CN213450595U

CN213450595U - Turbocharging device

Info

Publication number: CN213450595U
Application number: CN202021864255.XU
Authority: CN
Inventors: 凌旭; 肖芝; 刘翔; 张华然
Original assignee: Hunan Vocational College of Chemical Technology
Current assignee: Hunan Vocational College of Chemical Technology
Priority date: 2020-08-25
Filing date: 2020-08-25
Publication date: 2021-06-15
Anticipated expiration: 2030-08-25

Abstract

The utility model relates to a turbocharging device, the device includes the atmospheric pressure machine shell, the turbine shell and connect the turbine bearing body of atmospheric pressure machine shell and turbine shell respectively, install the turbine pivot in the turbine bearing body, the one end of turbine pivot extends to in the atmospheric pressure machine shell and the overcoat has the impeller, the other end of turbine pivot is connected to the turbine rotor that the minority is located turbine shell inside, the impeller facial make-up is equipped with the impeller blade, the turbine rotor facial make-up is equipped with turbine blade, the position that is close to the terminal surface that the turbine rotor was kept away from to the impeller blade on the internal surface of atmospheric pressure machine shell is equipped with first annular step, the position that is close to the terminal surface that the impeller blade kept away from. Local resistance and throttling resistance are formed in the leakage channel for high-pressure countercurrent gas, so that the leakage loss of the turbocharging device is effectively prevented or reduced, the performance and the working efficiency of the compressor and the turbine are improved, and the reliability of the turbocharging device is guaranteed.

Description

Turbocharging device

Technical Field

The utility model relates to a turbo charger art field especially relates to a turbo charger.

Background

The compressor and the turbine are one of the most critical component groups of the turbocharger, and have a decisive influence on the performance, the efficiency and the like of the turbocharger. In a turbocharger, the compressor compresses and collects fresh air for combustion in the engine, while the turbine absorbs, uses and supplies energy from the exhaust gases of the engine to the compressor. In recent years, with the increasing degree of modern engines, especially with the stricter restrictions on oil consumption and emission in China, the design trend of high-efficiency engines is more and more obvious, and the design and application of high-efficiency compressors and turbines become necessary because the improvement of the efficiency of the compressors and turbines can obviously improve the performance and efficiency of the whole turbocharger.

The basic structure of the existing supercharger compressor and turbine is shown in fig. 1, the compressor structure comprises 10 pressure shells, 20 impeller bodies, 30 bearing bodies and other parts, and the turbine comprises 40 turbine boxes, 50 turbines and other parts. The compressor compresses fresh air introduced from the pressure shell mainly through an impeller, expands the pressure of the compressed air through the pressure expansion disc and the pressure shell, collects the compressed air and provides the compressed air for the engine; the turbine introduces engine exhaust gas to the turbine in a predetermined flow direction through the turbine case, and the turbine absorbs and utilizes energy of the engine exhaust gas to supply the energy to the compressor.

When a turbocharger is designed, proper safety clearances H1 and H2 are usually arranged at the matching parts of an impeller and a turbine blade and a pressure shell and a turbine box so as to ensure that the impeller and the turbine blade cannot scrape the pressure shell and the turbine box during rotation to cause failure of the turbocharger, but when the impeller and the turbine blade work normally, air on the high-pressure side of the impeller and the high-pressure side of the turbine flows back to the low-pressure side of the impeller and the low-pressure side of the turbine through the safety clearances, so that the performance and the efficiency of a compressor and the turbine are reduced in a large proportion. The safety clearance is set to be larger, so that the impeller and the turbine can be better prevented from being scraped with the pressure shell and the turbine box, but the leakage loss is larger, and the efficiency of the gas compressor and the turbine is reduced; the safety clearance is set to be too small, and the impeller and the turbine are easily scratched on the air compressor shell and the turbine shell, so that the service life and the reliability of the turbocharger are reduced.

Accordingly, the inventors provide a turbocharger device.

SUMMERY OF THE UTILITY MODEL

(1) Technical problem to be solved

The embodiment of the utility model provides a turbocharging device, the position of keeping away from turbine rotor's terminal surface through being close to the impeller blade on the internal surface of aerostatic press shell is equipped with first annular step, the position that is close to turbine blade and keeps away from the terminal surface of impeller on the internal surface of turbocharging machine shell is equipped with second annular step, form local resistance and throttle resistance in revealing the passageway to high-pressure gas against the current, thereby effectively prevent or reduce turbocharging device's leakage loss, improve the compressor, the performance and the work efficiency of turbine, guarantee turbocharging device's reliability.

