JP5614131B2 - Fan blade and fan - Google Patents

Description

  The present invention relates to a fan rotor blade used for a fan that takes air into an engine flow path formed in an engine case in an aircraft engine.

  In recent years, in the field of aircraft engines, a composite material (FRP) of a thermosetting resin and a reinforcing fiber has been attracting attention as a lightweight and high-strength material, and a composite material of a thermosetting resin and a reinforcing fiber is a constituent material. Various developments have been made on the fan rotor blades (see Patent Documents 1 to 4). The contents of the fan rotor blades according to the prior art are as follows.

  The fan rotor blade according to the prior art includes a blade body, and this blade body is a composite of a thermosetting resin such as epoxy resin or a thermoplastic resin such as polyether ether ketone and a reinforcing fiber such as carbon fiber. It is made of a material and has a laminated structure (multilayer structure) in the thickness direction (the thickness direction of the wing body). Moreover, the wing body has a suction surface (back surface) on one side and a pressure surface (abdominal surface) on the other side.

  A blade root is integrally formed on the base end side of the wing body, and the blade root is formed of a thermosetting resin such as epoxy resin or a thermoplastic resin such as polyether ether ketone and a reinforcing fiber such as carbon fiber. It is composed of a composite material and has a laminated structure in the thickness direction (blade root thickness direction). The blade root can be fitted into a fitting groove (fitting notch) formed on the outer peripheral surface of the fan disk of the fan.

  A sheath that protects the front edge side of the wing body is provided on the front edge side of the wing body, and the sheath is made of metal. Furthermore, a guard for reinforcing the wing body may be provided on the rear edge side of the wing body (or from the leading edge side to the rear edge side), and this guard is made of metal like the sheath.

JP 2009-68493 A JP 2008-32000 A JP-A-9-217602 US Pat. No. 5,375,978

  By the way, the blade root has more layers than the blade body, and the stack (laminated structure) is exposed at the trailing edge and leading edge of the blade root, so that foreign matters such as birds sucked into the engine case When colliding (striking) with the leading edge of the wing, the blade energy may cause delamination due to the collision energy. In such a case, there is a problem that it is difficult to increase the durability of the fan rotor blade because the bending rigidity of the fan rotor blade is lowered.

  Accordingly, an object of the present invention is to provide a fan rotor blade having a novel configuration that can solve the above-described problems.

The first feature of the present invention is used for a fan that takes air into an engine flow path formed in an engine case in an aircraft engine, and is composed of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber. The fan blade is made of a thermosetting resin or a composite material of thermoplastic resin and reinforced fiber, has a laminated structure (multilayer structure) in the thickness direction, and has a negative pressure surface (back surface) on one side. And a wing body having a pressure surface (abdominal surface) on the other side, and formed integrally with a base end side of the wing body and made of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber, in the thickness direction. to have become a laminated structure, a fitting groove that can be fitted into (engaged notch) blade root formed on the outer peripheral surface of the fan of the fan disk, provided in front edge side of the blade body, made of metal And protect the leading edge side of the wing body And over scan, provided on at least one of the edges and the front edge after the blade root, is located at a position deviated from the engine flow path is composed of a metal, before the elastic force of itself Kitsubasane And a sandwiching clip configured to sandwich from both sides in the thickness direction.

  The “fan blade” is intended to include not only the fan blade in the narrow sense but also the most upstream compressor blade that takes air into the engine case.

According to the first feature, since the clamping clip that clamps the blade root from both sides in the thickness direction is provided on at least one of the trailing edge and the leading edge of the blade root, during operation of the aircraft engine, The blade root can be sufficiently delaminated by the clamping member without positioning the clamping clip in the engine flow path.
The second feature of the present invention is used for a fan that takes air into an engine flow path formed in an engine case in an aircraft engine, and is composed of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber. The fan rotor blade is composed of a thermosetting resin or a composite material of thermoplastic resin and reinforcing fiber, and has a laminated structure in the thickness direction, having a suction surface on one side and a pressure surface on the other side. And a wing body integrally formed on the base end side of the wing body, composed of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber, and has a laminated structure in the thickness direction, the trailing edge side And at least one of the front edge side is formed with a fitting portion that is gradually thinner along the direction connecting the front edge side and the rear edge side, and is fitted into a fitting groove formed on the outer peripheral surface of the fan disk of the fan. Wing roots that can be combined, and Provided on the leading edge side of the body, made of metal, and provided on at least one of the sheath that protects the leading edge side of the wing body, and the trailing edge and leading edge of the blade root, and deviated from the engine flow path A concave fitting portion that is located at a position and is made of metal and can be fitted to the fitted portion of the blade root; and the fitting portion and the fitted portion of the blade root; And a clamping cap configured to clamp the blade root from both sides in the thickness direction by fitting.

