Compressor rotor assembly structure and engine

Abstract

The application discloses a compressor rotor assembly structure, which is designed according to different axial fixing modes of different stages of blades under different axial load, wherein the tenon of the first to seventh stage blades is radially inclined, the axial component force of the centrifugal force of the blades is larger than the axial component force of the aerodynamic force, a first groove is arranged at the end of the tenon of the blade close to the next stage blade, a stopper is arranged at the first groove to limit the movement of the blade to one end, and a first lock plate is arranged at the bottom of the tenon to limit the movement of the blade to the other end; the axial fixing of the tenon of the eighth stage blade is different from that of other stages, a second groove is arranged at the end of the tenon of the eighth stage blade close to the seventh stage blade, the tenon is fixed by using the connecting pin of the seventh stage and the eighth stage wheel disc in the second groove, and a first lock plate is arranged at the bottom of the tenon to limit the other end; the tenon of the ninth to tenth stage blades is not radially inclined, the axial component force of the centrifugal force of the blades is equal to zero, and the tenon is not designed with a groove and is fixed by using a second lock plate with a double tail flat plate. The assembly structure fully improves the working reliability of the compressor rotor.

Description

Technical Field

[0001] This invention relates to the field of aero-engine rotor assembly technology, specifically to a compressor rotor assembly structure and an engine. Background Technology

[0002] The compressor of a turboprop aero-engine is a single-rotor, ten-stage subsonic axial-flow compressor. Its function is to use the output power of the turbine to draw in and compress outside air, increasing its pressure and temperature to form a continuous, high-pressure airflow from front to back. The compressor mainly consists of a compressor rotor and a compressor stator. The compressor rotor is supported on two rolling bearings. Its role is to use the power transmitted from the turbine to compress the air, increasing its pressure, and then transmit the remaining power to the propeller and accessories. The compressor rotor mainly consists of components such as a rotor disc, blades, roller bearings, and ball bearings.

[0003] In existing technology, the structure and assembly of the first to tenth stages of the compressor rotor are consistent. However, during operation, the axial force on each stage of the blades is different. Blades subjected to greater axial force are prone to backward displacement and loosening, which in turn affects the reliability of the compressor rotor and ultimately the safe use of the engine.

[0004] Patent CN110836199A discloses a connection structure between a high-pressure specific pressure pneumatic impeller blade and a rotor. This invention addresses the problem in the prior art where, during operation, the blades of the impeller are subjected to aerodynamic forces in the direction of the air intake, resulting in axial displacement that can easily lead to contact with the stator components, causing scratch damage to the end face of the stator components and thus affecting the normal operation of the compressor. The patent mainly proposes a locking structure for connecting blades with axial dovetail tenons and rotors with axial dovetail tenon structures. The locking structure includes blades, locking plates, rotors, and locking pins. The blades, locking plates, and rotors are arranged sequentially from top to bottom. The locking plates are inserted into the tenons at the root of the blades, and the rotors are fixedly connected to the locking plates by the locking pins.

[0005] The aforementioned patents all use the same connection and locking structure for each stage of the blades and the rotor, and do not take into account the different forces exerted on each stage of the blades, thus failing to guarantee the operational reliability of the compressor rotor. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defects of the prior art and provide a compressor rotor assembly structure that designs the assembly method of blades and rotor disk according to the stress conditions of each stage of blades, so as to fully improve the working reliability of each stage of blades and engine.

[0007] The objective of this invention is achieved through the following technical solution:

[0008] A compressor rotor assembly structure includes first to tenth stage blades and first to tenth stage discs that respectively mate with each stage blade. Each stage disc has tenons for inserting the blades. The tenons of the first to seventh stage blades have a first groove at the end near the next stage blade. The first to seventh stage discs have mounting holes at the positions opposite to the first grooves. A stopper is installed in the mounting hole, and the outer periphery of the other end of the stopper contacts the end face of the first groove to restrict blade movement. The tenon of the eighth stage blade has a second groove at the end near the seventh stage blade. A first locking plate is fitted to the bottom of the tenons of the first to eighth stage blades. A first locking plate groove is provided in the tenon groove for the first locking plate to be inserted. A limiting structure is provided on the first locking plate to prevent the first locking plate from coming out of the first locking plate groove. The first locking plate also has an extended end that extends out of the first locking plate groove. The extended end is bent and fits against the end face of the blade tenon. A second locking plate is fitted against the bottom of the ninth to tenth blade tenon. A second locking plate groove is provided in the tenon groove of the ninth to tenth wheel for the second locking plate to be inserted. A positioning structure is provided on the second locking plate to prevent the second locking plate from coming out of the second locking plate groove. The second locking plate has an extended end that extends to both ends of the blade tenon. The extended end is bent and fits against the end face of the blade tenon.

