Turbine rotating fan blade, fan provided with turbine rotating fan blade, and turbine

Abstract

The present invention relates to a turbine rotating fan blade (2), which comprises a body (20) made of a composite material and a metal reinforcing member (3). The metal reinforcing member includes a metal upstream nose portion (31), and is characterized in that the metal upstream nose portion (31) includes at least on the metal part (27b) at the blade tip a groove (4) having a longitudinally narrowing thickness (AX). The groove defines on the metal part (27b) in height (H) at least one metal protrusion (5) having a predetermined worn portion. The metal protrusion has a longitudinally narrowing thickness and is configured to at least partially disengage from the metal part (27b) in the case of tangential friction in a second thickness direction (EP). The groove (4) and the metal protrusion (5) having a predetermined worn portion extend the first metal fin (32) and / or the second metal fin (33) and / or the upstream edge (22) of the body (20) made of a composite material.

Description

Field of the Invention

[0001] The present invention relates to a rotary turbine fan blade, a rotary turbine fan provided with the rotary turbine fan blade, and a turbine provided with the rotary turbine fan blade.

[0002] The field of the present invention relates to aircraft turbines, and more particularly to turbojet engines or turboprop engines. Background Art

[0003] It is known that a rotary turbine fan blade rotates in a fixed housing surrounding the rotary turbine fan blade, and there is a gap between the blade and the housing. The housing is internally covered with a wear-resistant material, which can be shaved by the rotating blade head. Document EP-A-1 312 762 describes such a blade. In the case of an impact after an imbalance that causes the bearing to disengage, the tip of this blade can be decomposed by the inner wall of the retaining housing to obtain a large gap required for the operation of the disconnector. According to this document, each blade has a weak area made by a groove near the tip of the blade. The groove is arranged on the outer arc surface and parallel to the tip of the blade. The groove is filled with resin, which ensures the aerodynamic continuity of the outer arc portion near the tip. The groove is arranged in the base material of the blade to a depth such that the remaining wall in the base material of the weak area on the leading edge side, inner arc side, and trailing edge side has sufficient resistance to enable shaving of this layer of wear-resistant material, and the remaining wall is fragile enough to break when a collision occurs between the tip of the blade and the inner wall of the retaining housing.

[0004] The rotational movement R of the engine that rotates the blade 2 associated with various external elements (such as bird ingestion) or vibration phenomena can cause a sudden and significant contact between the blade head 27 and the wear-resistant material 301 located on the housing 300 of the fan, as shown in Figure 1 as shown.

[0005] Such contact between the blade and the housing may be a cause of significant damage. In fact, instantaneous and sudden contact may cause deformation of the blade, which will increase the contact on the blade surface or the contact depth in the wear-resistant material. If this phenomenon is not controlled, this phenomenon may cause damage to the blade and even significant loss of material.

[0006] To avoid this situation, the radial clearance J at the head of the fan 280 and the dimensions of the volume of the blade 2 are designed to avoid the engagement of the blade in the wear-resistant material and damage to the engine.

[0007] Studies have shown that when the blade rotates at a high speed, the blade deforms under the action of centrifugal force and aerodynamic force. The radial clearance J at the blade head decreases, and ultimately in some cases, this clearance J does not ensure sufficient margin to avoid contact between the blade head 27 and the wear-resistant material. This frictional force results in a tangential load on the blade head 27 (shown by the arrow F in Figure 2 ), which is directed from the inner arc portion 24 of the blade 2 towards the outer arc portion 25, and this tangential load is in the direction opposite to the rotation of the blade 2 around the engine's rotational axis AX.

[0008] This constraint represents additional deformation of the blade. Therefore, various situations may occur.

[0009] According to the first situation, if this deformation causes the clearance to increase, thereby reducing the force and separating the blade surface from the wear-resistant material, the blade is defined as non-self-engaging. Therefore, it can be estimated that in the first situation, when the blade comes into contact with the wear-resistant material, the behavior of the blade is healthy.

[0010] Conversely, according to the second situation, if the deformation results in a positive clearance consumption, the blade is defined as self-engaging. In the second situation, the blade will continue to sink into the wear-resistant material, and the force on the blade will increase. Therefore, the blade and the surrounding parts of the blade may suffer serious damage.

[0011] The simplest solution to avoid this self-engaging phenomenon or at least reduce the severity of this self-engaging phenomenon is to increase the clearance at the blade head to have an additional margin before the blade contacts the wear-resistant material. This strategy enables avoiding any damage to the engine, but may have a significant impact on the aerodynamic performance of the blade. Increasing the clearance at the head increases the leakage flow rate and the associated losses in this area.

[0012] In addition, it is desirable to avoid the configuration of the leading edge of the blade head, which, in the case of self-engagement, is difficult to disengage due to the geometric profile of the configuration and increases the severity of self-engagement. Summary of the Invention

[0013] The first object of the present invention is to obtain a rotating turbine fan blade that can limit the severity of self-engagement of the blade head on the leading edge without degrading the aerodynamic performance.

