Adaptive elastic deformation shaft connection structure and engine rotor assembly

Abstract

The application relates to the field of aero-engines, and particularly discloses a self-adaptive elastic deformation shaft connecting structure and an engine rotor assembly. The self-adaptive elastic deformation shaft connecting structure comprises a limiting part, the limiting part comprises a first shaft blocking section, an elastic connecting section and a second shaft blocking section which are sequentially connected. The connecting structure can ensure the reliable connection between shaft structures, and the connecting strength of the connecting position of the two shafts cannot be reduced due to the gap caused by thermal deformation, so that the unreliable situation cannot occur.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engines, in particular to a self-adaptive elastic deformation shaft connection structure and an engine rotor assembly. BACKGROUND

[0002] In different working states such as starting, cruising and emergency, the aero-engine has the problem of unreliable connection caused by different thermal deformations of bearing, main shaft, central shaft and other multi-layer shafting structures. For example, due to different working temperatures, the bearing inner ring, turbine shaft, compressor shaft and other parts will produce relative displacement and thermal expansion difference, etc., which cannot guarantee that the bearing inner ring and the rear section of the turbine disc and other parts are in a compressed state at the same time in different working states, thereby easily causing engine vibration failure or bearing wear failure.

[0003] At present, nuts, nut locking plates and other structures are usually used to ensure the end face fit and axial compression of the turbine shaft and other shaft parts, such as Figure 1 As shown in the partial schematic view of a certain engine, from the figure we can see that the rear section of the turbine shaft 4' is pressed against the bearing inner ring 5', and then the nut 61' + nut locking plate 62' structure is used to ensure the axial compression of the bearing inner ring 5' and the rear section of the turbine shaft 4' on the low-pressure compressor shaft 3'. Or as Figure 2 shown, it is another partial schematic view of an engine, from the figure we can see that the rear section of the turbine shaft 4" is pressed against the bearing inner ring, and then the nut 61" + nut locking plate 62" structure is used to ensure the axial compression of the bearing inner ring 5", and the nut 63" + stop washer 64" structure is used to ensure the axial compression of the turbine shaft 4" on the center pull rod 3". If the engine wants to use the connection mode shown in Figure 2 , it must also be in the case of unlimited structure, that is, there is more installation space, otherwise it is not possible to use two sets of nut compression structures to ensure the axial compression of all parts as shown in Figure 2 .

[0004] The patent document (Chinese patent publication No. CN109209641B) discloses a connection structure of an engine rotor assembly, and the axial structure is too long, which will occupy a large space when applied in the field of aero-engines. SUMMARY

[0005] One aspect of the present application is to provide a self-adaptive elastic deformation shaft connection structure for ensuring reliable connection between shaft structures. The connection strength at the connection position of the two shafts will not be reduced due to the gap caused by thermal deformation, and the unreliable situation will not occur.

[0006] The purpose of the present application can be achieved by the following technical solutions:

[0007] The application discloses a self-adaptive elastic deformation shaft connecting structure, which comprises a limiting part, the limiting part comprises a first shaft blocking section, an elastic connecting section and a second shaft blocking section which are sequentially connected.

[0008] In a further scheme, the connecting structure further comprises an elastic sealing part, the elastic sealing part is connected to the limiting part and is used for providing self-adaptive elastic deformation to the radial direction of the shaft part to be connected; the elastic sealing part can be a sealing bristle ring with elastic and sealing functions, that is, the sealing bristle ring is connected to other parts, and during the connecting process, the elastic force generated between the sealing bristle ring and the part to be connected is used to adjust the gap between the parts to be connected on both sides of the sealing bristle ring, improve the sealing strength, and compensate the change amount of the radial length of the shaft part, such as the compressor shaft, caused by heating and the like through the elastic deformation of the sealing bristle ring.

[0009] In a further scheme, a groove is arranged on the inner wall of the second shaft blocking section, and a through hole is arranged on the groove bottom surface.

[0010] In a further scheme, the through holes are arranged in multiple rows in parallel.

