Aircraft engine turbine rotor structure and margin plate bending line design method

Abstract

The invention discloses an aero-engine turbine rotor structure which comprises a turbine disc and a plurality of turbine working blades, the turbine working blades are installed in corresponding mortises in the turbine disc through tenons of the turbine working blades, and the contact edge, located on the blade basin side of a blade body, of a margin plate is an inwards-concave margin plate concave face. The contact edge, located on the blade back side of the blade body, of the edge plate is an outwards-protruding edge plate convex face. The side face, located on the blade basin side of the blade body, of the tenon is an inwards-concave tenon concave face, and the side face, located on the blade back side of the blade body, of the tenon is an outwards-convex tenon convex face. And two side wall surfaces of the mortise are respectively a mortise convex surface matched with the tenon concave surface and a mortise concave surface matched with the tenon convex surface of the tenon. According to the structure, the area of the joggling contact surface can be increased, so that the stress of the joggling contact surface is reduced, the bearing capacity of the tenon on the turbine working blade and the mortise on the turbine disc is improved, the vibration of the turbine working blade can be reduced, the high bearing capacity and stable rotation of the turbine working blade are ensured, and the safety of the turbine working blade under the high-rotating-speed working condition is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine engines, and in particular, to a turbine rotor structure of an aeroengine. In addition, the present invention also relates to a design method for the bend line of the shroud plate. Background Art

[0002] The turbine blades of a gas turbine engine operate at high temperatures and high speeds. The rotational speed of the turbine blades can reach tens of thousands of revolutions per minute. A single blade bears a centrifugal load of several tons. The turbine blades are usually connected to the turbine disk by a tenon joint structure. Therefore, it is required that the tenon joint structure has a higher load-bearing capacity; during the high-speed rotation process, the turbine blades are excited by their own rotation and aerodynamic forces and will vibrate. Excessive vibration will reduce the blade life or even cause fracture. Therefore, it is necessary to suppress blade vibration; in addition, due to the increasing gas temperature of the turbine, traditional superalloy materials are difficult to meet the high-temperature usage requirements. Some turbine working blades are prepared with high-temperature-resistant ceramic matrix composites to improve the temperature resistance of the turbine working blades. However, the existing turbine blade airfoil is of an arc surface configuration, and the shroud plate and the tenon are of a straight plane configuration, resulting in difficulties in preparing ceramic matrix composite turbine working blades and low load-bearing capacity.

[0003] The existing turbine working blades are connected to the tenon groove of the turbine disk by a tenon. Both the tenon and the tenon groove are of a straight configuration. The straight direction is consistent with the axial direction of the rotation center or has a certain axial included angle. The contact surface between the blade tenon and the turbine disk tenon groove is a plane. The larger the contact area between the tenon and the tenon groove, the stronger its load-bearing capacity. Under the condition of a certain axial dimension, the contact area can be increased by increasing the axial included angle of the tenon. However, due to the limitations of the blade installation angle and the space of adjacent blades, its axial angle is generally not more than 20°. Therefore, it is difficult to further increase the contact area between the tenon and the tenon groove by this scheme.

[0004] The existing turbine working blades use a shroud structure or assemble damping sheets to achieve vibration reduction of the blades. The shroud is to add a circumferential plate-like structure at the tip position of the turbine blade. The shrouds of adjacent blades are in contact with each other. When the blades vibrate, the shrouds of adjacent blades are pressed against each other and rubbed, thereby suppressing vibration; the damping sheet is to horizontally install a metal sheet at the joint position between the shroud plates of the turbine working blades and adjacent shroud plates. During the rotation process, the two shroud plates are pressed tightly under the action of centrifugal force to suppress blade vibration. These two methods add new structures and parts to the turbine blades, increase the weight of the blades, increase the centrifugal load during the rotation of the turbine working blades, and are complex in processing and assembly. Summary of the Invention

[0005] The present invention provides an aero-engine turbine rotor structure and a design method for the bending line of the rim plate, so as to solve the technical problems that in the existing straight-plane contact tenon, due to the limitations of the axial dimension and the blade installation angle, it is difficult to further increase the tenon joint contact area and the tenon joint bearing capacity, and that in the existing turbine working blades, a crown structure or damping sheets are used to achieve vibration reduction of the blades, which adds new structures and parts to the turbine blades, increases the weight of the blades, increases the centrifugal load during the rotation of the turbine working blades, and makes the processing and assembly more complex.