[0009] The present invention also provides an engine having a compressor rotor assembly structure as described above.

[0010] Compared with the prior art, the present invention has the following beneficial effects:

[0011] In this invention, the rotor assembly structure is designed with different axial fixing methods based on the varying axial loads on each stage of the blades. For the first to seventh stages, the tenons of the blades have a larger radial inclination, and the axial component of the centrifugal force acting backward is greater than the axial component of the aerodynamic force acting forward. A first groove is created at the end of the blade tenon near the next stage blade, and a stop is installed at this groove to restrict the blade's movement to one end. A first locking plate is installed at the bottom of the tenon to restrict the blade's movement to the other end. The axial fixing of the eighth-stage blade tenon differs from the other stages. A second groove is created at the end of the tenon near the seventh-stage blade, and the connecting pin between the seventh and eighth-stage rotors is used to fix it within this groove. A first locking plate is installed at the bottom of the tenon to limit movement to the other end. For the ninth and tenth-stage blades, since the tenons are not radially inclination, the axial component of the centrifugal force is zero. No groove is designed for the blade tenons; instead, a double-tailed flat second locking plate is used for fixation. This design of different structures and fixing methods for parts based on actual stress conditions fully ensures the reliability and safety of the blades, thereby improving the operational reliability of the compressor rotor. Attached Figure Description

[0012] Figure 1 This is a cross-sectional view of the assembly of the first to seventh stage blades and the disk as described in Example 1;

[0013] Figure 2 This is a schematic diagram of the tenon grooves of the first to seventh level wheel discs described in Example 1;

[0014] Figure 3 This is a schematic diagram of the structure of the first locking plate described in Example 1;

[0015] Figure 4 for Figure 1 NN cross-section diagram;

[0016] Figure 5 This is a cross-sectional view of the assembly of the eighth to tenth stage blades and the disk in the compressor rotor assembly structure described in Example 1;

[0017] Figure 6 This is a schematic diagram of the tenon groove of the eighth-level wheel described in Example 1;

[0018] Figure 7 This is a schematic diagram of the tenon groove of the ninth to tenth level wheel as described in Example 1;

[0019] Figure 8 This is a schematic diagram of the structure of the second locking plate described in Example 1. Detailed Implementation

[0020] To clearly illustrate the technical features of this solution, the following detailed description, in conjunction with the accompanying drawings, will explain the technical solution in detail.

[0021] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein. Therefore, the scope of protection of this application is not limited to the specific embodiments disclosed below.

[0022] Furthermore, it should be understood in the description of this application that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "a plurality of" means two or more, unless otherwise explicitly specified.

[0023] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a communication connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0024] In this application, unless otherwise expressly specified and limited, the "above" or "below" of the second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. In the description of this specification, references to terms such as "an embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described can be combined in any suitable manner in one or more embodiments or examples.

[0025] Example 1

[0026] An engine is provided, whose compressor rotor assembly structure includes first to tenth stage blades 1 and first to tenth stage impellers 2 that respectively mate with each stage blade. Each blade 1 consists of a blade body 11 and dovetail tenons 12. The blade body has a precise profile, sufficient strength, and low surface roughness, enabling it to withstand aerodynamic forces and significant centrifugal forces. The blade body profile improves the compressor's pressure ratio and efficiency. The impeller 2 has evenly distributed dovetail tenons 21 broached on its rim for each stage blade to embed into. The blades are positioned laterally and radially by the dovetail tenons. The force borne by the blades 1 is transmitted to the impeller 2 through the tenons 12. The dovetail tenon connection structure is easy to manufacture, reliable in operation, and has minimal damping effect on blade vibration.

