Turbine disc flange connection structure and aero-engine

Abstract

The application discloses a turbine disc flange connecting structure and an aero-engine. The connecting structure comprises a first turbine disc, a second turbine disc, a plurality of bolts and a plurality of nuts. The first turbine body of the first turbine disc is connected with the first connecting edge and surrounds to form a first recess. The second turbine body of the second turbine disc is connected with the second connecting edge and surrounds to form a second recess, and a stop portion is arranged in the second recess. The head of each bolt is provided with a limiting portion and an anti-rotation portion. The limiting portion is in abutment with the stop portion to limit the axial movement of the bolt along the second turbine disc. The anti-rotation portion is arranged opposite to the inner cylindrical surface of the shaft neck end portion of the first turbine disc to prevent the rotation of the bolt. The plurality of nuts are arranged in the first recess and are locked with the rod portions of the plurality of bolts one by one. The flange connecting structure of the two-stage turbine disc of the aero-engine is improved, the assembly of the connecting bolt in a narrow space is realized, the functions of the anti-rotation and axial limiting of the bolt are ensured, and the reliable connection of the turbine disc is ensured.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a turbine disc flange connection structure and an aero-engine. Background Technology

[0002] As the power of aero engines continues to increase, the rotational speed and temperature of turbine disks also continue to increase, which inevitably leads to a continuous increase in the stress on the wheel center. Currently, the mainstream methods to reduce the stress on the wheel center are to reduce the wheel center diameter and increase the wheel center width. However, considering that parts such as turbine shafts usually pass through the inside of the wheel center, reducing the wheel center diameter is largely limited. Therefore, increasing the wheel center width has become the main method to reduce the stress on the wheel center.

[0003] In one exemplary technology, such as Figure 1 As shown, the two-stage turbine disks 1 are mainly connected by flanges, and the centering function is achieved through the cylindrical surface. A turbine guide is usually installed between the two-stage turbine disks 1. Due to the installation of the guide, the assembly space 4 of the bolts 2 and nuts 3 will inevitably be limited. Figure 1 The size shown. After the turbine disk 1 is assembled in place, it is tightened by the conventional bolts 2 and the conventional flared self-locking nuts 3.

[0004] However, in order to reduce the stress on the wheel center, when the wheel center width La is widened, the assembly space 4 of the bolt 2 will become smaller and smaller. When the axial width of the assembly space 4 is less than the length of the bolt 2, the bolt 2 will be unable to be installed.

[0005] Therefore, how to assemble the connecting bolts 2 in the confined assembly space 4 and ensure the reliable connection of the turbine disk 1 has become an urgent problem to be solved. Summary of the Invention

[0006] The main objective of this invention is to provide a turbine disk flange connection structure and an aero-engine, which aims to enable the assembly of connecting bolts in a confined assembly space and ensure reliable connection of the turbine disk.

[0007] To achieve the above objectives, the present invention proposes a turbine disk flange connection structure, comprising:

[0008] The first turbine disk includes a first turbine body and a first connecting edge, wherein the first turbine body is connected to the first connecting edge and surrounds a first groove;

[0009] The second turbine disk includes a second turbine body and a second connecting edge. The second turbine body is connected to the second connecting edge and forms a second groove. The opening direction of the second groove is opposite to the opening direction of the first groove. A stop portion is provided in the second groove. The second connecting edge abuts against the first connecting edge and is provided with a plurality of evenly spaced connecting holes.

[0010] a plurality of bolts, each of the bolts is provided with a limiting portion and an anti-rotation portion connected with the limiting portion, each of the bolts is arranged from the second groove to the first groove through a pair of the connecting holes, the head of the bolt is arranged in the second groove and the limiting portion is in abutment with the stop portion to limit the axial movement of the bolt along the second turbine disk, and the anti-rotation portion is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disk to prevent the rotation of the bolt; and

[0011] a plurality of nuts, each of which is arranged in the first groove and is locked with the rod portion of one of the bolts to fix the first turbine disk and the second turbine disk.