[0014] The second object of the present invention is to obtain a rotating turbine fan blade that can avoid the configuration of the leading edge of the blade head, which, in the case of self-engagement, is difficult to disengage due to the geometric profile of the configuration and increases the severity of self-engagement.

[0015] To this end, a first subject of the present invention is a rotating turbine fan blade, which blade comprises:

[0016] A body, made of a composite material, having: an upstream edge and a downstream edge, an outer arc portion and an inner arc portion, as well as a blade root and a blade head edge, the body extending between the upstream edge and the downstream edge along a first longitudinal direction; the body extending between the outer arc portion and the inner arc portion along a second thickness direction, the second thickness direction being transverse to the first direction; the body extending between the blade root and the blade head edge along a third height direction, the third height direction being transverse to the first direction and the second direction, the blade root having the function of being attached to a longitudinally rotating fan hub,

[0017] A metal reinforcement member, comprising: an upstream metal nose portion, a first metal fin and a second metal fin, the upstream metal nose portion forming the leading edge of the blade and being fixed to the upstream edge; the first metal fin being connected downstream of the first outer arc side of the upstream metal nose portion and being fixed to the upstream portion of the outer arc portion; the second metal fin being connected downstream of the second inner arc side of the upstream metal nose portion and being fixed to the upstream portion of the inner arc portion, the upstream metal nose portion having a metal blade head portion located upstream of the blade head edge,

[0018] The blade is characterized in that,

[0019] The upstream metal nose portion includes at least one groove at least on the metal blade head portion, the at least one groove having a thickness that narrows longitudinally and opening along the third height direction on the metal blade head portion,

[0020] The at least one groove defines at least one metal protrusion having a predetermined wear portion at a determined non-zero height along the third height direction on the metal blade head portion, the at least one metal protrusion having a predetermined wear portion having a thickness that narrows longitudinally and being configured to at least partially disengage from the metal blade head portion in the case of tangential friction in the second thickness direction,

[0021] The at least one groove and the at least one metal protrusion having a predetermined wear portion extend upstream of the first metal fin and / or the second metal fin and / or the upstream edge of the body made of a composite material in the first longitudinal direction.

[0022] With the present invention, a metallic projection with a predetermined wear portion arranged at the head of the metallic blade is sufficient to avoid self - engagement of the blade assembly with the leading edge of the blade assembly. The wear of the wear - resistant material of the fan housing by the metallic projection with a predetermined wear portion at the blade head during possible rotation of the blade head can be gradual, so as to maintain a sufficient height of the blade head, thereby reducing the leakage flow between the blade and the housing, while avoiding the self - engagement of the second housing as described above. The projection with a predetermined rupture portion or fracture zone on the self - engaging blade enables detachment from the blade upon contact, thus limiting damage to the blade head. Therefore, instead of replacing many components during a critical event that causes the self - engagement phenomenon of the blade, only the blade can be repaired or replaced. The determination of the clearance at the blade head no longer takes into account the self - engaging nature of the blade. This makes it possible to reduce the clearance, which improves the aerodynamic performance of the blade. Thus, sizing the blade according to engine objectives (diameter, rotational speed, etc.) will determine the best solution for manufacturing the region with a predetermined rupture portion among the proposed embodiments.

[0023] According to an embodiment of the present invention, at least one metallic projection with a predetermined wear portion has a longitudinally narrowing thickness over a major part of the length of the upstream metallic nose in a first longitudinal direction.

[0024] According to an embodiment of the present invention, the longitudinally narrowing thickness of the metallic projection with a predetermined wear portion is constant over at least a part of a determined non - zero height.

[0025] According to an embodiment of the present invention, the longitudinally narrowing thickness of the metallic projection with a predetermined wear portion is constant over a major part of the length of the upstream metallic nose.

[0026] According to an embodiment of the present invention, the thickness of the metallic blade head portion increases from upstream to downstream, and at least one groove is defined by a ridge of the upstream metallic nose, wherein the thickness occupied by the at least one groove relative to the ridge increases from upstream to downstream over a major part of the length of the upstream metallic nose.

[0027] According to an embodiment of the present invention, the thickness of the metallic blade head portion increases from upstream to downstream, and at least one groove is defined by a ridge of the upstream metallic nose, wherein the determined non - zero height occupied by the at least one groove relative to the ridge decreases from upstream to downstream over a major part of the length of the upstream metallic nose.

[0028] According to an embodiment of the present invention, at least one groove is formed by at least one shoulder, and at least one shoulder is connected to the first outer arc side of the upstream metallic nose.

[0029] According to an embodiment of the present invention, at least one groove is formed by a shoulder, and the shoulder is connected to the second inner arc side of the upstream metallic nose. The shoulder may include a curved portion.

[0030] According to an embodiment of the present invention, the upstream metal nose includes grooves, the grooves being at least a first groove and at least a second groove. The first groove is formed by a first shoulder, the first shoulder being connected to the first outer arc side surface of the upstream metal nose, and the second groove is formed by a second shoulder, the second shoulder being connected to the second inner arc side surface of the upstream metal nose.

[0031] According to an embodiment of the present invention, the shoulders are curved.

[0032] According to an embodiment of the present invention, a metal protrusion having a predetermined wear portion surrounds at least one groove.

