A turbocharger and an engine

Abstract

The present invention provides a turbocharger and an engine. The disclosed turbocharger includes a turbine housing, a turbine, and a bearing housing. The turbine housing forms an exhaust passage, an annular intake passage, and a radial jet port located between the exhaust passage and the annular intake passage. The turbine is installed in the exhaust passage, and the outer peripheral edge of its turbine blades faces the radial jet port. A plurality of nozzle vanes are fixed to the radial jet port, and the outer end surface of the nozzle vanes abuts against the outer wall surface of the radial jet port. By providing a plurality of nozzle vanes, the incoming air flow can be made more uniform. Keeping the flow cross-sectional area of the intake passage, the radius of the center line of the intake passage, the width of the nozzle vanes, and the diameter of the turbine within an appropriate range and making the four cooperate with each other can ensure the exhaust uniformity while reducing the exhaust frictional loss along the way and ensuring the conversion efficiency of the turbine.

Description

Technical Field

[0001] The present invention relates to an engine turbocharging technology, and particularly to a turbocharger and an engine including the turbocharger. Background Art

[0002] In order to improve engine efficiency, setting a turbocharger has become one of the important options. The turbocharger includes a turbine section and a compressor section. The turbine section converts the high-temperature and high-pressure gas discharged from the engine into mechanical energy to provide power for the compressor section. The compressor section increases the intake pressure of the engine under the drive of the turbine section, providing a prerequisite for improving engine efficiency. A bearing body is formed between the turbine section and the compressor section, and both ends of the intermediate shaft penetrate the bearing body and are respectively connected to the compressor impeller and the turbine.

[0003] The turbine section includes a turbine housing and a turbine. An axial exhaust passage is formed inside the turbine housing and in the middle part. An annular intake flow passage is formed around the exhaust passage. A radial jet port is formed between the intake flow passage and the exhaust passage. The intake flow passage communicates with the engine exhaust valve to introduce the high-temperature and high-pressure gas of the engine. The turbine is installed at the bottom of the exhaust passage and rotates coaxially with the impeller of the compressor section. The turbine includes a plurality of turbine blades, and the outer peripheral edge of the turbine blades faces the radial jet port. The high-temperature and high-pressure engine exhaust forms a high-speed impact on the turbine blades after passing through the annular intake flow passage and the radial jet port, causing the turbine to rotate at a high speed and synchronously driving the impeller of the compressor section to rotate.

[0004] In order to ensure the efficiency of the turbine section, in the prior art, a nozzle ring formed by a plurality of adjustable nozzle blades is provided at the radial jet port. The nozzle blades of the nozzle ring are usually positioned by an inner mounting disc and an outer cover plate. In order to take into account the performance of large and small flow rates of the turbine section and to achieve the rotation of the nozzle blades, a predetermined gap (wall surface gap) is maintained between the nozzle blades and the wall surfaces of the mounting disc and the cover plate.

[0005] Since the performance and efficiency improvement of the turbine are restricted by the exhaust characteristics, the exhaust uniformity entering the turbine affects the stability of the turbine. To improve the exhaust uniformity, the exhaust flow path (friction loss) needs to be increased, and increasing the friction loss will increase the along-path loss. Therefore, during the flow of the engine exhaust in the turbine section, improving the turbine performance and efficiency is restricted by multiple factors including the exhaust passage structure, the compression limit of the radial jet port, and the flow guiding of the nozzle ring. How to balance the above contradictions and ensure the turbine performance and efficiency is the direction of the efforts of those skilled in the art. Summary of the Invention

[0006] The first object of the present invention is to provide a turbocharger with higher efficiency.

[0007] The second object of the present invention is to provide an engine including the above turbocharger.

