Ultrafast laser drilling clamp for aero-engine blade and clamping method

Abstract

The invention provides an ultrafast laser drilling clamp for an aero-engine blade and a clamping method. The clamp comprises a clamp base, a first side plate, a second side plate, a compression expansion assembly and an air blowing unit, the side plates are connected to the clamp base through bolts, the compression expansion assembly is installed on the side plates and composed of compression bolts, movable conical blocks, movable clamping jaws and rubber sleeves, and the air blowing unit is connected and fixed to the side plates through threaded structures. The end face and the inner wall of the blade body are positioned and clamped through mounting and dismounting of the first side plate and the second side plate, precise clamping of the ceramic matrix composite guide blade is achieved, the ultrafast laser drilling requirements of different parts of the guide blade are met, the air blowing unit is located in an inner cavity of the guide blade, air is blown to a hole outlet area in the ultrafast laser drilling process, and the hole drilling efficiency is improved. The device has the functions of cooling an outlet area and blowing away ablated products, high-quality drilling is achieved, and meanwhile heat damage in the blade is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of ultrafast laser processing, and in particular to an ultrafast laser hole-making fixture and a clamping method for aircraft engine blades. Background Art

[0002] As aircraft performance requirements become increasingly stringent, the thrust-to-weight ratio of aircraft engines continues to increase, resulting in increasingly higher inlet temperatures for aircraft engine blades. Currently, the temperature before the engine turbine has exceeded 1900K, which far exceeds the temperature resistance of high-temperature alloy materials. Ceramic-based composites are a new type of thermal structural material that possesses the performance requirements of aircraft engine structural materials, such as high temperature resistance, high specific strength, and high specific stiffness. They are an important material for the preparation of modern aircraft engine blades. The use of film hole cooling technology can further increase the inlet temperature of ceramic-based composite blades, ensuring reliable operation of the blades in high-temperature environments. The pulse duration of ultrafast lasers is extremely short (<10ps), and there is sufficient cooling time before the next pulse arrives, with almost no heat-affected zone. Therefore, high-resolution, high-quality micromachining can be performed on almost all solid materials with minimal thermal damage. It is an effective method for precision machining of film holes on ceramic-based composite blades.

[0003] Ceramic-matrix composite guide vanes are manufactured using a near-net-shape process, which can lead to inconsistent blank profile deformation and deviations from the theoretical design model. Existing fixture patents cannot meet positioning and clamping requirements. To achieve ultrafast laser processing of large numbers of film holes (with diameters ranging from 0.4mm to 0.8mm) in locations such as the guide vane lip and blade body, specialized fixtures are required. Existing patents disclose fixtures for machining film holes in metal guide vanes. Patent (CN114101822A) discloses a device for machining film holes in turbine blades. This device uses the blade end and back faces as positioning points, and uses locking bolts and screws inserted through the blade process holes for securement and clamping. This allows for machining of several film holes on the blade in a single clamping operation. Patent (CN103894733A) discloses a fixture for laser machining film holes in turbine guide vanes. This fixture uses the top point of the lip as a positioning point and uses a clamping assembly to clamp the ridges on the lip. When machining film holes on the blade body, the auxiliary support assembly at the corresponding location must be removed.

[0004] At present, ultrafast laser hole making of ceramic matrix composite guide vanes has the following shortcomings:

[0005] Ceramic-matrix composite (CMC) guide vanes are mostly manufactured using an integrated molding process. Due to the relatively low stiffness of the lip plate, lip plate deformation and assembly errors can occur during the integrated manufacturing of the lip plate and blade body. The positioning and clamping areas of existing laser hole-making fixtures are located on the lip plate, which can easily lead to positioning errors and affect the positional accuracy of the holes. Furthermore, CMCs are a new type of material. When ultrafast lasers are used to create small holes in CMCs, a large amount of ablation products is generated, making chip removal difficult. These ablation products accumulate below the hole and on the exit surface, impacting further processing of the material with the ultrafast laser and resulting in poor hole quality. The ablation products, after being irradiated by the laser, reach very high temperatures, further damaging the exit surface quality and causing ablation defects on the inner surface of the blade. To achieve precise machining of the air film holes in CMC guide vanes, it is urgently necessary to develop a dedicated ultrafast laser hole-making fixture and clamping method. Summary of the Invention

[0006] In response to the technical problems raised above, an ultrafast laser hole-making fixture and clamping method for aircraft engine blades are provided. The fixture consists of a fixture base, a first side plate, a second side plate, a compression and expansion assembly, and a blowing unit, which can achieve precise positioning, clamping, and blowing protection during the processing process.