[0012] Optionally, the limiting portion is an arc edge of the head of the bolt, and the anti-rotation portion is a straight edge connected with the arc edge of the head of the bolt.

[0013] Optionally, the radius of the arc edge is defined as R1, the distance from the center of the straight edge to the arc edge is defined as L1, and the distance from the inner cylindrical surface of the shaft neck end of the first turbine disk to the center of the connecting hole is defined as L2, which satisfy the relationship L1 < L2 < R1.

[0014] Optionally, the stop portion is an annular boss protruding from the bottom of the second groove, and the distance from the annular boss to the center of the connecting hole is defined as L3, which satisfy the relationship L1 < L3.

[0015] Optionally, it also satisfies the relationship R1 > L3.

[0016] Optionally, the distance from the outer cylindrical surface of the shaft neck of the second turbine disk to the center of the connecting hole is defined as L4, which satisfy the relationship R1 < L4.

[0017] Optionally, the length of the nut is defined as L5, and the distance from the outer end surface of the rod portion of the bolt to the first turbine body in the assembled position is defined as L6, which satisfy the relationship L5 < L6.

[0018] Optionally, the connecting hole is a circular hole or a U-shaped hole.

[0019] Optionally, the connecting hole is coated with a lubricant.

[0020] The application also provides an aero-engine comprising the turbine disk flange connection structure as described above, and the turbine disk flange connection structure comprises:

[0021] a first turbine disk comprising a first turbine body and a first connecting edge, the first turbine body is connected with the first connecting edge and surrounds to form a first groove;

[0022] The second turbine disk comprises a second turbine body and a second connecting edge, the second turbine body is connected with the second connecting edge and forms a second recess, the opening direction of the second recess is opposite to the opening direction of the first recess, and a stopper is arranged in the second recess; the second connecting edge is abutted with the first connecting edge and is provided with a plurality of connecting holes which are uniformly arranged at intervals;

[0023] A plurality of bolts, the head of each bolt is provided with a limiting portion and an anti-rotation portion connected with the limiting portion, each bolt is arranged from the second recess to the first recess through a pair of connecting holes, the head of the bolt is arranged in the second recess and the limiting portion is abutted with the stopper to limit the axial movement of the bolt along the second turbine disk, and the anti-rotation portion is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disk to prevent the rotation of the bolt; and

[0024] A plurality of nuts are arranged in the first recess respectively and are locked with the rod portions of the plurality of bolts one by one to fix the first turbine disk and the second turbine disk.

[0025] In the technical scheme, the turbine disk flange connecting structure comprises a first turbine disk, a second turbine disk, a plurality of bolts and a plurality of nuts. The first turbine disk comprises a first turbine body and a first connecting edge, and the first turbine body is connected with the first connecting edge and forms a first recess. The second turbine disk comprises a second turbine body and a second connecting edge, and the second turbine body is connected with the second connecting edge and forms a second recess, the opening direction of the second recess is opposite to the opening direction of the first recess, and a stopper is arranged in the second recess; the second connecting edge is abutted with the first connecting edge and is provided with a plurality of connecting holes which are uniformly arranged at intervals. The head of each bolt is provided with a limiting portion and an anti-rotation portion connected with the limiting portion, each bolt is arranged from the second recess to the first recess through a pair of connecting holes, the head of the bolt is arranged in the second recess and the limiting portion is abutted with the stopper to limit the axial movement of the bolt along the second turbine disk, and the anti-rotation portion is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disk to prevent the rotation of the bolt. A plurality of nuts are arranged in the first recess respectively and are locked with the rod portions of the plurality of bolts one by one to fix the first turbine disk and the second turbine disk.