[0008] The turbocharger provided by the present invention includes a turbine housing, a turbine, and a bearing housing. The turbine housing forms an exhaust passage, an annular intake passage, and a radial jet port located between the exhaust passage and the annular intake passage. The turbine is installed in the exhaust passage, and the outer peripheral edge of its turbine blades faces the radial jet port. A plurality of nozzle vanes are fixed to the radial jet port, and the outer end face of the nozzle vanes abuts against the outer wall surface of the radial jet port. By setting a plurality of nozzle vanes, the incoming air flow can be made more uniform. At the same time, the turbocharger satisfies B / D = 0.12 - 0.15 and (A / R) / B = 2.7 - 3.3;

[0009] Wherein: A is the flow cross-sectional area of the intake passage;

[0010] R is the radius of the center line of the intake passage;

[0011] B is the width of the nozzle vane;

[0012] D is the maximum diameter of the turbine.

[0013] Keeping the flow cross-sectional area A of the intake passage, the radius R of the center line of the intake passage, the width B of the nozzle vane, and the diameter of the turbine (such as the maximum diameter D) within an appropriate range and making the four cooperate with each other can ensure the exhaust uniformity while reducing the exhaust frictional loss along the way and ensuring the conversion efficiency of the turbine.

[0014] In an alternative technical solution, a plurality of nozzle vanes are fixed, and the outer end face of the nozzle vanes abuts against the inner wall surface of the radial jet port, reducing the air flow separation caused by the outer end face gap and reducing the energy loss, which is thus beneficial to improving the efficiency of the turbocharger.

[0015] In a further technical solution, the turbine housing includes a cover plate, and the outer end face of the nozzle vane abuts against the inner wall surface of the cover plate, or the inner wall surface of the cover plate is in sealed cooperation with the outer end face of the nozzle vane. By providing a cover plate that cooperates with the outer end face of the nozzle vane, the air flow separation caused by the outer end face gap can be further reduced, and the energy loss can be reduced.

[0016] In a further technical solution, the turbocharger further includes a mounting chassis fixed to the bearing housing, and the inner end face of the nozzle vane abuts against the outer surface of the mounting chassis, or the inner end face of the nozzle vane is in sealed cooperation with the outer surface of the mounting chassis. This can also reduce the air flow separation caused by the inner end face gap of the nozzle vane and reduce the energy loss.

[0017] In an alternative technical solution, the turbocharger further includes a nozzle ring substrate and a spring member. The nozzle vanes are fixed to the nozzle ring substrate; the turbine housing forms a substrate cavity; the peripheral surface of the nozzle ring substrate mates with the inner wall surface of the substrate cavity of the turbine housing; the spring member is supported between the bearing body and the nozzle ring substrate, such that the outer end surface of the nozzle vane abuts against the outer wall surface of the radial jet port. In a preferred solution, the nozzle ring substrate is annular, and a clearance fit is formed between its inner peripheral wall surface and the outer peripheral edge of the turbine blades of the turbine. On the one hand, a suitable fit clearance can be formed at the outer peripheral edge of the turbine blades to ensure the turbine energy conversion efficiency; on the other hand, the air flow separation caused by the clearance at the inner end surface of the nozzle vane can be reduced, and the energy loss can be reduced.

[0018] The present invention also provides an engine, including an engine body and a matching turbocharger, where the turbocharger is any one of the above-mentioned turbochargers. Since the above-mentioned turbocharger has the above technical effects, the engine including this turbocharger also has corresponding technical effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings included in and forming a part of the specification illustrate the exemplary, features, and aspects of the present invention and are used to explain the principles of the present invention.

[0020] Figure 1 Is a perspective view of the turbocharger provided in Embodiment 1 of the present invention, which mainly shows the structure of the turbine part.

[0021] Figure 2 Is Figure 1 An exploded view of the turbocharger shown in.

[0022] Figure 3 Schematically shows the distribution positions of multiple nozzle vanes of the nozzle ring in the embodiment.

[0023] Figure 4 The experimental data performance graph of the specific embodiment of the present invention.

[0024] Figure 5 Is the implementation data performance graph of the comparative example (existing turbocharger).

[0025] Figure 6 Is a schematic cross-sectional structure view of the turbocharger provided in Embodiment 2 of the present invention.

