JP3831265B2 - Method for manufacturing stationary blade structure - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an integrally molded fiber reinforced resin unit and a method for manufacturing a stationary blade structure obtained by combining the same, and in particular, an I type, a C type, and the like including a fiber reinforced core portion and an integrally molded resin skin portion. The present invention relates to a method for manufacturing a stationary blade structure obtained by joining units in an annular shape.
[0002]
[Prior art and problems to be solved by the invention]
Gas turbine engines are widely used in aircraft, generators and the like because they not only provide a large output but also have very good efficiency. For example, an aircraft gas turbine engine is provided with a stationary blade that serves as an outlet guide vane that guides the sucked air to the moving blade and rectifies the bypass flow. The stationary blade is generally formed of a metal material such as a titanium alloy, an aluminum alloy, and stainless steel. In the case of a metal stator blade, vanes are first formed by casting, forging, pressing, or the like, and then each vane is joined to a case called a platform by welding or brazing.
[0003]
However, in the conventional manufacturing method as described above, it is necessary to perform machining, finishing, coating, and the like after the vane is formed, and not only there are many processing steps, but complicated processing of details is difficult, Moreover, there is a problem that it is heavy and expensive due to the use of a metal material.
[0004]
Therefore, recently, a method of manufacturing a stationary blade by using a resin or a resin composite material has attracted attention, and some proposals have been made. For example, Japanese Patent Laid-Open No. 5-278063 discloses a method of forming a wing body having a smaller dimension than a desired wing shape by laminating prepreg materials, and inserting the wing body into a mold for obtaining a desired wing shape. Discloses a method of manufacturing a wing component by performing compression molding in a state where a thermoplastic resin is press-fitted and filled in a gap formed between the two. By making the stationary blades made of resin, there are advantages such as shortening of the production period, simplification of work, improvement of shape accuracy, cost reduction, and weight reduction. However, since the resin blade parts are attached to the platform with adhesives or bolts to form the stationary blades, there are problems that the number of components of the stationary blades increases and the number of manufacturing steps increases accordingly.
[0005]
In JP-A-11-350904, a temporary assembly is formed by combining a unit (static blade) having a core portion and a skin portion covering the core portion, and a tape is wound around and fixed to the temporary assembly. A method of manufacturing a wing structure is disclosed. The unit is provided with an exposed portion of the core portion, and the exposed portion, the platform piece, and the coating layer of the tape are directly welded, so that the unit can be firmly fixed. However, when the units are combined together, there is a problem that it becomes difficult to form a uniform shape due to unit tolerances, and it is difficult to fix the unit at a desired position. Further, since the temporarily assembled stationary blade structure is wound and fixed with tape, this work process is necessary. Furthermore, since the stationary blade structure is completed by fixing all the units, there is a disadvantage that the entire stationary blade structure must be replaced even if some units need to be replaced.
[0006]
Furthermore, when a thermoplastic resin is used for the skin part, the thermoplastic resin (polyether ale ketone: PEEK) has a high melting temperature (melting point 345 ° C.) and low fluidity in the molten state, so the rigidity of the core part is low. However, there is a problem that it is subject to a restriction on the blade design that shrinkage deformation is likely to occur when fused and integrated, and the skin portion of the stationary blade is difficult to thin. In addition, the thermoplastic resin has a problem that the abrasion resistance against sand or the like is not sufficient.
[0007]
Accordingly, an object of the present invention is to provide a method for easily producing a stator blade structure having a uniform shape, which can be replaced for each unit, has high strength and is excellent in wear resistance.
[0008]
[Means for Solving the Problems]
As a result of diligent research in view of the above object, the present inventors have determined that a skin made of a thermosetting resin having rubber or rubber elasticity around a core portion of a unit such as an I-type or C-type obtained by dividing a stationary blade structure into multiple parts. After the parts are integrally formed, the outer platform piece and the inner platform piece are joined to the adjacent outer platform piece and inner platform piece, respectively, to form a temporary assembly, which is fixed by the support member and the fixing member. Thus, it was discovered that each unit can be replaced and a stationary blade structure having a uniform shape can be easily manufactured, and the present invention has been conceived.
