A device for adjusting and positioning the spatial position and attitude of blades in an aero-engine

Abstract

The present application provides a device for adjusting and positioning the spatial position and attitude of blades in an aircraft engine, comprising: a base plate having a spherical rolling groove thereon; two side plates having spherical rolling grooves thereon, which are arranged opposite to each other and connected to the base plate; a fixed plate having an adjustment groove thereon, which is connected to the base plate and / or the two side plates; a central axis block, which is used for threaded connection with the blade, is arranged between the two side plates, and partially extends into the adjustment groove; three rolling balls, each rolling ball is correspondingly arranged in a spherical rolling groove; three connecting rods, one end of each connecting rod is correspondingly connected to a rolling ball, and the other end is connected to the central axis block; a Y-axis steering angle adjustment positioning bolt, which is screwed on the fixed plate, extends into the adjustment groove, and abuts against the central axis block; two Z-axis steering angle adjustment positioning bolts, each Z-axis steering angle adjustment positioning bolt is correspondingly screwed on a side plate and abuts against the central axis block.

Description

Technical Field

[0001] The present application belongs to the technical field of blade spatial position and attitude adjustment and positioning design in aircraft engines, and specifically relates to a blade spatial position and attitude adjustment and positioning device in aircraft engines. Background Art

[0002] Blades are one of the most critical components of aircraft engines, including fan blades, compressor blades, turbine blades, etc. Due to structural and performance requirements, blades often have special structures such as partitions and spoiler columns, and are designed with variable cross-sections and complex surface structures.

[0003] During a series of processing, inspection, and testing processes for aircraft engine blades, it is often necessary to accurately adjust the blade's spatial position and posture and reliably locate it according to the blade's structure and size, and to provide the blade's spatial angle.

[0004] Currently, the blade spatial position attitude adjustment and positioning device in aircraft engines has the following defects:

[0005] 1) It is only applicable to a certain type of blade and has poor versatility;

[0006] 2) It is inconvenient to operate, and the blade spatial position and posture cannot be infinitely adjusted, making it difficult to accurately adjust the blade spatial position and posture;

[0007] 3) It is difficult to reliably position the blades;

[0008] 4) The spatial angle of the blade cannot be accurately given.

[0009] This application is proposed in view of the above-mentioned technical defects.

[0010] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0011] The purpose of this application is to provide a device for adjusting and positioning the spatial position and attitude of blades in an aircraft engine, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0012] The technical solution of this application is:

[0013] A device for adjusting and positioning the spatial position and attitude of blades in an aero-engine, comprising:

[0014] a bottom plate having a spherical rolling groove thereon;

[0015] Two side plates with spherical rolling grooves are arranged opposite to each other and connected to the bottom plate;

[0016] a fixed plate having an adjustment slot thereon and connected to the bottom plate and / or the two side plates;

[0017] The middle shaft block is used for threaded connection with the blades, is set between the two side plates, and partially extends into the adjustment slot;

[0018] Three rolling balls, each of which is correspondingly set in a spherical rolling groove;

[0019] Three connecting rods, one end of each connecting rod is connected to a corresponding rolling ball, and the other end is connected to the central axis block;

[0020] Two Y-axis steering angle adjustment positioning bolts are screwed onto the fixing plate, extending into the adjustment slots and resting against the center axis block;

[0021] Two Z-axis steering angle adjustment positioning bolts, each Z-axis steering angle adjustment positioning bolt is correspondingly screwed on a side plate and rests on the central axis block.

[0022] According to at least one embodiment of the present application, in the above-mentioned device for adjusting and positioning the spatial position and attitude of blades in an aero-engine, one end of the central axis block has an adjustment protrusion;

[0023] The adjustment protrusion extends into the adjustment slot and abuts against the Y-axis steering angle adjustment positioning bolt.

[0024] According to at least one embodiment of the present application, the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine further includes:

[0025] The X-axis steering clamping block is screwed on the middle axis block and is provided with a bayonet; the bayonet is used to clamp on the tenon of the blade.

