Ceramic matrix composite blade forming die

Abstract

A ceramic matrix composite blade forming mold comprises a blade back mold, a blade basin mold and a front edge module. Wherein the front edge module comprises an inner molded surface for molding the front edge of the blade preform and an arc-shaped outer molded surface which is propped against the blade back mold and the blade basin mold; the blade back mold and the blade basin mold have an assembling state that the blade back mold and the blade basin mold abut against the outer molded surface and the tail edge side is opened and a mold closing state that the tail edge side is closed, and the blade back mold and / or the blade basin mold can rotate with the front edge module as the axis so as to be switched to the mold closing state from the assembling state; and in a mold closing state, the blade back mold, the blade basin mold and the front edge module provide wall surfaces for forming a blade body of the blade prefabricated body. According to the ceramic-based composite material blade forming mold, a blade body can be formed in a rotary mold closing mode, wrinkles of a composite material laying layer in the mold closing process are avoided, and the surface quality of a finished product is improved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aero-engine, concretely relates to a ceramic matrix composite vane forming die. BACKGROUND

[0002] Compared with traditional metal materials, ceramic matrix composites (CMC) have the performance advantages of high temperature resistance, corrosion resistance and low density, and have been widely used in the manufacture of hot end parts of aero-engines, such as turbine and compressor blades. Ceramic matrix composite vane usually has multiple layers of composite material to form a preform, and then is formed by curing and infiltration. In this process, the accuracy of the position and shape of the lay-up has a significant impact on the surface precision of the final product. However, the ceramic matrix composite lay-up has poor ductility, and when the vane morphology is complex, it is easy to form lay-up defects such as wrinkles, which affects the product quality. Therefore, providing a forming die capable of improving the forming quality and reducing lay-up defects has a positive significance for improving the production efficiency of ceramic matrix composite vane. SUMMARY

[0003] The utility model discloses a ceramic matrix composite vane forming die, which improves the surface precision of the ceramic matrix composite vane.

[0004] According to an embodiment of the utility model, a ceramic matrix composite vane forming die is provided, which has a cavity for forming a vane preform and includes a blade body forming section. The blade body forming section includes a blade back mold, a blade basin mold and a leading edge module. Wherein:

[0005] The leading edge module includes an inner profile surface and an outer profile surface. The inner profile surface is the outer profile forming surface of the leading edge of the vane preform, and the outer profile surface is configured as a circular arc surface.

[0006] The blade back mold includes a blade back forming surface and a blade back leading edge arc surface. The blade back leading edge arc surface cooperates with part of the outer profile surface.

[0007] The blade basin mold includes a blade basin forming surface and a blade basin leading edge arc surface. The blade basin leading edge arc surface cooperates with part of the outer profile surface.

[0008] The ceramic matrix composite vane forming die has an assembled state and a closed die state. In the assembled state, the blade back mold and the blade basin mold abut the outer profile surface of the leading edge module respectively, and one end of the tail edge of the vane preform is opened for forming. The blade back mold and / or the blade basin mold can rotate around the leading edge module, so that one end of the tail edge of the vane preform for forming is closed by the blade back mold and the blade basin mold, so as to switch from the assembled state to the closed die state.

[0009] In the closed state, the back mold, the platform mold and the leading edge module jointly provide a wall surface of the cavity for forming the airfoil of the blade preform.

[0010] The forming mold can realize the closing of the blade preform in a rotary closing mode, so that the airfoil layers are gradually compacted from the leading edge to the trailing edge, thereby reducing the risk of wrinkles at the leading edge of the blade preform and improving the forming quality of the blade preform.

[0011] Further, in some embodiments, the outer surface of the leading edge module is configured as a ruled surface.

[0012] The ruled surface is beneficial to reduce the friction of the outer surface of the leading edge module and facilitate the rotary closing.

[0013] Further, in some embodiments, the back mold and / or the platform mold is provided with a relief area, which extends away from the blade preform by the leading edge module, and which provides a mating surface of the back mold and the platform mold in the assembled state.

[0014] The relief area can prevent interference between the back mold and the platform mold and provide space for the rotary closing.