[0009]
That is, the manufacturing method of the stator blade structure of the present invention having a plurality of vanes, an outer platform, and an inner platform is as follows: (1) By integrally connecting the flange portions to both ends of the web portion constituting the vane. A core portion having an outer platform piece and an inner platform piece is formed, and a skin portion made of a thermosetting resin having rubber or rubber elasticity is integrally formed on the surface of the core portion, thereby forming a stationary blade structure unit. And (2) joining the outer platform piece and the inner platform piece of the adjacent stationary blade structure unit, respectively, to form an annular temporary assembly, and (3) the outer platform of the temporary assembly. And attaching the inner platform to the outer annular support member and the inner annular support member, respectively (4) The temporary assembly is fixed to the outer fixing member and the inner fixing member using an outer fixing member and an inner fixing member that engage with the side annular supporting member and the inner annular supporting member.
[0010]
It is preferable to use thermosetting urethane rubber as the thermosetting resin having rubber or rubber elasticity. Each of the outer platform piece and the inner platform piece has a connecting step at each end, and this step is overlapped with a step having a complementary shape of an adjacent unit, and is thermosetting having rubber or rubber elasticity. It is preferable to join the outer platform piece and the inner platform piece by the elastic action of the resin.
[0011]
The outer annular support member and the inner annular support member each have a receiving portion having a width equal to or slightly narrower than the wall thickness of one end portion of the outer platform and the platform, and one end of each of the outer platform and the inner platform. It is preferable to press-fit the part to the receiving part of each of the outer annular support member and the inner annular support member. The receiving portion for mounting the outer platform is preferably provided on the inner surface of the outer annular support member.
[0012]
The outer fixing member and / or the inner fixing member has an annular shape and has a stopper protruding on one surface thereof, and the stopper is combined with a notch formed on the outer platform and / or the inner platform of the temporary assembly. Thus, it is preferable to fix the temporary assembly in a predetermined position.
[0013]
The core part is preferably formed of a fiber reinforced prepreg laminate or a light metal. Carbon fiber polyetheretherketone or carbon fiber reinforced epoxy resin is preferably used as the fiber reinforced prepreg material, and aluminum alloy or magnesium alloy is preferably used as the light metal. Moreover, it is preferable to form the flange part of the said core part by bending the both ends of the laminated body of fiber reinforced prepreg material.
[0014]
DETAILED DESCRIPTION OF THE INVENTION
[1] Stator blade structure unit
The stationary blade structure unit has a basic structure including one vane, an outer platform piece, and an inner platform piece, and the shape of the flange portion integrally connected to both ends of the web portion constituting the vane, It can be classified into I type, C type and the like. Hereinafter, the I type and C type units will be described in detail.
[0015]
(1) Type I unit
As an example of a stationary blade structure including an I-type unit, FIG. 1 shows a gas turbine stationary blade structure 1. The gas turbine stationary blade structure 1 includes an outer platform 11, an inner platform 12, and a plurality of vanes 13 fixed to the platforms 11 and 12 at equal intervals. The turbine stationary blade structure 1 has a shape divided by the number of vanes. As shown in FIG. 2 (a), each unit 2 has one vane 13, an outer platform piece 21, and an inner platform piece 22, and is a substantially I-shaped integrally molded body as a whole. It has become. In FIG. 2, both platform pieces 21 and 22 are drawn flat for the sake of simplicity, but they are actually arcuate.
[0016]
Step portions 23 and 23 'are provided at both ends in the circumferential direction of the outer platform piece 21 formed in an arc shape, and both ends in the circumferential direction of the inner platform piece 22 formed in an arc shape. Are provided with stepped portions 24, 24 '. Further, as shown in FIG. 2 (b), convex portions 25, 25 ′ are provided at the other end portions of the outer platform piece 21, and convex portions 27, 27 ′ are provided at the other end portions of the inner platform piece 22. 'Is provided. Since the shape of the steps 23, 23 'and 24, 24' of the platform pieces 21, 22 of adjacent I-type units 2 are complementary, each I-type unit 2 must be closely joined as shown in FIG. Can do.
[0017]
As shown in FIG. 3, each I-type unit 2 includes a substantially I-shaped core portion 3 and a skin portion 4 integrally formed with the core portion 3. The skin portion 4 covers the surface of the outer platform piece 21, the surface of the inner platform piece 22, and the surface of the vane 13.
