Engine rotor and engine thereof

Abstract

The invention discloses an engine rotor, comprising a compressor rotor and a turbine rotor. The compressor rotor comprises a shaft neck, an axial-flow blade disk and a centrifugal impeller. The shaft neck comprises a straight shaft portion, a tapered portion and a connecting portion. The radial dimension of the tapered portion gradually increases. A first step surface is formed at the connection between the connecting portion and the tapered portion. The extension of the connecting portion protrudes toward one end away from the tapered portion to form a second step surface. The axial-flow blade disk is positioned with a stopper of the first step surface, the centrifugal impeller is positioned with a stopper of the second step surface, and the axial-flow blade disk, the connecting portion and the centrifugal impeller are fixed. The turbine rotor comprises a turbine shaft and a turbine rotor assembly. The turbine shaft comprises a mounting portion, an oblique cone portion and a positioning portion. The turbine rotor assembly is mounted on the mounting portion. The radial dimension of the oblique cone portion gradually increases. One end of the positioning portion protrudes away from the oblique cone portion to form a third step surface. One end of the centrifugal impeller away from the second step surface is positioned with the stopper of the third step surface and is fixedly connected to the positioning member.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular, to an engine rotor. In addition, the present invention also relates to an engine comprising the above engine rotor. Background Art

[0002] The rotor system of the core machine of small and medium-sized aircraft engines mainly includes the compressor rotor assembly, the turbine rotor assembly and its connecting shaft. At present, the rotor fulcrum layout of the core machine of small and medium-sized aircraft engines mostly adopts the two forms of "1-1-0" or "1-0-1". The "1-1-0" form is supported by two bearings, with the front bearing located in front of the compressor and the rear bearing located between the compressor and the turbine. The "1-0-1" form also uses two bearings for support, with the front bearing located in front of the compressor and the rear bearing located behind the turbine. The core machine rotor systems of small and medium-sized aircraft engines with the above two layout forms both use the "end teeth + pull rod" form to connect the compressor and turbine rotors and complete the torque transmission.

[0003] However, the connection and torque transmission form of "end teeth + pull rod" places high demands on the design and processing of the end teeth, and is responsible for the problem of difficulty in alignment during the assembly process, resulting in assembly difficulties. Summary of the invention

[0004] The invention provides an engine rotor to solve the technical problem of how to reduce the difficulty of assembling the engine rotor.

[0005] According to one aspect of the present invention, an engine rotor is provided, including a compressor rotor and a turbine rotor, the compressor rotor including a journal, an axial flow blade disk and a centrifugal impeller, the journal including a straight shaft portion, a tapered portion connected to the straight shaft portion and a connecting portion connected to the tapered portion, the radial dimension of the tapered portion gradually increases from an end connected to the straight shaft portion toward an end connected to the connecting portion, a first step surface is formed at the connection between the connecting portion and the tapered portion, the extension of the connecting portion protrudes toward an end away from the tapered portion to form a second step surface, the axial flow blade disk is positioned at a stopper of the first step surface, and the centrifugal impeller is positioned at a stopper of the second step surface The axial flow blade disk, the connecting part and the centrifugal impeller are connected and fixed by a first bolt; the turbine rotor comprises a turbine shaft and a turbine rotor assembly, the turbine shaft comprises a mounting portion, an oblique cone portion connected to the mounting portion and a positioning portion connected to the oblique cone portion, the turbine rotor assembly is mounted on the mounting portion, the radial dimension of the oblique cone portion gradually increases from an end connected to the mounting portion toward an end connected to the positioning portion, an end of the positioning portion which is away from the oblique cone portion protrudes to form a third step surface, an end of the centrifugal impeller which is away from the second step surface is positioned with the stop mouth of the third step surface and is fixedly connected to the positioning portion by a second bolt.

[0006] Furthermore, a compressor rotor assembly is mounted on the straight shaft portion, and a limit step is provided at one end of the straight shaft portion close to the conical portion. The compressor rotor assembly includes a locking nut, a conical tooth, a first bearing and a first sealing member arranged in sequence along the axial direction of the straight shaft portion from the free end of the straight shaft portion toward the conical portion, the first sealing member abuts against the limit step, the locking nut is threadedly connected to the straight shaft portion and is used to axially lock the conical tooth and the first bearing between the locking nut and the first sealing member.