[0026] Figure 7 Is Figure 6 An enlarged view of part Y in, schematically showing the positioning principle of the nozzle ring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] Various exemplary embodiments, features, and aspects of the present invention will be described in detail below with reference to the accompanying drawings. The same reference numerals in the drawings denote elements having the same or similar functions. Although various aspects of the embodiments are shown in the drawings, the drawings do not have to be drawn to scale unless otherwise specified. The term "exemplary" as used herein means "serving as an example, embodiment, or illustration". Any embodiment described herein as "exemplary" does not have to be construed as superior to or better than other embodiments.

[0028] Unless otherwise indicated in combination with the context or specifically stated, in this document, azimuth terms such as "circumferential" and "axial" are determined based on the rotation axis of the turbine in the turbocharger; "outer" and "inner" are determined based on the main gas flow direction in the exhaust passage of the turbine section, consistent with the flow direction is "front", and opposite to the flow direction is "rear".

[0029] Please refer to Figure 1 and Figure 2 , Figure 1 is a perspective view of a turbocharger provided in the first embodiment of the present invention, which mainly shows the structure of the turbine part. Figure 2 is Figure 1 the exploded view of the turbine part of the turbocharger shown in Figure 1 and Figure 2 mainly show the structure of the turbine part.

[0030] The turbocharger provided in the first embodiment of the present invention includes a turbine housing 100, a turbine 200, and a bearing housing 400. The turbine housing 100 forms an exhaust passage 101 and an intake passage 102. The intake passage 102 is formed around the exhaust passage 101 and is a ring structure. The exhaust passage 101 communicates with the annular intake passage 102 through an annular radial jet port 103.

[0031] The turbine housing 100 is generally volute-shaped and has an intake port to introduce engine exhaust into the annular intake passage 102, so that the exhaust enters the exhaust passage 101 through the radial jet port 103 and impacts the turbine blades of the turbine 200.

[0032] The turbine 200, as the rotor part of the turbine section, is installed on the intermediate shaft and is located behind the exhaust passage 101. The outer peripheral edge of the turbine blades of the turbine 200 faces the radial jet port 103 to receive engine exhaust and rotate under the impact of the engine exhaust.

[0033] In this embodiment, a plurality of nozzle vanes 310 are fixed to the radial jet port 103, and the outer end face 310a of the nozzle vanes 310 abuts against the outer wall surface of the radial jet port 103. The plurality of nozzle vanes 310 can be evenly arranged around the rotation axis of the turbine 200 and are relatively fixed to form a complete nozzle ring.

[0034] A plurality of nozzle vanes 130 are provided to guide and distribute the exhaust gas entering the turbine 200, which can make the entering air flow more uniform; and the plurality of nozzle vanes are fixed, and the outer end surface 310a of the nozzle vane 310 abuts against the inner wall surface of the radial jet port 103, so as to reduce the air flow separation caused by the outer end surface gap and reduce the energy loss, thereby being beneficial to improving the efficiency of the turbocharger.

[0035] At the same time, the turbocharger satisfies the conditions of B / D = 0.12 - 0.15 and (A / R) / B = 2.7 - 3.3. Wherein: A is the flow cross-sectional area of the intake passage 102;

[0036] R is the radius of the center line of the intake passage 102;

[0037] B is the width of the nozzle vane 310;

[0038] D is the maximum diameter of the turbine.

[0039] Keeping the flow cross-sectional area A of the intake passage 102, the radius R of the center line of the intake passage 102, the width B of the nozzle vane 310, and the diameter of the turbine (such as the maximum diameter D) within an appropriate range and making the four cooperate with each other can ensure the exhaust gas uniformity while reducing the exhaust gas frictional loss along the way and ensuring the conversion efficiency of the turbine.

[0040] As Figure 1 and 2 shown, the turbine housing 100 includes a cover plate 110. The outer end surface 310a of the nozzle vane 310 abuts against the inner wall surface of the cover plate 110. The cover plate 110 is processed as a separate component, which can ensure the cooperation between the outer end surface 310a of the nozzle vane 310 and the inner wall surface of the cover plate 110. In a preferred solution, the nozzle vane 310 can be positioned on the cover plate 110 or fixed to the cover plate 110 by means of grooves, holes, pins, etc. At the same time, the inner wall surface of the cover plate 110 can be in sealing fit with the outer end surface 310a of the nozzle vane 310.