[0018]
It is preferable that the core part 3 consists of a laminated body or a light metal of a fiber reinforced prepreg material. The fiber reinforced prepreg material is obtained by impregnating a reinforcing fiber such as carbon fiber, aramid fiber, glass fiber, or boron fiber with a matrix resin made of a thermoplastic resin or a thermosetting resin. The average diameter of the reinforcing fibers is preferably about 3 to 200 μm. Examples of the thermoplastic resin include polyether ether ketone (PEEK), polyamide such as nylon, polyimide, polyester such as polyethylene terephthalate and polybutylene terephthalate, polyacetal, polyphenylene sulfide, and polyether ketone. Examples of the thermosetting resin include epoxy resin, polyurethane, and unsaturated polyester. As the fiber reinforced prepreg material, a carbon fiber composite material composed of carbon fiber and the above resin is preferable. From the viewpoint of mechanical strength and heat resistance, a combination of carbon fiber and PEEK, or a combination of carbon fiber and epoxy resin. Is more preferable. APC-2 (manufactured by CYTEC FIBERITE) is a commercial product of carbon fiber reinforced PEEK. Light metals are aluminum alloys (Al-Mg, Al-Mn, Al-Mg-Si, Al-Cu, Al-Cu-Si, Al-Cu-Mg-Ni, etc.), magnesium alloys (Mg- Zn-based, Mg-rare earth element-based, etc.) are preferred.
[0019]
FIG. 4 shows a core portion made of a fiber-reinforced prepreg material. The core portion 3 includes a web portion 31 constituting the vane 13, a flange portion 32 constituting the outer platform piece 21, and a flange portion 33 constituting the inner platform piece 22. The web portion 31 and the flange portions 32 and 33 are integrated, and the flange portions 32 and 33 are in a state where both ends of the laminated fiber-reinforced prepreg material are divided in half and bent on both sides.
[0020]
As shown in FIG. 5, the I-type unit has an outer platform piece 21, an inner platform piece 22, and a vane 13 that are integrally molded, and the surface of the core portion 3 is covered by the skin portion 4.
[0021]
As the material constituting the skin portion, rubber or a thermosetting resin having rubber elasticity is used from the viewpoint of improving the wear resistance against sand, wrinkles and the like. Specifically, urethane rubber, silicone rubber, chloroprene rubber, and other rubber materials are preferable, and urethane rubber is more preferable. As the urethane rubber, for example, a cast type urethane rubber obtained by a reaction between a polyol prepolymer and toluene diisocyanate (TDI) or 4,4′-methylenebis (phenylisocyanate) (MDI) can be preferably used. Examples of the casting type urethane rubber include MDI and polyether polyol-based prepolymers, which are preferably mixed and cast.
[0022]
Since the thermosetting resin has a low viscosity in a liquid state, the skin layer can be thinly formed in casting by casting. Since the shape of the wing is important for the rectifying action, the wing design can be increased by making the skin layer thin. In addition, since molding can be performed at a temperature lower than that of the thermoplastic resin (about 100 ° C. or lower), a decrease in rigidity of the core due to heat can be suppressed, and a dimensional error due to thermal contraction can be suppressed low. For this reason, it becomes possible to produce a unit with high dimensional accuracy. Furthermore, when urethane rubber or the like having self-adhesiveness is used as the thermosetting resin having rubber or rubber elasticity, the adhesion with the core portion is improved. Thereby, various fiber reinforced prepreg materials and light metals can be used for the core portion, and there is an advantage that the range of material selection increases.
[0023]
(2) C type unit
6A shows the C-type unit, and FIG. 6B shows the portion X thereof. Each C-type unit 6 includes a substantially C-shaped core portion 7 and a skin portion 8 formed integrally with the core portion 7. As shown in FIG. 7, the C-shaped core portion 7 includes a web portion 71 constituting a vane, a flange portion 72 constituting an outer platform piece 61, and a flange portion 73 constituting an inner platform piece 62. The web portion 71 and the flange portions 72 and 73 are integrated, and the flange portions 72 and 73 are formed by bending both ends of the fiber reinforced prepreg material to the same side.
[0024]
As shown in FIGS. 6A and 6B, the C-type unit has an outer platform piece 61, an inner platform piece 62 and a vane 53 which are integrally formed, and the surface of the C-type core portion 7 is formed by the skin portion 8. Covering.