[0006] The technical solution adopted by the present invention is as follows:

[0007] An aero-engine turbine rotor structure includes a turbine disk and a plurality of turbine working blades. A plurality of tenon grooves evenly distributed in the circumferential direction are machined on the outer edge surface of the turbine disk. The turbine working blades include a blade body, a rim plate and a tenon head connected in sequence, and the turbine working blades are installed in the corresponding tenon grooves on the turbine disk through their tenon heads. The contact edge of the rim plate on the blade concave side of the blade body is an inner concave rim plate concave surface, and the contact edge of the rim plate on the blade back side of the blade body is an outer convex rim plate convex surface; the side surface of the tenon head on the blade concave side of the blade body is an inner concave tenon head concave surface, and the side surface of the tenon head on the blade back side of the blade body is an outer convex tenon head convex surface; the two side wall surfaces of the tenon groove are respectively a tenon groove convex surface matching the tenon head concave surface of the tenon head and a tenon groove concave surface matching the tenon head convex surface of the tenon head.

[0008] Further, a blade root blade concave line is formed at the junction of the blade concave surface of the blade body and the rim plate, and a blade root blade back line is formed at the junction of the blade back surface of the blade body and the rim plate; the bending curvatures of the rim plate concave surface and the tenon head concave surface are respectively close to the bending curvature of the blade root blade concave line; the bending curvatures of the rim plate convex surface and the tenon head convex surface are respectively close to the bending curvature of the blade root blade back line.

[0009] Further, the bending curvature of the rim plate concave surface is the same as the bending curvature of the tenon head concave surface; the bending curvature of the rim plate convex surface is the same as the bending curvature of the tenon head convex surface.

[0010] Further, the bending curvatures of the rim plate concave surface, the tenon head concave surface, the rim plate convex surface and the tenon head convex surface are all the same.

[0011] Further, the aero-engine turbine rotor structure further includes a lock piece for locking the tenon head in the corresponding tenon groove. The lock piece includes a connecting piece and retaining pieces connected to both ends of the connecting piece; the connecting piece is pressed against the bottom surface of the tenon groove by the tenon head, and both ends of the connecting piece extend out from both axial sides of the tenon groove; the two retaining pieces are bent upwards respectively to closely adhere to the axial end surfaces of the corresponding tenon head and the turbine disk.

[0012] Further, the two side edges of the connecting piece are arc surfaces respectively matching the tenon groove concave surface and the tenon groove convex surface of the tenon groove.

[0013] Furthermore, the turbine working blade is formed by a metal material or a ceramic matrix composite material.

[0014] According to another aspect of the present invention, there is also provided a method for designing the fillet bending line, which is used to design the arc bending lines on both sides of the fillet in the aero-engine turbine rotor structure as described in any one of the above, including the following steps: making a plurality of inscribed circles in the root cross-section of the turbine working blade; making a connection line of the inscribed circle centers formed by connecting the inscribed circle centers in sequence; determining the first arc bending line by three points including the leading edge center in the root cross-section, the midpoint of the connection line of the inscribed circle centers, and the trailing edge center; translating the first arc bending line along both sides in the axial direction to form the first concave arc bending line of the fillet concave surface and the first convex arc bending line of the fillet convex surface.

[0015] According to another aspect of the present invention, there is also provided a method for designing the fillet bending line, characterized in that it is used to design the arc bending lines on both sides of the fillet in the aero-engine turbine rotor structure as described in any one of the above, including the following steps: determining the second arc bending line by three points including the leading edge center in the root cross-section, the midpoint of the fillet blade concave line of the root blade concave line, and the trailing edge center; translating the second arc bending line along both sides in the axial direction to form the second concave arc bending line of the fillet concave surface and the second convex arc bending line of the fillet convex surface.

[0016] Furthermore, the first arc bending line or the second arc bending line is translated along both sides in the axial direction by half of the Ye Shanshan pitch; or, the distances of the first arc bending line translated along both sides in the axial direction are not equal, but the distance between the first concave arc bending line and the first convex arc bending line formed after translation is one Ye Shanshan pitch; or the distances of the second arc bending line translated along both sides in the axial direction are not equal, but the distance between the second concave arc bending line and the second convex arc bending line formed after translation is one Ye Shanshan pitch.