[0041] By providing the cover plate 110 that cooperates with the outer end surface of the nozzle vane 310, the air flow separation caused by the outer end surface gap can be further reduced, and the energy loss can be reduced. Correspondingly, the turbocharger further includes a mounting chassis 120 fixed to the bearing body 400, and the inner end surface (not indicated in the figure) of the nozzle vane 310 abuts against the outer surface of the mounting chassis 120, or the inner end surface of the nozzle vane 310 is in sealing fit with the outer surface of the mounting chassis 120; this can also reduce the air flow separation caused by the inner end surface gap of the nozzle vane 310 and reduce the energy loss.

[0042] It can be understood that the cover plate 110 is positioned and fixed to the main body of the turbine housing 100 in an existing manner.

[0043] Please refer to Figure 3 This figure illustrates the distribution of nozzle vanes 310 in Example 1. Nozzle vanes 310 maintain an appropriate radial angle relative to the radial direction, which maximizes exhaust gas efficiency entering turbine 200 while balancing exhaust losses. In the preferred embodiment, the inlet guide angle C1 is 55 to 60 degrees, and the outlet guide angle is 70 to 75 degrees. In a specific embodiment, the inlet guide angle C1 is 55 degrees, and the outlet guide angle is 75 degrees.

[0044] This comparison test compares a conventional turbocharger and a turbocharger according to an embodiment of the present invention, under identical flow characteristics. In the embodiment of the present invention, B / D = 0.12, (A / R) / B = 2.7, a maximum turbine diameter of 44.0, and A / R = 27.464. The conventional turbocharger (comparative embodiment) exhibits identical flow characteristics, but with B / D = 0.1, A / R = 12, and (A / R) / B = 1.35.

[0045] Parameter selection takes into account:

[0046] 1. The flow rate of the turbine section depends on the ratio of the flow cross-sectional area A of the intake passage 102 to the radius R of the center line of the intake passage 102. When the flow rate and intake pressure are determined, the flow cross-sectional area A of the intake passage 102 affects the total pressure loss of the turbine box.

[0047] 2. The width B of the nozzle blade 310 , together with the A / R ratio, theoretically determines the airflow angle of the exhaust gas entering the radial jet port 103 .

[0048] 3. The three-dimensional characteristics of the exhaust gas: the airflow angle of the radial jet port 103 is non-uniform both in the circumferential direction and in the radial direction.

[0049] Experimental data of specific embodiments of the present invention:

[0050]

[0051]

[0052]

[0053]

[0054] Comparative Example (Existing Turbocharger) Implementation Data:

[0055]

[0056]

[0057]

[0058] In the above table:

[0059]

[0060] For the performance graph formed based on the above experimental data, please refer to Appendix Figure 4 and Figure 5 , it can be seen that compared with the comparative example and the embodiments of the present invention, the efficiency of the specific embodiments of the present invention is improved more. According to the above data, corresponding expansion can be carried out, and it can be determined that B / D = 0.12 - 0.15 and (A / R) / B = 2.7 - 3.3 also have the effect of improving the turbine efficiency.

[0061] Please refer to Figure 6 and Figure 7 、 Figure 6 FIG. is a schematic structural diagram of a turbocharger in another embodiment of the present invention. Figure 7 is Figure 6 an enlarged view of part Y in FIG., which schematically shows the positioning principle of the nozzle ring.

[0062] Compared with the first embodiment, in this embodiment, the turbocharger further includes a nozzle ring substrate 320 and a spring member 330. The nozzle ring substrate 320 and the spring member 330 can form a complete nozzle ring with the nozzle vanes 310. The nozzle vanes 310 can be fixed on the nozzle ring substrate 320.