[0025]
FIG. 6C is a front view of the C-type unit, and FIG. 6D is a bottom view. Similarly to the I-type unit, step portions 63 and 63 'are provided at both ends in the circumferential direction of the outer platform piece 61 formed in an arc shape, and the circle of the inner platform piece 62 formed in an arc shape is provided. Step portions 64 and 64 'are provided at both ends in the circumferential direction. Further, convex portions 65 and 65 ′ are provided at the other end portions of the outer platform piece 61, and convex portions 67 and 67 ′ are provided at the other end portions of the inner platform piece 62. Since the shapes of the step portions 63, 63 ′ and 64, 64 ′ of the platform pieces 61, 62 of the adjacent C-type unit 6 are complementary, as shown in FIG. 8, the C-type units 6 are closely joined to each other. be able to. As shown in FIG. 8, the stationary blade structure including the C-type unit is formed by combining the C-type units in an annular shape.
[0026]
Both the material forming the C-type core portion 7 and the resin forming the skin portion may be the same as those of the I-type unit.
[0027]
As shown in FIG. 6 (e), the stationary blade structure unit is a unit having a notch 68 at the center of one end of the outer platform piece as shown in FIG. It is preferable to use it in appropriate combination with the unit. As a result, when the stationary blade structure is assembled, the notched portion 68 can be engaged with the protruding stopper attached to the fixing member to prevent the stationary blade structure from rotating. The notch 68 is not limited to the outer platform piece, but can be appropriately provided on the outer platform piece and / or the inner platform piece, and can be engaged with a stopper attached to the outer fixing member and / or the inner fixing member.
[0028]
[2] Manufacturing method
(1) Stator blade structure unit
Since the manufacturing method of the stationary blade structure unit is basically the same for both the I type and the C type, the C type unit will be described here.
[0029]
The stator blade structure unit first forms a core portion having an outer platform piece and an inner platform piece by integrally connecting flange portions to both ends of the web portion constituting the vane. The flange portion is formed by bending both ends of a laminated body of fiber reinforced prepreg materials constituting the core portion.
[0030]
As a method for forming the core portion, a case where carbon fiber reinforced PEEK formed by impregnating PEEK into carbon fibers arranged in one direction will be described as an example. A plurality of carbon fiber reinforced PEEK sheets cut into an appropriate shape are laminated so that the longitudinal direction of the vane 53 (the radial direction of the gas turbine stationary blade structure) coincides with the arrangement direction of the carbon fibers. Set in partial mold and heat press molded. Hot press molding is performed, for example, by heating a mold to around 300 ° C. to form a preform and then heating and pressurizing the preform. The cavity of the core mold is about 0.1 to 2 mm smaller than the size of the vane 53 and has a shape approximate to the shape of the vane 53. The heating temperature of the core mold is a temperature at which PEEK is melted and fluidized, and is preferably around 400 ° C. The molding pressure is 3-25 kgf / cm. ² Preferably 15 kgf / cm ² Before and after are particularly preferred.
[0031]
The stator blade structure unit is integrally molded by covering the molded core portion 7 with a skin portion 8 made of a thermosetting resin having rubber or rubber elasticity. First, the molded core portion 7 is placed in a casting mold. The cavity of the casting mold has the same shape as the final shape of the vane. When thermosetting urethane rubber is used as the rubber or rubber elastic thermosetting resin, the mold temperature is set to a temperature that does not require temperature adjustment, for example, room temperature (25 ° C.) to 150 ° C., for example, about 40 ° C. After mixing the two raw material liquids (for example, MDI liquid and polyether polyol liquid), the urethane rubber raw material mixed liquid is injected into the gap between the core part 7 and the mold previously placed in the mold, for 5 to 300 minutes, for example, Hold for 60 minutes (primary curing).
[0032]
Next, the unit solidified by primary curing is taken out of the mold, and this is held in a heating furnace at 25 to 150 ° C., for example, 70 ° C., for 0 to 24 hours, for example, 10 hours, and further cured (secondary curing). Thereby, the crosslinking reaction of polyurethane is promoted, and the skin portion 8 made of thermosetting urethane rubber having a thickness of about 0.1 to 2 mm is obtained around the core portion 7. The molded C-type unit 6 has platform pieces 61 and 62, and the entire core portion 7 is covered with a resin.