[0017] The present invention has the following beneficial effects:

[0018] In the aero-engine turbine rotor structure of the present invention, by respectively designing the two side surfaces of the tenon head as the tenon head concave surface and the tenon head convex surface with arc bends, and respectively designing the two side wall surfaces of the tenon groove as the tenon groove convex surface matching the tenon head concave surface of the tenon head and the tenon groove concave surface matching the tenon head convex surface of the tenon head, compared with the traditional straight tenon head and tenon groove connection structure, in the structure of the present invention, due to the contact and cooperation of the arc bending surfaces of the tenon head and the tenon groove, the contact area of the tenon joint can be increased under the condition of a certain axial space, thereby reducing the stress on the tenon joint contact surface and enhancing the bearing capacity of the tenon head on the turbine working blade and the tenon groove on the turbine disk to withstand a greater centrifugal load of the working blade.

[0019] When the turbine working blade is in a rotating state, due to the excitation of rotation and gas aerodynamic force, the turbine working blade will undergo circumferential vibration. In the structure of the present invention, due to the curved arc surface design between the tenon and the mortise groove, when the tenon undergoes circumferential vibration, friction along the circumferential direction is generated between the tenon and the mortise groove of the turbine disk. Through the frictional force along the circumferential direction of the joint contact surface between the two, the vibration damping of the turbine working blade is increased, the vibration energy of the turbine working blade is consumed, and thus the vibration of the turbine working blade is suppressed. Similarly, the concave and convex surfaces of the shroud on both sides are also arc-shaped curved surfaces. When the turbine working blade vibrates, the arc-shaped curved surfaces on both sides of the shroud cooperate with the corresponding arc-shaped curved surfaces on the upper shroud of the adjacent turbine working blades on the left and right respectively and generate circumferential friction, consuming the vibration energy of the turbine working blade, thereby suppressing the vibration of the turbine working blade. Therefore, in the structure of the present invention, under the combined friction suppression of the tenon and the shroud, the vibration of the turbine working blade can be effectively reduced, the high load-bearing capacity and stable rotation of the turbine working blade are ensured, its safety under high-speed working conditions is improved, and at the same time, no new structures and parts need to be added to the turbine working blade, thus reducing the blade weight and the centrifugal load during the rotation of the turbine working blade.

[0020] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings to further describe the present invention in detail. Brief Description of the Drawings

[0021] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0022] Figure 1 is a schematic spatial structure diagram of a turbine working blade in a preferred embodiment of the present invention;

[0023] Figure 2 is a schematic spatial structure diagram of a turbine disk in a preferred embodiment of the present invention;

[0024] Figure 3 is Figure 1 the assembly state diagram of the turbine working blade in Figure 2 and the turbine disk in

[0025] Figure 4 is a partial schematic spatial diagram of an aeroengine turbine rotor structure in a preferred embodiment of the present invention;

[0026] Figure 5 is a schematic diagram of the connection line of the inscribed circle centers of the design;

[0027] Figure 6 is a schematic diagram of the shroud bending line design method of the present invention Figure One ;

[0028] Figure 7 Schematic diagram of the design method of the flange bending line of the present invention Figure Two ;

[0029] Figure 8 is Figure 1 Schematic diagram of the spatial structure of the middle locking piece;

[0030] Figure 9 Schematic diagram of the spatial structure of the turbine working blade formed by preparing a ceramic matrix composite material.

[0031] Legend:

[0032] 1. Turbine disk; 11. Tenon groove; 111. Tenon groove convex surface; 112. Tenon groove concave surface;

[0033] 2. Turbine working blade; 201. Root blade basin line; 202. Root blade back line; 21. Blade body; 22. Flange; 221. Flange concave surface; 222. Flange convex surface; 23. Tenon head; 231. Tenon head concave surface; 232. Tenon head convex surface; 24. Blade root;

[0034] 3. Locking piece; 31. Connecting piece; 32. Retaining piece;