[0011] In a further scheme, the through holes are arranged in two rows in parallel and are arranged in an up-and-down staggered and uniformly spaced manner.

[0012] In a further scheme, the elastic connecting section is a connecting section provided with multiple annular through grooves.

[0013] In a further scheme, the annular through grooves are strip-shaped waist grooves arranged in multiple rows in parallel.

[0014] In a further scheme, the annular through grooves are arranged in two rows in parallel and are arranged in an up-and-down staggered and uniformly spaced manner.

[0015] The application has the following beneficial effects:

[0016] The elastic connecting section is used for locking and compensation, so that the connection between the shaft parts is more reliable, and the situation that the connection is unreliable due to the excessive gap caused by thermal deformation does not occur; compared with the existing shaft connecting mode in which the parts to be pressed are connected in an unreliable manner due to thermal deformation, the shaft connecting mode is safer, and the service life of the elastic deformation shaft connecting parts can be prolonged.

[0017] Another aspect of the present application is to provide an engine rotor assembly, comprising a compressor rotor shaft, a turbine rotor shaft, a bearing, an end locking piece and the connecting structure in the above solution, the turbine rotor shaft is connected to the end of the compressor rotor shaft, the connecting structure is connected to the connecting end of the compressor rotor shaft and the turbine rotor shaft, the first shaft shoulder end face and the second shaft shoulder end face are sequentially arranged on the compressor rotor shaft, the second shaft shoulder end face is arranged with an axial gap from the end face of the turbine rotor shaft, the end face of the first shaft block is used for limiting the first shaft shoulder end face on the compressor rotor shaft, the end face of the second shaft block is used for limiting the end face of the bearing, the middle part of the turbine rotor shaft is limited by the other end face of the bearing, and the end locking piece is locked at the end of the compressor rotor shaft and used for limiting the turbine rotor shaft.

[0018] In a further solution, the end locking piece is a locking nut.

[0019] In a further solution, the connecting structure is an integrally formed thin-walled sleeve piece.

[0020] In different working states of the engine, the reliable connection of the turbine shaft and the compressor shaft can be ensured, the axial compression of the bearing inner ring can be ensured, and in the case of limited structure, a shorter rotor shaft can be used to realize the reliable working of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0022] Figure 1 is a partial connection schematic diagram of an engine shaft part in the prior art;

[0023] Figure 2 is a partial connection schematic diagram of another engine shaft part in the prior art;

[0024] Figure 3 is a partial connection schematic diagram of a self-adapting elastic deformation shaft connecting structure in the embodiment of the present application;

[0025] Figure 4 is a partial connection schematic diagram of an engine with a self-adapting elastic deformation shaft connecting structure in the embodiment of the present application.

[0026] In the figure: 1. Limiting portion; 11. First shaft stop section; 12. Elastic connecting section; 121. Annular through groove; 13. Second shaft stop section; 131. Groove; 132. Through hole; 3. Compressor rotor shaft; 31. First shaft shoulder end face; 32. Second shaft shoulder end face; 4. Turbine rotor shaft; 5. Bearing member; 6. Shaft end locking member; 7. Axial clearance. DETAILED DESCRIPTION

[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0028] like Figure 3 As shown, an adaptive elastic deformation shaft connection structure includes a limiting portion 1, and the limiting portion 1 includes a first shaft blocking segment 11, an elastic connection segment 12 and a second shaft blocking segment 13 connected in sequence.

[0029] Its working principle is to use the limiting part 1 to limit two shafts or shaft-like structures that will produce thermal deformation. The two shafts or shaft-like structures are locked by the elastic connecting section 12 in conjunction with the locking piece, providing a certain compensation for the gap value generated after thermal deformation. The compensation enables the first shaft blocking section 11 and the second shaft blocking section 13 of the connecting structure to always press the two shafts or shaft-like structures connected thereto, ensuring a reliable connection between the shaft-like structures, and preventing the connection strength of the two shaft connection positions from being reduced due to the gap generated by thermal deformation, causing unreliable situations.