[0027] Among them, such as Figure 1 As shown, the tenons 12 of the first to seventh stage blades have a large radial inclination. The axial component of the centrifugal force of these blades in the direction of the next stage blade is greater than the axial component of the aerodynamic force in the direction of the previous stage blade. Therefore, the tenons 12 of the first to seventh stage blades have a first groove 13 at the end near the end of the next stage blade, as shown. Figure 2As shown, the first to seventh stage wheel discs 2 have mounting holes 22 at the positions opposite to the first groove 13. A stopper 3 is installed in the mounting hole 22, extending out from the outer periphery of the end of the mounting hole 22 and contacting the end face of the first groove 13 to prevent the blade 1 from loosening or moving towards the next stage blade under the action of centrifugal force. Simultaneously, a first locking piece 4 is fitted to the bottom of the tenon 12 of the first to seventh stage blades. Figure 2 and Figure 4 In the first to seventh level wheel tenon grooves 21, a first locking plate groove 23 is provided for the first locking plate 4 to be inserted. A limiting structure 41 is provided on the first locking plate 4 to prevent the first locking plate from coming out of the first locking plate groove 23. Figure 1 As shown, the first locking plate 4 also has an extended end 42 extending out of the first locking plate groove 23. The extended end 42 is bent and fits against the end face of the blade tenon 12 to prevent the blade 1 from moving in the direction of the previous stage blade.

[0028] The aforementioned stopper 3 is preferably a stop pin. The end of the stop pin must contact the bottom of the mounting hole. At least the stop pins on the first and second stage wheel discs must be pressed to the bottom of the mounting hole to prevent the stopper from sinking and weakening its stopping effect. The stop pin and the mounting hole are interference-fitted, with an interference amount of 0.023 to 0.002 mm.

[0029] The blade tenon 12 and the wheel mortise 21 are fitted with a clearance fit, which can ensure the free thermal expansion of the blade tenon during operation. Preferably, the fit clearance is 0.006 to 0.036 mm.

[0030] Each level of the wheel 2 is connected to the others by connecting pins 5. The wheel 2 has pin holes 24 for installing the connecting pins 5. Figure 1 As shown, the connecting pin 5 between the first to seventh level wheel is located below the first locking plate 4.

[0031] The structure of the first locking piece 4 is as follows: Figure 3 As shown, its limiting structure 41 is an arc structure. In this embodiment, the radius of the arc structure is taken as 0.1 to 0.3 mm, taking into account the actual size of the tenon groove.

[0032] The eighth-stage wheel differs in structure from the other wheel stages; therefore, the axial fixing of the tenon of the eighth-stage blade differs from that of the other stages. Figure 5 As shown, the tenon 12 of the eighth-stage blade has a second groove 14 at its end near the seventh-stage blade. A connecting pin 5 between the seventh and eighth-stage discs extends into the second groove 14 and contacts its end face, thus preventing the eighth-stage blade from loosening or moving. Figure 6As shown, the bottom of the eighth-stage blade tenon 12 is also fitted with a first locking piece 4, and the wheel tenon 21 is also provided with a first locking piece groove 23 for the first locking piece 4 to be inserted. The end of the first locking piece is bent and fitted to the end face of the eighth-stage blade tenon. The structure of the first locking piece is as described above and will not be described again here.

[0033] For the ninth and tenth stage blades, since the tenon is not radially inclined, the axial component of the centrifugal force is zero. Furthermore, because the axial component of the aerodynamic force is small, the tenon of the blade does not require a groove. Figure 5 and Figure 7 As shown, a second locking piece 6 is directly attached to the bottom of the tenon 12 of the ninth to tenth stage blades. A second locking piece groove 25 is provided in the tenon 21 of the ninth to tenth stage wheel for the second locking piece 6 to be inserted. A positioning structure 61 is provided on the second locking piece 6 to prevent the second locking piece from coming out of the second locking piece groove 25. The second locking piece has extension ends 62 that extend to both ends of the blade tenon. The two extension ends 62 are bent and attached to the two end faces of the blade tenon 12 respectively.

[0034] The structure of the second locking piece 6 is as follows: Figure 8 As shown, its positioning structure 61 is circular in shape. If the two extended ends of the positioning structure are defined as two tails, then the second locking plate is a double-tailed flat plate structure. Only the second locking plate can lock and limit the ninth / tenth stage blade.

[0035] To further ensure the positioning stability of each stage of the blades, the first locking plate and the first locking plate groove, and the second locking plate and the second locking plate groove adopt a clearance interference fit, with an interference of 0.08mm to a clearance of 0.07mm; in addition, the surface of the first locking plate away from the first locking plate groove, the surface of the second locking plate away from the second locking plate groove, and the bottom surface of the corresponding tenon groove are flush.