[0026] According to at least one embodiment of the present application, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, the X-axis steering clamp has a screw-connected protrusion;

[0027] The screw-on protrusion is screwed on the middle shaft block through a fine-pitch thread.

[0028] According to at least one embodiment of the present application, the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine further includes:

[0029] Two fastening bolts are connected to the X-axis steering clamp to tighten the tenon of the blade from both sides.

[0030] According to at least one embodiment of the present application, in the above-mentioned device for adjusting and positioning the blade spatial position and attitude in an aircraft engine, the central axis block and the X-axis steering clamp block are made of ferromagnetic material;

[0031] The device for adjusting and positioning the blade spatial position and attitude in the aero-engine further comprises:

[0032] The three digital display magnetic inclinometers are X-axis steering digital display magnetic inclinometer, Y-axis steering digital display magnetic inclinometer, and Z-axis steering digital display magnetic inclinometer. Among them, the X-axis steering digital display magnetic inclinometer is connected to the X-axis steering clamping block, and the Y-axis steering digital display magnetic inclinometer and the Z-axis steering digital display magnetic inclinometer are connected to the central axis block.

[0033] According to at least one embodiment of the present application, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, the X-axis steering clamp has a tenon tooth reference association surface;

[0034] The tenon tooth reference association surface is associated with the tenon tooth reference of the blade, and an X-axis steering digital display magnetic inclinometer is connected thereto. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a schematic diagram of the working of the blade spatial position and posture adjustment and positioning device in an aero-engine provided by an embodiment of the present application;

[0036] Figure 2 Schematic diagram of a partial structure of a blade spatial position and attitude adjustment and positioning device in an aero-engine provided by an embodiment of the present application;

[0037] Figure 3 This is a schematic diagram of the working principle of the blade spatial position and posture adjustment and positioning device in an aero-engine provided by an embodiment of the present application;

[0038] Figure 4 This is a schematic diagram of the installation positions of the X-axis digital display magnetic inclinometer, the Y-axis digital display magnetic inclinometer, and the Z-axis digital display magnetic inclinometer provided in the embodiment of the present application;

[0039] in:

[0040] 1-base plate; 2-side plate; 3-fixed plate; 4-center axis block; 5-blade; 6-rolling ball; 7-connecting rod; 8-Y-axis steering angle adjustment positioning bolt; 9-Z-axis steering angle adjustment positioning bolt; 10-X-axis steering clamp; 11-fastening bolt; 12-digital display magnetic inclinometer.

[0041] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0042] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0043] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0044] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0045] The following is combined with Figures 1 to 4 This application is described in further detail.

[0046] A device for adjusting and positioning the spatial position and attitude of blades in an aero-engine, comprising:

[0047] Base plate 1, having spherical rolling grooves thereon;

[0048] Two side plates 2, which have spherical rolling grooves, are arranged oppositely and connected to the bottom plate 1. The circles where the spherical rolling grooves on the two side plates 2 are located are perpendicular to the circles where the spherical rolling grooves on the bottom plate 1 are located, and the centers of the circles are the same.

[0049] A fixed plate 3 having an adjustment slot thereon and connected to the bottom plate 1 and / or the two side plates 2;

[0050] The middle shaft block 4 is used for threaded connection with the blade 5, with the screw connection portion of the middle shaft block 4 facing away from the fixed plate 3, and is set between the two side plates 2, partially extending into the adjustment groove, with its center located at the center of the circle;

[0051] Three rolling balls 6, each rolling ball 6 is correspondingly arranged in a spherical rolling groove;

[0052] Three connecting rods 7, one end of each connecting rod 7 is connected to a corresponding rolling ball 6, and the other end is connected to the central axis block 4, pointing to the center of the circle;

[0053] Two Y-axis steering angle adjustment positioning bolts 8 are screwed on the fixing plate 3, extending into the adjustment slot and resting on the central axis block 4;

[0054] Two Z-axis steering angle adjustment positioning bolts 9 , each Z-axis steering angle adjustment positioning bolt 9 is correspondingly screwed on a side plate 2 and rests on the central axis block 4 .