[0007] Furthermore, the locking ring includes an abutment portion perpendicular to the axis of the straight shaft portion and a locking portion parallel to the axis of the straight shaft portion, the abutment portion is clamped between the locking nut and the conical teeth, a locking groove is provided on the locking portion, a first spiral retaining ring is embedded in the locking groove, and a first stop washer is clamped between the first spiral retaining ring and the locking bolt.

[0008] Furthermore, an oil-slinging pan is installed on the straight shaft portion, and the oil-slinging pan is sandwiched between the first bearing and the first sealing member.

[0009] Furthermore, the turbine rotor assembly includes a turbine disc, turbine blades, a turbine front baffle and a turbine rear baffle, the turbine disc is connected to the mounting portion by threads, the turbine front baffle is installed on a side of the turbine disc close to the centrifugal impeller, the turbine rear baffle is installed on a side of the turbine disc away from the centrifugal impeller, and the turbine blades are installed on the end of the turbine disc away from the mounting portion.

[0010] Furthermore, both the turbine front baffle and the turbine rear baffle are provided with air inlet holes, and the air inlet holes are used to introduce gas to cool the turbine disk.

[0011] Furthermore, a first limiting step is provided on the mounting portion, and a limiting nut is threadedly connected to the mounting portion, and the limiting nut is used to axially lock the turbine disc between the first limiting step and the second limiting step.

[0012] Furthermore, a limiting groove is provided on the turbine disc, a second spiral retaining ring is embedded in the limiting groove, and a second stop washer is sandwiched between the second spiral retaining ring and the limiting nut.

[0013] Furthermore, a second limiting step is provided on the mounting portion, a third limiting step is provided on the turbine disc, the limiting step and the third limiting step form a mounting groove along the axial direction of the mounting portion, a turbine rotor auxiliary component is embedded in the mounting groove, and the turbine rotor auxiliary component includes a second sealing member, an elastic ring, a second bearing and a third sealing member which are arranged in sequence from the second limiting step toward the third limiting step.

[0014] According to another aspect of the present invention, an engine is provided, which comprises the engine rotor as described above.

[0015] The present invention has the following beneficial effects:

[0016] The engine rotor of the present invention includes a compressor rotor and a turbine rotor. The structure of the journal on the compressor rotor and the structure of the turbine shaft on the turbine rotor are improved to facilitate the assembly of the engine rotor.

[0017] Specifically, the journal in the compressor rotor includes a straight shaft portion, a tapered portion and a connecting portion, wherein the connecting portion is used to assemble the axial flow blade disk and the centrifugal impeller. In order to facilitate the installation of the axial flow blade disk and the centrifugal impeller, a first step surface and a second step surface are formed on the connecting portion. The connection of the axial flow blade disk and the first step surface are centered by a stopper, and the centrifugal impeller and the second step surface are also centered by a stopper. In specific implementation, the axial flow blade disk is installed in cooperation with the first step surface, and the centrifugal impeller is installed in cooperation with the second step surface. The connecting portion is provided with a plurality of mounting holes along the circumferential direction. The axial flow blade disk and the centrifugal impeller are provided with through holes that match the mounting holes. After the mounting holes are aligned with the through holes, they are connected and fixed by a first bolt, so that the axial flow blade disk and the centrifugal impeller are accurately installed on the connecting portion. The radial dimension of the tapered portion gradually increases from one end connected to the straight shaft portion toward one end connected to the connecting portion, so that the radial dimension of the connecting portion is also increased accordingly, so that the number of first bolts can be increased when the axial flow blade disk and the centrifugal impeller are installed, thereby improving the rigidity of the connection.

[0018] The turbine shaft in the turbine rotor includes a mounting portion, an inclined cone portion and a positioning portion, wherein the turbine rotor assembly is mounted on the mounting portion, and one end of the positioning portion away from the inclined cone portion protrudes to form a third step surface, and the third step surface is centered with a stopper at one end of the centrifugal impeller away from the second step, and then the positioning portion is fixedly connected to the centrifugal impeller by using a second bolt to fix the compressor rotor to the turbine rotor, and the radial dimension of the inclined cone portion gradually increases from the end connected to the mounting portion toward the end connected to the positioning portion, so that the radial dimension of the positioning portion is also increased accordingly, so that the number of second bolts set can be increased when the positioning portion and the centrifugal impeller are installed, thereby improving the stiffness of the connection.