[0007] The technical means adopted in the present invention are as follows:

[0008] A fixture for ultrafast laser hole making of aircraft engine blades, the fixture is used for clamping the ultrafast laser processing of air film holes on the upper edge plate, blade body and lower edge plate of a ceramic-based composite material guide vane; it comprises a fixture base, a first side plate, a second side plate, a compression and expansion component and a blowing unit, the fixture base has a connecting flange, the first side plate and the second side plate are mounted on the fixture base, the positioning of the blade body end face is achieved based on the first side plate and the second side plate, the compression and expansion component and the blowing unit are mounted on at least one of the side plates, the compression and expansion component is used to achieve positioning and compression of the inner wall of the blade body, and achieve precise clamping of the ceramic-based composite material guide vane, the blowing unit is located in the inner cavity of the guide vane, and a plurality of blowing holes are provided on the blowing unit, through which high-speed and high-pressure cooling gas is ejected to achieve blowing cooling of the hole outlet area during the ultrafast laser hole making process.

[0009] Furthermore, the first side plate and the second side plate both have threaded holes for installing the compression expansion assembly and the blowing unit, and grooves that fit with the ridges of the edge plate. The surfaces of the first side plate and the second side plate are the fitting surfaces of the blade end face, thereby realizing the positioning of the blade end face.

[0010] Furthermore, the first side plate and the second side plate are detachably mounted on the fixture base, and the ultrafast laser hole making fixture can complete the processing of the air film holes in all areas of the guide vane by one positioning. The first side plate and the second side plate both have the function of independent positioning and clamping, and the side plates at the corresponding positions can be selectively removed to realize the clamping of the upper edge plate and the lower edge plate, thereby meeting the ultrafast laser hole making of the air film holes in the corresponding parts.

[0011] Furthermore, the compression and expansion assembly is located in the inner cavity of the guide vane, and includes a compression bolt, a movable cone block, a movable claw and a rubber sleeve. The compression bolt and the movable cone block are located in the middle of the movable claw. The movable claw is composed of several separate movable blocks. The inner wall is provided with a conical hole that cooperates with the movable cone block, and the outside is covered with a rubber sleeve. The rubber sleeve realizes the tightening of the movable claw in the initial state. The compression bolt is connected to the side plate. By tightening the compression bolt, the movable cone block is moved toward the side plate, thereby driving the movable claw and the rubber sleeve to expand and contact with the inner cavity wall of the blade to achieve fixation and expansion of the inner wall of the blade body.

[0012] Furthermore, the air inlet end of the air blowing unit has a threaded structure on the outside, which is connected to the side plate. The structure of the air blowing cooling unit and the specifications and shapes of the air vents opened thereon are adjusted according to the shape of the inner cavity of the guide vane.

[0013] Furthermore, according to the position and processing requirements of the guide vane air film holes, the shape of the blowing holes includes at least one of a round hole, a square hole, and an inclined hole, and the arrangement of the blowing holes includes an array with equal or unequal distances along the axial direction, and an equal angle or variable angle arrangement along the radial direction.

[0014] The present invention also discloses a method for clamping an ultrafast laser hole-making fixture for an aero-engine blade, comprising the following steps:

[0015] Step 1: Processing the air film hole on the upper edge plate: Use bolts to install the first side plate on the fixture base, place the compression expansion assembly of the first side plate in the inner cavity I of the guide vane, and press the blade end surface I against the plane of the first side plate to limit the guide vane. Then, press the ridge of the lower edge plate against the side of the groove of the first side plate to assist in limiting the angle of the guide vane. Tighten the clamping bolts so that the movable claws and rubber sleeves fit against the inner wall of the guide vane air inlet to complete the positioning and clamping of the guide vane. Connect the fixture base to the machine tool workbench, and realize five-axis linkage ultrafast laser processing of the hole in the upper edge plate by rotating the workbench.