[0033]
(2) Stator blade structure
A method for manufacturing a gas turbine stationary blade structure will be described as an example of the stationary blade structure. Since the gas turbine stationary blade structure is basically the same for both I-type and C-type, the C-type unit will be described here.
[0034]
The platform pieces 61 and 62 of a plurality of adjacent C-type units 6 are assembled in an annular shape to produce a temporary assembly. The outer peripheral portion of the annular temporary assembly is composed of an outer platform, and complementary step portions of the outer platform pieces are connected to each other. The inner periphery comprises an inner platform, and complementary steps of the inner platform pieces are connected to each other. The step portions 63, 63 ′ and 64, 64 ′ for joining the C-type unit are made of rubber or thermosetting resin having rubber elasticity. For this reason, when the step portions 63, 63 ′ and 64, 64 ′ having complementary shapes are overlapped and assembled in an annular shape, the step portions 64, 64 ′ are between the overlapped step portions 63, 63 ′. A repulsive force due to the elastic action of the rubber or rubber-curing thermosetting resin is generated between the units, which prevents the units from joining and coming off. Therefore, it is not necessary to fix the units with an adhesive or the like when connecting the units. For example, tape or the like is wound around the outer peripheral surface of the outer platform 11 formed by combining the outer platform pieces 61, 61 ... and the inner peripheral surface of the inner platform 12 formed by combining the inner platform pieces 62, 62 ... Since it is not necessary to weld and fix while attaching, the number of steps can be reduced correspondingly, and the weight can be reduced.
[0035]
The produced temporary assembly has such a strength that it can be handled. The outer platform and the inner platform of the temporary assembly are attached to the support member, and the temporary assembly is fixed to the fixing member using the fixing member. As the support member, for example, an inner annular support member 80 and an outer annular support member 90 shown in FIGS. 9 and 10 are used. The inner annular support member 80 has a cylindrical portion 83 that can be fitted into the inner peripheral portion of the temporary assembly and flange portions 82 and 84 formed at both ends thereof. A concave portion (receiving portion) 87 having the same thickness as the end portion 17 or slightly narrower than that is formed. A plurality of screw holes 81 are formed in the flange portion (inward flange portion) 84 at the other end. The outer annular support member 90 forms a fan case of a gas turbine engine. The outer annular support member 90 has a cylindrical portion 93 for accommodating the temporary assembly and flange portions formed at both ends thereof, and the inner circumference of the cylindrical portion 93 is the same as the thickness of the one end portion 15 of the outer platform. An annular concave portion (receiving portion) 95 that is slightly narrower than that is formed. A plurality of screw holes 91 are formed in the flange portion 92 on the side where the temporary assembly is inserted. An annular inner fixing member 86 that engages with the inner annular support member 80 includes a recess 87 'that is the same as or slightly narrower than the wall thickness of the one end portion 17' of the inner platform. A plurality of screw holes 81 'are formed. A plurality of screw holes 91 ′ and stopper holes 97 ′ are formed in the annular outer fixing member 96 that engages with the outer annular support member 90.
[0036]
As shown in FIG. 11, the convex portion 17 formed at one end of the inner platform of the temporary assembly is press-fitted into the concave portion (receiving portion) 87 of the inner annular support member 80. Next, the convex portion 17 ′ formed on the other end of the inner platform is press-fitted into the concave portion (receiving portion) 87 ′ of the fixing member 86. Thereafter, the inner annular support member 80 and the inner fixing member 86 are screwed together. 9 and 10, a temporary assembly in which the inner platform is fixed by the inner annular support member 80 and the inner fixing member 86 is inserted into the outer annular support member 90 and formed at one end of the outer platform of the temporary assembly. The formed convex portion 15 is press-fitted into a concave portion (receiving portion) 95 formed on the inner side surface of the outer annular support member 90. Next, after the annular outer fixing member 96 is brought into contact with the convex portion 15 ′ formed at the other end of the outer platform, the flange portion 92 of the outer annular support member 90 and the outer fixing member 96 are screwed together. At that time, in order to prevent the stationary blade structure from rotating, as shown in FIG. 12, the stopper 97 is inserted into the stopper holes 97 ′ formed in at least two places, preferably 3 to 4 places on the outer fixing member 96. Is engaged with a notch 68 formed in the outer platform to position the stationary blade structure.