[0035] 41. Inscribed circle; 42. Connection line of the centers of the inscribed circles; 43. Leading edge center; 44. Midpoint of the connection line; 45. Trailing edge center; 46. First arc bending line; 47. First concave arc bending line; 48. First convex arc bending line; 49. Midpoint of the blade basin line; 51. Second arc bending line; 52. Second concave arc bending line; 53. Second convex arc bending line;

[0036] 61. Mortise joint contact surface. Specific implementation manners

[0037] The following describes the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0038] Refer to Figure 1-3, A preferred embodiment of the present invention provides an aeroengine turbine rotor structure, which includes a turbine disk 1 and a plurality of turbine working blades 2. A plurality of circumferentially uniformly distributed tenon grooves 11 are machined on the outer edge surface of the turbine disk 1. The turbine working blade 2 includes a blade body 21, a rim plate 22 and a tenon head 23 connected in sequence. The turbine working blade 2 is installed in the corresponding tenon groove 11 on the turbine disk 1 through its tenon head 23. The contact edge of the rim plate 22 on the blade body suction side is an inwardly concave rim plate concave surface 221, and the contact edge of the rim plate 22 on the blade body pressure side is an outwardly convex rim plate convex surface 222. The side surface of the tenon head 23 on the blade body suction side is an inwardly concave tenon head concave surface 231, and the side surface of the tenon head 23 on the blade body pressure side is an outwardly convex tenon head convex surface 232. The two side wall surfaces of the tenon groove 11 are respectively a tenon groove convex surface 111 matching the tenon head concave surface 231 of the tenon head 23, and a tenon groove concave surface 112 matching the tenon head convex surface 232 of the tenon head 23.

[0039] In the existing turbine working blades, the tenon head is connected to the tenon groove of the turbine disk. Both the tenon head and the tenon groove are in a straight configuration, and the contact surface between them is a plane. However, the contact bearing area is limited by the axial dimension of the tenon head and it is difficult to bear a greater centrifugal load of the working blade. On the other hand, the contact surface between the rim plates of the turbine working blades is also straight. During the high-speed rotation of the turbine working blades, neither the straight tenon joint structure (referring to the straight-line plane structure of the contact surface between the tenon head and the tenon groove) nor the straight rim plate structure can provide sufficient circumferential friction to damp the vibration of the blade when the blade vibrates. Therefore, it is necessary to add structures or parts such as blade crowns or damping sheets to the blade to damp the vibration of the blade.

[0040] In the aeroengine turbine rotor structure of the present invention, by respectively designing the two side surfaces of the tenon head 23 as the arc-bent tenon head concave surface 231 and the tenon head convex surface 232, and respectively designing the two side wall surfaces of the tenon groove 11 as the tenon groove convex surface 111 matching the tenon head concave surface 231 of the tenon head 23, and the tenon groove concave surface 112 matching the tenon head convex surface 232 of the tenon head 23. Thus, compared with the traditional straight tenon head and tenon groove connection structure, in the structure of the present invention, due to the contact fit of the arc-bent surfaces of the tenon head 23 and the tenon groove 11, the area of the tenon joint contact surface 61 can be increased under the condition of a certain axial space, thereby reducing the stress of the tenon joint contact surface 61 and enhancing the bearing capacity of the tenon head 23 on the turbine working blade 2 and the tenon groove 11 on the turbine disk 1 to bear a greater centrifugal load of the working blade.

[0041] When the turbine working blade 2 is in a rotating state, due to the excitation of rotation and gas aerodynamic force, the turbine working blade 2 will undergo circumferential vibration. In the structure of the present invention, due to the curved arc surface design between the contact of the tenon 23 and the mortise 11, when the tenon 23 undergoes circumferential vibration, friction along the circumferential direction is generated between the tenon 23 and the mortise 11 of the turbine disk 1. Through the frictional action along the circumferential direction of the tenon-mortise contact surface 61 between the two, the vibration damping of the turbine working blade 2 is increased, the vibration energy of the turbine working blade 2 is consumed, and thus the vibration of the turbine working blade 2 is suppressed. Similarly, the concave flanges 221 and the convex flanges 222 on both sides of the flange 22 are also arc-shaped curved surfaces. When the turbine working blade 2 vibrates, the arc-shaped curved surfaces on both sides of the flange 22 cooperate with the arc-shaped curved surfaces on the corresponding sides of the flanges 22 of the adjacent turbine working blades 2 on the left and right and generate friction along the circumferential direction, consuming the vibration energy of the turbine working blade 2, thereby suppressing the vibration of the turbine working blade 2. Therefore, in the structure of the present invention, under the combined friction suppression of the tenon 23 and the flange 22, the vibration of the turbine working blade 2 can be effectively reduced, the high load-bearing capacity and stable rotation of the turbine working blade 2 are ensured, and its safety under high-speed working conditions is improved. At the same time, there is no need to add new structures and parts to the turbine working blade 2, thereby reducing the blade weight and the centrifugal load during the rotation of the turbine working blade 2.