[0015] Further, in some embodiments, the back mold and the platform mold each include a plurality of sub-components arranged in layers along the blade height direction of the blade preform.

[0016] For a blade preform with a complex profile along the blade height direction, the layered mold facilitates the demolding of the parts after forming.

[0017] Further, in some embodiments, the back mold and the platform mold each include an interlayer fixing mechanism for fixedly connecting the sub-components of the back mold and the platform mold together along the blade height direction of the blade preform.

[0018] Further, in some embodiments, the interlayer fixing mechanism uses a fastening bolt.

[0019] Further, in some embodiments, the back mold and the platform mold each include a plurality of the interlayer fixing mechanisms, at least part of the interlayer fixing mechanisms are arranged on one side of the back mold and the platform mold at the leading edge of the blade preform, and at least part of the interlayer fixing mechanisms are arranged on one side of the back mold and the platform mold at the trailing edge of the blade preform.

[0020] Further, in some embodiments, a closing fixing device is further included, which locks and fixes the back mold and the platform mold in the closed state.

[0021] Further, in some embodiments, the mold clamping fixture is a clamping bolt.

[0022] Further, in some embodiments, in the mold clamping state, the trailing edge cavity is formed on the trailing edge side of the blade preform by the blade back mold and the blade platform mold. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a schematic diagram of a turbine blade structure in an embodiment;

[0024] Figure 2 is a schematic diagram of an assembled state of a ceramic matrix composite blade forming mold in an embodiment;

[0025] Figure 3 is a schematic diagram of a mold clamping state of a ceramic matrix composite blade forming mold in an embodiment;

[0026] Figure 4 is a schematic diagram of a parameter design of a leading edge module in an embodiment;

[0027] Figure 5 is a schematic diagram of a leading edge module in an embodiment;

[0028] Figure 6a 、 Figure 6b 、 Figure 6c is a schematic diagram of a rotating mold clamping process in an embodiment.

[0029] Meaning of reference signs:

[0030] 1 - turbine blade; 11 - leading edge line; 12 - blade platform; 13 - blade back; 14 - trailing edge; 15 - cavity; 2 - blade body forming section; 21 - leading edge module; 211 - inner profile surface; 212 - outer profile surface; 213 - transition surface; 22 - blade back mold; 221 - blade back mold leading edge curved surface; 23 - blade platform mold; 24 - interlayer bolt; 25 - mold clamping bolt; 26 - trailing edge cavity; 27 - avoidance area; 3 - blade body preform.

[0031] The above drawings are intended to make a detailed description of the present application, so that those skilled in the art can understand the technical concept of the present application, and are not intended to limit the present application. In order to express simply, the above drawings only schematically draw the structure related to the technical features of the present application, and do not draw the complete structure and all details strictly according to the actual proportion. DETAILED DESCRIPTION

[0032] The present application will be further described in detail below by specific embodiments in combination with the drawings.

[0033] Reference to an "embodiment" herein means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase that the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of one another. Those skilled in the art will recognize from the disclosure herein that substitutions of elements from one embodiment to another can be made without departing from the scope of the application.

[0034] In the description of the application, unless otherwise clearly specified and limited, the technical terms "mounting", "connection", "connecting" and the like should be understood in a broad sense, for example, they can be movable connection, fixed connection or integral. For those skilled in the art, the specific meaning of the above terms in the embodiments of the application can be understood according to the specific circumstances.

[0035] In the description of the application, the terms indicating the orientation or position relationship such as "upper", "lower", "left", "right", "transverse", "longitudinal", "height", "length", "width" and the like are intended to accurately describe the embodiments and simplify the description, and are not intended to limit the parts or structures involved to have a specific orientation, be mounted or operated in a specific orientation, and cannot be understood as limiting the embodiments herein.

[0036] In the description of the application, the terms "first", "second" and the like are only used to distinguish different objects, and cannot be understood as indicating relative importance or limiting the number, specific order or primary and secondary relationship of the described technical features. In the description of the application, "a plurality of" means at least two.

[0037] The hot end components of an aero-engine or a gas turbine need to withstand high environmental temperature. For high-temperature-resistant blades, the use temperature and service performance of traditional high-temperature alloy materials have reached the limit under the condition of using traditional cooling technology and thermal barrier coating technology. Ceramic matrix composites (CMC) have the advantages of high-temperature resistance, corrosion resistance and low density, and become an excellent choice for hot end components such as turbine and compressor blades.