(2) Technical scheme

In a first aspect, an embodiment of the present invention provides a turbocharger device, which includes a gas compressor casing, a turbine casing, and a turbine bearing body respectively connecting the gas compressor casing and the turbine casing, a turbine rotating shaft is arranged in the turbine bearing body, one end of the turbine rotating shaft extends into the air compressor shell and is sleeved with an impeller, the other end of the turbine shaft is connected to a turbine rotor located at least partially inside the turbine housing, the impeller is provided with impeller blades, the turbine rotor is provided with turbine blades, the inner surface of the air compressor shell is provided with a first annular step close to the end surface of the impeller blade far away from the turbine rotor, and a second annular step is arranged on the inner surface of the turbine shell at a position close to the end surface of the turbine blade far away from the impeller.

Further, the first annular step comprises a horizontal first step surface parallel to the axis of the turbine rotating shaft and a first vertical step surface perpendicular to the axis of the turbine rotating shaft, the length of the first horizontal step surface from the front edge of the impeller blade is greater than or equal to 0.2mm, and the length of the first horizontal step surface from the tail edge of the impeller blade is less than or equal to 0.4 mm.

Further, the second annular step comprises a second horizontal step surface parallel to the axis of the turbine rotating shaft and a second vertical step surface perpendicular to the axis of the turbine rotating shaft, the distance between the second horizontal step surface and the leading edge of the turbine blade is greater than or equal to 0.2mm, and the distance between the second horizontal step surface and the trailing edge of the impeller blade is less than or equal to 0.4 mm.

Further, a plurality of first grooves are formed in the inner surface of the air compressor shell at positions corresponding to the impeller blades.

Further, a plurality of second grooves are formed in the inner surface of the turbine housing at positions corresponding to the turbine blades.

Furthermore, the length and the depth of each first groove are the same, and the length of each first groove is 0.5mm-2mm, and the depth of each first groove is 1mm-3 mm.

Furthermore, the length and the depth of each second groove are the same, the length of each second groove is 0.5mm-2mm, and the depth of each second groove is 1mm-3 mm.

Further, the sum of the lengths of the first grooves in the plane of the first horizontal step surface is smaller than the width of the impeller blade.

Further, the sum of the lengths of the second grooves in the plane of the second horizontal step surface is smaller than the width of the turbine blade.

Further, the step height of the first annular step is equal to a first safety clearance between the inner surface of the gas compressor housing and the impeller blade, and the step height of the second annular step is equal to a second safety clearance between the inner surface of the turbine housing and the turbine blade.

(3) Advantageous effects

To sum up, the utility model discloses a position that is close to the terminal surface that turbine rotor was kept away from to the impeller blade on the internal surface of aerostatic press shell is equipped with first annular step, and the position that is close to the terminal surface that turbine blade kept away from the impeller on the internal surface of turbine shell is equipped with second annular step, forms local resistance and throttle resistance in revealing the passageway to high-pressure gas against the current to effectively prevent or reduce turbocharging device's leakage loss, improve the compressor, the performance and the work efficiency of turbine, guarantee turbocharging device's reliability.

The utility model discloses an internal surface that the position that the internal surface of pneumatic press shell and impeller blade correspond is equipped with a plurality of first recesses and the internal surface of turbine shell and the position that turbine blade corresponds are equipped with a plurality of second recesses, the machining of not only being convenient for, throttling resistance when increase gas leakage that can also be by a relatively large margin has effectively reduced from the loss of revealing of impeller, turbine high pressure side direction low pressure side. The local resistance generated by the annular steps on the inner surfaces of the compressor housing and the turbine housing is combined with the throttling resistance generated by the first grooves and the second grooves to effectively prevent or reduce the leakage loss of the turbocharger.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

FIG. 1 is a schematic view of a prior art turbocharger configuration.

Fig. 2 is a schematic structural diagram of the turbocharger device of the present invention.

Fig. 3 is an enlarged view of a in fig. 2.

Fig. 4 is an enlarged view of B in fig. 2.