[0042] Optionally, as Figure 1 shown, at the junction of the suction surface of the blade body 21 and the flange 22, a blade root suction line 201 is formed, and at the junction of the pressure surface of the blade body 21 and the flange 22, a blade root pressure line 202 is formed. The bending curvatures of the concave flange 221 and the concave tenon 231 are respectively close to the bending curvature of the blade root suction line 201. The bending curvatures of the convex flange 222 and the convex tenon 232 are respectively close to the bending curvature of the blade root pressure line 202.

[0043] When preparing the turbine working blade 2 with ceramic matrix composite materials, since the rabbet concave surfaces 231 and rabbet convex surfaces 232 on both sides of the rabbet 23 are respectively similar to the bending of the root blade face line 201 and the root blade back line 202 at the blade root, that is, the bending of the rabbet 23 is similar to the bending of the blade profile at the blade root. Therefore, in the entire root region, the rabbet 23 can be well maintained below the blade root, and the fibers of the blade body can continuously extend vertically to the rabbet 23, thereby reducing the preparation difficulty of the rabbet 23 prepared with ceramic matrix composite materials. At the same time, the continuous fibers can improve the bearing capacity of the rabbet 23 for the centrifugal load of the blade body. On the other hand, in the present invention, the structure of the curved flange 22 is more conformable to the blade profile at the blade root than the straight flange structure. Therefore, the cantilever structure of the flange 22 is shorter, which is beneficial to improving the strength of the flange 22 under the action of centrifugal force during rotation and can also reduce the preparation difficulty of the cantilever structure of the flange 22 prepared with ceramic matrix composite materials. Therefore, overall, the structure of the turbine working blade 2 prepared with ceramic matrix composite materials makes the rabbet 23 and the flange 22 more conformable to the blade root profile, thereby greatly reducing the machining amount in the process of preparing the turbine working blade 2 with ceramic matrix composite materials, reducing the preparation difficulty, and at the same time avoiding the fibers from being bent and cut, and further improving the bearing capacity of the rabbet 23 and the flange 22 of the turbine working blade 2 made of ceramic matrix composite materials.

[0044] Further, the bending curvature of the flange concave surface 221 is the same as that of the rabbet concave surface 231. The bending curvature of the flange convex surface 222 is the same as that of the rabbet convex surface 232. In this further solution, for the structure of the turbine working blade 2 prepared with ceramic matrix composite materials, when the bending curvature of the flange concave surface 221 is the same as that of the rabbet concave surface 231 and the bending curvature of the flange convex surface 222 is the same as that of the rabbet convex surface 232, the rabbet 23 and the flange 22 can be further made more conformable to the blade root profile, thereby further greatly reducing the machining amount in the process of preparing the turbine working blade 2 with ceramic matrix composite materials, further reducing the preparation difficulty, and at the same time avoiding the fibers from being bent and cut, and further improving the bearing capacity of the rabbet 23 and the flange 22 of the turbine working blade 2 made of ceramic matrix composite materials.

[0045] Furthermore, the bending curvatures of the flange concave surface 221, the tenon concave surface 231, the flange convex surface 222, and the tenon convex surface 232 are the same. In a further aspect of the present application, for the structure of the turbine working blade 2 made of ceramic matrix composite material, when the bending curvatures of the flange concave surface 221, the tenon concave surface 231, the flange convex surface 222, and the tenon convex surface 232 are the same, the tenon 23 and the flange 22 can be made to fit better with the blade root profile, thereby further significantly reducing the machining amount during the preparation of the turbine working blade 2 made of ceramic matrix composite material, further reducing the preparation difficulty, while avoiding the fibers from being bent and cut, and further improving the bearing capacity of the tenon 23 and the flange 22 of the turbine working blade 2 made of ceramic matrix composite material.

