Single support bearing system structure of radial flow turbocharger

Abstract

The invention discloses a single support bearing system structure of a radial-flow turbocharger. The single support bearing system structure comprises a support body, a main shaft, a rotor system, a single radial bearing and a thrust bearing system, the main shaft is arranged in the supporting body; the rotor systems are arranged at the two ends of the main shaft; the rotor system comprises a rotor pressure impeller and a rotor turbine; a rotor pressure impeller and a rotor turbine are respectively arranged at two ends of the main shaft; a radial bearing is arranged on one side of the rotor turbine; the axial length of the radial bearing extends to cover the centroid area of the turbine rotor, and the ratio of the axial size of the radial bearing to the diameter of an inner hole of the radial bearing is increased; the thrust bearing system is arranged on one side of the rotor pressure impeller and bears the axial force of the rotor system. According to the design, the overall structure is simplified, the number of parts and the assembly complexity are reduced, the manufacturing cost and the axial size of the system are reduced, and the reliability and maintainability are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbocharger, in particular to a radial flow turbocharger single support bearing system structure. BACKGROUND

[0002] In the bearing system of turbocharger, the double support point support system is widely used. The system is composed of a rotor compressor on the left side and a rotor turbine on the right side, and the two ends are respectively installed on the compressor end radial bearing and the turbine end radial bearing through the shaft neck to realize radial positioning and support. The two bearings are respectively embedded in the compressor end bearing seat and the turbine end bearing seat, and are fixed on the support body as the basis of the overall structure, which provides sufficient rigidity and stability for the equipment.

[0003] However, although the double support point support layout provides high structural rigidity and carrying capacity, it also brings some significant technical problems: Firstly, the machining precision of the support body is high. Since the rotor needs to pass through two bearing support points at the same time, the inner hole of the support body must ensure very high coaxiality, otherwise it will cause bearing load imbalance, rotor deflection, uneven oil film distribution, and further cause vibration aggravation, bearing wear and even failure. This high precision machining requirement significantly increases the manufacturing cost and process difficulty, especially in mass production, it is difficult to stably control the quality.

[0004] Secondly, when using double radial bearing structure, although the two support points need to maintain sufficient axial spacing to maintain structural stability, the axial effective carrying area of a single bearing is small, resulting in large overall bearing span. This large span design directly increases the axial size of the turbocharger, making the shaft system too long. This not only limits the installation and application of the equipment in a compact space, but also increases the overall size of the machine, which is not conducive to the realization of the requirements of modern engines for small size and light weight of the power system. SUMMARY

[0005] The present application provides a radial flow turbocharger single support bearing system structure to overcome the problems of high machining precision, large axial size and bulky overall structure of the prior art.

[0006] In order to achieve the above purpose, the technical scheme of the present application is: A radial flow turbocharger single support bearing system structure, comprising a support body, a main shaft, a rotor system, a radial bearing and a thrust bearing system; the support body is provided with the main shaft; the main shaft is provided with the rotor system at both ends; The rotor system comprises a rotor pressure impeller and a rotor turbine; the rotor pressure impeller and the rotor turbine are respectively arranged at the two ends of the main shaft; a radial bearing is arranged on one side of the rotor turbine; the axial length of the radial bearing extends to cover the center of mass area of the rotor turbine, and the ratio of the axial size of the radial bearing to the inner hole diameter thereof is increased; the thrust bearing system is arranged on one side of the rotor pressure impeller to bear the axial force of the rotor system.

[0007] Further, the inner hole diameter of the radial bearing is D, and the axial size is L, wherein L / D≥2.0.

[0008] Further, the inner hole surface of the radial bearing is provided with an oil wedge structure divided into two sections in the axial direction, and each section of the oil wedge is provided with an independent oil inlet hole and an oil supply channel.

[0009] Further, the radial bearing is uniformly arranged with a plurality of inclined holes in the circumferential direction above the end face close to the rotor pressure impeller.

[0010] Further, the arrangement direction of each inclined hole arranged uniformly in the circumferential direction is from the bearing outer ring to the inner hole.

[0011] Further, the thrust bearing system comprises a compressor end bearing seat, a bearing sleeve, a thrust bearing and an auxiliary thrust bearing; the compressor end bearing seat is arranged on the main shaft and close to the end portion on one side of the rotor pressure impeller, and forms a sealing and supporting structure with the bearing sleeve; The thrust bearing is arranged in the compressor end bearing seat, and the bearing sleeve is arranged outside the compressor end bearing seat, one end face of which is matched with the auxiliary thrust bearing to provide reverse support under reverse load or transient working condition; the other end face is matched with the end face of the thrust bearing to form the main thrust bearing surface of the rotor under normal working condition.

[0012] Further, the radial turbine supercharger single support bearing system structure further comprises a bearing seat, and the auxiliary thrust bearing can be selectively mounted on the support body or the bearing seat.