[0033] According to an embodiment of the present invention, the blade head edge includes another metal protrusion having a predetermined wear portion. The other metal protrusion having a predetermined wear portion has a longitudinally narrowed thickness and extends at least one metal protrusion having a predetermined wear portion. Thus, if the protrusion of the strengthening member is considered as the first protrusion, then the other protrusion having a predetermined wear portion on the blade head edge of the blade body is an additional protrusion. The additional protrusion completes the first protrusion of the metal strengthening member by the extension of the additional protrusion in the first longitudinal direction.

[0034] A second subject of the present invention is a rotating turbine fan, which includes a longitudinally rotating fan hub and a plurality of blades as described above. The plurality of blades are fixed to the longitudinally rotating fan hub through the blade roots of the plurality of blades.

[0035] A third subject of the present invention is a turbine, which includes the rotating fan as described above, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine downstream of the fan. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The present invention will be better understood by reading the following description given by way of non-limiting example only and with reference to the accompanying drawings.

[0037] Figure 1 [[ID=2y]]] shows a schematic front view of a blade according to the prior art.

[0038] Figure 2 shows a schematic view along the radial direction of the head of a blade according to the prior art.

[0039] Figure 3 shows a schematic axial cross-sectional view of a turbine including a blade according to the present invention.

[0040] Figure 4 shows a schematic perspective view of a blade according to an embodiment of the present invention. It should be noted that in the translation of the above content, the tag

[0037] in line 22 of the original text is mislabeled as

[0037] in the translation. It should be

[0037] in both the original and the translation. Also, in the translation of line 27, "2y" should be "27". These are likely input errors in the original text for translation. The above translation has been corrected according to the correct understanding.​​​

[0041] Figure 5 shows an enlarged schematic perspective view of the blade head according to the first embodiment of the present invention.

[0042] Figure 6 shows an enlarged schematic cross-sectional view of the blade head according to the first embodiment of the present invention.

[0043] Figure 7 shows an enlarged schematic perspective view of the blade head according to the second embodiment of the present invention.

[0044] Figure 8 shows the Figure 7 enlarged schematic cross-sectional view of the blade head according to the second embodiment of the present invention.

[0045] Figure 9 shows the Figure 7 enlarged schematic top view of the blade head according to an embodiment of the present invention.

[0046] Figure 10 shows an enlarged schematic perspective view of the Figure 7 blade head according to a variant of the second embodiment of the present invention, wherein the height of the groove decreases from upstream to downstream.

[0047] Figure 11 shows an enlarged schematic perspective view of the blade head according to the third embodiment of the present invention.

[0048] Figure 12 [[ID=--44]]]shows an enlarged schematic perspective view of the blade head according to the fourth embodiment of the present invention.

[0049] Figure 13 shows an enlarged schematic cross-sectional view of a part of the blade head according to the fifth embodiment of the present invention.

[0050] Figure 14 shows an enlarged schematic cross-sectional view of a part of the blade head according to the sixth embodiment of the present invention.

[0051] Figure 15 shows an enlarged schematic cross-sectional view of a part of the blade head according to the seventh embodiment of the present invention.

[0052] Figure 16 shows the Figure 15 enlarged schematic perspective view of a part of the blade head according to the seventh embodiment of the present invention.

[0053] Figure 17 It should be noted that in the original text, there is a possible error in ID=44 where the dash in "---44" seems incorrect. It is presented as is in the translation for the sake of following the rules.​​​​​​​​​​​​Shows an enlarged schematic perspective view of a part of the blade head according to an eighth embodiment of the present invention. Detailed Description

[0054] The following refers to Figure 3 An example of a turbine 1 is described in more detail, to which one or more rotating fan blades 2 according to the present invention can be applied.

[0055] As is well known, the turbine 1 shown in Figure 3 is intended to be mounted on an aircraft (not shown) to propel the aircraft in flight.

[0056] The gas turbine engine or turbine assembly 1 extends around an axis AX or an axial direction AX (or a first longitudinal direction AX mentioned hereinafter) that is oriented from upstream to downstream. Subsequently, the terms "upstream", correspondingly "downstream", or "front", correspondingly "rear", or "left", correspondingly "right", or "axially" are selected along the general direction in which the gas flows in the turbine along the axis AX. The direction from the inside to the outside is the radial direction DR (or a third height direction DR mentioned hereinafter) starting from the axis AX.

[0057] For example, the turbine 1 is a two-body turbine. The turbine 1 includes a first stage formed by a rotating fan 280 and a central gas turbine engine 130, and the central gas turbine engine is located downstream of the rotating fan 280. At the center of the turbine, the gas generator 130 includes, in the gas flow direction from upstream to downstream, a low-pressure compressor CBP1, a high-pressure compressor CHP1, a combustion chamber 160, a high-pressure turbine THP1, and a low-pressure turbine TBP1. The low-pressure compressor, the high-pressure compressor, the combustion chamber, the high-pressure turbine, and the low-pressure turbine define the main gas flow FP1.