[0016] Step 2: Processing the air film holes on the blade: Install the second side plate on the fixture base, install the compression expansion assembly on the second side plate, fit the plane of the second side plate to the blade end surface II, fit the side wall of the second side plate groove to the ridge of the upper edge plate, tighten the compression bolts to complete the auxiliary positioning of the blade, blow air to the outlet area of ​​the blade film hole through the blowing unit, and control the spatial position of the ultrafast laser beam through the five-axis linkage of the machine tool worktable to achieve ultrafast laser processing of the blade film hole;

[0017] Step 3: Process the air film holes on the lower edge plate: Remove the first side plate. Before removing the first side plate, tighten the clamping bolts on the second side plate again so that it can independently complete the positioning and clamping of the guide vanes. Rotate the machine tool worktable so that the surface of the lower edge plate faces upward, and use ultrafast laser to process the air film holes on the lower edge plate as required.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] 1. The ultrafast laser hole-making fixture of the present invention includes a fixture base, a first side plate, a second side plate, a compression and expansion assembly, and an air blowing unit. The processing of the air film holes in all areas of the guide vane can be completed by positioning once. The first side plate and the second side plate both have independent positioning and clamping functions. The side plates at corresponding positions can be selectively removed to achieve the clamping of the upper and lower edge plates, meeting the ultrafast laser hole-making requirements of the air film holes at corresponding locations. The side plates are easy to disassemble and assemble, which can improve the processing efficiency while meeting the processing procedures.

[0020] 2. The blowing unit of the present invention is located in the inner cavity of the guide vane and is connected to the side plate by threads. The blowing unit has a series of blowing holes. The blowing holes emit high-speed and high-pressure cooling gas. During the ultrafast laser hole making process, the air is blown towards the hole outlet area, cooling the outlet area and blowing away the ablation products, thereby achieving high-quality hole making while avoiding thermal damage inside the blade.

[0021] 3. The compression expansion assembly in the present invention is composed of a compression bolt, a movable cone block, a movable claw and a rubber sleeve. By tightening the compression bolt, the movable claw and the rubber sleeve are expanded, and the inner wall of the blade is fixed and tightened, thereby improving the positioning accuracy, avoiding the positioning error caused by the deformation of the edge plate when positioning the edge plate, and improving the position accuracy of the hole making. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0023] Figure 1Schematic diagram of the fixture structure and guide vane clamping according to an embodiment of the present invention;

[0024] Figure 2 Schematic diagram of the guide vane structure in an embodiment of the present invention;

[0025] Figure 3 This is a structural diagram of a compression expansion assembly in an embodiment of the present invention;

[0026] Figure 4 The shape of the air blowing pipe of the air blowing unit in the embodiment of the present invention;

[0027] Figure 5 The blowing hole shape of the blowing unit in the embodiment of the present invention;

[0028] Figure 6 Schematic diagrams of processing the upper and lower edge plates and the blade film holes in an embodiment of the present invention, wherein (a), (b), and (c) are schematic diagrams of processing the upper edge plate, the blade body, and the lower edge plate, respectively.

[0029] In the figure: 1. Clamp base; 2. Second side panel; 3. First side panel; 4. Blowing unit; 5. Compression expansion assembly; 51. Compression bolt; 52. Movable cone block; 53. Movable claw; 54. Rubber sleeve; 6. Connecting bolt; 7. Ceramic matrix composite material guide vane; a. Lower edge plate; b. Blade body; c. Upper edge plate; d1. Guide vane inner cavity I; d2. Guide vane inner cavity II; e1. Blade body end surface I; e2. Blade body end surface II; f1. Lower edge plate ridge; f2. Upper edge plate ridge. DETAILED DESCRIPTION

[0030] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0031] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0032] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, operations, devices, components and / or combinations thereof.

[0033] Unless otherwise specifically stated, the relative arrangement of the parts and steps, numerical expressions and numerical values ​​described in these embodiments do not limit the scope of the present invention. At the same time, it should be clear that, for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. The techniques, methods and equipment known to ordinary technicians in the relevant fields may not be discussed in detail, but where appropriate, the techniques, methods and equipment should be considered as part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that similar numbers and letters represent similar items in the following figures, so once an item is defined in one figure, it does not need to be further discussed in subsequent figures.