[0030] The connection structure also includes an elastic sealing portion, which is connected to the limiting portion and is used to provide adaptive elastic deformation in the radial direction of the shaft parts to be connected. The elastic sealing portion can be a sealing sieve ring with elastic and sealing functions, that is, it is connected to other parts through the sealing sieve ring. During the connection process, the elastic force generated between the sealing sieve ring and the parts to be connected adjusts the gap between the parts to be connected on both sides of the sealing sieve ring, thereby improving the sealing strength. The elastic deformation of the sealing sieve ring itself is used to compensate for the change in radial length of the shaft parts connected thereto, such as the compressor shaft, caused by heating. The shape of the elastic sealing sieve ring can be set according to the structure and installation position of the shaft parts to be connected, which should be easily conceivable to those skilled in the art.

[0031] According to the above working principle, the structures of some preferred embodiments are as follows: Figure 3As shown, the inner wall of the second shaft blocking section 13 is provided with a groove 131, and the groove bottom surface of the groove 131 is provided with a through hole 132. The groove 131 and the through hole 132 can dissipate heat from the turbine rotor shaft 4 installed in the groove 131 during the self-deformation of the shaft, and guide the thermal and strain forces to the elastic connection section 12.

[0032] The number of rows of the through holes 132 is two, and the two rows of through holes 132 are arranged in uniform intervals in an up-down staggered manner. In this way, the strain forces released by the elastic deformation shaft during deformation are more uniform. Those skilled in the art should be able to think that the number of rows of the through holes here can be designed according to the length of the turbine rotor shaft 4, so it can be multiple rows.

[0033] The elastic connection section 12 is a connection section provided with a plurality of annular through grooves 121. The deformation amount of the elastic connection section 12 can be improved, and the stress concentration caused by the deformation of the elastic connection section 12 itself can be reduced.

[0034] The number of rows of the annular through grooves 121 is two, and the two rows of annular through grooves 121 are arranged in uniform intervals in an up-down staggered manner. This further improves the deformation amount of the elastic connection section 12.

[0035] Those skilled in the art should understand that the annular through grooves 121 can have various shapes, such as rectangular, circular, waist-shaped, etc., and can be used to compensate for the thermal expansion difference of shaft parts at high temperatures. The elastic connection section 12 can provide a certain deformation compensation at high temperatures through the structure of the annular through grooves 121. Selecting different shapes of annular through grooves can correspondingly change the deformation compensation size. In specific use, the specific limitations can be designed according to the design requirements such as temperature during use.

[0036] According to the working principle of the above-mentioned connection structure, when it is applied to an engine rotor assembly, it can obviously obtain an engine rotor assembly as shown in Figure 4 The engine rotor assembly includes a compressor rotor shaft 3, a turbine rotor shaft 4, a bearing 5, an axial end locking piece 6, and the above-mentioned connection structure. The turbine rotor shaft 4 is connected to the axial end of the compressor rotor shaft 3, the connection structure is connected to the connection end of the compressor rotor shaft 3 and the turbine rotor shaft 4, the compressor rotor shaft 3 is sequentially provided with a first shaft shoulder end face 31 and a second shaft shoulder end face 32, the second shaft shoulder end face 32 is provided with an axial gap 7 with an end face of the turbine rotor shaft 4, an axial end face of the first shaft blocking section 11 is used to limit the first shaft shoulder end face 31 on the compressor rotor shaft 3, an axial end face of the second shaft blocking section 13 is used to limit an end face of the bearing 5, a middle part of the turbine rotor shaft 4 is limited by the other end face of the bearing 5, and the axial end locking piece 6 is locked at the end of the compressor rotor shaft 3 and is used to limit the turbine rotor shaft 4.

[0037] When the nut is locked, the self-adapting elastic deformation shaft connecting structure can provide displacement compensation by virtue of the elastic connecting section 12 according to its unique structural characteristics. Under the tension of the shaft end locking member 6, the turbine rotor shaft 4 is attached to the B face of the compressor rotor shaft 3 as shown in the A face. Figure 4 When the axial dimension changes due to thermal deformation, the compensation function of the self-adapting elastic deformation shaft connecting structure is activated, and the inner ring of the bearing member 5, the A face of the turbine rotor shaft 4 and the B face of the compressor rotor shaft 3 are always in a compressed state, ensuring reliable connection of the engine shaft system.