[0046] Preferably, as Figure 4 and Figure 8 shown, the aeroengine turbine rotor structure further includes a locking piece 3 for locking the tenon 23 in the corresponding mortise 11. The locking piece 3 includes a connecting piece 31 and retaining pieces 32 connected to both ends of the connecting piece 31. The connecting piece 31 is pressed against the bottom surface of the mortise 11 by the tenon 23, and both ends of the connecting piece 31 extend out from both axial sides of the mortise 11. The two retaining pieces 32 are bent upwards respectively to closely adhere to the axial end surfaces of the corresponding tenon 23 and the turbine disk 1. In a preferred embodiment of the present invention, the locking piece 3 is made of a superalloy sheet by sheet metal working. Figure 8 is the form after the locking piece is installed. During the processing, one of the retaining pieces 32 of the locking piece 3 remains horizontal. After being assembled on the turbine working blade 2 and the turbine disk 1, the horizontal retaining piece 32 is bent by an external force, as Figure 4 shown, to fix the turbine working blade 2.

[0047] Further, as Figure 8 shown, the two side edges of the connecting piece 31 are arc-shaped surfaces respectively matching the mortise concave surface 112 and the mortise convex surface 111 of the mortise 11, so as to further improve the stability of the locking piece 3 installed in the mortise 11, and further improve the fixing stability of the turbine working blade 2.

[0048] Optionally, the turbine working blades 2 are made of metal materials or ceramic-based composite materials. During operation, as the temperature of the turbine increases, some turbine working blades use ceramic-based composite materials that can withstand higher temperatures to improve their temperature resistance. However, the straight plane tenon and edge plate structure of the existing turbine blades is difficult to transition between the blade body arc surface configuration and the straight plane configuration tenon and edge plate when continuous fiber stacking is used. Therefore, a large number of machining processes are required. While the preparation is difficult, it will also cause the fibers to be bent and cut, which is not conducive to improving the load-bearing capacity of the ceramic-based composite tenon and edge plate. In the structure of the present invention, ceramic-based composite materials can be used to prepare the turbine working blades 2, and its structure is as follows Figure 9 As shown, the turbine working blade 2 of the ceramic-based composite material adopts an arc-curved edge plate 22 and a tenon 23 structure, and the tenon 23 adopts a dovetail structure, which further reduces the difficulty of processing. Since the curvature of the tenon 23 is similar to the curvature of the blade shape at the root of the blade, the tenon 23 can be well maintained below the root 24 in the entire blade root 24 area, and the fibers of the blade body can extend vertically and continuously to the tenon 23, thereby reducing the difficulty of preparing the ceramic-based composite material tenon 23. At the same time, the continuous fibers can improve the bearing capacity of the tenon 23 to the centrifugal load of the blade body. On the other hand, since the edge plate 22 structure in the present invention fits the blade root 24 blade shape better than the straight edge plate structure, the cantilever structure of the edge plate 22 is shorter, which is conducive to improving the strength of the edge plate 22 under the action of centrifugal force when rotating, and can also reduce the difficulty of preparing the cantilever structure of the ceramic-based composite material edge plate 22. In summary, the structure of the ceramic-based composite turbine working blade 2 provided by the present invention makes the tenon 23 and the edge plate 22 more closely fit the root blade shape of the blade, greatly reduces the amount of machining in the process of preparing the turbine working blade 2 using ceramic-based composite materials, reduces the difficulty of preparation, and avoids the bending and cutting of the fibers, thereby improving the bearing capacity of the tenon 23 and the edge plate 22 of the ceramic-based composite turbine working blade 2.

[0049] Reference Figure 5-6 The preferred embodiment of the present invention further provides a method for designing a lip plate bending line, which is used to design arc bending lines on both sides of the lip plate 22 in the aero-engine turbine rotor structure as described above, and comprises the following steps:

[0050] A plurality of inscribed circles 41 are drawn within the root cross section of the turbine rotor blade 2 .

[0051] An inscribed circle center connecting line 42 is drawn by sequentially connecting the centers of the inscribed circles 41.

[0052] The first arc bending line 46 is determined by three points: the leading edge center 43 in the blade root cross section, the midpoint 44 of the line connecting the centers of the inscribed circles 42 , and the trailing edge center 45 .