[0034] In the description of the present invention, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "horizontal, vertical, vertical, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention: the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0035] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figures. For example, if the device in the drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below their position devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0036] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0037] like Figure 1 、 Figure 2As shown, an embodiment of the present invention discloses an ultrafast laser hole-making fixture for aircraft engine blades, which is used for ultrafast laser processing of air film holes in the lower edge plate a, blade body b, and upper edge plate c of a ceramic matrix composite material guide vane 7; the ceramic matrix composite material guide vane to be hole-made includes a blade body b, and the two sides of the blade body b are respectively provided with a lower edge plate a and an upper edge plate c, and the outer sides of the lower edge plate a and the upper edge plate c are respectively provided with a lower edge plate ridge f1 and an upper edge plate ridge f2, and the lower edge plate a and the upper edge plate c are respectively provided with a blade body end surface Ie1 and a blade body end surface IIe2, and the lower edge plate a and the upper edge plate c are also respectively provided with a guide vane inner cavity I d1 and the inner cavity IId2 of the guide vane, the device specifically includes a fixture base 1, a first side plate 3, a second side plate 2, a compression expansion component 5 and a blowing unit 4, the fixture base 1 has a connecting flange, during use, the bottom of the fixture base 1 is connected to the machine tool workbench, the first side plate 3 and the second side plate 2 are installed on the fixture base 1 by connecting bolts 6, the positioning of the blade end surface is achieved based on the first side plate and the second side plate, the compression expansion component and the blowing unit are installed on at least one of the side plates, in this embodiment, the first side plate 3 and the second side plate 2 are both provided with a compression expansion component and a blowing unit, the first side plate 3 and the second side plate 2 It is provided with threaded holes for installing the compression expansion component 5 and the blowing unit 4, as well as grooves that fit with the ridges f of the edge plate, which can realize the positioning of the blade end face e. The compression expansion component 5 is connected to the side plate by a compression bolt 51, which can realize the positioning and compression of the inner wall of the blade, and realize the precise clamping of the ceramic-based composite material guide vane. The blowing unit 4 is located in the guide vane cavity d, and is installed and fixed to the side plate through a threaded structure arranged on the outside of the air inlet end of the blowing unit 4. The blowing holes on the blowing unit 4 emit high-speed and high-pressure cooling gas to realize blowing in the hole outlet area during the ultrafast laser hole making process, thereby improving the hole making quality and avoiding thermal damage caused by ablation products.

[0038] In this embodiment, the ultrafast laser hole making fixture can complete the preparation of air film holes in all areas of the guide vane 7 by one positioning. The first side panel 3 and the second side panel 2 both have the functions of independent positioning and clamping. When processing the air film holes on the upper and lower edge panels, the side panels at the corresponding positions can be selectively removed to meet the ultrafast laser hole making of the air film holes in the corresponding parts. The side panels are easy to disassemble and assemble, which can improve the processing efficiency while meeting the processing procedures.

[0039] like Figure 3As shown, in this embodiment, the compression and expansion assembly 5 is composed of a compression bolt 51, a movable cone block 52, a movable claw 53 and a rubber sleeve 54. The compression bolt 51 and the movable cone block 52 are located in the middle of the movable claw 53. The movable claw is composed of several separate movable blocks. In this embodiment, the movable claw 53 is composed of three separate movable blocks. The inner wall is provided with a conical hole that cooperates with the movable cone block 52, and the outside is covered with a rubber sleeve 54. The rubber sleeve 54 realizes the tightening of the movable claw 53 in the initial state. By tightening the compression bolt 51, the movable cone block 52 moves toward the side plate to expand the movable claw 53 and the rubber sleeve 54, and contacts the inner cavity wall of the blade to fix and clamp the inner wall of the blade body, thereby improving the positioning accuracy, avoiding the positioning error caused by the deformation of the edge plate when positioning the edge plate, and improving the positioning accuracy of the hole.

[0040] like Figure 4 As shown, in this embodiment, the outer side of the air inlet end of the blowing unit 7 has a threaded structure, which is connected to the side plate through the threaded structure. The cross-sectional shape of the blowing unit changes according to the shape of the guide vane inner cavity d, and can be circular, square, or imitate the shape of the guide vane inner cavity, etc., thereby meeting different cooling gas jet requirements when processing the air film holes on the blade body.