[0038] Under different engine states, when the turbine rotor shaft 4 and the compressor rotor shaft 3 produce thermal expansion differences affecting the connection reliability of the rotor, the elastic connecting section 12 can compensate for the thermal expansion difference by virtue of its elastic deformation, always ensuring reliable connection of the turbine shaft and the compressor shaft, the bearing inner ring and other parts, thereby improving the connection reliability of the multi-layer shaft system structure of the engine.

[0039] The shaft end locking member 6 is a locking nut. The locking nut is a commonly used part and is more convenient to obtain.

[0040] The self-adapting elastic deformation shaft connecting structure is an integrally formed thin-walled sleeve member. It can facilitate the machining of the above connecting structure, improve its connection strength and reliability, and of course other components or simple shape adaptability changes can also be thought of by those skilled in the art, which can be obtained by conventional technical means.

[0041] It should be noted that the terms "first", "second", and the like in the present application are used to distinguish similar objects, and do not necessarily indicate a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented. In the present application, the terms "up", "down", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate the orientation or positional relationship shown in the drawings.

[0042] In the description of the present application, the description of the terms "one embodiment", "example", "specific example" and the like means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0043] The above shows and describes the basic principles, main features and advantages of the present application. Those skilled in the art should understand that the present application is not limited to the above-mentioned embodiments, and the above-mentioned embodiments and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application.

Claims

1. An engine rotor assembly, characterized in that: The invention comprises a compressor rotor shaft (3), a turbine rotor shaft (4), a bearing member (5), a shaft end locking member (6), and an adaptive elastic deformation shaft connection structure, wherein the connection structure comprises a limiting portion (1), and the limiting portion (1) comprises a first shaft stop section (11), an elastic connection section (12), and a second shaft stop section (13) connected in sequence; A groove (131) is provided on the inner side wall of the second shaft stop section (13), and a through hole (132) is provided on the bottom surface of the groove (131); The elastic connecting section (12) is a connecting section provided with a plurality of annular through grooves (121); The turbine rotor shaft (4) is connected to the shaft end of the compressor rotor shaft (3), and the connecting structure is connected to the connecting ends of the compressor rotor shaft (3) and the turbine rotor shaft (4). A first shaft shoulder end face (31) and a second shaft shoulder end face (32) are sequentially provided on the compressor rotor shaft (3), and an axial gap (7) is provided between the second shaft shoulder end face (32) and one end face of the turbine rotor shaft (4). The shaft end face of the first shaft stop section (11) is used to limit the first shaft shoulder end face (31) on the compressor rotor shaft (3), and the shaft end face of the second shaft stop section (13) is used to limit one end face of the bearing component (5). The middle part of the turbine rotor shaft (4) is limited by the other end face of the bearing component (5). The shaft end locking component (6) is locked at the end of the compressor rotor shaft (3) and is used to limit the turbine rotor shaft (4).

2. An engine rotor assembly according to claim 1, characterized in that: The shaft end locking piece (6) is a locking nut.

3. The engine rotor assembly according to claim 1, characterized in that: The connecting structure is an integrally formed thin-walled shaft kit.

4. The engine rotor assembly according to claim 1, characterized in that: The through holes (132) are arranged in multiple rows in parallel.

5. An engine rotor assembly according to claim 4, characterized in that: The number of rows of through holes (132) is two, and the two rows of through holes (132) are staggered and evenly spaced up and down.

6. The engine rotor assembly according to claim 1, characterized in that: The annular through grooves (121) are strip-shaped waist grooves arranged in multiple rows in parallel.

7. The engine rotor assembly according to claim 1, characterized in that: The annular through grooves (121) are arranged in two rows, staggered and evenly spaced from top to bottom.

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