[0058] The rotating fan 280 includes a set of rotating fan blades 2 that extend radially outward from the rotating fan hub 250. The rotating fan blades 2 are externally surrounded by a fan housing 300, and the fan housing includes one or more layers 301 of wear-resistant material on the following surface of the fan housing, and this surface is positioned to face the blade head 27 of the blade 2.

[0059] The turbine 1 has an upstream intake end 290 located upstream of the fan 280 and a downstream exhaust end 310. The turbine 1 further includes an inter-flow path housing 360, and the inter-flow path housing defines a main flow path, and the main flow FP1 flows through this main flow path. The main flow passes through the low-pressure compressor CBP1, the high-pressure compressor CHP1, the high-pressure turbine THP1, and the low-pressure turbine TBP1 downstream of the fan 280.

[0060] The housing 360 between the flow channels includes, from upstream to downstream, the housing 361 of the low-pressure compressor CBP1, the intermediate housing 260, the housing 362 of the high-pressure compressor CHP1, the housing 363 of the high-pressure turbine THP1, and the housing 190 of the low-pressure turbine TBP1. The intermediate housing is inserted between the low-pressure compressor CBP1 and the high-pressure compressor CHP1.

[0061] The low-pressure compressor CBP1 and the high-pressure compressor CHP1 may each include one or more stages, each stage being formed by a set of stationary vanes (or stator vane means) and a set of rotating blades (or rotor vane means).

[0062] The stationary vanes 101 of the low-pressure compressor CBP1 are fixed to the housing 361. The rotating blades 102 of the low-pressure compressor CBP1 are fixed to the first rotating transmission shaft 410.

[0063] The stationary vanes 103 of the high-pressure compressor CHP1 are fixed to the housing 362. The rotating blades 104 of the high-pressure compressor CHP1 are fixed to the second rotating transmission shaft 400.

[0064] The high-pressure turbine THP1 and the low-pressure turbine TBP1 may each include one or more stages, each stage being formed by a set of stationary vanes (or stator vane means) and a set of rotating blades (or rotor vane means).

[0065] The stationary vanes 105 of the high-pressure turbine THP1 are fixed to the housing 363. The rotating blades 106 of the high-pressure turbine THP1 are fixed to the second rotating transmission shaft 400.

[0066] The stationary vanes 107 of the low-pressure turbine TBP1 are fixed to the housing 190. The rotating blades 108 of the low-pressure turbine TBP1 are fixed to the first rotating transmission shaft 410.

[0067] Under the action of the thrust of the gas from the combustion chamber 160, the rotating blades 108 of the low-pressure turbine TBP1 drive the rotating blades 102 of the low-pressure compressor CBP1 to rotate around the axis AX. Under the action of the thrust of the gas from the combustion chamber 160, the rotating blades 106 of the high-pressure turbine THP1 drive the rotating blades 104 of the high-pressure compressor CHP1 to rotate around the axis AX.

[0068] The rotating fan blade 2 is upstream of the blades 101, 102, 103, 104, 105, 106, 107, and 108 and has a different shape from the blades.

[0069] In operation, air flows through the rotating fan 280. A first portion FP1 (main stream FP1) of the air flow is directed through the low-pressure compressor CBP1 and the high-pressure compressor CHP1, where the air flow is compressed and delivered to the combustion chamber 160. The hot combustion products (not shown in the figures) from the combustion chamber 160 are used to drive the turbines THP1 and TBP1, thereby generating the thrust of the turbine 1. The turbine 1 also includes a secondary flow path 390 for passing a secondary flow FS1 of the air flow discharged from the rotating fan 280 around the inter-flow path housing 360. More particularly, the secondary flow path 390 extends between the inner wall 201 of the nacelle 200 or cowl 200 and the inter-flow path housing 360 surrounding the central gas turbine engine 130, and the fan housing 300 is an upstream portion of the nacelle 200 or cowl 200. The arm 340 connects the intermediate housing 260 to the inner wall 201 of the nacelle 200 in the secondary flow path 390 of the secondary flow FS1.

[0070] Hereinafter, reference is made to Figures 4 to 17 describe the rotating turbine fan blade 2 according to the present invention.

[0071] In Figure 4 the blade 2 includes a body 20 made of a composite material, the body extending between an upstream edge 22 and a downstream edge 23 remote from the upstream edge along a first longitudinal direction AX. The body 20 has a three-dimensional curvature in a plurality of plane sections selected perpendicular to the first longitudinal direction AX.

[0072] The composite body 20 extends between an outer arc portion 24 and an inner arc portion 25 remote from the outer arc portion along a second thickness direction EP, the second thickness direction being transverse to the first direction AX. When the fan hub 250 with the blade root 26 fixed rotates about the axial direction AX, the outer arc portion 24 rotates outward in the rotational direction of the fan blade 2. The body 20 has a three-dimensional curvature in a plurality of plane sections selected perpendicular to the second thickness direction EP. The outer arc portion 24 is symmetric with respect to the inner arc portion 25.