[0026] It can be understood that the flange connecting structure of the two-stage turbine disk of the aero-engine is improved, the limiting portion and the anti-rotation portion are arranged on the head of the bolt, the limiting portion is abutted with the stopper to limit the axial movement of the bolt along the second turbine disk, and the anti-rotation portion is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disk to prevent the rotation of the bolt, so that the assembly of the connecting bolt in the narrow assembly space is realized, the functions of the anti-rotation and the axial limiting of the bolt are ensured, and the reliable connection of the turbine disk is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to make the technical solutions of the embodiments of the present application or the prior art clearer, the accompanying drawings needed in the embodiments or prior art description will be briefly introduced. Obviously, the accompanying drawings in the following description only show some embodiments of the present application, and for those skilled in the art, other drawings can be obtained from the structures shown in the drawings without any creative effort.

[0028] Figure 1 Structure diagram of an exemplary structure in the prior art;

[0029] Figure 2 Structure diagram of an embodiment of the turbine disc flange connecting structure of the present application;

[0030] Figure 3 Exploded view of an embodiment of the turbine disc flange connecting structure of the present application;

[0031] Figure 4 Structure diagram of a bolt in an embodiment of the turbine disc flange connecting structure of the present application;

[0032] Figure 5 Front view of a bolt head in an embodiment of the turbine disc flange connecting structure of the present application;

[0033] Figure 6 Structure diagram of a first turbine disc and a nut in an embodiment of the turbine disc flange connecting structure of the present application;

[0034] Figure 7 Structure diagram of a second turbine disc and a bolt in an embodiment of the turbine disc flange connecting structure of the present application;

[0035] Figure 8 Exploded view of an embodiment of the turbine disc flange connecting structure of the present application;

[0036] Figure 9 Assembly diagram of a second turbine disc and a bolt in an embodiment of the turbine disc flange connecting structure of the present application;

[0037] Figure 10 Assembly diagram of a second turbine disc and a bolt in an embodiment of the turbine disc flange connecting structure of the present application;

[0038] Figure 11 Assembly diagram of an embodiment of the turbine disc flange connecting structure of the present application;

[0039] Figure 12 Structure diagram of a connecting hole in another embodiment of the turbine disc flange connecting structure of the present application.

[0040] Explanation of the reference signs:

[0041] 10, first turbine disk; 20, second turbine disk; 30, bolt; 40, nut; 11, first turbine body; 12, first connecting edge; 21, second turbine body; 22, second connecting edge; 10a, first groove; 20a, second groove; 301, limiting portion; 302, anti-rotation portion; 211, stop portion; 100a, connecting hole.

[0042] The purposes, functional features and advantages of the present application will be further described with reference to the embodiments in combination with the accompanying drawings. DETAILED DESCRIPTION

[0043] The technical solutions in the embodiments of the present application will be clearly and completely described below in combination with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work belong to the protection scope of the present application.

[0044] It should be noted that if the embodiments of the present application involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement condition, etc. between components in a certain posture (as shown in the drawings), and if the certain posture changes, the directional indications also change accordingly.

[0045] In addition, if the embodiments of the present application involve descriptions of "first", "second", etc., the descriptions of "first", "second", etc. are only for description purposes, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first" and "second" can explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing throughout the text is that it includes three parallel schemes, for example, "A and / or B" includes A scheme, or B scheme, or A and B schemes. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the fact that a person skilled in the art can realize it, and when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope of the present application.

[0046] The present application provides a turbine disk flange connection structure, which is suitable for an engine, especially an aero-engine, which is not limited here.