[0053] Translate the first circular arc bending line 46 axially on both sides to form the first concave circular arc bending line 47 of the flange concave surface 221 and the first convex circular arc bending line 48 of the flange convex surface 222.

[0054] When using the flange bending line design method of the present invention to design the circular arc bending lines on both sides of the flange 22 in the aeroengine turbine rotor structure as described in any one of the above, the entire design operation steps are simple and easy to implement, and the configurations of the flange concave surface 221 and the flange convex surface 222 on both sides of the flange 22 of the designed turbine working blade 2 are closer to the blade root configuration. When the turbine working blade 2 is prepared using a ceramic matrix composite material, the machining amount during the preparation process can be significantly reduced, the preparation difficulty can be lowered, and the continuity of the blade body fibers and the tenon fibers of the ceramic matrix composite material turbine working blade 2 can be improved, enhancing the load-bearing capacity of the ceramic matrix composite material turbine working blade.

[0055] Refer to Figure 7 , a preferred embodiment of the present invention further provides a flange bending line design method for designing the circular arc bending lines on both sides of the flange 22 in the aeroengine turbine rotor structure as described in any one of the above, including the following steps:

[0056] Determine the second circular arc bending line 51 from three points: the leading edge center 43 in the blade root cross-section, the midpoint 49 of the blade root blade concave line 201, and the trailing edge center 45.

[0057] Translate the second circular arc bending line 51 axially on both sides to form the second concave circular arc bending line 52 of the flange concave surface 221 and the second convex circular arc bending line 53 of the flange convex surface 222.

[0058] Similarly, when using the flange bending line design method of the present invention to design the circular arc bending lines on both sides of the flange 22 in the aeroengine turbine rotor structure as described in any one of the above, the entire design operation steps are simpler and easier to implement, and the configurations of the flange concave surface 221 and the flange convex surface 222 on both sides of the flange 22 of the designed turbine working blade 2 are closer to the blade root configuration. When the turbine working blade 2 is prepared using a ceramic matrix composite material, the machining amount during the preparation process can be significantly reduced, the preparation difficulty can be lowered, and the continuity of the blade body fibers and the tenon fibers of the ceramic matrix composite material turbine working blade 2 can be improved, enhancing the load-bearing capacity of the ceramic matrix composite material turbine working blade.

[0059] Preferably, the first circular arc bending line 46 or the second circular arc bending line 51 is translated by half of the blade pitch along both axial sides respectively. Alternatively, the distances translated by the first circular arc bending line 46 along both axial sides are not equal, but the distance between the first concave circular arc bending line 47 and the first convex circular arc bending line 48 formed after translation is one blade pitch. Or the distances translated by the second circular arc bending line 51 along both axial sides are not equal, but the distance between the second concave circular arc bending line 52 and the second convex circular arc bending line 53 formed after translation is one blade pitch. Thus, when the adjacent turbine working blades 2 are installed in the adjacent two tenon grooves 11 on the turbine disk 1, the flanges 22 of the adjacent turbine working blades 2 are well butt-jointed, which is convenient for installation and reduces the air leakage. At the same time, through the good circumferential friction between the adjacent flanges 22, the vibration energy of the turbine working blades 2 is consumed, thereby further suppressing the vibration of the turbine working blades 2.

[0060] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An aeroengine turbine rotor structure, comprising a turbine disk (1) and a plurality of turbine working blades (2). A plurality of circumferentially evenly distributed tenon grooves (11) are machined on the outer edge surface of the turbine disk (1). The turbine working blades (2) include a blade body (21), a shroud (22) and a tenon head (23) connected in sequence. The turbine working blades (2) are installed in the corresponding tenon grooves (11) on the turbine disk (1) through their tenon heads (23). It is characterized in that the contact edge of the shroud (22) on the blade concave side of the blade body is an inwardly concave shroud concave surface (221), and the contact edge of the shroud (22) on the blade back side of the blade body is an outwardly convex shroud convex surface (222); the side surface of the tenon head (23) on the blade concave side of the blade body is an inwardly concave tenon head concave surface (231), and the side surface of the tenon head (23) on the blade back side of the blade body is an outwardly convex tenon head convex surface (232); the two side wall surfaces of the tenon groove (11) are respectively a tenon groove convex surface (111) matching the tenon head concave surface (231) of the tenon head (23), and a tenon groove concave surface (112) matching the tenon head convex surface (232) of the tenon head (23).