[0073] The composite body 20 extends along a third height direction DR between the blade root 26 of the body 20 and the upper edge 27 of the blade head remote from the blade root 26, wherein the third height direction DR is transverse to the first direction AX and the second direction EP. The third height direction DR is oriented from the bottom to the top of the blade root 26, to the upper edge 27 of the blade head, and to the metal blade head portion 27b described hereinafter. The blade root 26 is adapted to be fixed to the longitudinally rotating fan hub 250. For this purpose, the blade root 26 may have an increased cross-section along the direction EP relative to the intermediate region 26b, which increased cross-section may be, for example, a dovetail shape or the like, and the intermediate region is located between the blade root 26 and the upper edge 27 of the blade head. Thus, the blade root 26 can be inserted into the outer peripheral receiving portion of the fan hub 250 to be fixed to the outer peripheral receiving portion.

[0074] An embodiment of the composite body 20 will be described hereinafter. The body 20 of the blade 2 is made of a composite material three-dimensionally woven in a resin. The composite body 20 includes a resin matrix, and the fiber reinforcement 4 is embedded in the resin matrix. In the finished state of the blade 2, the fiber reinforcement includes at least warp threads extending along the third height direction DR and at least weft threads extending along the first longitudinal direction AX. A possible method for manufacturing the body 20 of the blade 2 is as follows. During a first weaving step, the warp threads and the weft threads are three-dimensionally woven to form the fiber reinforcement. Then, during a second molding step, the fiber reinforcement is arranged in a mold, in which the fiber reinforcement is deformed according to a three-dimensional curvature imposed by a predetermined three-dimensional curvature of the inner wall of the mold, and then the resin is injected around the fiber reinforcement in the mold to give the three-dimensional shape of the body 20 of the blade 2 in the finished state. After molding the resin around the fiber reinforcement, the warp threads and the weft threads exhibit the three-dimensional curvature of the body 20 in the finished state. The fiber reinforcement 4 may be formed from a one-piece fiber preform obtained by three-dimensional weaving or multi-layer weaving with different thicknesses. The fiber reinforcement includes warp threads and weft threads. In particular, the warp threads and the weft threads may include carbon, glass, basalt, and / or aramid fibers. The matrix is typically a polymer matrix, such as an epoxy resin, a bismaleimide, or a polyamide. The blade can be formed by molding through a vacuum resin injection process of the RTM (Resin Transfer Molding) or VARRTM (Vacuum Resin Transfer Molding) type. By three-dimensional weaving, it should be understood that the warp threads follow a zigzag path to connect the weft threads belonging to different layers of weft threads except for the unlocking portion. It should be noted that, in particular, three-dimensional weaving with interlocking weaving may include surface two-dimensional weaving. Different three-dimensional weavings can be employed, such as interlocking weaving, multi-satin weaving, or multi-voile weaving.

[0075] Upstream of the upstream edge 22, the metal reinforcing member 3 (also referred to as a protector) is fixed, for example, by bonding with an adhesive layer 7, and the metal reinforcing member forms the leading edge 30 of the blade 2 ( Figure 4 ). The reinforcing member 3 has the function of facing the incoming aerodynamic flow during flight to overcome erosion of the blade and protect the blade from the problem of bird ingestion.

[0076] The following refers to Figures 5 to 17 the metal blade head portion 27b of the metal reinforcing member 3 is described.

[0077] The metal reinforcing member 3 includes an upstream metal nose 31 that forms the leading edge 30 of the blade 2 and is fixed to the upstream edge 22. The upstream metal nose 31 is formed by a first outer arc side 32b and a second inner arc side 33b that are connected to each other in the direction of the thickness direction EP and terminate at the leading edge 30 upstream. The metal reinforcing member 3 includes a first fin 32 that is connected downstream of the first outer arc side 32b and is fixed to the upstream portion 28 of the outer arc portion 24 of the main body 2 by an adhesive layer 7. The metal reinforcing member 3 includes a second fin 33 that is connected downstream of the second inner arc side 33b and is bonded to the upstream portion 29 of the inner arc portion 25 of the main body 2 by an adhesive layer 7. The upstream metal nose 31, the first fin 32, and the second fin 33 define a cavity in which the upstream edge 22, the upstream portion 28 of the outer arc portion 24, and the upstream portion 29 of the inner arc portion 25 are located. The upstream metal nose 31 is filled and is thicker than each of the fins 32 and 33 in the main region 34 of the member 3. The main body 20, the upstream metal nose 31, the first fin 32, and the second fin 33 have three-dimensional curvature in a first cross-section selected from a plurality of different planes perpendicular to the first direction AX, in a second cross-section selected from a plurality of different planes perpendicular to the second direction EP, and in a third cross-section selected from a plurality of different planes perpendicular to the third direction DR. The member 3 ends above the main region 34 of the member along the third height direction DE with a metal blade head portion 27b that is upstream of the first blade head edge 27 of the composite material main body 2.

