Integrated bearing shell structure of axial flow turbocharger
By adopting an integrated bearing shell structure and clearance matching design in the axial flow turbocharger, the problem of assembly difficulty and cost of the split design under large volumes is solved, and higher reliability and convenient installation are achieved.
Patent Information
- Application Number
- CN202421064212.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-16
- Publication Date
- 2025-03-04
- Estimated Expiration
- 2034-05-16
AI Technical Summary
As the volume of the axial flow turbocharger becomes larger, the assembly of the bearing shell of the separate design is difficult and the casting and processing cost is high, which affects the use.
The integrated bearing shell structure is adopted, and the press-end bearing seat is directly connected to the integrated bearing shell, and the sealing lubrication and cooling of the vortex end is achieved through gap fitting and air guide hole design.
It reduces the number of supercharger parts, improves operating safety and reliability, reduces casting and processing difficulty and cost, and is suitable for large-volume axial flow superchargers, improving the reliability and installation convenience of bearing shells.
Smart Images
Figure CN222558826U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of turbochargers, in particular to an integrated bearing shell structure of an axial-flow turbocharger. Background Art
[0002] Turbocharging technology is a key technology that uses the exhaust energy of diesel engines to compress the intake air, thereby improving engine power, fuel economy and reducing emissions. The bearing shell is one of the important parts of the turbocharger. The reasonable design of the bearing shell is not only related to the stability of the bearing system, but also plays an important role in the rationality of the assembly clearance between other matching parts.
[0003] Currently, the bearing shells of smaller axial-flow turbochargers mostly adopt a split design, and the bearing shells are divided into two parts: a pressure-end bearing seat and a bearing shell.
[0004] However, as diesel engines require large flow and high pressure ratios, the size of axial-flow turbochargers will also increase. If the bearing shell still adopts a separate design, there will be problems such as difficulty in assembly and high casting and processing costs, which is not conducive to the use of the bearing shell. Utility Model Content
[0005] The utility model aims to provide an integrated bearing shell structure for an axial-flow turbocharger, aiming to solve the technical problem that as the volume of the existing axial-flow turbocharger increases, the bearing shell adopts a separate design, which leads to great assembly difficulty and high casting and processing costs, which is not conducive to the use of the bearing shell.
[0006] To achieve the above-mentioned purpose, the utility model adopts an axial-flow turbocharger integrated bearing shell structure, including a compressor impeller, a compression end bearing seat, an integrated bearing shell, turbine blades and a turbine shaft, the compression end bearing seat is fixedly connected to the integrated bearing shell and is located in the integrated bearing shell, the turbine shaft is movably connected to the integrated bearing shell and is located in the integrated bearing shell, the turbine shaft is also movably connected to the compression end bearing seat and passes through the compression end bearing seat, the turbine blades are fixedly connected to the turbine shaft and are located at one end of the turbine shaft, and the compressor impeller is fixedly connected to the turbine shaft and is located at the other end of the turbine shaft.
[0007] Wherein, the turbine blades include a turbine seat and a plurality of blades, the turbine seat is fixedly connected to the turbine shaft and is located at one end of the turbine shaft away from the compressor impeller, and the plurality of blades are fixedly connected to the turbine seat and are distributed circumferentially on the turbine seat.
[0008] Wherein, the one-piece bearing shell has two air guide holes, and the two air guide holes are symmetrically arranged in the one-piece bearing shell.
[0009] Wherein, the one-piece bearing shell, the pressure end bearing seat and the turbine shaft are clearance-fitted.
[0010] The utility model discloses an integrated bearing shell structure of an axial-flow turbocharger. By integrating the compression end bearing seat directly with the integrated bearing shell, the number of parts of the turbocharger is reduced, and the operational safety and reliability thereof is improved. In addition, the integrated bearing shell is processed by shell casting and mating surface milling, and is assembled with the compression end bearing seat, the turbine blades and the turbine shaft in a clearance fit. By providing an air guide hole on the integrated bearing shell that guides from the compressor impeller to the turbine shaft and the turbine blade end, the compression end low-temperature (relative to the turbine end high-temperature) high-pressure gas during the operation of the turbocharger can be guided to the turbine end, so as to achieve the goal of sealing the turbine end lubricating oil and cooling the turbine, thereby reducing the risk caused by turbine end lubricating oil leakage during the operation of the turbocharger and improving the fatigue life of the turbine. Through the above-mentioned method, it is achieved that the bearing shell can be applied to large-volume axial-flow superchargers, greatly improving its reliability and convenient installation requirements, reducing the difficulty and process steps of casting and processing, and facilitating the use of the bearing shell. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0012] Figure 1 It is a structural schematic diagram of an integrated bearing shell structure of an axial-flow turbocharger of the utility model.
[0013] Figure 2 It is a structural schematic diagram of the integrated bearing shell of the utility model.
[0014] 1-compressor impeller, 2-compression end bearing seat, 3-integrated bearing shell, 4-turbine blades, 5-turbine shaft, 6-turbine seat, 7-blades, 8-air guide holes. DETAILED DESCRIPTION
[0015] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.