[0047] Reference Figure 2 and Figure 3In an embodiment of the present application, the turbine disc flange connecting structure comprises a first turbine disc 10, a second turbine disc 20, a plurality of bolts 30 and a plurality of nuts 40. The first turbine disc 10 comprises a first turbine body 11 and a first connecting edge 12, the first turbine body 11 is connected with the first connecting edge 12 and encloses a first recess 10a. The second turbine disc 20 comprises a second turbine body 21 and a second connecting edge 22, the second turbine body 21 is connected with the second connecting edge 22 and encloses a second recess 20a, the opening direction of the second recess 20a is opposite to the opening direction of the first recess 10a, and the second recess 20a is provided with a stop portion 211. Figure 3 、 Figures 9 to 12 As shown in the drawings, the second connecting edge 22 abuts against the first connecting edge 12 and is provided with a plurality of connecting holes 100a which are uniformly arranged at intervals. Referring to Figures 2 to 5 The head of each bolt 30 is provided with a limiting portion 301 and an anti-rotation portion 302 connected with the limiting portion 301, each bolt 30 passes through a pair of connecting holes 100a from the second recess 20a to the first recess 10a, the head of the bolt 30 is arranged in the second recess 20a and the limiting portion 301 abuts against the stop portion 211 to limit the axial movement of the bolt 30 along the second turbine disc 20, and the anti-rotation portion 302 is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disc 10 to prevent the rotation of the bolt 30. A plurality of nuts 40 are arranged in the first recess 10a and are locked with the shanks of the plurality of bolts 30 one by one to fix the first turbine disc 10 and the second turbine disc 20.

[0048] It should be noted that the anti-rotation portion 302 is arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disc 10 specifically refers to that the outer wall of the anti-rotation portion 302 corresponds to the position of the inner cylindrical surface of the shaft neck end of the first turbine disc 10 and the two are gap-fitted to ensure that the anti-rotation portion 302 of the head of the bolt 30 and the stop cylindrical surface of the first turbine disc 10 neither interfere with each other nor can prevent the rotation of the head of the bolt 30.

[0049] Referring mainly to Figure 4 and Figure 5 In the embodiment, the limiting portion 301 can be an arc edge of the head of the bolt 30, and the anti-rotation portion 302 can be a straight edge connected with the arc edge of the head of the bolt 30. The arc edge can include at least one arc, preferably one arc, to facilitate processing and manufacturing; the straight edge can include a straight line or a combination of a straight line and an inclined line, preferably a straight line, to facilitate processing and manufacturing, which is not limited here.

[0050] It can be understood that the flange connection structure of the two-stage turbine disc of the aero-engine is improved, the limiting portion 301 and the anti-rotation portion 302 are arranged on the head of the bolt 30, the limiting portion 301 is in abutment with the stop portion 211 to limit the axial movement of the bolt 30 along the second turbine disc 20, and the anti-rotation portion 302 is arranged opposite to the inner cylindrical surface of the shaft neck end portion of the first turbine disc 10 to prevent the rotation of the bolt 30, so that the assembly of the connecting bolt 30 in a narrow assembly space is realized, the functions of the anti-rotation and axial limiting of the bolt 30 are ensured, and the reliable connection of the turbine disc is ensured.

[0051] To further improve the anti-rotation effect of the bolt 30, improve the space utilization, and ensure the reliable connection of the turbine disc, with reference to Figure 5 and Figure 6 In an embodiment, when the limiting portion 301 is a circular arc edge and the anti-rotation portion 302 is a straight line edge, the radius of the circular arc edge is defined as R1, the distance from the straight line edge to the center of the circular arc edge is defined as L1, and the distance from the inner cylindrical surface of the shaft neck end portion of the first turbine disc 10 to the hole center of the connecting hole 100a is defined as L2, which satisfies the relationship L1 < L2 < R1.

[0052] The above relationship limits the gap between the straight line edge of the head of the bolt 30 and the inner cylindrical surface of the shaft neck rear end surface, realizes the axial anti-rotation of the bolt 30, and improves the reliability of the flange connection structure of the turbine disc.

[0053] In the embodiment, R1 can be 5.5 mm, L1 can be 4.0 mm, and L2 can be preferably 4.3 mm, which is not limited here.

[0054] With reference to Figure 5 and Figure 7 In an embodiment, the stop portion 211 can be an annular boss protruding on the groove bottom of the second groove 20a, and the distance from the annular boss to the hole center of the connecting hole 100a is defined as L3, which satisfies the relationship L1 < L3.