[0019] In summary, the installation of the axial flow blade disk is positioned by the first step surface set on the connecting part of the shaft neck, and the centrifugal impeller is positioned by the second step surface, so that the axial flow blade disk and the centrifugal impeller are both coaxially arranged with the shaft neck and the convenience during installation is improved. After the two are positioned at the connecting part, they are locked and fixed by the first bolt, and then the third step on the positioning part of the turbine shaft is used to stop the centrifugal impeller, so that the shaft neck and the turbine shaft are coaxially arranged, and then the positioning part is locked and fixed with the centrifugal impeller by the second bolt. The stop centering structure formed by the above three positioning steps realizes the rapid positioning of accessories on the compressor rotor and the turbine rotor, thereby reducing the difficulty of installation and improving installation efficiency.

[0020] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0022] Figure 1 is a schematic structural diagram of an engine rotor according to a preferred embodiment of the present invention;

[0023] Figure 2 is a schematic diagram of the half structure of a compressor rotor in a preferred embodiment of the present invention;

[0024] Figure 3 1 is a schematic diagram of the half side structure of the journal of the preferred embodiment of the present invention;

[0025] Figure 4 is a schematic structural diagram of a locking ring in a preferred embodiment of the present invention;

[0026] Figure 5 is a schematic diagram of the half structure of a turbine rotor in a preferred embodiment of the present invention;

[0027] Figure 6 is a schematic diagram of the half structure of a turbine disk in a preferred embodiment of the present invention;

[0028] Figure 7 It is a schematic diagram of the half structure of the turbine shaft of the preferred embodiment of the present invention.

[0029] Legend:

[0030] 100, journal; 101, straight shaft portion; 102, limit step; 103, tapered portion; 104, connecting portion; 105, first step surface; 106, second step surface; 107, first bolt;

[0031] 200, locking nut; 201, conical teeth; 202, first bearing; 203, first sealing member; 204, locking ring; 205, abutment portion; 206, locking portion; 207, locking groove; 208, first spiral retaining ring; 209, first stop washer; 210, oil slinger;

[0032] 300, axial flow blade disk; 301, centrifugal impeller;

[0033] 400, turbine shaft; 401, mounting portion; 402, first limiting step; 403, second limiting step; 404, oblique cone portion; 405, positioning portion; 406, third step surface; 407, second bolt;

[0034] 500, turbine disc; 501, third limiting step; 502, turbine blade; 503, turbine front baffle; 504, turbine rear baffle; 505, limiting groove; 506, second spiral retaining ring; 507, second stop washer; 508, limiting nut;

[0035] 600, second sealing member; 601, elastic ring; 602, second bearing; 603, third sealing member. DETAILED DESCRIPTION

[0036] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0037] like Figure 1 to Figure 7As shown, an engine rotor of the present embodiment includes a compressor rotor and a turbine rotor, wherein the compressor rotor includes a journal 100, an axial flow blade disk 300 and a centrifugal impeller 301, wherein the journal 100 includes a straight shaft portion 101, a conical portion 103 connected to the straight shaft portion 101 and a connecting portion 104 connected to the conical portion 103, wherein the radial dimension of the conical portion 103 gradually increases from an end connected to the straight shaft portion 101 toward an end connected to the connecting portion 104, wherein a first step surface 105 is formed at the connection between the connecting portion 104 and the conical portion 103, wherein the extension of the connecting portion 104 protrudes toward an end away from the conical portion 103 to form a second step surface 106, wherein the axial flow blade disk 300 is positioned at a stopper with respect to the first step surface 105, and wherein the centrifugal impeller 301 is positioned at a stopper with respect to the second step surface 106, The axial flow blade disk 300, the connecting portion 104 and the centrifugal impeller 301 are connected and fixed by a first bolt 107; the turbine rotor includes a turbine shaft 400 and a turbine rotor assembly, the turbine shaft 400 includes a mounting portion 401, an oblique cone portion 404 connected to the mounting portion 401, and a positioning portion 405 connected to the oblique cone portion 404, the turbine rotor assembly is installed on the mounting portion 401, the radial dimension of the oblique cone portion 404 gradually increases from the end connected to the mounting portion 401 toward the end connected to the positioning portion 405, the positioning portion 405 protrudes from one end away from the oblique cone portion 404 to form a third step surface 406, the end of the centrifugal impeller 301 away from the second step surface 106 is positioned with the stop of the third step surface 406 and is fixedly connected to the positioning portion 405 by a second bolt 407.