2. The aeroengine turbine rotor structure according to claim 1, characterized in that a blade root blade concave line (201) is formed at the connection between the blade concave surface of the blade body (21) and the shroud (22), and a blade root blade back line (202) is formed at the connection between the blade back surface of the blade body (21) and the shroud (22); the bending curvatures of both the shroud concave surface (221) and the tenon head concave surface (231) are respectively close to the bending curvature of the blade root blade concave line (201); the bending curvatures of both the shroud convex surface (222) and the tenon head convex surface (232) are respectively close to the bending curvature of the blade root blade back line (202).

3. The aeroengine turbine rotor structure according to claim 2, characterized in that the bending curvature of the shroud concave surface (221) is the same as the bending curvature of the tenon head concave surface (231); the bending curvature of the shroud convex surface (222) is the same as the bending curvature of the tenon head convex surface (232).

4. The aeroengine turbine rotor structure according to claim 3, characterized in that the bending curvatures of the shroud concave surface (221), the tenon head concave surface (231), the shroud convex surface (222) and the tenon head convex surface (232) are all the same.

5. The aeroengine turbine rotor structure according to claim 1, characterized in that the aeroengine turbine rotor structure further includes a lock piece (3) for locking the tenon head (23) in the corresponding tenon groove (11). The lock piece (3) includes a connecting piece (31) and retaining pieces (32) connected to both ends of the connecting piece (31); the connecting piece (31) is pressed against the bottom surface of the tenon groove (11) through the tenon head (23), and both ends of the connecting piece (31) extend out from both axial sides of the tenon groove (11); the two retaining pieces (32) are respectively bent upward to closely adhere to the axial end surfaces of the corresponding tenon head (23) and the turbine disk (1).

6. The aeroengine turbine rotor structure according to claim 5, characterized in that The two side edges of the connecting piece (31) are arc-shaped surfaces that respectively match the concave surface (112) and the convex surface (111) of the mortise groove (11).

7. The aero-engine turbine rotor structure according to claim 1, wherein The turbine working blade (2) is formed by a metal material or a ceramic matrix composite material.

8. A method for designing the bending line of a flange, characterized in that, The method for designing the arc bending lines on both sides of the rim plate (22) in the aero-engine turbine rotor structure according to any one of claims 1-4 includes the following steps: Draw a plurality of inscribed circles (41) in the root section of the turbine working blade (2); Draw a connecting line (42) of the centers of the inscribed circles formed by sequentially connecting the centers of the inscribed circles (41); Determine the first arc bending line (46) from three points: the leading edge center (43) in the root section, the midpoint (44) of the connecting line of the centers of the inscribed circles (42), and the trailing edge center (45); Translate the first arc bending line (46) along both sides of the axis respectively to form the first concave arc bending line (47) of the rim plate concave surface (221) and the first convex arc bending line (48) of the rim plate convex surface (222).

9. A design method for the bending line of the flange, characterized in that, The method for designing the arc bending lines on both sides of the rim plate (22) in the aero-engine turbine rotor structure according to any one of claims 1-4 includes the following steps: Determine the second arc bending line (51) from three points: the leading edge center (43) in the root section, the midpoint (49) of the blade basin line of the root blade basin line (201), and the trailing edge center (45); Translate the second arc bending line (51) along both sides of the axis respectively to form the second concave arc bending line (52) of the rim plate concave surface (221) and the second convex arc bending line (53) of the rim plate convex surface (222).

10. The method for designing the rim plate bending line according to any one of claims 8 or 9, wherein The first arc bending line (46) or the second arc bending line (51) is translated along both sides of the axis by half of the Ye Shanshan pitch respectively; or The distances of the translation of the first arc bending line (46) along both sides of the axis are not equal, but the distance between the first concave arc bending line (47) and the first convex arc bending line (48) formed after translation is one Ye Shanshan pitch; or the distances of the translation of the second arc bending line (51) along both sides of the axis are not equal, but the distance between the second concave arc bending line (52) and the second convex arc bending line (53) formed after translation is one Ye Shanshan pitch.

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