[0078] Refer to Figures 5 to 17, the upstream metal nose 31 includes one or more metal protrusions 5 having a predetermined wear portion on the metal blade head portion 27b. Each metal protrusion 5 having a predetermined wear portion has a narrowing thickness EP5 along the first longitudinal direction AX and a determined non-zero height H along the third height direction DR. The one or more metal protrusions 5 having a predetermined wear portion are defined by one or more grooves 4, and the one or more grooves have a narrowing thickness along the first longitudinal direction AX and are at least arranged on the metal blade head portion 27b of the upstream metal nose 31. The one or more metal protrusions 5 having a predetermined wear portion are configured to at least partially disengage from the metal blade head portion 27b in the case of tangential friction in the second thickness direction EP. The one or more grooves 4 and the one or more metal protrusions 5 having a predetermined wear portion extend upstream of the first metal fin 32 and / or the second metal fin 33 and / or the upstream edge 22 of the composite body 21. Thus, in the case where the protrusion is in too obvious contact with the wear-resistant material 301 located on the housing 300 of the fan 280, the protrusion 5 serves as a fracture portion. The protrusion 5 having a predetermined fracture portion is present in the self-engagement portion of the blade 2, that is, in a part that can come into contact with the wear-resistant material 301 of the housing 300 of the fan 280 as described above. Thus, in the case where a significant force is generated on the metal blade head portion 27b due to the contact between the protrusion and the wear-resistant material 301, the protrusion 5 will partially disengage from the blade, which enables it to directly leave the contact with the wear-resistant material 301 and will avoid self-engagement. The size of the protrusion 5 can be determined according to the size of the portion of the blade closest to the wear-resistant material 301. The protrusion 5 forms a thinning portion of the metal blade head portion 27b.

[0079] Reference Figures 5 to 17 , the one or more grooves 4 have a determined non-zero height H above the main portion 34 and are bounded downward by a transition surface 8 that connects the protrusion 5 to the main portion 34, and the thickness EP34 of the main portion is greater than the thickness EP5 of the protrusion 5. The transition surface 8 turns upward in the third height direction DR and may, for example, have a ramp fracture portion 9 or a ridge portion 9 that connects the transition surface to the main portion 34 and / or the protrusion 5.

[0080] According to Figures 5 to 12 In an embodiment according to the present invention, the longitudinally narrowing thickness EP5 of the metal protrusion 5 having a predetermined wear portion is at least constant over a part of a determined height H starting from the top. Thus, during the rotation of the blade 2, in the case of starting self-engagement, this part of the height of the metal protrusion 5 having a predetermined wear portion does not provide an increasing resistance during the friction with the wear-resistant material 301 of the fan housing 300 and is more easily worn, which reduces the risk of self-engagement and enables the achievement of the second object described above.

[0081] In Figure 5 、 Figure 6 and Figure 9 in the embodiments of the present invention shown, the longitudinally narrowing thickness EP5 of the metal projection 5 having a predetermined wear portion is constant over the entire defined height H. The transition surface 8 can be planar and, for example, perpendicular to the projection 5.

[0082] In Figures 7 to 10 in the embodiments of the present invention shown, the longitudinally narrowing thickness EP5 of the metal projection 5 having a predetermined wear portion is constant over the upper part 51 of the height H.

[0083] The transition surface 8 can be curved (e.g., concave) in a plurality of plane sections, as in Figures 7 to 10 in which these plane sections are selected perpendicular to the first longitudinal direction AX. The transition surface 8 can form a chamfer 42 and / or 43 or an upwardly turned shoulder 42 and / or 43.

[0084] Thus, in Figures 4 to 10 it is possible to provide a first groove 4 formed by the first curved shoulder 42 and / or a second groove 4 formed by the second curved shoulder 43, the first curved shoulder being connected to the first outer arc side surface 32b of the upstream metal nose portion 31, and the second curved shoulder being connected to the second inner arc side surface 33b of the upstream metal nose portion 31.

[0085] In other embodiments not shown, the projection 5 can be located on one side of the first outer arc side surface 32b of the upstream metal nose portion 31, in which case the groove 4 is located on one side of the second inner arc side surface 33b of the upstream metal nose portion 31. In other embodiments not shown, the projection 5 can be located on one side of the second inner arc side surface 33b of the upstream metal nose portion 31, in which case the groove 4 is located on one side of the first outer arc side surface 32b of the upstream metal nose portion 31.

[0086] In Figures 5 to 17 in the embodiments of the present invention shown, the longitudinally narrowing thickness EP5 of the metal projection 5 having a predetermined wear portion is constant over a major part 311 of the length of the upstream metal nose portion 31 along the longitudinal direction AX. For example, the major part 311 of the length of the upstream metal nose portion 31 along the longitudinal direction AX represents at least 50% of the length of the upstream metal nose portion 31 along the longitudinal direction AX. The length of the upstream metal nose portion 31 along the longitudinal direction AX is selected between the leading edge 30 and the upstream edge 22, or between the leading edge 30 and the first metal fin 32, or between the leading edge 30 and the second metal fin 33.

[0087] In Figure 9In the embodiment of the present invention shown, the thickness EP5 of the metal blade head portion 27b and / or the metal protrusion 5 having a predetermined worn portion increases in the direction from upstream to downstream along the longitudinal direction AX. One or more grooves 4 are defined by the ridges 9 of the upstream metal nose 31. The thicknesses e1, e2 occupied by at least one groove 4 relative to the ridge 9 increase in the direction from upstream to downstream along the longitudinal direction AX over the major part 311 of the length of the upstream metal nose 31. Thus, in the case where the thickness e1 is selected at a more upstream position than the thickness e2, e1 < e2. The major part 311 may have the definition mentioned above.