[0036] The rotor assembly structure of this embodiment is designed to accommodate the different axial loads on each stage of the blades, which can effectively prevent the blades from loosening or moving, thus ensuring the reliability and safety of the blades and improving the reliability of the compressor rotor.

[0037] Example 2

[0038] A compressor rotor assembly structure includes first to tenth stage blades and first to tenth stage discs that respectively mate with each stage blade, such as... Figure 1 As shown, the tenons 12 of the first to seventh stage blades have a large radial inclination. The axial component of the centrifugal force of these blades in the direction of the next stage blade is greater than the axial component of the aerodynamic force in the direction of the previous stage blade. Therefore, the tenons 12 of the first to seventh stage blades have a first groove 13 at the end near the end of the next stage blade, as shown. Figure 2As shown, the first to seventh stage wheel discs 2 have mounting holes 22 at the positions opposite to the first groove 13. A stopper 3 is installed in the mounting hole 22, extending out from the outer periphery of the end of the mounting hole 22 and contacting the end face of the first groove 13 to prevent the blade 1 from loosening or moving towards the next stage blade under the action of centrifugal force. Simultaneously, a first locking piece 4 is fitted to the bottom of the tenon 12 of the first to seventh stage blades. Figure 2 and Figure 4 In the first to seventh level wheel tenon grooves 21, a first locking plate groove 23 is provided for the first locking plate 4 to be inserted. A limiting structure 41 is provided on the first locking plate 4 to prevent the first locking plate from coming out of the first locking plate groove 23. Figure 1 As shown, the first locking plate 4 also has an extended end 42 extending out of the first locking plate groove 23. The extended end 42 is bent and fits against the end face of the blade tenon 12 to prevent the blade 1 from moving in the direction of the previous stage blade.

[0039] The aforementioned stopper 3 is preferably a stop pin. The end of the stop pin must contact the bottom of the mounting hole. At least the stop pins on the first and second stage wheel discs must be pressed to the bottom of the mounting hole to prevent the stopper from sinking and weakening its stopping effect. The stop pin and the mounting hole are interference-fitted, with an interference amount of 0.023 to 0.002 mm.

[0040] The blade tenon 12 and the wheel mortise 21 are fitted with a clearance fit, which can ensure the free thermal expansion of the blade tenon during operation. Preferably, the fit clearance is 0.006 to 0.036 mm.

[0041] Each level of the wheel 2 is connected to the others by connecting pins 5. The wheel 2 has pin holes 24 for installing the connecting pins 5. Figure 1 As shown, the connecting pin 5 between the first to seventh level wheel is located below the first locking plate 4.

[0042] The structure of the first locking piece 4 is as follows: Figure 3 As shown, its limiting structure 41 is an arc structure. In this embodiment, the radius of the arc structure is taken as 0.1 to 0.3 mm, taking into account the actual size of the tenon groove.

[0043] The eighth-stage wheel differs in structure from the other wheel stages; therefore, the axial fixing of the tenon of the eighth-stage blade differs from that of the other stages. Figure 5 As shown, the tenon 12 of the eighth-stage blade has a second groove 14 at its end near the seventh-stage blade. A connecting pin 5 between the seventh and eighth-stage discs extends into the second groove 14 and contacts its end face, thus preventing the eighth-stage blade from loosening or moving. Figure 6As shown, the bottom of the eighth-stage blade tenon 12 is also fitted with a first locking piece 4, and the wheel tenon 21 is also provided with a first locking piece groove 23 for the first locking piece 4 to be inserted. The end of the first locking piece is bent and fitted to the end face of the eighth-stage blade tenon. The structure of the first locking piece is as described above and will not be described again here.

[0044] For the ninth and tenth stage blades, since the tenon is not radially inclined, the axial component of the centrifugal force is zero. Furthermore, because the axial component of the aerodynamic force is small, the tenon of the blade does not require a groove. Figure 5 and Figure 7 As shown, a second locking piece 6 is directly attached to the bottom of the tenon 12 of the ninth to tenth stage blades. A second locking piece groove 25 is provided in the tenon 21 of the ninth to tenth stage wheel for the second locking piece 6 to be inserted. A positioning structure 61 is provided on the second locking piece 6 to prevent the second locking piece from coming out of the second locking piece groove 25. The second locking piece has extension ends 62 that extend to both ends of the blade tenon. The two extension ends 62 are bent and attached to the two end faces of the blade tenon 12 respectively.

