CN204312397U - With the turbosupercharger of gas compressor footpath diagonal impeller - Google Patents

Abstract

A turbocharger with a radial oblique flow impeller of a compressor, including a turbine case, a bearing body, a compressor pressure casing, a rotor shaft, a turbine rotor, a thrust vane, an oblique flow impeller of a compressor, a thrust bearing, and a sealing sleeve , heat shield, oil seal cover, sealing ring. The turbine box is connected with the bearing body through the collar sleeve, the heat shield is installed between the turbine box and the end plane of the bearing body, the turbine rotor is fixedly installed at one end of the rotor shaft, and the rotor shaft is installed on the inner ring of the sliding bearing on the bearing body, and the The push piece, the seal sleeve and the oblique flow impeller of the compressor are installed on the other end of the rotor shaft in turn, and are fixed on the rotor shaft by nuts, and the thrust bearing is installed on the outer circle of the seal sleeve, and fixed on the bearing body by screws , The pressure end seal ring is installed on the circular boss of the seal sleeve, the oil seal cover is set on the seal sleeve and fixed in the bearing body, and the compressor pressure shell is connected with the bearing body through screws and pressure plates.

Description

Turbocharger with compressor radial impeller

technical field

The utility model relates to the technical field of turbochargers, in particular to a method of reducing the axial load of the impeller of the compressor by adopting radial oblique flow impellers and improving the low flow rate of the supercharger, which is easy to generate on the side of the inlet rim of the bladeless diffuser. Backflow turbocharger.

Background technique

The turbocharger uses the exhaust of the engine to drive the turbine, and the rotation of the turbine drives the coaxial compressor to work. The compressor compresses the fresh air entering the engine, thereby increasing the intake air volume of the engine, increasing the power of the engine, and reducing the power consumption of the engine. fuel consumption.

Existing turbocharger as shown in accompanying drawing 1, comprises turbine box 1, bearing body 2, compressor pressure shell 3, rotor shaft 4, turbine rotor 5, thrust vane 6, compressor impeller 7, thrust bearing 8. Sealing sleeve 9, heat shield 10, oil sealing cap 11, sealing ring 12.

The turbine box 1 is connected to the bearing body 2 through a collar sleeve, the heat shield 10 is installed between the end plane of the turbine box 1 and the bearing body 2, the turbine rotor 5 is fixedly installed on one end of the rotor shaft 4, and the rotor shaft 4 is installed on the bearing body The inner ring of the sliding bearing on 2, the thrust plate 6, the sealing sleeve 9 and the compressor impeller 7 are installed on the other end of the rotor shaft 4 in sequence, and are fixed on the rotor shaft 4 by nuts, and the thrust bearing 8 is installed on the sealing sleeve 9 and fixed on the bearing body 2 by screws, the pressure end sealing ring 12 is installed on the round boss of the sealing sleeve 9, the oil sealing cover 11 is set on the sealing sleeve 9 and fixed in the bearing body 2, and the compressed air The machine pressure shell 3 is connected with the bearing body 2 through screws and pressure plates.

The radial flow impeller 7 that existing turbocharger adopts is as shown in accompanying drawing 3, 4, comprises wheel hub 7-1, plural long blades 7-2 and plural short blades 7-3, long blades 7-2 and short The number of blades 7-3 is the same, long blades 7-2 and short blades 7-3 are evenly distributed on the hub 7-1 in a staggered shape, long blades 7-2 air outlet top 7-2-1 and short blades 7- 3 The air outlet top 7-3-1 is parallel to the hub 7-1's axle center line, the outer circle profile diameter of the long blade 7-2 air outlet top 7-2-1 and the short blade 7-3 air outlet top 7-3 The diameter of the outer circle of -1 is the same as the diameter of the disc of hub 1, both being D1.

With the development of turbochargers towards high speed and high pressure ratio, the entire turbocharger bearing system is under severe test, and the pressure ratio of the compressor increases, resulting in the axial load from the turbocharger end to the pressure end Increase, the axial load of the impeller mainly refers to the pressure P1 of the compressor inlet on the front of the impeller and the pressure P2 in the back clearance of the impeller. The pressure P2 in the back clearance of the compressor wheel is higher than the inlet pressure P1 when the supercharger is in normal operation. , when the axial load generated by the pressure P2 in the back clearance of the impeller is too large, the oil film between the thrust bearing 8 and the thrust plate 6 is not enough to bear the axial load, resulting in aggravated dry friction between parts. Under the action, the thrust bearing 8 wears out quickly, and when it is serious, the impeller blades will rub against the compressor casing to damage the supercharger.

Furthermore, the traditional radial flow impeller tends to generate backflow at the inlet rim side of the vaneless diffuser under the low flow rate of the supercharger.

In the field of turbocharger industry, in order to overcome the increase of axial load, we mainly start from two aspects. One is to increase the bearing capacity of the oil film by designing a new thrust bearing surface structure, so that the axial load that the thrust bearing can bear As the load value increases, this solution cannot reduce the axial load on the back of the compressor impeller. When the axial load on the back of the impeller is too large, the turbine rotor system and the thrust bearing will still have direct contact and dry wear The second is to achieve the purpose of indirectly reducing the axial load by increasing the A/R value of the turbine box flow channel, but the resulting problem is that after increasing the turbine box flow channel, the low-speed performance of the engine will be greatly affected. Contrary to current engines' emphasis on low-speed performance.