[0038] In this embodiment, the conical portion 103 is provided to increase the radial dimension of the connecting portion 104, that is, to increase the distribution diameter of the first bolts 107, so that the number of the first bolts 107 can be increased, and the stiffness of the connection between the journal 100, the axial flow blade disk 300 and the centrifugal impeller 301 can be improved. Since the torque is transmitted through the first bolts 107 after the connection, the stability after the connection can be increased by increasing the number of the first bolts 107. Similarly, the inclined cone portion 404 is provided to increase the radial dimension of the positioning portion 405, so as to increase the number of the second bolts 407, and improve the connection stiffness between the turbine shaft 400 and the centrifugal impeller 301, so as to increase the stability after the turbine shaft 400 and the centrifugal impeller 301 are connected.

[0039] Specifically, the journal 100 in the compressor rotor includes a straight shaft portion 101, a tapered portion 103 and a connecting portion 104, wherein the connecting portion 104 is used to assemble the axial flow blade disk 300 and the centrifugal impeller 301. In order to facilitate the installation of the axial flow blade disk 300 and the centrifugal impeller 301, a first step surface 105 and a second step surface 106 are formed on the connecting portion 104. The connection between the axial flow blade disk 300 and the first step surface 105 is centered by a stopper, and the connection between the centrifugal impeller 301 and the second step surface 106 is also centered by a stopper. In specific implementation, the axial flow blade disk 300 is installed in cooperation with the first step surface 105, and the centrifugal impeller 301 is installed in cooperation with the second step surface 106. The connection portion 104 is provided with a plurality of mounting holes along the circumferential direction. The axial flow blade disk 300 and the centrifugal impeller 301 are provided with through holes that match the mounting holes. After the mounting holes are aligned with the through holes, they are connected and fixed by the first bolts 107, so that the axial flow blade disk 300 and the centrifugal impeller 301 are accurately installed on the connection portion 104. The radial dimension of the tapered portion 103 gradually increases from the end connected to the straight shaft portion 101 to the end connected to the connection portion 104, so that the radial dimension of the connection portion 104 is also increased accordingly, so that the number of the first bolts 107 can be increased when the axial flow blade disk 300 and the centrifugal impeller 301 are installed, thereby improving the rigidity of the connection.

[0040] The turbine shaft 400 in the turbine rotor includes a mounting portion 401, an inclined cone portion 404 and a positioning portion 405, wherein the turbine rotor assembly is mounted on the mounting portion 401, and the positioning portion 405 protrudes from one end of the inclined cone portion 404 to form a third step surface 406, and the third step surface 406 is centered with the stopper at one end of the centrifugal impeller 301 away from the second step surface 106, and then the positioning portion 405 is fixedly connected to the centrifugal impeller 301 by using the second bolt 407 to fix the compressor rotor to the turbine rotor, and the radial dimension of the inclined cone portion 404 gradually increases from the end connected to the mounting portion 401 toward the end connected to the positioning portion 405, so that the radial dimension of the positioning portion 405 is also increased accordingly, so that the number of second bolts 407 can be increased when the positioning portion 405 and the centrifugal impeller 301 are installed, thereby improving the stiffness of the connection.

[0041] In summary, the installation of the axial flow blade disk 300 is positioned by the first step surface 105 provided on the connection portion 104 of the journal 100, and the centrifugal impeller 301 is positioned by the second step surface 106, so that the axial flow blade disk 300 and the centrifugal impeller 301 are both coaxially arranged with the journal 100 and the convenience during installation is improved. After the two are positioned at the connection portion 104, they are locked and fixed by the first bolt 107, and then the third step surface 406 on the positioning portion 405 of the turbine shaft 400 is used to stop the centrifugal impeller 301, so that the journal 100 and the turbine shaft 400 are coaxially arranged, and then the positioning portion 405 is locked and fixed with the centrifugal impeller 301 by the second bolt 407. The stop centering structure formed by the above three positioning steps realizes the rapid positioning of the accessories on the compressor rotor and the turbine rotor, thereby reducing the difficulty of installation and improving the installation efficiency.