[0037]
FIG. 13 shows a stationary blade structure fixed by an inner annular support member 80, an outer annular support member 90, an inner fixing member 86, and an outer fixing member 96. In the inner platform of the stationary blade structure, convex portions 17 and 17 ′ at both ends are press-fitted into concave portions (receiving portions) 87 and 87 ′ of the inner annular support member 80 and the inner fixing member 86. In the outer platform of the stationary blade structure, the convex portion 15 at one end is press-fitted into the concave portion (receiving portion) 95 of the outer annular support member 90, the convex portion 15 'at the other end and the outer fixing member 96 are in contact with each other, and the stopper 97 It is positioned by. The flange portion 92 of the outer annular support member 90 and the outer fixing member 96 are screwed together, and the flange portion 84 of the inner annular support member 80 and the inner fixing member 86 are screwed together.
[0038]
In either case of the I-type unit or the C-type unit, it can be similarly attached to the support member. The support member may be made of metal or plastic as long as it has an integral shape.
[0039]
FIG. 14 shows another example in which the stationary blade structure is attached to the gas turbine engine. In this example, the outer platform of the vane structure is attached to the engine member. When engine members are used as the outer annular support member and the inner annular support member, various support methods may be adopted depending on the engine structure in which the stationary blade structure can be incorporated, such as a fan case or an intermediate case. it can. Moreover, it has the advantage that the number of parts can be reduced by using an engine member for a support member in this way.
[0040]
Although the present invention has been described with the above specific examples, the present invention is not limited thereto, and the shape, material, molding conditions, etc. of the unit may be changed without departing from the spirit of the present invention.
[0041]
【The invention's effect】
As described above, according to the present invention, since a unit such as an I-type or a C-type including a core portion and a skin portion integrally formed around the core portion by casting is used, the vane and the platform are remarkably fixed. It is strong. Further, the skin portion is formed of rubber or rubber-elastic thermosetting resin, so that it has excellent wear resistance and can be molded at a low temperature, so that thermal shrinkage is small and dimensional accuracy is high.
[0042]
In the present invention, the stationary blade structure unit is assembled in an annular shape by the elastic action of rubber or rubber-curing thermosetting resin to form a temporary assembly, and the temporary assembly is attached to the support member to form the stationary blade structure. Therefore, the total number of processing steps can be reduced, and the manufacturing cost can be reduced. In addition, a gas turbine stationary blade structure having a uniform shape is obtained, and since the unit is not fixed, only the damaged unit can be replaced. In addition, since the melt viscosity of the thermosetting resin is low and the thickness of the skin portion can be reduced, the degree of freedom in blade design is great, and the dimensional accuracy of the stationary blade structure is good. Furthermore, since winding with a tape is not required for assembly, the stationary blade structure can be reduced in weight.
[Brief description of the drawings]
FIG. 1 is a front view showing an example of a stationary blade structure including an I-type unit.
FIG. 2 shows an example of an I-type unit constituting a stationary blade structure, (a) is a schematic perspective view thereof, and (b) is a front view thereof.
FIG. 3 is a partially broken perspective view showing a structure of an I-type unit.
FIG. 4 is a perspective view showing an example of a core portion of an I-type unit.
FIG. 5 is a cross-sectional view of the I-type unit shown in FIG. 3 taken along the line AA.
FIG. 6 shows an example of a C-type unit, where (a) is a perspective view thereof, and (b) is an enlarged view of a portion X of (a). (c) is a front view, (d) is a bottom view, and (e) is a plan view of a C-type unit having a notch.
FIG. 7 is a perspective view showing an example of a core portion of a C-type unit.
FIG. 8 is a perspective view showing a state in which a plurality of C-type units are combined.
FIG. 9 is a longitudinal sectional view showing a state before the temporary assembly of the stationary blade structure is attached to the inner annular support member and the outer annular support member.
FIG. 10 is a perspective view showing how a temporary assembly of a stationary blade structure is attached to an inner annular support member and an outer annular support member.
FIG. 11 is a perspective view showing how the inner platform of the temporary assembly is fixed by the inner annular support member and the inner fixing member.
FIG. 12 is a partial perspective view showing a state in which the outer platform of the temporary assembly is fixed by the outer annular support member and the outer fixing member.
FIG. 13 is a longitudinal sectional view showing an example in which a stator blade structure is attached to an inner annular support member and an outer annular support member.