A second feature of the present invention is a fan for taking air into an engine flow path formed in an engine case in an aircraft engine, the fan being provided in the engine case so as to be rotatable around an axis, and having a plurality of outer peripheral surfaces. The present invention includes: a fan disk having a fitting groove (fitting notch) formed therein; and a fan rotor blade having a first feature that is provided by fitting into each fitting groove of the fan disk. To do.

  According to the second feature, in addition to the effects of the first feature, the fan disk is rotated by the operation of the aircraft engine, whereby the plurality of fan rotor blades are rotated integrally with the fan disk. The air can be taken into the engine case.

According to the present invention, delamination of the blade root is sufficiently suppressed by the holding clip or the holding cap without positioning the holding clip or the holding cap in the engine flow path during operation of the aircraft engine. Therefore, it is possible to maintain the bending rigidity of the fan rotor blade and to sufficiently enhance the durability of the fan rotor blade without causing a decrease in the aerodynamic performance of the fan rotor blade.

FIG. 1 is a side view of a fan rotor blade according to the first embodiment of the present invention. 2A is a perspective view of the base end side portion (hub side portion) of the fan rotor blade according to the first embodiment of the present invention as viewed from the rear, and FIG. 2B is IIB-IIB in FIG. It is an expanded sectional view along a line. FIG. 3 is a half sectional view of the front portion of the aircraft engine according to the first embodiment of the present invention. FIG. 4A is a perspective view of a base end side portion of the fan rotor blade according to the second embodiment of the present invention, and FIG. 4B is a base end of the fan rotor blade according to the second embodiment of the present invention. It is the perspective view which looked down at the side part. FIG. 5 is an exploded perspective view of the base end side portion of the fan rotor blade according to the second embodiment of the present invention as seen from below.

(First embodiment)
A first embodiment of the present invention will be described with reference to FIGS. In the drawings, “FF” indicates the forward direction, and “FR” indicates the backward direction.

  As shown in FIG. 3, the fan 1 which concerns on 1st Embodiment of this invention takes in air into the engine flow path 5 formed in the engine case 3 in an aircraft engine. Here, the engine case 3 includes a cylindrical core cowl 7 and a cylindrical nacelle 11 provided outside the cylindrical core cowl 7 so as to surround a plurality of (only one shown) struts 9. ing. Further, the engine flow path 5 is formed between the annular (tubular) core flow path (main flow path) 13 formed inside the core cowl 7 and the inside of the nacelle 11 and the outside of the core cowl 7 from the middle. It branches off into an annular (tubular) bypass flow path 15. The configuration of the fan 1 according to the first embodiment of the present invention will be briefly described as follows.

  A fan disk 17 is rotatably provided at a front portion of the core cowl 7 via a bearing 19, and the fan disk 17 includes a plurality of stages of low-pressure turbines (not shown) disposed behind the fan 1. A low-pressure turbine rotor (not shown) is integrally connected coaxially. A plurality of fitting grooves (fitting notches) 21 are formed at equal intervals on the outer peripheral surface of the fan disk 17.

  A fan rotor blade 23 is fitted in each fitting groove 21 of the fan disk 17, and each fan rotor blade 23 is made of a thermosetting resin or a composite material (FRP) of a thermoplastic resin and a reinforcing fiber. ) As a constituent material. A plurality of spacers 25 are provided between the bottom surface (back surface) of each fitting groove 21 of the fan disk 17 and the fan rotor blade 23. An annular front retainer 27 that holds a plurality of fan rotor blades 23 from the front is integrally provided on the front side of the fan disk 17, and a plurality of fan rotor blades 23 are provided on the rear side of the fan disk 17. An annular rear retainer 29 is integrally provided to hold the rear from the rear. The front retainer 27 is integrally connected to a nose cone 31 that guides air, and the rear retainer 29 is coaxial with the low-pressure compressor rotor 35 in the low-pressure compressor 33 disposed on the rear side of the fan 1. Are integrally connected to each other.

  Therefore, by rotating the fan disk 17 by the operation of the aircraft engine, the plurality of fan rotor blades 23 are rotated together with the fan disk 17 to be brought into the engine flow path 5 (the core flow path 13 and the bypass flow path 15). Can take in air.

  Next, the configuration of the fan rotor blade 23 according to the first embodiment of the present invention will be described.

  As shown in FIGS. 1 and 2, the fan rotor blade 23 is used for the fan 1 as described above and includes a wing body 37, and the wing body 37 is made of epoxy resin, phenol. It is composed of a composite material of a thermosetting resin such as resin or polyimide resin and a reinforcing fiber such as carbon fiber, aramid fiber, or glass fiber, and has a laminated structure in the thickness direction (thickness direction of the wing body 37) ( Multi-layer structure). The wing body 37 has a suction surface (back surface) 39 on one side and a pressure surface (abdominal surface) 41 on the other side. A first recess (first stepped portion) 43 is formed on the front edge side of the suction surface 39 of the wing body 37, and a second recess (second step) is formed on the front edge side of the pressure surface 41 of the wing body 37. A stepped portion 45 is formed.