[0055] In the embodiment, L3 needs to be slightly larger than L1, and L3 can be 4.1 mm, so that the bolt 30 can smoothly enter the connecting hole 100a on the flange edge of the turbine disc.

[0056] Further, the relationship R1 > L3 is also satisfied, so that the circular arc edge of the head of the bolt 30 is stopped by the stop portion 211, and the axial limiting of the bolt 30 is realized.

[0057] In the embodiment, the distance from the outer cylindrical surface of the shaft neck of the second turbine disc 20 to the hole center of the connecting hole 100a is defined as L4, which satisfies the relationship R1 < L4.

[0058] L4 is slightly larger than R1, and L4 can be 5.6 mm, to ensure that the bolt 30 can be axially freely moved in the connecting hole 100a on the turbine disc flange.

[0059] Further, in the embodiment, referring to Figures 5 to 8 , the length of the nut 40 is defined as L5, and the distance from the outer end surface of the shank of the bolt 30 to the first turbine body 11 in the assembled position is defined as L6, which satisfies the relationship L5 < L6. L5 can be 7.0 mm, and L6 can be 8.0 mm.

[0060] In the assembly process, first, the bolt 30 can be loaded into the second turbine disc 20. When loading, the bolt 30 is first inserted into the connecting hole 100a on the flange of the second turbine disc 20 with the straight edge facing the center, as shown in Figure 9 When the head of the bolt 30 passes through the annular boss of the shaft neck of the second turbine disc 20, the bolt 30 is rotated along its axis, with the straight edge facing away from the center, as shown in Figure 10 At this time, since R1 is greater than L3 (5.5 > 4.1 in the example), the axial positioning of the bolt 30 is achieved. At this time, vaseline or other lubricants can be applied in the connecting hole 100a of the flange of the second turbine disc 20 and the bolt 30, so that the bolt 30 cannot be loosened in the second turbine disc 20.

[0061] Then, the outer ring surface of the stop of the first turbine disc 10 is heated (the turbine disc stop is usually selected to have an interference fit). After heating, the first turbine disc 10 and the flange of the second turbine disc 20 are connected together, as shown in Figure 11 At this time, the straight edge of the bolt 30 is directed towards the stop cylinder surface of the first turbine disc 10. Since the size L2 in the first turbine disc 10 is slightly larger than the size L1 of the head of the bolt 30 (4.3 > 4.0 in the example), it is ensured that the straight edge of the head of the bolt 30 does not interfere with the stop cylinder surface of the first turbine disc 10, and the rotation of the head of the bolt 30 is prevented.

[0062] Referring to Figure 8 and Figure 11 After the first turbine disc 10 and the second turbine disc 20 are assembled together, the head of the bolt 30 can be moved to the left side end surface of the annular boss of the second turbine disc 20, to ensure that L5 < L6, so that the nut 40 can be assembled with the threads of the shank of the bolt 30.

[0063] Finally, the nut 40 can be tightened using a special tool. At this time, due to the unique features of the turbine disc flange connection structure, the bolt 30 cannot be detached or rotated inside the blind area of the two-stage turbine disc, and reliable assembly of the bolt 30 and the nut 40 is finally achieved.

[0064] In addition, referring to Figure 11 and Figure 12In some embodiments, the connecting hole 100a can be a circular hole or a U-shaped hole, and the like, which is not limited herein.

[0065] When the two-stage turbine disc structure is more compact, the shaft journal axial length of the second turbine disc 20 is too short, which makes it difficult for the bolt 30 to be inserted into the turbine disc flange bolt 30 hole, and the structure of the second turbine disc 20 flange connecting hole 100a can be changed to a U-shaped hole, as shown in Figure 12 During assembly, the bolt 30 can be inserted into the U-shaped hole in the turbine disc in the radial direction, and the remaining assembly method is the same as the above-mentioned circular hole assembly method, which is not described herein.