[0055] With the above-mentioned embodiment disclosed in the apparatus for adjusting and positioning the blade spatial position and attitude in the aero-engine, the blade spatial position and attitude adjustment and positioning can be performed as follows:

[0056] Twist the two Y-axis steering angle adjustment positioning bolts 8 to rotate the central axis block 4 around the Y-axis, thereby adjusting the deflection angle of the blade 5 around the Y-axis. After adjustment, lock nuts can be set on the two Y-axis steering angle adjustment positioning bolts 8 for locking. During the adjustment process, the balls 6 located in the spherical rolling grooves of the two side plates 2 rotate, and the balls 6 located in the spherical rolling grooves of the bottom plate 1 slide around the Y-axis.

[0057] Twist the two Z-axis steering angle adjustment positioning bolts 9 to rotate the central axis block 4 around the Z-axis, thereby adjusting the deflection angle of the blade 5 around the Z-axis. After adjustment, lock nuts can be set on the two Z-axis steering angle adjustment positioning bolts 9 for locking. During the adjustment process, the balls 6 located in the spherical rolling grooves of the two side plates 2 slide around the Z-axis, and the balls 6 located in the spherical rolling grooves of the bottom plate 1 rotate;

[0058] The blade 5 is twisted to rotate the blade 5 relative to the central axis block 4 around the X-axis, thereby adjusting the deflection angle of the blade 5 around the X-axis.

[0059] As for the blade spatial position and attitude adjustment and positioning device in the aircraft engine disclosed in the above embodiment, technical personnel in the field can understand that it can accurately adjust the spatial position and attitude of the blade 5 by turning the Y-axis steering angle adjustment positioning bolt 8, the Z-axis steering angle adjustment positioning bolt 9, and the blade 5, which is easy to operate, and can perform stepless adjustment of the spatial position and attitude of the blade 5, and the adjustment process is smooth, and the blade 5 can be reliably positioned.

[0060] In some optional embodiments, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, one end of the central axis block 4 has an adjustment protrusion;

[0061] The adjustment protrusion extends into the adjustment slot and abuts against the Y-axis steering angle adjustment positioning bolt 8.

[0062] In some optional embodiments, the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine further includes:

[0063] The X-axis steering clamp 10 is screwed onto the center shaft block 4 and has a bayonet thereon; the bayonet is used to clamp onto the tenon of the blade 5 .

[0064] As for the blade spatial position attitude adjustment and positioning device in the aircraft engine disclosed in the above embodiment, technical personnel in the field can understand that its design is to connect the blade 5 with the X-axis steering clamp 10 screwed on the central axis block 4. The deflection angle of the blade 5 around the X-axis can be adjusted by screwing the X-axis steering clamp 10. After the adjustment is in place, the nut can be tightened to lock it. The X-axis steering clamp 10 is detachable from the central axis block 4, and different blades 5 can be adapted by replacing the X-axis steering clamp 10, which has high versatility.

[0065] In some optional embodiments, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, the X-axis steering clamp 10 has a screw-connected protrusion;

[0066] The screw-connecting protrusion is screwed onto the central shaft block 4 via a fine-pitch thread. The design of the fine-pitch thread can ensure the accuracy of adjusting the deflection angle of the blade 5 around the X-axis.

[0067] In some optional embodiments, the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine further includes:

[0068] Two fastening bolts 11 are connected to the X-axis steering clamp 10 to tighten the tenon of the blade 5 from both sides.

[0069] In some optional embodiments, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, the central axis block 4 and the X-axis steering clamp block 10 are made of ferromagnetic materials;

[0070] The device for adjusting and positioning the blade spatial position and attitude in the aero-engine further comprises:

[0071] Three digital display magnetic angle meters 12 are respectively an X-axis steering digital display magnetic angle meter, a Y-axis steering digital display magnetic angle meter, and a Z-axis steering digital display magnetic angle meter. Among them, the X-axis steering digital display magnetic angle meter is connected to the X-axis steering clamp 10, as shown in FIG. Figure 4 As shown in the A position, the Y-axis digital display magnetic inclinometer and the Z-axis digital display magnetic inclinometer are connected to the middle shaft block 4, as shown in the Figure 4 The B and C positions shown in FIG can monitor the deflection angles of the blade 5 around the X, Y, and Z axes.