[0042] Reference Figure 2 A compressor rotor assembly is mounted on the straight shaft portion 101, and a limit step 102 is provided at one end of the straight shaft portion 101 close to the conical portion 103. The compressor rotor assembly comprises a locking nut 200, a conical tooth 201, a first bearing 202 and a first sealing member 203 arranged in sequence along the axial direction of the straight shaft portion 101 from the free end of the straight shaft portion 101 toward the conical portion 103, the first sealing member 203 abuts against the limit step 102, the locking nut 200 is threadedly connected to the straight shaft portion 101 and is used to axially lock the conical tooth 201 and the first bearing 202 between the locking nut 200 and the first sealing member 203.

[0043] In this embodiment, the first bearing 202 is a ball bearing, and the conical teeth 201, the ball bearing and the first sealing member 203 are installed on the straight shaft portion 101 through the locking nut 200, wherein the first bearing 202 is used to reduce the friction when the journal 100 rotates, so that the rotation is smooth, and at the same time, the journal 100 can be supported to ensure that the journal 100 is selectively rotated at the correct position. The first sealing member 203 is set to prevent the lubricating oil from leaking out of the first bearing 202, and plays a sealing role.

[0044] During installation, the locking nut 200, the tapered teeth 201, the first bearing 202 and the first sealing member 203 are arranged in sequence along the axial direction of the straight shaft portion 101 from the free end of the straight shaft portion 101 toward the tapered portion 103. First, the first sealing member 203 is abutted against the limiting step 102, and then the first bearing 202 and the tapered teeth 201 are sequentially installed, and finally locked and fixed by the locking nut 200.

[0045] Reference Figure 4The locking ring 204 includes an abutment portion 205 perpendicular to the axis of the straight shaft portion 101 and a locking portion 206 parallel to the axis of the straight shaft portion 101, the abutment portion 205 is clamped between the locking nut 200 and the conical tooth 201, a locking groove 207 is opened on the locking portion 206, a first spiral retaining ring 208 is embedded in the locking groove 207, and a first stop washer 209 is clamped between the first spiral retaining ring 208 and the locking nut 200.

[0046] In this embodiment, a locking ring 204 is provided to facilitate the installation of the first stop washer 209 and the first spiral retaining ring 208. Specifically, the first stop washer 209 is provided to prevent the locking nut 200 from rotating under the action of inertia due to the rotation of the rotor after being fixed, thereby affecting the locking of the conical teeth 201 and the first bearing 202. The first spiral retaining ring 208 is provided to tighten the first stop washer 209 to prevent the first stop washer 209 from axially disengaging.

[0047] Furthermore, an oil-slinging plate 210 is installed on the straight shaft portion 101 , and the oil-slinging plate 210 is sandwiched between the first bearing 202 and the first sealing member 203 .

[0048] In this embodiment, an oil-slinging pan 210 is provided to replenish the lubricating oil to the first bearing 202 so as to keep the lubricating oil in a good working condition.

[0049] Reference Figure 5 to Figure 7 The turbine rotor assembly includes a turbine disc 500, turbine blades 502, a turbine front baffle 503 and a turbine rear baffle 504. The turbine disc 500 is connected to the mounting portion 401 by threads. The turbine front baffle 503 is installed on a side of the turbine disc 500 close to the centrifugal impeller 301, and the turbine rear baffle 504 is installed on a side of the turbine disc 500 away from the centrifugal impeller 301. The turbine blades 502 are installed on the end of the turbine disc 500 away from the mounting portion 401.

[0050] In this embodiment, turbine thread surfaces are arranged at intervals on the contact surface between the turbine disc 500 and the mounting portion 401, and correspondingly, threads matching the turbine thread surfaces are also provided on the mounting portion 401, so that the turbine disc 500 and the mounting portion 401 are matched and fixed by thread connection. The thread connection method is convenient for the installation and fixation of the turbine disc 500. When installing, the turbine disc 500 can be radially fixed by simply screwing the turbine into the mounting portion 401. The turbine blades 502, the turbine front baffle 503 and the turbine rear baffle 504 are all installed on the turbine disc 500. Specifically, the turbine front baffle 503 is installed on the side of the turbine disc 500 close to the centrifugal impeller 301, the turbine rear baffle 504 is installed on the side of the turbine disc 500 away from the centrifugal impeller 301, and the turbine blades 502 are installed on the end of the turbine disc 500 away from the mounting portion 401.

[0051] Furthermore, both the turbine front baffle 503 and the turbine rear baffle 504 are provided with air inlet holes, and the air inlet holes are used to introduce gas to cool the turbine disk 500 .