[0041] like Figure 5 As shown, in this embodiment, according to the position and processing requirements of the cooling holes of the guide vane 7, the shape of the blowing holes can be round holes, square holes, inclined holes, etc., and their positions can be equidistant or unequally spaced arrays along the axial direction, and arranged at equal angles or at variable angles along the radial direction, so as to control the airflow inside the blade body, obtain better cooling gas jets, improve the hole making quality and prevent thermal damage caused by ablation products. Figure 4 Two optional implementations are shown in the figure, in which one blowing unit has a square cross-section, and blowing holes arranged in an array are provided on its four walls. The specifications of the blowing holes are consistent and are all circular holes; the cross-section of the other blowing unit is the shape of the inner cavity of the guide vane, and not all of its walls are provided with blowing holes. The specifications of the blowing holes are also different and are generally circular holes. The positions of the circular holes are mostly arranged perpendicular to the arc of the simulated guide vane. Figure 5 Three optional implementations are shown in the figure. All three blowing units are circular. In method a, the circular holes are arranged in an equidistant array at equal angles. In method b, the circular holes are replaced by inclined holes, which are arranged in an equidistant array at equal angles. In method c, the arranged holes are arranged in a spiral form along the blowing unit, and the pitch is determined according to the actual application scenario.

[0042] The present invention also discloses a method for clamping an ultrafast laser hole making fixture for an aero-engine blade, which can realize the processing of air film holes on the edge plate and the blade body, such as Figure 6 As shown, the following steps are included:

[0043] Step 1: Process the hole on the upper edge plate. Use the connecting bolts 6 to install the first side plate 3 on the fixture base 1. Place the compression expansion assembly 5 of the first side plate 3 in the inner cavity Id1 of the blade body. The blade end surface Ie1 is pressed against the plane of the first side plate 3 to define the position of the guide vane 7. Then, press the ridge f1 of the lower edge plate against the side of the groove of the first side plate 3 to assist in defining the angle of the guide vane 7. Tighten the clamping bolts 51. The movable cone block 52 moves so that the movable claw 53 and the rubber sleeve 54 fit against the inner wall of the blade body, completing the positioning and clamping of the guide vane 7. Connect the fixture base 1 to the machine tool workbench. The five-axis ultrafast laser processing of the hole in the upper edge plate c is achieved by rotating the workbench.

[0044] Step 2: Processing the film holes on the blade. Install the second side plate 2 on the fixture base 1, and install the compression expansion assembly on the second side plate 2. The plane of the second side plate 2 is aligned with the blade end surface IIe2, and the sidewall of the groove of the second side plate 2 is aligned with the ridge f2 of the upper edge plate. Tighten the compression bolt 51 to complete the auxiliary positioning of the guide vane 7. Use the blowing unit to blow air into the exit area of ​​the blade film hole. The five-axis linkage of the machine tool worktable controls the spatial position of the ultrafast laser beam to achieve ultrafast laser processing of the blade film hole.

[0045] Step 3: Process the holes in the lower edge plate. Tighten the hold-down bolts on the second side plate 2 again so that it can independently position and clamp the guide vanes 7. Remove the first side plate 3, rotate the machine table so that the surface of the lower edge plate a faces upward, and use ultrafast laser to process the air film holes in the lower edge plate as required.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An ultrafast laser hole making fixture for aircraft engine blades, characterized in that: The fixture is used for clamping the air film holes of the upper edge plate, blade body and lower edge plate of the ceramic-based composite material guide vane for ultrafast laser processing; it includes a fixture base, a first side plate, a second side plate, a compression and expansion component and a blowing unit, the fixture base has a connecting flange, the first side plate and the second side plate are installed on the fixture base, the positioning of the blade body end face is achieved based on the first side plate and the second side plate, the compression and expansion component and the blowing unit are installed on at least one of the side plates, the compression and expansion component is used to achieve positioning and compression of the inner wall of the blade body, and realize precise clamping of the ceramic-based composite material guide vane, the blowing unit is located in the inner cavity of the guide vane, and a plurality of blowing holes are provided on the blowing unit, through which high-speed and high-pressure cooling gas is ejected to realize blowing cooling of the hole outlet area during the ultrafast laser hole making process.