[0072] In some optional embodiments, in the above-mentioned blade spatial position attitude adjustment and positioning device in the aircraft engine, the X-axis steering clamp 10 has a tenon tooth reference association surface;

[0073] The tenon reference associated surface is associated with the tenon reference of the blade 5, and an X-axis steering digital display magnetic inclinometer is connected thereto to ensure the reference for the blade 5 to rotate around its own axis and provide a basis for positioning.

[0074] In the blade spatial position attitude adjustment and positioning device in the aircraft engine disclosed in the above embodiment, the connection can be designed as a non-detachable connection or a detachable connection according to actual needs, wherein the non-detachable connection can be welding or one-piece molding, and the detachable connection can be a threaded connection or a bolt connection, and a locking nut can be provided on the bolt.

[0075] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0076] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A device for adjusting and positioning the blade spatial position and attitude in an aero-engine, characterized in that: include: A bottom plate (1) having a spherical rolling groove thereon; Two side plates (2) with spherical rolling grooves thereon are arranged opposite to each other and connected to the bottom plate (1); A fixed plate (3) having an adjustment slot thereon and connected to the bottom plate (1) and / or the two side plates (2); A central shaft block (4) is used for threaded connection with the blade (5), is arranged between the two side plates (2), and partially extends into the adjustment slot; Three rolling balls (6), each rolling ball (6) is correspondingly arranged in a spherical rolling groove; Three connecting rods (7), one end of each connecting rod (7) is connected to a corresponding rolling ball (6), and the other end is connected to the central shaft block (4); Two Y-axis steering angle adjustment positioning bolts (8) are screwed onto the fixing plate (3), extend into the adjustment slot, and abut against the middle shaft block (4); Two Z-axis steering angle adjustment positioning bolts (9), each Z-axis steering angle adjustment positioning bolt (9) is correspondingly screwed on a side plate (2) and abuts against the middle axis block (4).

2. The device for adjusting and positioning the blade spatial position and attitude in an aircraft engine according to claim 1, characterized in that: One end of the central axis block (4) is provided with an adjustment protrusion; The adjustment protrusion extends into the adjustment slot and abuts against the Y-axis steering angle adjustment positioning bolt (8).

3. The device for adjusting and positioning the blade spatial position and attitude in an aero-engine according to claim 1, characterized in that: Also includes: The X-axis steering clamping block (10) is screwed on the middle axis block (4) and has a bayonet; the bayonet is used to clamp on the tenon of the blade (5).

4. The device for adjusting and positioning the blade spatial position and attitude in an aero-engine according to claim 3, characterized in that: The X-axis steering clamp (10) is provided with a screw-connected protrusion; The screw-connecting protrusion is screw-connected to the middle shaft block (4) through a fine-pitch thread.

5. The device for adjusting and positioning the blade spatial position and attitude in an aircraft engine according to claim 3, characterized in that: Also includes: Two fastening bolts (11) are connected to the X-axis steering clamp (10) to tighten the tenons of the blade (5) from both sides.

6. The device for adjusting and positioning the blade spatial position and attitude in an aero-engine according to claim 3, characterized in that: The middle shaft block (4) and the X-axis steering clamp block (10) are made of ferromagnetic materials; The device for adjusting and positioning the blade spatial position and attitude in the aero-engine further comprises: The three digital magnetic angle meters (12) are respectively an X-axis steering digital magnetic angle meter, a Y-axis steering digital magnetic angle meter, and a Z-axis steering digital magnetic angle meter, wherein the X-axis steering digital magnetic angle meter is connected to the X-axis steering clamping block (10), and the Y-axis steering digital magnetic angle meter and the Z-axis steering digital magnetic angle meter are connected to the central axis block (4).

7. The device for adjusting and positioning the blade spatial position and attitude in an aircraft engine according to claim 6, characterized in that: The X-axis steering clamp (10) is provided with a tenon tooth reference associated surface; The tenon tooth reference association surface is associated with the tenon tooth reference of the blade (5), and an X-axis steering digital display magnetic angle meter is connected thereto.

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