[0013] Further, the support body and the bearing seat are correspondingly provided with two independent oil inlet holes and oil channels to independently supply oil to the two sections of the oil wedge of the radial bearing.

[0014] Further, the main shaft is further provided with an oil throwing disc close to the compressor end.

[0015] Beneficial effects: The bearing system for radial turbochargers of the present invention employs an extended radial bearing arranged on one side, whose axial span covers the centroid region of the turbine rotor, achieving concentrated support for the high-speed rotor system. By increasing the axial length of a single radial bearing, the bearing's load-bearing area is effectively increased, and the bearing's span relative to the main shaft is reduced, resulting in more concentrated bearing forces and a more uniform load distribution, thereby significantly improving the bearing's load-bearing capacity and operational stability.

[0016] Meanwhile, by using only a single radial bearing on the turbine side, the overall structure is simplified, the number of parts and assembly complexity are reduced, which helps to lower manufacturing costs and system axial dimensions, and improve reliability and maintainability. Combined with the synergistic effect of the thrust bearing system, it can efficiently withstand combined radial and axial loads, making it suitable for stable operation of turbochargers under high-speed and high-load conditions. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a cross-sectional view of the device structure of the present invention; Figure 2 This is a cross-sectional view of a radial bearing; In the figure, 1: rotor impeller; 2: rotor turbine; 3: main shaft; 4: support body; 5: bearing housing; 6: thrust bearing; 7: oil slinger; 8: oblique hole; 9: oil wedge structure; 21: radial bearing; 22: auxiliary thrust bearing; 23: compressor end bearing housing; 24: bearing sleeve. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] This embodiment provides a single-support bearing system structure for a radial-flow turbocharger, such as... Figure 1 As shown, it includes a support body 4, a main shaft 3, a rotor system, a radial bearing 21, and a thrust bearing system; the main shaft 3 is disposed inside the support body 4; the rotor system is disposed at both ends of the main shaft 3; The rotor system includes a rotor impeller 1 and a rotor turbine 2; the rotor impeller 1 and rotor turbine 2 are respectively provided at both ends of the main shaft 3; a radial bearing 21 is provided on one side of the rotor turbine 2; the axial length of the radial bearing 21 extends to cover the centroid region of the turbine rotor 2, and the axial dimension of the radial bearing 21 is increased relative to its inner diameter; the thrust bearing system is provided on one side of the rotor impeller 1 to bear the axial force of the rotor system.

[0021] The support body 4 is the load-bearing skeleton of the integral structure. The main shaft 3, as the rotating core, runs through the entire system and is rotatably installed inside the support body 4. One end of the main shaft 3 is connected to the rotor impeller 1, and the other end is connected to the rotor turbine 2, forming a high-speed rotating rotor assembly. In this embodiment, the rotor turbine 2 is preferably made of a cast high-temperature alloy, and the rotor impeller 1 is preferably made of aluminum alloy.

[0022] The radial bearing 21 is mounted on the bearing housing 5, near the outer periphery of the main shaft 3 at the end of the rotor turbine 2, and is used to provide reliable radial support for the high-speed rotor system; while a thrust bearing system is provided on the side of the rotor impeller 1 to bear the axial force generated by the rotor system.

[0023] Specifically, the axial length of the radial bearing 21 is extended, with the ratio of its axial dimension L to the inner diameter D satisfying L / D≥2.0, thereby significantly improving the bearing's support stiffness and operational stability. This extended structure allows the axial span of the radial bearing 21 to cover the centroid region of the turbine rotor, achieving centralized support for the entire high-speed rotor system from a single-sided radial bearing, simplifying the structural layout, and reducing system complexity and assembly difficulty.

[0024] Furthermore, such as Figure 2 The inner surface of the radial bearing 21 is provided with an axially divided oil wedge structure 9, each segment having an independent oil inlet and supply channel to form a dual-wedge dynamic pressure lubrication effect, enhancing oil film stability and improving the bearing's load-bearing capacity and anti-disturbance performance under varying operating conditions. In this embodiment, the main oil circuit is preferably located between the two branch oil circuits to ensure balanced oil supply pressure between the two oil wedge segments.

[0025] Furthermore, such as Figure 2 Above the end face of the radial bearing 21 near the rotor impeller 1, a plurality of oblique holes 8 are evenly arranged circumferentially. These oblique holes 8 extend obliquely from the outer ring of the bearing toward the inner hole, and are used to throw lubricating oil toward the inner hole surface of the radial bearing 21 during high-speed rotation, to assist lubrication and enhance the cooling effect, and prevent local overheating.