In the figure:

1-a gas compressor housing; 2-an impeller; 3-a turbine bearing body; 4 turbine housing-; 5-a turbine rotor; 6-impeller blades; 7-a turbine shaft; 8-turbine blades; 10-pressing the shell; 11-a first annular step; 12-a first groove; 20-an impeller body; 30-a bearing body; 40-a turbine box; 41-a second annular step; 42-a second groove; 50-a turbine; 61-first leading edge; 62-a first trailing edge; 81-a second leading edge; 82-a second trailing edge; 111-a first horizontal step surface; 112-a first vertical step face; 411-a second horizontal step surface; 412-a second vertical step surface.

Detailed Description

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention, but are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, substitutions and improvements in the parts, components and connections without departing from the spirit of the invention.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

Fig. 2 is a schematic structural view of a turbocharger device according to an embodiment of the present invention, as shown in fig. 2, the device comprises an air compressor shell 1, a turbine shell 4 and a turbine bearing body 3 respectively connecting the air compressor shell 1 and the turbine shell 4, wherein a turbine rotating shaft 7 is installed in the turbine bearing body 3, one end of the turbine rotating shaft 7 extends into the air compressor shell 1 and is externally sleeved with an impeller 2, the other end of the turbine rotating shaft 7 is connected with a turbine rotor 5 which is at least partially positioned in the turbine shell 4, an impeller blade 6 is installed on the impeller 2, a turbine blade 8 is installed on the turbine rotor 5, a first annular step 11 is arranged on the inner surface of the air compressor shell 1, close to the end face, far away from the turbine rotor 5, of the impeller blade 6, and a second annular step 41 is arranged on the inner surface of the turbine shell 4, close to the end face, far away from the.

The utility model discloses a position that is close to the terminal surface that turbine rotor was kept away from to the impeller blade on the internal surface of aerostatic press shell is equipped with first annular step, the position that is close to the terminal surface that turbine blade kept away from the impeller on the internal surface of turbine shell is equipped with second annular step, form local resistance and throttle resistance in revealing the passageway to high-pressure gas against the current to effectively prevent or reduce turbocharging device's leakage loss, improve the performance and the work efficiency of compressor, turbine, guarantee turbocharging device's reliability.

As a preferred embodiment, as shown in fig. 3, the first annular step 11 includes a horizontal first step surface 111 parallel to the axis of the turbine rotary shaft 7 and a vertical first step surface 112 perpendicular to the axis of the turbine rotary shaft 7, the length of the first horizontal step surface 111 from the first leading edge 61 of the impeller blades 6 is greater than or equal to 0.2mm, and the length of the first horizontal step surface 111 from the first trailing edge 62 of the impeller blades 6 is less than or equal to 0.4 mm.

As another preferred embodiment, as shown in fig. 4, the second annular step 41 includes a second horizontal step surface 411 parallel to the axis of the turbine rotary shaft 7 and a second vertical step surface 412 perpendicular to the axis of the turbine rotary shaft 7, the length of the second horizontal step surface 411 from the second leading edge 81 of the turbine blade 8 is greater than or equal to 0.2mm, and the length of the second horizontal step surface 411 from the second trailing edge 82 of the impeller blade 6 is less than or equal to 0.4 mm.

As other alternative embodiments.

Preferably, as shown in fig. 3 and 4, the inner surface of the gas compressor casing 1 is provided with a plurality of first grooves 12 at positions corresponding to the impeller blades 6, and the inner surface of the turbine casing 4 is provided with a plurality of second grooves 42 at positions corresponding to the turbine blades 8, wherein the number of the first grooves and the second grooves is 3-5. The utility model discloses an internal surface that the position that the internal surface of pneumatic press shell and impeller blade correspond is equipped with a plurality of first recesses and the internal surface of turbine shell and the position that turbine blade corresponds are equipped with a plurality of second recesses, the machining of not only being convenient for, throttling resistance when increase gas leakage that can also be by a relatively large margin has effectively reduced from the loss of revealing of impeller, turbine high pressure side direction low pressure side. The local resistance generated by the annular steps on the inner surfaces of the compressor housing and the turbine housing is combined with the throttling resistance generated by the first grooves and the second grooves to effectively prevent or reduce the leakage loss of the turbocharger.

Preferably, as shown in fig. 3 and 4, each first groove 12 has the same length and depth, the first groove 12 has a length of 0.5mm to 2mm and a depth of 1mm to 3mm, each second groove 42 has the same length and depth, and the second groove 42 has a length of 0.5mm to 2mm and a depth of 1mm to 3 mm.

