (H) greater than or equal to 50 mm and less than or equal to 100 mm above the opening (5) along the height direction (DR).

5. The guide vane according to any one of claims 2 to 4, characterized in that, The first upstream portion (611) of the contact surface (610) is positioned at a height greater than or equal to 50 mm and less than or equal to 100 mm above the second upstream portion (71) of the air streamline (7) along the height direction (DR).

6. The guide vane according to any one of claims 1 to 5, characterized in that, A plate (10) forms a connection between the first end (21) and the second end (31), the plate being attached below and abutting the first end (21) and the second end (31), and the plate being positioned abutting the opening (5) and the second reinforcement portion (62).

7. The guide vane according to any one of claims 1 to 5, characterized in that, The second reinforcing portion (62) extends below the first end (21), below the second end (31) and below the opening (5) to form a base (63) with a non-zero height (H3).

8. The guide vane according to claim 7, characterized in that, The plate (10) is attached below the base (63) and abuts against the base.

9. The guide vane according to claim 6 or 8, characterized in that, The plate (10) is made of composite material.

10. The guide vane according to any one of claims 1 to 8, characterized in that, The reinforcement (6) is made of the first composite material.

11. The guide vane according to any one of claims 1 to 8, characterized in that, The reinforcement (6) is made of a second nonwoven composite material having fibers embedded in a matrix.

12. The guide vane according to any one of claims 1 to 8, characterized in that, The reinforcing member (6) is made of at least one metal.

13. The guide vane according to any one of the preceding claims, characterized in that, The reinforcing member (6) has a Young's modulus greater than or equal to 5 GPa.

14. The guide vane according to any one of claims 2 to 5, characterized in that, The filler material (41) includes a protrusion (42) at the contact surface (610), the protrusion being fitted into the hollow portion (64) of the first reinforcing portion (61).

15. Aircraft turbines (100) without rectifiers, including: Shell (101), A fan (200) having a fan hub (201) and peripheral fan blades (202) fixed to the fan hub (201). The fan hub (201) has a downstream hub portion (203) that is surrounded by the inner surface (102) of the upstream portion (103) of the housing (101) and protrudes from the upstream portion (103) of the housing (101). The fan hub (201) is rotatably mounted relative to the upstream portion (103) of the housing about a rotation axis (AX) pointing from upstream to downstream. The turbine (100) further includes a secondary flow guide vane (1) according to any one of the preceding claims, the secondary flow guide vane being positioned adjacent to the outer wall (104) of the upstream portion (103) of the housing (101) via the mounting side (11) of the secondary flow guide vane, and the secondary flow guide vane being positioned downstream relative to the peripheral fan blades (202).

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