[0026] Furthermore, the thrust bearing system is used to withstand the axial thrust generated by the rotor during operation, and mainly includes a compressor end bearing housing 23, a bearing sleeve 24, a thrust bearing 6, and an auxiliary thrust bearing 22. The compressor end bearing housing 23 is mounted on the main shaft 3, at the end near the rotor compressor 1, and together with the bearing sleeve 24, forms a sealing and support structure. The bearing sleeve 24 is fitted onto the outside of the compressor end bearing housing 23 to achieve axial positioning and sealing. The thrust bearing 6 is disposed within the compressor end bearing housing 23, and the bearing sleeve 24 is fitted onto the outside of the compressor end bearing housing 23. One end face of the bearing sleeve 24 is opposite to the auxiliary thrust bearing 22, providing reverse support under reverse load or transient conditions; its other end face is in contact with the end face of the thrust bearing 6, forming the main thrust bearing surface of the rotor under normal operating conditions, ensuring the reliability and stability of the rotor's axial positioning.

[0027] Furthermore, the radial turbocharger single support bearing system structure also includes a bearing housing 5, and the auxiliary thrust bearing 22 can be selectively installed on the support body 4 or the bearing housing 5 to improve assembly flexibility.

[0028] Furthermore, to ensure the efficient operation of the lubrication system, the support body 4 and the bearing seat 5 are respectively provided with two independent oil inlets and oil passages, which independently supply oil to the two oil wedge structures 9 of the radial bearing 21, thereby achieving precise oil supply control, avoiding oil circuit crosstalk, and improving lubrication reliability.

[0029] Furthermore, the main shaft 3 is also equipped with an oil slinger 7 near the compressor end, which uses the centrifugal force generated by rotation to evenly throw out the lubricating oil, further enhancing the lubrication and cooling effect on the bearing area and preventing the lubricating oil from accumulating or leaking.

[0030] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A single-support bearing system structure for a radial-flow turbocharger, characterized in that: It includes a support body (4), a main shaft (3), a rotor system, a radial bearing (21), and a thrust bearing system; the main shaft (3) is disposed inside the support body (4); the rotor system is disposed at both ends of the main shaft (3); The rotor system includes a rotor impeller (1) and a rotor turbine (2); the rotor impeller (1) and rotor turbine (2) are respectively provided at both ends of the main shaft (3); a radial bearing (21) is provided on one side of the rotor turbine (2); the axial length of the radial bearing (21) extends to cover the centroid region of the rotor turbine (2), and the ratio of the axial dimension of the radial bearing (21) to its inner diameter increases; the thrust bearing system is provided on one side of the rotor impeller (1) to bear the axial force of the rotor system.

2. The single-support bearing system structure for a radial turbocharger according to claim 1, characterized in that: The radial bearing (21) has an inner diameter of D and an axial dimension of L, where L / D ≥ 2.

0.

3. The single-support bearing system structure for a radial turbocharger according to claim 1, characterized in that: The inner surface of the radial bearing (21) is provided with an oil wedge structure (9) divided into two sections along the axial direction. Each section of the oil wedge is provided with an independent oil inlet hole and oil supply channel.

4. The single-support bearing system structure for a radial turbocharger according to claim 1, characterized in that: The radial bearing (21) has a plurality of oblique holes (8) evenly arranged circumferentially above the end face near the rotor impeller (1).

5. The single-support bearing system structure for a radial turbocharger according to claim 4, characterized in that: The arrangement direction of each of the inclined holes (8) is uniformly distributed circumferentially, extending from the outer ring of the bearing to the inner hole.

6. The single-support bearing system structure for a radial turbocharger according to claim 1, characterized in that: The thrust bearing system includes a compressor end bearing housing (23), a bearing sleeve (24), a thrust bearing (6), and an auxiliary thrust bearing (22); the compressor end bearing housing (23) is mounted on the main shaft (3) and close to the end of the rotor impeller (1), and together with the bearing sleeve (24), it forms a sealing and support structure; The thrust bearing (6) is installed inside the compressor end bearing housing (23), and the bearing sleeve (24) is fitted on the outside of the compressor end bearing housing (23). One end face of the bearing sleeve is in relative cooperation with the auxiliary thrust bearing (22) to provide reverse support under reverse load or transient conditions. The other end face of the bearing sleeve is in contact with the end face of the thrust bearing (6) to form the main thrust bearing surface of the rotor under normal operating conditions.

7. A single-support bearing system structure for a radial-flow turbocharger according to claim 1 or 6, characterized in that: The radial turbocharger single support bearing system structure also includes a bearing housing (5), and the auxiliary thrust bearing (22) can be selectively installed on the support body (4) or the bearing housing (5).

8. The single-support bearing system structure for a radial turbocharger according to claim 7, characterized in that: The support body (4) and bearing seat (5) are respectively provided with two independent oil inlets and oil passages, which independently supply oil to the two oil wedges of the radial bearing (21).

9. The structure of a single-support bearing system for a radial-flow turbocharger according to claim 1, characterized in that: The main shaft (3) is also equipped with an oil slinger (7) near the compressor end.

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