[0063] The turbine housing 100 forms an appropriate substrate cavity. The peripheral surface of the nozzle ring substrate 320 cooperates with the inner wall surface of the substrate cavity of the turbine housing 100 to accurately position the nozzle ring substrate 320 and the nozzle vanes 310. The spring member 330 can be supported between the bearing body 400 and the nozzle ring substrate 320, so that the outer end surface 310a of the nozzle vanes 310 abuts against the outer wall surface of the radial jet port 103. In a preferred solution, the nozzle ring substrate 320 is annular, and its inner peripheral wall surface forms a clearance fit with the outer peripheral edge of the turbine blades of the turbine 200. In this way, on the one hand, an appropriate fit clearance can be formed at the outer peripheral edge of the turbine blades to ensure the energy conversion efficiency of the turbine 200; on the other hand, the air flow separation caused by the clearance at the inner end surface of the nozzle vanes 310 can be reduced, and the energy loss can be reduced.

[0064] In this embodiment, the spring member 330 can be a disc spring including an annular structure to ensure the sealing performance and keep an appropriate clearance between the front surface of the disc spring and the rear edge of the turbine blades. It can be understood that the spring member 330 can be a circlip, a torsion spring or other elastic components.

[0065] The present invention also provides an engine, which includes an engine body and a cooperating turbocharger, and the turbocharger is any of the above-mentioned turbochargers. Since the above-mentioned turbocharger has the above technical effects, the engine including this turbocharger also has corresponding technical effects.

[0066] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made. These improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A turbocharger, comprising a turbine housing (100), a turbine (200) and a bearing housing (400). The turbine housing (100) forms an exhaust passage (101), an annular intake passage (102) and a radial jet port (103) located between the exhaust passage (101) and the annular intake passage (102). The turbine (200) is installed in the exhaust passage (101), and the outer peripheral edge of its turbine blades faces the radial jet port (103). A plurality of nozzle vanes (310) are fixed to the radial jet port (103); characterized in that, Satisfy B / D = 0.12 - 0.15, and (A / R) / B = 2.7 - 3.3; Wherein: A is the flow cross-sectional area of the intake passage (102); R is the radius of the center line of the intake passage (102); B is the width of the nozzle vane (310); D is the maximum diameter of the turbine (200).

2. The turbocharger according to claim 1, characterized in that, The outer end surface (310a) of the nozzle vane (310) abuts against the inner wall surface of the radial jet port (103).

3. The turbocharger according to claim 2, characterized in that, The turbine housing (100) includes a cover plate (110), and the outer end surface (310a) of the nozzle vane (310) abuts against the inner wall surface of the cover plate (110).

4. The turbocharger according to claim 3, characterized in that, The inner wall surface of the cover plate (110) is in sealing fit with the outer end surface (310a) of the nozzle vane (310).

5. The turbocharger according to claim 4, characterized in that, It further includes a mounting chassis (120) fixed to the bearing body (400), and the inner end surface of the nozzle vane (310) abuts against the outer surface of the mounting chassis (120).

6. The turbocharger according to claim 5, characterized in that, The inner end surface of the nozzle vane (310) is in sealing fit with the outer surface of the mounting chassis (120).

7. The turbocharger according to claim 2, characterized in that, It further includes a nozzle ring substrate (320) and a spring member (330). The nozzle vane (310) is fixed on the nozzle ring substrate (320); the turbine housing (100) forms a substrate cavity; the peripheral surface of the nozzle ring substrate (320) is in fit with the inner wall surface of the substrate cavity of the turbine housing (100); the spring member (330) is supported between the bearing body (400) and the nozzle ring substrate (320), so that the outer end surface (310a) of the nozzle vane (310) abuts against the outer wall surface of the radial jet port (103).

8. The turbocharger according to claim 7, characterized in that, The nozzle ring substrate (320) is annular, and its inner peripheral wall surface forms a clearance fit with the outer peripheral edge of the turbine blades of the turbine (200).

9. The turbocharger according to claim 8, characterized in that, Relative to the radial direction, the inlet guide angle (C1) of the nozzle vane (310) is 55 degrees to 60 degrees, and the outlet guide angle is 70 degrees to 75 degrees.

10. An engine, comprising an engine body and a matching turbocharger, characterized in that, The turbocharger is the turbocharger according to any one of claims 1 to 9.

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