[0038] To improve the working efficiency of an aero-engine or a gas turbine, the hot end blade structure often has a complex aerodynamic shape.

[0039] A ceramic matrix composite component is usually formed by laminating a plurality of composite material layers, and then performing subsequent solidification and infiltration work. The lamination accuracy greatly affects the surface precision of the final product. After lamination is completed, mold pressing treatment is needed, but the extensibility of the ceramic matrix composite lamination layer is poor, and there are difficulties in lamination and mold pressing of complex surfaces. Wrinkles are easily formed during mold closing, which affects the surface quality of the finished product.

[0040] In order to solve the above problems, the embodiment of the utility model provides a ceramic matrix composite blade forming die, through the rotary die combining mode, effectively solve the surface quality defects such as composite material layer folding in the forming process.

[0041] In one embodiment, the ceramic matrix composite turbine blade 1 structure is as shown in Figure 1 The turbine blade longitudinal two ends are edge plates 16, and the two edge plates 16 are a blade body between them, the blade body has a leading edge line 11 and a trailing edge 14, and an internal cavity 15 is formed, the leading edge line 11 is the collection of the most forward end points of the blade on all height sections, and in order to improve the aerodynamic efficiency, the leading edge line 11 usually has a certain arc in the blade height direction. The blade body has a blade basin 12 and a blade back 13, wherein the blade basin 12 is compressed in the working state of the turbine blade 1, and the profile structure thereof is concave; correspondingly, the profile structure of the blade back 13 is convex. When forming and manufacturing, the edge plate 16 is integrally formed into a large curvature arc surface structure, and the forming is relatively simple; due to the complex structure of the blade body, a special forming die needs to be provided for the blade body to solve the forming problems such as layer folding.

[0042] As shown in Figure 2 The ceramic matrix composite blade forming die provides a cavity for blade preform forming, and the die has a blade body forming section 2, the blade body forming section 2 includes a leading edge module 21, a blade back die 22 and a blade basin die 23, in combination Figure 5 The leading edge module 21 includes an inner profile surface 211 and an outer profile surface 212, the inner profile surface 211 is the outer contour forming surface of the leading edge of the blade body preform 3, and the outer profile surface 212 is a circular arc surface. The blade back die 22 includes a blade back forming surface and a blade back die leading edge arc surface 221, and the blade basin die 23 includes a blade basin forming surface and a blade basin leading edge arc surface, and the blade back die leading edge arc surface 221 and the blade basin leading edge arc surface are matched with part of the outer profile surface 212 respectively.

[0043] The ceramic matrix composite blade basin forming die has an assembled state as shown in Figure 2 and a die combining state as shown in Figure 3 In the assembled state, the leading edge module 21 abuts against the leading edge of the blade body preform 3, and the inner profile surface 211 defines the profile surface of the leading edge of the blade body preform 3; the blade back die 22 and the blade basin die 23 abut against the outer profile surface 212 of the leading edge module 21 respectively, and the tail edge one end of the blade back die 22 and the blade basin die 23 is open. The blade back die 22 and / or the blade basin die 23 can rotate around the leading edge module 21 with the leading edge module 21 as the shaft, so that the tail edge one end is closed, so as to switch from the assembled state as shown in Figure 2 to the die combining state as shown in Figure 3 In the die combining state, the leading edge module 21, the blade back die 22 and the blade basin die 23 jointly provide the wall surface of the cavity for the forming of the blade body preform 3.