2. The ultrafast laser hole making fixture for aero-engine blades according to claim 1, characterized in that: The first side plate and the second side plate both have threaded holes for installing the compression expansion assembly and the blowing unit, and grooves that fit with the ridges of the edge plate. The surfaces of the first side plate and the second side plate are the fitting surfaces of the blade end face, thereby realizing the positioning of the blade end face.

3. The ultrafast laser hole making fixture for aero-engine blades according to claim 1, characterized in that: The first side plate and the second side plate are detachably mounted on the fixture base. The ultrafast laser hole making fixture can complete the processing of the air film holes in all areas of the guide vane with one positioning. The first side plate and the second side plate both have the functions of independent positioning and clamping. The side plates at the corresponding positions can be selectively removed to realize the clamping of the upper edge plate and the lower edge plate, thereby meeting the ultrafast laser hole making of the air film holes in the corresponding parts.

4. The ultrafast laser hole making fixture for aero-engine blades according to claim 1, characterized in that: The compression and expansion assembly is located in the inner cavity of the guide vane, and includes a compression bolt, a movable cone block, a movable claw and a rubber sleeve. The compression bolt and the movable cone block are located in the middle of the movable claw. The movable claw is composed of several separate movable blocks. The inner wall is provided with a conical hole that cooperates with the movable cone block, and the outside is covered with a rubber sleeve. The rubber sleeve realizes the tightening of the movable claw in the initial state. The compression bolt is connected to the side plate. By tightening the compression bolt, the movable cone block is moved toward the side plate, thereby driving the movable claw and the rubber sleeve to expand and contact with the inner cavity wall of the blade to achieve fixation and expansion of the inner wall of the blade body.

5. The ultrafast laser hole making fixture for aero-engine blades according to claim 1, characterized in that: The air inlet end of the air blowing unit has a threaded structure on the outside, which is connected to the side plate. The structure of the air blowing cooling unit and the specifications and shapes of the air vents opened thereon are adjusted according to the shape of the inner cavity of the guide vane.

6. The ultrafast laser hole making fixture for aero-engine blades according to claim 1, characterized in that: According to the position and processing requirements of the guide vane air film holes, the shape of the blowing holes includes at least one of a round hole, a square hole, and an inclined hole. The arrangement of the blowing holes includes an array with equal or unequal distances along the axial direction, and an equal angle or variable angle arrangement along the radial direction.

7. A method for clamping an ultrafast laser hole-making fixture for an aero-engine blade according to any of claims 1 to 6, characterized in that: The following steps are involved: Step 1: Processing the air film hole on the upper edge plate: Use bolts to install the first side plate on the fixture base, place the compression expansion assembly of the first side plate in the inner cavity I of the guide vane, and press the blade end surface I against the plane of the first side plate to limit the guide vane. Then, press the ridge of the lower edge plate against the side of the groove of the first side plate to assist in limiting the angle of the guide vane. Tighten the clamping bolts so that the movable claws and rubber sleeves fit against the inner wall of the guide vane air inlet to complete the positioning and clamping of the guide vane. Connect the fixture base to the machine tool workbench, and realize five-axis linkage ultrafast laser processing of the hole in the upper edge plate by rotating the workbench. Step 2: Processing the air film holes on the blade: Install the second side plate on the fixture base, install the compression expansion assembly on the second side plate, fit the plane of the second side plate to the blade end surface II, fit the side wall of the second side plate groove to the ridge of the upper edge plate, tighten the compression bolts to complete the auxiliary positioning of the blade, blow air to the outlet area of ​​the blade film hole through the blowing unit, and control the spatial position of the ultrafast laser beam through the five-axis linkage of the machine tool worktable to achieve ultrafast laser processing of the blade film hole; Step 3: Process the air film holes on the lower edge plate: Remove the first side plate. Before removing the first side plate, tighten the clamping bolts on the second side plate again so that it can independently complete the positioning and clamping of the guide vanes. Rotate the machine tool worktable so that the surface of the lower edge plate faces upward, and use ultrafast laser to process the air film holes on the lower edge plate as required.

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