[0088] In Figures 1 to 17 In the embodiment of the present invention shown, another thickness of the first blade head edge 27 of the composite body 2 may increase in the direction from upstream to downstream along the longitudinal direction AX over the upstream part (e.g., over at least 20% or at least 50% of the length of the first blade head edge 27 selected along the longitudinal direction AX starting from the upstream edge 22). The length of the first blade head edge 27 may be selected between the upstream edge 22 and the downstream edge 23 of the composite body 20 along the longitudinal direction AX.

[0089] In Figure 7 , Figure 9 and Figure 10 In the embodiment of the present invention shown, the determined non-zero heights H, h1, h2 occupied by one or more grooves 4 and protrusions 5 relative to the ridge 9 decrease in the direction from upstream to downstream along the longitudinal direction AX over the major part 311 of the length of the upstream metal nose 31. Thus, in the case where the height h1 is selected at a more upstream position than the height h2, h1 > h2. The major part 311 may have the definition mentioned above.

[0090] In Figure 11 In the embodiment of the present invention shown, the metal protrusion 5 having a predetermined worn portion surrounds one or more grooves 4. The protrusion 5 includes two first longitudinally narrowing portions 51 and a second longitudinally narrowing portion 52, and the first longitudinally narrowing portion and the second longitudinally narrowing portion extend in the height direction DR of the first outer arc side surface 32b and the second inner arc side surface 33b of the upstream metal nose 31, respectively. The groove 4 is defined between the longitudinally narrowing portions 51 and 52 and is above the bottom 40 located between these longitudinally narrowing portions 51 and 52. This enables the aerodynamic profile of the blade to be maintained, so that the outer surface remains unchanged. The groove 4 may be a hollow portion that can be machined.

[0091] In Figures 12 to 17In the embodiment of the present invention shown, the blade head edge 27 includes another protrusion 6 (or a second protrusion 6 with a predetermined worn portion) having a predetermined worn portion. The another protrusion with the predetermined worn portion has a narrowing thickness along the longitudinal direction AX and extends downstream of the metal protrusion 5 (or the first metal protrusion 5 with a predetermined worn portion) along the longitudinal direction AX. Therefore, the another protrusion 6 with the predetermined worn portion is made of the composite material of the main body 20 of the blade 2. The another protrusion 6 forms a thinning portion of the blade head edge 27. Therefore, in the case where the another protrusion 6 comes into overly obvious contact with the wear-resistant material 301 on the housing 300 of the fan 280, the another protrusion 6 serves as a breaking portion. The another protrusion 6 with a predetermined breaking portion exists in the self-bonding portion of the blade 2, that is, in a part that can come into contact with the wear-resistant material 301 of the housing 300 of the fan 280 as described above. Therefore, in the case where a significant force is generated on the blade head edge 27 due to the contact between the another protrusion and the wear-resistant material 301, the another protrusion 6 will partially detach from the blade, which enables it to directly leave the contact with the wear-resistant material 301 and will avoid self-bonding. The size of the another protrusion 6 can be determined according to the size of the part of the blade closest to the wear-resistant material 301.

[0092] The another protrusion 6 with a predetermined worn portion can be defined by a chamfer 61 that extends along the longitudinal direction AX and is connected to the inner arc portion 25 (or is connected to the outer arc portion 24 in other embodiments not shown), as shown in Figure 12 , Figure 13 and Figures 14 to 17 shown. The chamfer 61 can be planar.

[0093] The another protrusion 6 can end with a planar surface 62 that narrows along the longitudinal direction AX and has a non-zero thickness EP62, as shown in Figure 12 and Figures 15 to 17 shown.

[0094] The chamfer 61 can extend on a part of the length of the blade head edge 27 starting from the upstream edge 22 of the blade head edge to form a local chamfer 61, as shown in Figure 17 shown (the adhesive layer 7 is not shown in Figure 17 ).

[0095] The another protrusion 6 can end with a ridge 63 that extends along the longitudinal direction AX and has a zero thickness, as shown in Figure 13 shown.

[0096] Another protrusion 6 may end upwardly with a circular edge 64 that extends along the longitudinal direction AX and is connected to the inner arc portion 25 and the outer arc portion 24, as shown in Figure 14 FIG. The radius of curvature of the circular edge 64 in a plurality of different planes transverse to the direction AX is smaller than the radius of curvature of the inner arc portion 25 and the outer arc portion 24.

[0097] Of course, the embodiments, features, possible implementations, and examples described above can be combined with each other or selected independently of each other.