Preferably, as shown in fig. 3 and 4, the sum of the lengths of the first grooves 12 in the plane of the first horizontal step surface 111 is smaller than the width of the impeller blade 6, and the sum of the lengths of the second grooves 42 in the plane of the second horizontal step surface 411 is smaller than the width of the turbine blade 8.

Preferably, as shown in fig. 2, the step height of the first annular step 11 is equal to a first safety clearance between the inner surface of the air compressor housing 1 and the impeller blade 6, and the step height of the second annular step 41 is equal to a second safety clearance between the inner surface of the turbine housing 4 and the turbine blade 8, the first safety clearance being the shortest distance from the first horizontal step face to the impeller blade, and the second safety clearance being the shortest distance from the second horizontal step face to the turbine blade. The impeller blades and the turbine blades are guaranteed not to be scraped with the inner surface of the gas compressor shell and the inner surface of the turbine shell in the rotating process of the gas compressor shell and the turbine shell respectively, so that the turbocharger device is prevented from being out of work.

It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.

The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.

Claims

1. A turbocharger device, comprising: air compressor housing (1), turbine shell (4) and connect respectively air compressor housing (1) with turbine bearing body (3) of turbine housing (4), install turbine pivot (7) in turbine bearing body (3), the one end of turbine pivot (7) extends to in air compressor housing (1) and overcoat have impeller (2), the other end of turbine pivot (7) is connected to the part and is located at least turbine rotor (5) inside turbine housing (4), impeller (2) facial make-up is equipped with impeller blade (6), turbine rotor (5) facial make-up is equipped with turbine blade (8), be close to on the internal surface of air compressor housing (1) impeller blade (6) are kept away from the position of the terminal surface of turbine rotor (5) is equipped with first annular step (11), be close to on the internal surface of turbine housing (4) turbine blade (8) are kept away from the position of the terminal surface of impeller (2) is established and is established There is a second annular step (41).

2. The turbocharging device according to claim 1, wherein said first annular step (11) comprises a first horizontal step surface (111) parallel to the axis of said turbine shaft (7) and a first vertical step surface (112) perpendicular to the axis of said turbine shaft (7), the length of said first horizontal step surface (111) from the first leading edge (61) of said impeller blade (6) being greater than or equal to 0.2mm, and the length of said first horizontal step surface (111) from the first trailing edge (62) of said impeller blade (6) being less than or equal to 0.4 mm.

3. The turbocharging device according to claim 1, wherein said second annular step (41) comprises a second horizontal step face (411) parallel to the axis of said turbine shaft (7) and a second vertical step face (412) perpendicular to the axis of said turbine shaft (7), said second horizontal step face (411) having a length from the second leading edge (81) of said turbine blade (8) of greater than or equal to 0.2mm, and said second horizontal step face (411) having a length from the second trailing edge (82) of said impeller blade (6) of less than or equal to 0.4 mm.

4. The turbocharging device according to claim 2, wherein a plurality of first grooves (12) are provided on the inner surface of the compressor housing (1) at positions corresponding to the impeller blades (6).

5. A turbocharging device according to claim 3, wherein a plurality of second grooves (42) are provided on the inner surface of the turbine housing (4) at positions corresponding to the turbine blades (8).

6. The turbocharging device according to claim 4, wherein each of said first grooves (12) has the same length and depth, and wherein said first grooves (12) have a length of 0.5mm-2mm and a depth of 1mm-3 mm.

7. The turbocharging device according to claim 5, wherein each of said second grooves (42) has the same length and depth, and said second grooves (42) have a length of 0.5mm-2mm and a depth of 1mm-3 mm.

8. Turbocharging device according to claim 4, wherein the sum of the lengths of each of said first grooves (12) in the plane of said first horizontal step surface (111) is smaller than the width of said impeller blades (6).

9. Turbocharging device according to claim 5, wherein the sum of the lengths of each of said second grooves (42) in the plane of said second horizontal step surface (411) is smaller than the width of said turbine blade (8).

10. The turbocharging device according to claim 1, wherein the step height of said first annular step (11) is equal to a first safety clearance between the inner surface of the gas compressor housing (1) and the impeller blades (6), and the step height of said second annular step (41) is equal to a second safety clearance between the inner surface of the turbine housing (4) and the turbine blades (8).