[0044] In a preferred embodiment, the outer surface 212 of the leading edge module 21 is configured as a ruled surface, which can directly serve as a pivot point to reduce structural design complexity and rotational friction. Figure 4 As shown, the leading edge module 21 needs to ensure that it can wrap around the leading edge line 11 of the blade at different blade height positions. The most concave point of the leading edge line 11 along the blade height direction (the tangent point between the leading edge line 11 and the vertical plane) can be selected as the shape boundary of the leading edge module 21 for design. Furthermore, the projection of the leading edge module 21 in the horizontal plane should wrap around the leading edge within all height sections, while having a minimum wall thickness d to meet strength requirements. In the modeling software, by stretching the shape boundary of the leading edge module 21 along a fixed direction and trimming it using the inner and outer design surfaces of the blade, the inner surface 211 can be obtained to fit the leading edge of the blade preform 3, and the outer surface 212 can be a ruled surface structure, as shown below. Figure 5 As shown. In a further preferred embodiment, as Figure 6b As shown, a smooth arc transition surface 213 is provided at the position where the outer surface 212 of the leading edge module 21 connects with the blade preform 3. The transition surface 213 can reduce the risk of wrinkles forming on the parting line of the blade preform 3 at the boundary of the leading edge module 21.

[0045] In a preferred embodiment, such as Figure 3 As shown, a clearance area 27 is provided between the leaf back mold 22 and the leaf base mold 23. In one embodiment, as... Figure 2 and Figure 3 As shown, the clearance area 27 is formed by the convex arc surface on the blade back mold 22 and the concave arc surface on the blade basin mold 23. In the assembled state, the convex surface of the blade back mold 22 and the concave surface of the blade basin mold 23 abut against each other to provide space for the tail edge to open. In the closed state, the concave and convex surfaces separate to form the clearance area 27. The clearance area 27 prevents the blade back mold 22 and the blade basin mold 23 from interfering with each other in the assembled state and provides space for rotation and mold closing.

[0046] In a preferred embodiment, the blade back mold 22 and the blade base mold 23 are respectively configured as layered structures composed of multiple layers of sub-components, with each layer of sub-components stacked along the blade height direction. In a further preferred embodiment, an inter-layer fixing mechanism is provided between the sub-components to fix them together, allowing the sub-components of the blade back mold 22 and the blade base mold 23 to rotate as a whole during the mold closing process. In one embodiment, such as Figure 2 and Figure 3 As shown, the interlayer fixing mechanism is an interlayer bolt 24, which fastens each layer of sub-components together. In a further preferred embodiment, the blade back mold 22 and the blade basin mold 23 are each provided with an interlayer bolt 24 on the leading edge side and the trailing edge side of the blade preform 3, respectively.

[0047] In a preferred embodiment, a mold closing fixing device is arranged between the blade back mold 22 and the blade pan mold 23, which can lock and fix the blade back mold 22 and the blade pan mold 23 in the closed state so as to cure and form the blade preform. In a further preferred embodiment, as shown in Figure 2 and Figure 3 , the mold closing fixing device is configured as a mold closing bolt 25.

[0048] In a preferred embodiment, as shown in Figure 3 , in the closed state, the blade back mold 22 and the blade pan mold 23 form an incomplete gap, i.e. a trailing edge cavity 26, on the trailing edge side of the blade preform 3, which communicates to the area of the cavity for forming the trailing edge of the blade preform 3, so that the excess composite material layer during the mold closing process can be accommodated by the trailing edge cavity 26, thereby reducing the risk of wrinkle formation and further improving the surface quality of the blade preform 3.

[0049] In one embodiment, the process of forming the blade preform 3 using the ceramic matrix composite blade forming mold provided in the above embodiments is as follows:

[0050] First, according to the design requirements, the blade preform 3 is obtained by laying up composite material layers.

[0051] Next, the inner profile surface 211 of the leading edge module 21 is attached to the leading edge of the blade preform 3 and fixed on a support frame (not shown); at the same time, the blade back mold 22 and the blade pan mold 23 are assembled so that they abut each other at the avoidance area 27 and jointly abut the outer profile surface 212 of the leading edge module 21, and the blade pan side of the blade preform 3 is compacted by the blade pan mold 23. The blade back mold 22 is rotated around the leading edge module 21, and during the rotation process, the blade back mold front arc surface 221 of the blade back mold 22 keeps abutting the outer profile surface 212 of the leading edge module 21, so that the blade back mold 22 gradually attaches from the leading edge to the trailing edge of the blade preform, as shown in Figure 6a , Figure 6b and Figure 6c , the blade back mold 22 extrudes the wrinkles formed on the blade back side of the blade preform 3 from the leading edge to the trailing edge during the mold closing process, and when the blade back mold 22 and the blade pan mold 23 are completely closed, the wrinkles are extruded into the trailing edge cavity 26; the blade back mold 22 and the blade pan mold 23 are locked by the mold closing bolt 25, and the subsequent laying up is completed according to the part design, and the whole is cured and formed, finally the shape of the trailing edge area is modified by machining to remove the wrinkle defects formed by the trailing edge cavity 26, and the forming process is completed.