  The wing body 37 is made of a composite material of a thermoplastic resin such as polyether ether ketone or polyphenylene sulfide and a reinforced fiber instead of the composite material of the thermosetting resin and the reinforced fiber. It doesn't matter.

  A blade root 47 is integrally formed on the base end side of the blade body 37. The blade root 47 is formed of a thermosetting resin such as an epoxy resin, a phenol resin, or a polyimide resin and a carbon fiber, an aramid fiber, or glass. It is composed of a composite material with reinforcing fibers such as fibers, and has a laminated structure (multilayer structure) in the thickness direction (the thickness direction of the blade root 47). The blade root 47 has a dovetail 49 that can be fitted to the fan disk 17.

  The blade root 47 is made of a composite material of a thermoplastic resin such as polyether ether ketone or polyphenylene sulfide and a reinforcing fiber instead of the composite material of the thermosetting resin and the reinforcing fiber. It doesn't matter.

  Here, the boundary between the blade body 37 and the blade root 47 is located on the flow path surface 5 f of the engine flow path 5.

  A sheath 51 that protects the front edge side of the wing body 37 is provided on the front edge side of the wing body 37, and the sheath 51 is made of a metal such as a titanium alloy. The sheath 51 includes a sheath body 53 that covers the front edge side of the wing body, and the sheath body 53 is gradually thinner toward the front. A first joining piece 55 is integrally formed on one side of the rear edge of the sheath body 53, and the first joining piece 55 is inserted into the first recess 43 of the wing body 37 via a sheet-like adhesive. Are joined. Further, a second joining piece 57 is integrally formed on the other side of the rear edge of the sheath body 53, and the second joining piece 57 is inserted into the second recess 45 of the wing body 37 via a sheet-like adhesive. Are joined.

  A clamping clip (an example of a clamping member) 59 is provided on the rear edge of the blade root 47 via a sheet-like adhesive, and this clamping clip 59 has its own elastic force (elastic force of the clamping clip 59). Thus, the blade root 47 is sandwiched from both sides in the thickness direction (the thickness direction of the blade root 47), and is made of a metal such as a titanium alloy. The sandwiching clip 59 includes a clip body 61 that covers the rear edge of the blade root 47, and a first sandwiching piece 63 that can be pressed against one side surface of the blade root 47 is integrally formed on one side of the clip body 61. A second clamping piece 65 that is formed and can be pressed against the other side surface of the blade root 47 is integrally formed on the other side of the clip body 61.

  Instead of or in addition to the holding clip 59 provided on the rear edge of the blade root 47, a holding clip 59 may be provided on the front edge of the blade root 47.

  Then, the effect | action and effect of 1st Embodiment of this invention are demonstrated.

  Since a pinching clip 59 that clamps the blade root 47 from both sides in the thickness direction by its own elastic force is provided on at least one of the trailing edge and the leading edge of the blade root 47, the clamping clip 59 is provided during operation of the aircraft engine. Without being positioned in the engine flow path 5, the delamination of the blade root 47 can be sufficiently suppressed by the holding clip 59.

  Therefore, according to the first embodiment of the present invention, the bending rigidity of the fan rotor blade 23 is maintained and the durability of the fan rotor blade 23 is sufficiently enhanced without deteriorating the aerodynamic performance of the fan rotor blade 23. be able to.

(Second Embodiment)
A second embodiment of the present invention will be described with reference to FIGS. 4 (a) and 4 (b) and FIG. In the drawings, “FF” indicates the forward direction, and “FR” indicates the backward direction.

  As shown in FIGS. 4A, 4B, and 5, the fan rotor blade 67 according to the second embodiment of the present invention is used for the fan 1 and according to the first embodiment of the present invention. It has the same components as the fan rotor blade 23. Hereinafter, a part different from the fan rotor blade 23 according to the first embodiment of the present invention in the configuration of the fan rotor blade 67 according to the second embodiment of the present invention will be described. Of the plurality of components in the fan rotor blade 67 according to the second embodiment of the present invention, those corresponding to the components in the fan rotor blade 23 according to the first embodiment of the present invention are the same in the figure. Give a number.