[0066] The turbine disc flange connecting structure of the present application changes the traditional assembly method of the bolt 30 and the nut 40 between the turbine disc flanges, and through the modification of the structure of the first turbine disc 10, the second turbine disc 20 and the bolt 30, the assembly of the bolt 30 and the nut 40 in the blind area between the first turbine disc 10 and the second turbine disc 20 can be successfully completed, which significantly improves the space utilization and reliability of the engine.

[0067] The present application also provides an aero-engine, which comprises the turbine disc flange connecting structure, and the specific structure of the turbine disc flange connecting structure is referred to the above-mentioned embodiments. Since the aero-engine provided by the present application comprises all the schemes of all the embodiments of the above-mentioned turbine disc flange connecting structure, it at least has the same technical effects as the turbine disc flange connecting structure, which is not described herein.

[0068] The above-mentioned is only the optional embodiments of the present application, and does not limit the patent scope of the present application, and any equivalent structural transformation made under the inventive concept of the present application, and direct / indirect application in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A turbine disk flange connection structure, characterized by, The turbine disc flange connecting structure comprises: a first turbine disc comprising a first turbine body and a first connecting edge, the first turbine body being connected with the first connecting edge and surrounding a first recess; a second turbine disc comprising a second turbine body and a second connecting edge, the second turbine body being connected with the second connecting edge and surrounding a second recess, the opening direction of the second recess being opposite to that of the first recess, and a stopper being arranged in the second recess; the second connecting edge abutting against the first connecting edge and both being provided with a plurality of connecting holes arranged uniformly at intervals; a plurality of bolts, the head of each bolt being provided with a limiting portion and an anti-rotation portion connected with the limiting portion, each bolt being arranged from the second recess through a pair of connecting holes into the first recess, the head of the bolt being arranged in the second recess and the limiting portion abutting against the stopper to limit the axial movement of the bolt along the second turbine disc, and the anti-rotation portion being arranged opposite to the inner cylindrical surface of the shaft neck end of the first turbine disc to prevent the rotation of the bolt; and a plurality of nuts, each being arranged in the first recess and being locked with the rod portion of a corresponding bolt to fix the first turbine disc and the second turbine disc.

2. The turbine disk flange joint structure according to claim 1, wherein The limiting portion is an arc edge of the head of the bolt, and the anti-rotation portion is a straight edge connected with the arc edge of the head of the bolt.

3. The turbine disk flange joint structure according to claim 2, wherein The radius of the arc edge is defined as R1, the distance from the straight edge to the center of the arc edge is defined as L1, and the distance from the inner cylindrical surface of the shaft neck end of the first turbine disc to the center of the connecting hole is defined as L2, which satisfy the relationship L1 4. The turbine disk flange joint structure according to claim 3, wherein The stopper is an annular boss protruding from the bottom of the second recess, and the distance from the annular boss to the center of the connecting hole is defined as L3, which satisfy the relationship L1 5. The turbine disk flange joint structure according to claim 4, wherein The relationship R1>L3 is also satisfied.

6. The turbine disk flange joint structure according to claim 4, wherein The distance from the outer cylindrical surface of the shaft neck of the second turbine disc to the center of the connecting hole is defined as L4, which satisfy the relationship R1 7. The turbine disk flange joint structure according to claim 3, wherein The length of the nut is defined as L5, and the distance from the outer end surface of the rod portion of the bolt to the first turbine body in the assembled position is defined as L6, which satisfy the relationship L5 8. The turbine disk flange joint structure as recited in claim 1, characterized by The connecting hole is a circular hole or a U-shaped hole.

9. The turbine disk flange joint structure as recited in claim 1, characterized by The connecting hole is coated with a lubricant.

10. An aeroengine characterised in that, The turbine disc flange connecting structure according to any one of claims 1-9.

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