[0045] The structure of the second locking piece 6 is as follows: Figure 8 As shown, its positioning structure 61 is circular in shape. If the two extended ends of the positioning structure are defined as two tails, then the second locking plate is a double-tailed flat plate structure. Only the second locking plate can lock and limit the ninth / tenth stage blade.

[0046] To further ensure the positioning stability of each stage of the blades, the first locking plate and the first locking plate groove, and the second locking plate and the second locking plate groove adopt a clearance interference fit, with an interference of 0.08 mm to a clearance of 0.07 mm.

[0047] The difference between this embodiment and Embodiment 1 is that the surface of the first locking piece away from the first locking piece groove, the surface of the second locking piece away from the second locking piece groove, and the bottom surface of the corresponding tenon groove have a height difference. In actual operation, a concavity of 0.3max is allowed, that is, the height difference between the first locking piece / second locking piece and the bottom surface of the corresponding tenon groove is kept within 0.3mm.

[0048] Example 3

[0049] The difference between this embodiment and Embodiment 1 is that the limiting structure of the first locking piece can be any shape other than an arc, as long as it can prevent the first locking piece from coming off; similarly, the positioning structure of the second locking piece can also be any shape other than a circle.

[0050] Obviously, the above embodiments are merely examples to clearly illustrate the technical solutions of the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A compressor rotor assembly structure, characterized in that, The system includes first to tenth stage blades and first to tenth stage discs that respectively mate with each stage blade. Each stage disc has a tenon for inserting the blade. The tenons of the first to seventh stage blades have a first groove at the end near the next stage blade. The first to seventh stage discs have mounting holes at the positions opposite to the first grooves. A stop is installed in the mounting holes, and the outer periphery of the other end of the stop contacts the end face of the first groove to restrict blade movement. The tenon of the eighth stage blade has a second groove at the end near the seventh stage blade. A first locking piece is fitted to the bottom of the tenons of the first to eighth stage blades. The tenons of the first to eighth stage discs have... A first locking plate groove is provided for the first locking plate to be inserted. A limiting structure is provided on the first locking plate to prevent the first locking plate from coming out of the first locking plate groove. The first locking plate also has an extended end that extends out of the first locking plate groove. The extended end is bent and fits against the end face of the blade tenon. A second locking plate is fitted to the bottom of the ninth to tenth level blade tenon. A second locking plate groove is provided in the ninth to tenth level wheel tenon for the second locking plate to be inserted. A positioning structure is provided on the second locking plate to prevent the second locking plate from coming out of the second locking plate groove. The second locking plate has an extended end that extends to both ends of the blade tenon. The extended end is bent and fits against the end face of the blade tenon.

2. The compressor rotor assembly structure according to claim 1, characterized in that, The end of the stop member contacts the bottom of the mounting hole.

3. The compressor rotor assembly structure according to claim 1, characterized in that, The stop and the mounting hole are interference fit.

4. The compressor rotor assembly structure according to claim 1, characterized in that, The interference fit between the stop and the mounting hole is 0.023 to 0.002 mm.

5. The compressor rotor assembly structure according to claim 1, characterized in that, The height difference between the surface of the first locking plate away from the first locking plate groove, the surface of the second locking plate away from the second locking plate groove, and the bottom surface of the corresponding tenon groove is within 0.3mm.

6. The compressor rotor assembly structure according to claim 1, characterized in that, The limiting structure on the first locking plate is an arc structure with a radius of 0.1 to 0.3 mm.

7. The compressor rotor assembly structure according to claim 1, characterized in that, The blade tenon and the wheel disc tenon are fitted with a clearance.

8. The compressor rotor assembly structure according to claim 7, characterized in that, The clearance between the blade tenon and the wheel mortise is 0.006 to 0.036 mm.

9. The compressor rotor assembly structure according to claim 1, characterized in that, The fit between the first locking plate and the first locking plate groove, and between the second locking plate and the second locking plate groove, is an interference fit of 0.08 mm to a clearance fit of 0.07 mm.

10. An engine, characterized in that, The compressor rotor assembly structure is provided as described in any one of claims 1 to 9.

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