[0052] The purpose of the above embodiments is to make further detailed description of the utility model in combination with the drawings, so that the technical concept of the utility model can be understood by the person skilled in the art. Within the scope disclosed by the utility model, the optimization or equivalent replacement of the parts structure involved, and the combination of the implementation manners in different embodiments without structural and principle conflicts, all fall within the protection scope of the utility model.

Claims

1. A ceramic matrix composite blade forming mold having a cavity for forming a blade preform, characterized by, The blade body forming section comprises a blade back mold, a blade basin mold and a leading edge module; wherein, The leading edge module comprises an inner profile surface and an outer profile surface, the inner profile surface is an outer profile forming surface of the blade preform leading edge, and the outer profile surface is configured as a circular arc surface; The blade back mold comprises a blade back forming surface and a blade back leading edge arc surface, and the blade back leading edge arc surface cooperates with part of the outer profile surface; The blade basin mold comprises a blade basin forming surface and a blade basin leading edge arc surface, and the blade basin leading edge arc surface cooperates with part of the outer profile surface; The ceramic matrix composite blade forming mold has an assembled state and a closed mold state, in the assembled state, the blade back mold and the blade basin mold abut the outer profile surface of the leading edge module respectively, for forming an open end of the blade preform trailing edge; the blade back mold and / or the blade basin mold can rotate around the leading edge module, so that the blade back mold and the blade basin mold close the end for forming the blade preform trailing edge, to switch from the assembled state to the closed mold state; In the closed mold state, the blade back mold, the blade basin mold and the leading edge module jointly provide the wall surface of the cavity for forming the blade body of the blade preform.

2. The ceramic matrix composite vane forming mold of claim 1, wherein, The outer profile surface of the leading edge module is configured as a straight surface.

3. The ceramic matrix composite vane forming mold of claim 1 or 2, wherein, The blade back mold and / or the blade basin mold are provided with a relief area, the relief area extends away from the blade preform by the leading edge module, and the relief area provides a cooperation surface of the blade back mold and the blade basin mold in the assembled state.

4. The ceramic matrix composite vane forming mold of claim 1 or 2, wherein, The blade back mold and the blade basin mold respectively comprise a plurality of sub-components, which are arranged in layers along the blade height direction of the blade preform.

5. The ceramic matrix composite vane forming mold of claim 4, wherein, The blade back mold and the blade basin mold respectively comprise an interlayer fixing mechanism, which fixes and connects the sub-components of the blade back mold and the blade basin mold together along the blade height direction of the blade preform.

6. The ceramic matrix composite vane forming mold of claim 5, wherein, The interlayer fixing mechanism adopts a fastening bolt.

7. The ceramic matrix composite vane forming mold of claim 5, wherein, The blade back mold and the blade basin mold respectively comprise a plurality of interlayer fixing mechanisms, at least part of the interlayer fixing mechanisms are arranged on one side of the blade back mold and the blade basin mold at the leading edge of the blade preform, and at least part of the interlayer fixing mechanisms are arranged on one side of the blade back mold and the blade basin mold at the trailing edge of the blade preform.

8. The ceramic matrix composite vane forming mold of claim 1 or 2, wherein, Further comprising a closed mold fixing device, which locks and fixes the blade back mold and the blade basin mold in the closed mold state.

9. The ceramic matrix composite vane forming mold of claim 8, wherein, The closed mold fixing device is a fixing bolt.

10. The ceramic matrix composite vane forming mold of claim 1 or 2, wherein, In the closed mold state, the blade back mold and the blade basin mold form a trailing edge cavity on one side of the trailing edge of the blade preform, and the trailing edge cavity is communicated to the cavity for forming the trailing edge of the blade preform.

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