[0052] In this embodiment, air inlet holes are provided on the turbine front baffle 503 and the turbine disc 500 rear baffle to facilitate the introduction of gas into the turbine disc 500 to cool the turbine disc 500, thereby preventing the turbine disc 500 from continuously increasing in temperature due to the inability to dissipate heat after working for a long time, thereby causing excessively high temperature to affect the normal operation of the turbine disc 500. In specific implementation, the turbine front baffle 503 and the turbine rear baffle 504 are both provided with air inlet holes evenly distributed along the axial direction.

[0053] Furthermore, a first limiting step 402 is provided on the mounting portion 401 , and a limiting nut 508 is threadedly connected to the mounting portion 401 . The limiting nut 508 is used to axially lock the turbine disk 500 between the first limiting step 402 and the limiting nut 508 .

[0054] In this embodiment, a first limiting step 402 is provided on the mounting portion 401, the first end of the turbine disk 500 abuts against the first limiting step 402, and the second end of the turbine disk 500 abuts against a limiting nut 508 threadedly connected to the mounting portion 401, and the turbine disk 500 is axially fixed between the limiting nut 508 and the first limiting step 402 by tightening the limiting nut 508.

[0055] Furthermore, a limiting groove 505 is provided on the turbine disk 500 , a second spiral retaining ring 506 is embedded in the limiting groove 505 , and a second stop washer 507 is sandwiched between the second spiral retaining ring 506 and the limiting nut 508 .

[0056] In this embodiment, a second stop washer 507 is provided to prevent the limiting nut 508 from loosening due to the inertia of the rotor after being fixed, thereby locking the turbine disk 500 by the limiting nut 508, and the second stop washer 507 is tightened by providing a second spiral retaining ring 506 to prevent the second stop washer 507 from axially disengaging.

[0057] Furthermore, a second limiting step 403 is provided on the mounting portion 401, and a third limiting step 501 is provided on the turbine disk 500. The second limiting step 403 and the third limiting step 501 form a mounting groove along the axial direction of the mounting portion 401, and a turbine rotor auxiliary component is embedded in the mounting groove. The turbine rotor auxiliary component includes a second sealing member 600, an elastic ring 601, a second bearing 602 and a third sealing member 603 which are arranged in sequence from the second limiting step 403 to the third limiting step 501.

[0058] In this embodiment, since the centrifugal force generated by the turbine disk 500 when working is usually large, the mounting portion 401 generates a large radial force, so the second bearing 602 adopts a roller bearing to support the mounting portion 401. In order to install and fix the roller bearing, a second limiting step 403 is provided on the mounting portion 401, and a third limiting step 501 is provided on the turbine disk 500. Then, the second sealing member 600, the elastic ring 601, the second bearing 602 and the third sealing member 603 are arranged in sequence between the second limiting step 403 and the third limiting step 501, so that the roller bearing is limited and fixed. The elastic ring 601 can be pre-compressed on the elastic ring 601 in the initial state of the turbine rotor, so as to compensate for the deformation of the rotor in the large state, so as to improve the reliability of the rotor. Specifically, when the engine is in a large state or a high state, the temperature of the rotor parts is high and the temperature distribution gradient is large. At the same time, due to the different materials of each part, the expansion amount is different, and the preload force is lost. At this time, the pre-compression amount of the elastic ring 601 is compensated to ensure that there is sufficient pressing force in the large state, thereby ensuring the stability of the rotor during operation.

[0059] According to another aspect of the present invention, an engine is provided, which comprises the engine rotor as described above.