Claims

1. A rotating turbine fan blade (2), the rotating turbine fan blade (2) comprising: A body (20) made of a composite material, the body having: an upstream edge (22) and a downstream edge (23), an outer arc portion (24) and an inner arc portion (25), and a blade root (26) and a blade tip edge (27), the body (20) extending between the upstream edge and the downstream edge along a first longitudinal direction; the body (20) extending between the outer arc portion and the inner arc portion along a second thickness direction, the second thickness direction being transverse to the first longitudinal direction; the body (20) extending between the blade root and the blade tip edge along a third height direction, the third height direction being transverse to the first longitudinal direction and the second thickness direction, the blade root (26) having a function of being attached to a longitudinal rotating fan hub (250), A metal reinforcing member (3), the metal reinforcing member comprising: an upstream metal nose (31), a first metal fin (32), and a second metal fin (33), the upstream metal nose forming a leading edge (30) of the rotating turbine fan blade (2) and being fixed to the upstream edge (22), the upstream metal nose (31) being formed by a first outer arc side surface (32b) and a second inner arc side surface (33b), the first outer arc side surface and the second inner arc side surface being connected to each other in the second thickness direction and terminating at the leading edge (30) upstream; the first metal fin being connected downstream of the first outer arc side surface (32b) of the upstream metal nose (31) and being fixed to an upstream portion (28) of the outer arc portion (24); the second metal fin being connected downstream of the second inner arc side surface (33b) of the upstream metal nose (31) and being fixed to an upstream portion (29) of the inner arc portion (25), the upstream metal nose (31) having a metal blade tip portion (27b) located upstream of the blade tip edge (27), The rotating turbine fan blade is characterized in that, The upstream metal nose (31) includes at least one groove (4) at least on the metal blade tip portion (27b), the at least one groove having a longitudinally narrowing thickness and opening along the third height direction on the metal blade tip portion (27b), The at least one groove (4) defines at least one metal protrusion (5) having a predetermined wear portion along the third height direction on the metal blade tip portion (27b), the at least one metal protrusion having a longitudinally narrowing thickness on a main portion (311) of the length of the upstream metal nose (31) along the first longitudinal direction and being configured to at least partially separate from the metal blade tip portion (27b) in the case of tangential friction in the second thickness direction, The at least one groove (4) and the at least one metal protrusion (5) with a predetermined wear portion extend upstream in the first longitudinal direction upstream of the first metal fin (32) and / or the second metal fin (33) and / or the upstream edge (22) of the body (20) made of a composite material.

2. The rotating turbine fan blade according to claim 1, wherein The longitudinally narrowing thickness of the metal protrusion (5) with a predetermined wear portion is constant at least over a part of the determined non-zero height.

3. The rotating turbine fan blade according to claim 1, characterized in that, The longitudinally narrowing thickness of the metal protrusion (5) with a predetermined wear portion is constant over a major part (311) of the length of the upstream metal nose (31).

4. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that The thickness of the metal blade head portion (27b) increases from upstream to downstream, and the at least one groove (4) is defined by a ridge (9) of the upstream metal nose (31), wherein the thickness occupied by the at least one groove (4) relative to the ridge (9) increases from upstream to downstream over a major part (311) of the length of the upstream metal nose (31).

5. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The thickness of the metal blade head portion (27b) increases from upstream to downstream, and the at least one groove (4) is defined by a ridge (9) of the upstream metal nose (31), wherein the determined non-zero height occupied by the at least one groove (4) relative to the ridge (9) decreases from upstream to downstream over a major part (311) of the length of the upstream metal nose (31).

6. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The at least one groove (4) is formed by at least one first shoulder (42), and the at least one first shoulder is connected to the first outer arc side surface (32b) of the upstream metal nose (31).

7. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The at least one groove (4) is formed by a second shoulder (43), and the second shoulder is connected to the second inner arc side surface (33b) of the upstream metal nose (31).

8. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The upstream metal nose (31) includes grooves (4), which are at least a first groove and a second groove. The first groove is formed by a first shoulder (42), and the first shoulder is connected to the first outer arc side surface (32b) of the upstream metal nose (31). The second groove is formed by a second shoulder, and the second shoulder is connected to the second inner arc side surface (33b) of the upstream metal nose (31).

9. The rotary turbine fan blade according to claim 6, characterized in that, The first shoulder (42) is curved.

10. The rotating turbine fan blade according to claim 7, wherein, The second shoulder (43) is curved.

11. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The metal protrusion (5) with a predetermined wear portion surrounds the at least one groove (4).

12. The rotary turbine fan blade according to any one of claims 1 to 3, characterized in that, The blade head edge (27) includes another metal protrusion (6) with a predetermined wear portion. The another metal protrusion with a predetermined wear portion has a longitudinally narrowing thickness and extends the at least one metal protrusion (5) with a predetermined wear portion.

13. A rotary turbine fan (280), the rotary turbine fan comprising a longitudinally rotating fan hub (250) and a plurality of rotary turbine fan blades (2) according to any one of claims 1 to 12, the plurality of rotary turbine fan blades being fixed to the longitudinally rotating fan hub (250) by blade roots (26) of the plurality of rotary turbine fan blades.

14. A turbine (1), the turbine comprising the rotary turbine fan (280) according to claim 13 and a low-pressure compressor, a high-pressure compressor, a combustion chamber (160), a high-pressure turbine and a low-pressure turbine downstream of the rotary turbine fan (280).

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