  A fitted portion 69 is formed on the rear edge side of the blade root 47 (dovetail 49), and the fitted portion 69 is gradually thinner in the rearward direction. Further, a clamping cap (an example of a clamping member) 71 is provided on the rear edge of the blade root 47 via a sheet-like adhesive, and the fitting portion 69 of the blade root 47 is attached to the clamping cap 71. A concave fitting portion 73 that can be fitted to the inner wall is formed. The clamping cap 71 clamps the blade root 47 from both sides in the thickness direction (the thickness direction of the blade root 47) by fitting, and is made of a metal such as a titanium alloy.

  Instead of providing the clamping cap 71 at the rear edge of the blade root 47 or in addition to providing the clamping cap 71, the clamping cap 71 may be provided at the front edge of the blade root 47.

  Then, the effect | action and effect of 2nd Embodiment of this invention are demonstrated.

  Since the clamping cap 71 is provided to clamp the blade root 47 from both sides in the thickness direction by fitting to at least one of the rear edge and the front edge of the blade root 47, the clamping cap 71 is not moved during operation of the aircraft engine. The delamination of the blade root 47 can be sufficiently suppressed by the clamping cap 71 without being positioned in the engine flow path 5.

  Therefore, according to the second embodiment of the present invention, the bending rigidity of the fan rotor blade 67 is maintained and the durability of the fan rotor blade 67 is sufficiently enhanced without deteriorating the aerodynamic performance of the fan rotor blade 67. be able to.

  The present invention is not limited to the description of the above-described embodiment. For example, a guard that reinforces the wing body 37 from the rear edge side or the leading edge side to the rear edge side of the wing body 37 is provided. It can be implemented in various ways. Further, the scope of rights encompassed by the present invention is not limited to these embodiments.

DESCRIPTION OF SYMBOLS 1 Fan 3 Engine case 5 Engine flow path 5f Flow path surface 7 Core cowl 11 Nacelle 13 Core flow path 15 Bypass flow path 17 Fan disk 21 Fitting groove 23 Fan rotor blade 37 Wing body 39 Negative pressure surface (rear surface)
41 Positive pressure surface (abdominal surface)
47 Blade root 49 Dovetail 51 Sheath 59 Clamping clip 61 Clip body 63 First clamping piece 65 Second clamping piece 67 Fan blade 69 Fitted part 71 Clamping cap 73 Fitting part

Claims (3)

In a fan blade that is used for a fan that takes air into an engine flow path formed in an engine case in an aircraft engine, and includes a composite material of a thermosetting resin or a thermoplastic resin and a reinforced fiber,
Is composed of a composite material of thermosetting resin or a thermoplastic resin and reinforcing fibers, the thickness direction has become a laminated structure, having a suction surface on one side, and the blade body having a pressure surface on the other side,
Is integrally formed on the proximal end side of the blade body, is composed of a composite material of thermosetting resin or a thermoplastic resin and reinforcing fibers, the thickness direction has become a laminate structure, the outer peripheral surface of the fan of the fan disk A blade root that can be fitted into the formed fitting groove;
A sheath provided on the leading edge side of the wing body, made of metal, and protecting the leading edge side of the wing body;
Said provided at least one of the edges and the leading edge of the airfoil root is located at a position deviated from the engine flow path is composed of a metal, a Kitsubasane front by its own elasticity in the thickness direction A fan blade comprising a clamping clip configured to be clamped from both sides. In a fan blade that is used for a fan that takes air into an engine flow path formed in an engine case in an aircraft engine, and includes a composite material of a thermosetting resin or a thermoplastic resin and a reinforced fiber,
A wing body composed of a thermosetting resin or a composite material of thermoplastic resin and reinforcing fibers, having a laminated structure in the thickness direction, having a suction surface on one side, and a pressure surface on the other side;
It is integrally formed on the base end side of the wing body, and is composed of a thermosetting resin or a composite material of a thermoplastic resin and a reinforced fiber, and has a laminated structure in the thickness direction, at least of the trailing edge side and the leading edge side A fitting portion that is gradually thinned along the direction connecting the leading edge side and the trailing edge side is formed on any of the blade roots that can be fitted into the fitting grooves formed on the outer peripheral surface of the fan disk of the fan,
A sheath provided on the leading edge side of the wing body, made of metal, and protecting the leading edge side of the wing body;
Provided on at least one of the trailing edge and the leading edge of the blade root, located at a position away from the engine flow path, made of metal, and can be fitted into the fitted portion of the blade root A holding cap configured to hold the blade root from both sides in the thickness direction by fitting the fitting portion with the fitted portion of the blade root. A fan blade characterized by comprising. In a fan that takes air into an engine flow path formed in an engine case of an aircraft engine,
A fan disk provided in the engine case so as to be rotatable around an axis and having a plurality of fitting grooves formed on an outer peripheral surface;
A fan comprising the fan rotor blade according to claim 1 , wherein the fan rotor blade is provided by being fitted in each fitting groove of the fan disk.

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