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

Claims

1. An engine rotor, It is characterized in that include: A compressor rotor, the compressor rotor comprising a journal (100), an axial flow blade disk (300) and a centrifugal impeller (301), the journal (100) comprising a straight shaft portion (101), a conical portion (103) connected to the straight shaft portion (101) and a connecting portion (104) connected to the conical portion (103), the radial dimension of the conical portion (103) gradually increasing from an end connected to the straight shaft portion (101) toward an end connected to the connecting portion (104), the connection between the connecting portion (104) and the conical portion (103) being of a radial dimension. A first step surface (105) is formed and arranged radially outward along the journal (100); the extension of the connecting portion (104) protrudes toward one end away from the conical portion (103) to form a second step surface (106) arranged radially inward from the journal (100); the axial flow blade disk (300) is positioned at a stopper of the first step surface (105); the centrifugal impeller (301) is positioned at a stopper of the second step surface (106); and the axial flow blade disk (300), the connecting portion (104) and the centrifugal impeller (301) are connected and fixed; A turbine rotor, the turbine rotor comprising a turbine shaft (400) and a turbine rotor assembly, the turbine shaft (400) comprising a mounting portion (401), an oblique cone portion (404) connected to the mounting portion (401), and a positioning portion (405) connected to the oblique cone portion (404), the turbine rotor assembly being mounted on the mounting portion (401), the radial dimension of the oblique cone portion (404) gradually increasing from an end connected to the mounting portion (401) toward an end connected to the positioning portion (405), an end of the positioning portion (405) away from the oblique cone portion (404) protruding to form a third step surface (406) arranged radially outwardly along the turbine shaft (400), an end of the centrifugal impeller (301) away from the second step surface (106) being positioned with a stopper of the third step surface (406) and fixedly connected to the positioning portion (405); The turbine rotor assembly comprises a turbine disc (500), turbine blades (502), a turbine front baffle (503) and a turbine rear baffle (504); a second limiting step (403) is provided on the mounting portion (401); a third limiting step (501) is provided on the turbine disc (500); a mounting groove is formed along the axial direction of the mounting portion (401) between the second limiting step (403) and the third limiting step (501); a turbine rotor auxiliary assembly is embedded in the mounting groove; the turbine rotor auxiliary assembly comprises a second sealing member (600), an elastic ring (601), a second bearing (602) and a third sealing member (603) which are arranged in sequence from the second limiting step (403) toward the third limiting step (501).

2. The engine rotor according to claim 1, It is characterized in that A compressor rotor assembly is mounted on the straight shaft portion (101); a limit step (102) is provided at one end of the straight shaft portion (101) close to the conical portion (103); the compressor rotor assembly comprises a locking nut (200), a conical tooth (201), a first bearing (202) and a first sealing member (203) which are arranged in sequence along the axial direction of the straight shaft portion (101) from the free end of the straight shaft portion (101) toward the conical portion (103); the first sealing member (203) abuts against the limit step (102); the locking nut (200) is threadedly connected to the straight shaft portion (101) and is used to axially lock the conical tooth (201) and the first bearing (202) between the locking nut (200) and the first sealing member (203).

3. The engine rotor according to claim 2, It is characterized in that A locking ring (204) is installed on the straight shaft portion (101), and the locking ring (204) includes an abutting portion (205) perpendicular to the axis of the straight shaft portion (101) and a locking portion (206) parallel to the axis of the straight shaft portion (101), the abutting portion (205) is clamped between the locking nut (200) and the conical teeth (201), a locking groove (207) is opened on the locking portion (206), a first spiral retaining ring (208) is embedded in the locking groove (207), and a first stop washer (209) is clamped between the first spiral retaining ring (208) and the locking nut (200).

4. The engine rotor according to claim 2, It is characterized in that An oil-slinging plate (210) is installed on the straight shaft portion (101), and the oil-slinging plate (210) is sandwiched between the first bearing (202) and the first sealing member (203).

5. The engine rotor according to claim 1, It is characterized in that The turbine disc (500) is connected to the mounting portion (401) via threads; the turbine front baffle (503) is mounted on a side of the turbine disc (500) close to the centrifugal impeller (301); the turbine rear baffle (504) is mounted on a side of the turbine disc (500) away from the centrifugal impeller (301); and the turbine blades (502) are mounted on an end of the turbine disc (500) away from the mounting portion (401).

6. The engine rotor according to claim 5, It is characterized in that The turbine front baffle (503) and the turbine rear baffle (504) are both provided with air inlet holes, and the air inlet holes are used to introduce gas to cool the turbine disk (500).

7. The engine rotor according to claim 5, It is characterized in that The mounting portion (401) is provided with a first limiting step (402), and the mounting portion (401) is threadedly connected with a limiting nut (508), and the limiting nut (508) is used to axially lock the turbine disc (500) between the first limiting step (402) and the limiting nut (508).

8. The engine rotor according to claim 7, It is characterized in that The turbine disc (500) is provided with a limiting groove (505), a second spiral retaining ring (506) is embedded in the limiting groove (505), and a second stop washer (507) is sandwiched between the second spiral retaining ring (506) and the limiting nut (508).

9. An engine, It is characterized in that It comprises an engine rotor as described in any one of claims 1 to 8.

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