[0016] See also Figure 1 and Figure 2 The utility model provides an integrated bearing shell structure of an axial-flow turbocharger, comprising a compressor impeller 1, a compression end bearing seat 2, an integrated bearing shell 3, turbine blades 4 and a turbine shaft 5, wherein the compression end bearing seat 2 is fixedly connected to the integrated bearing shell 3 and is located in the integrated bearing shell 3, the turbine shaft 5 is movably connected to the integrated bearing shell 3 and is located in the integrated bearing shell 3, the turbine shaft 5 is also movably connected to the compression end bearing seat 2 and passes through the compression end bearing seat 2, the turbine blades 4 are fixedly connected to the turbine shaft 5 and are located at one end of the turbine shaft 5, and the compressor impeller 1 is fixedly connected to the turbine shaft 5 and is located at the other end of the turbine shaft 5.
[0017] In this embodiment, the compression end bearing seat 2 is directly integrated with the one-piece bearing shell 3, so that the number of supercharger parts is reduced and the operational safety and reliability are improved. In addition, the one-piece bearing shell 3 is processed by shell casting and mating surface milling, and is assembled with the compression end bearing seat 2, the turbine blades 4 and the turbine shaft 5 in a clearance fit manner. By opening an air guide hole 8 on the one-piece bearing shell 3 that guides from the compressor impeller 1 to the turbine shaft 5 and the turbine blade 4 end, the compression end low-temperature (relative to the turbine end high-temperature) high-pressure gas during the operation of the supercharger can be guided to the turbine end, so as to achieve the goal of sealing the turbine end lubricating oil and cooling the turbine, thereby reducing the risk of turbine end lubricating oil leakage during the operation of the turbocharger and improving the fatigue life of the turbine. Through the above-mentioned method, it is achieved that the bearing shell can be applied to large-volume axial flow superchargers, greatly improving its reliability and convenient installation requirements, reducing the difficulty and process steps of casting and processing, and facilitating the use of the bearing shell.
[0018] Furthermore, the turbine blade 4 includes a turbine seat 6 and a plurality of blades 7. The turbine seat 6 is fixedly connected to the turbine shaft 5 and is located at an end of the turbine shaft 5 away from the compressor impeller 1. The plurality of blades 7 are fixedly connected to the turbine seat 6 and are distributed circumferentially on the turbine seat 6.
[0019] In this embodiment, the turbine seat 6 and the turbine shaft 5 are integrally formed, and the plurality of blades 7 are evenly distributed on the turbine seat 6 .
[0020] Furthermore, the integrated bearing shell 3 has two air guide holes 8 , and the two air guide holes 8 are symmetrically arranged in the integrated bearing shell 3 .
[0021] In this embodiment, two air guide holes 8 are opened on the integrated bearing shell 3, and the air guide holes 8 extend from the front end position of the compressor impeller 1 to the back end position of the turbine seat 6, so as to guide the high-pressure gas from the end of the compressor impeller 1 to the turbine seat 6 to seal the lubricating oil and cool the turbine, thereby improving the operating safety of the axial flow turbocharger and the service life of the turbine.
[0022] Furthermore, the integrated bearing shell 3, the pressure end bearing seat 2 and the turbine shaft 5 are clearance-fitted.
[0023] In this embodiment, the compressor impeller 1, the compression end bearing seat 2, the integrated bearing shell 3, and the turbine shaft 5 cooperate with each other and together form a main barrier to protect the safety of the bearing system.
[0024] The above disclosure is only a preferred embodiment of the present invention, and certainly cannot be used to limit the scope of rights of the present invention. Ordinary technicians in this field can understand that all or part of the processes of the above embodiment and equivalent changes made according to the claims of the present invention still fall within the scope covered by the utility model.
Claims
1. An integrated bearing shell structure for an axial flow turbocharger, characterized in that: It includes a compressor impeller, a compression end bearing seat, an integrated bearing shell, turbine blades and a turbine shaft, the compression end bearing seat is fixedly connected to the integrated bearing shell and is located in the integrated bearing shell, the turbine shaft is movably connected to the integrated bearing shell and is located in the integrated bearing shell, the turbine shaft is also movably connected to the compression end bearing seat and passes through the compression end bearing seat, the turbine blades are fixedly connected to the turbine shaft and are located at one end of the turbine shaft, and the compressor impeller is fixedly connected to the turbine shaft and is located at the other end of the turbine shaft.
2. The axial flow turbocharger integrated bearing housing structure according to claim 1, characterized in that: The turbine blades include a turbine seat and a plurality of blades. The turbine seat is fixedly connected to the turbine shaft and is located at an end of the turbine shaft away from the compressor impeller. The plurality of blades are fixedly connected to the turbine seat and are distributed circumferentially on the turbine seat.
3. The axial flow turbocharger integrated bearing housing structure according to claim 1, characterized in that: The one-piece bearing shell has two air guide holes, and the two air guide holes are symmetrically arranged in the one-piece bearing shell.
4. The axial flow turbocharger integrated bearing housing structure according to claim 1, characterized in that: The one-piece bearing shell, the pressure-end bearing seat and the turbine shaft are clearance-fitted.