FIG. 14 is a longitudinal sectional view showing another example in which a stationary blade structure is attached to a gas turbine engine.
[Explanation of symbols]
1 ... Gas turbine stationary blade structure comprising an I-type unit
11 ... Outside platform
12 ... Inner platform
13 ... Vane
2 ... I-type unit
21 ... Outer platform piece
22 ... Inner platform piece
3 ... I-type core
31 ... Web section
32, 33 ... Flange
4 ... I-type skin
6 ... C type unit
53 ... Vane
61 ・ ・ ・ Outer platform piece
62 ... Inner platform piece
7 ... C-shaped core
71 ・ ・ ・ Web section
72, 73 ... Flange
8 ... C-type skin
15, 15 '・ ・ ・ Outer platform convex part
17, 17 '・ ・ ・ Inner platform convex part
80 ... Inner annular support member
83 ... Cylinder part
82, 84 ... Flange
87, 87 '... recess (receiving part)
90 ... Outer annular support member
93 ... Cylinder part
92, 94 ... Flange
95 ・ ・ ・ Recess (receiving part)
86 ・ ・ ・ Inner fixing member
96 ・ ・ ・ Outer fixing member
97 ・ ・ ・ Stopper

Claims (10)

A method of manufacturing a stator vane structure having a plurality of vanes, an outer platform, and an inner platform, wherein (1) an outer platform piece is formed by integrally connecting flange portions to both ends of a web portion constituting the vane. And forming a core portion having an inner platform piece, and integrally forming a skin portion made of a thermosetting resin having rubber or rubber elasticity on the surface of the core portion, thereby forming a stationary blade structure unit. 2) The outer platform piece and the inner platform piece of the adjacent stationary blade structure unit are joined to form an annular temporary assembly, and (3) the outer platform and the inner side of the temporary assembly. Each platform is attached to the outer annular support member and the inner annular support member, and (4) each of the outer annular support members. The temporary assembly is fixed to the outer fixing member and the inner fixing member by using an outer fixing member and an inner fixing member that are engaged with the member and the inner annular support member. Production method. The method for manufacturing a stationary blade structure according to claim 1, wherein a thermosetting urethane rubber is used as the rubber or a thermosetting resin having rubber elasticity. 3. The method for manufacturing a stationary blade structure according to claim 1, wherein each of the outer platform piece and the inner platform piece has a connecting step at each end, and the step is complementary to a unit adjacent to the step. A method for manufacturing a stationary blade structure, wherein the outer platform piece and the inner platform piece are joined to each other by an elastic action of the rubber or rubber-curing thermosetting resin on a step portion having an arbitrary shape. . The method for manufacturing a stationary blade structure according to any one of claims 1 to 3, wherein the outer annular support member and the inner annular support member have the same thickness as one end of the outer platform and the inner platform, respectively. A receiving portion having a slightly narrower width, and press-fitting one end of each of the outer platform and the inner platform into the receiving portion of the outer annular support member and the inner annular support member. A method of manufacturing a stationary blade structure, characterized by comprising: The method for manufacturing a stationary blade structure according to any one of claims 1 to 4, wherein the outer annular support member has a receiving portion on an inner surface to which an outer platform of the temporary assembly can be attached. A method for manufacturing a stationary vane structure. In the manufacturing method of the stationary blade structure according to any one of claims 1 to 5, the outer fixing member and / or the inner fixing member is annular, and has a stopper protruding on one surface thereof. A method of manufacturing a stationary blade structure, wherein the temporary assembly is fixed at a predetermined position by combining the stopper with a notch formed in the outer platform and / or the inner platform of the temporary assembly. . The method for manufacturing a stationary blade structure according to any one of claims 1 to 6, wherein the core portion is formed of a laminated body of a fiber-reinforced prepreg material or a light metal. The method for manufacturing a stationary blade structure according to claim 7, wherein carbon fiber polyether ether ketone or carbon fiber reinforced epoxy resin is used as the fiber reinforced prepreg material. The method for manufacturing a stationary blade structure according to claim 7, wherein an aluminum alloy or a magnesium alloy is used as the light metal. The method for manufacturing a stationary blade structure according to any one of claims 1 to 9, wherein the flange portion of the core portion is formed by bending both ends of the laminate of the fiber-reinforced prepreg material. A method for manufacturing a wing structure.

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