Contents of the invention

The purpose of this utility model is to overcome the above-mentioned deficiencies of the prior art and provide a turbocharger with a radial oblique flow impeller of the compressor, one is to reduce the shaft acting on the back of the impeller disc by reducing the area of the impeller disc to prevent supercharger failure caused by the failure of the thrust bearing of the supercharger; the second is to use a combination of oblique flow outlet and radial flow outlet at the outlet of the blade, and use the oblique flow outlet to improve the curvature of the impeller flange. Due to the uneven distribution of the flow field in the span direction of the impeller outlet, the radial flow outlet is used to balance the backflow at the hub of the diffuser inlet caused by the improper setting of the oblique flow outlet, and the effective combination of the oblique flow outlet and the outflow outlet , finally makes the inlet flow field distribution of the vaneless diffuser very ideal, and improves the working efficiency of the compressor.

The technical scheme of the utility model is: a turbocharger with a radial oblique flow impeller of a compressor, including a turbine box, a bearing body, a compressor casing, a rotor shaft, a turbine rotor, a thrust plate, a compressor impeller, a Push bearings, sealing sleeves, heat shields, oil seal covers, sealing rings.

The turbine box is connected with the bearing body through a collar sleeve, the heat shield is installed between the turbine box and the end plane of the bearing body, the turbine rotor is fixedly installed at one end of the rotor shaft, and the rotor shaft is installed on the inner ring of the sliding bearing on the bearing body, and the The push piece, sealing sleeve and compressor impeller are installed on the other end of the rotor shaft in sequence, and are fixed on the rotor shaft by nuts. The thrust bearing is installed on the outer circle of the sealing sleeve, and is fixed on the bearing body by screws. The pressure end The sealing ring is installed on the circular boss of the sealing sleeve, the oil sealing cover is set on the sealing sleeve and fixed in the bearing body, and the compressor pressure casing is connected with the bearing body through screws and pressure plates.

The compressor impeller adopts a radial oblique flow impeller, which includes a hub, four to six long blades and four to six short blades, the number of long blades and short blades is the same, and the long blades and short blades are staggered Evenly distributed on the hub, the top of the air outlet of the long blade and the top of the air outlet of the short blade adopt a combination of radial flow and oblique flow, the oblique edge of the oblique outlet of the long blade and the oblique edge of the oblique outlet of the short blade are in line with the hub The axis angle a is 15°～70°, the diameter of the tip outer circle of the oblique outlet of the oblique flow outlet of the long blade and the oblique outlet of the short blade is D1, the sideline of the runoff outlet of the long blade and the sideline of the runoff outlet of the short blade The diameter of the outer circle is D2, and D2 is smaller than D1. The sidelines of the long-blade runoff outlet and the short-blade runoff outlet are parallel to the centerline of the wheel hub. In order to reduce the stress concentration at the intersection, the diameter of the outer circle of the wheel hub is consistent with the diameter of the outer circle of the runoff outlet.

When the turbocharger is in normal operation, the axial load F acting on the impeller is mainly determined by the front pressure P1 of the compressor inlet impeller, the pressure P2 in the back gap of the impeller wheel and the contact area between the gas and the impeller, F=F2-F1, F1 P1 is the axial load acting on the front surface of the impeller, F2 is the axial load acting on the back of the impeller wheel by P2, and the pressure P2 in the back clearance of the impeller wheel of the compressor is higher than the inlet pressure P1 when the supercharger is in normal operation. After the area of the back of the impeller decreases, the force-receiving area also decreases, and the decrease of the load F2 acting on the back surface of the impeller will be greater than the decrease of the axial load F1 acting on the front surface of the impeller. The load in the front direction of the impeller is reduced. As the speed increases, the axial load F on the oblique flow impeller decreases more obviously, which reduces the load on the thrust bearing and effectively improves the operation of the turbocharger.

Furthermore, the combination of oblique flow outlet and radial flow outlet is adopted at the outlet of the blade. The oblique flow outlet is used to improve the uneven distribution of the flow field in the span direction of the impeller outlet caused by the excessive curvature of the impeller rim, and the radial flow outlet is used to balance the flow field caused by the impeller. The backflow at the diffuser inlet hub caused by improper setting of the oblique flow outlet, and through the effective combination of the oblique flow outlet and the outflow outlet, finally makes the inlet flow field distribution of the vaneless diffuser very ideal and improves the compressor performance. work efficiency.

Compared with the prior art, the utility model has the following characteristics:

1. On the existing radial flow impeller supercharger, change the impeller structure, reduce the outer circle radius of the impeller wheel back, and reduce the surface load F2 of the impeller wheel back by reducing the force-bearing surface, so as to realize the reduction of the rotor system. The axial load avoids the reduction of the life of the thrust bearing due to the large axial load, and improves the overall reliability of the supercharger.

2. Use the oblique flow outlet to improve the uneven distribution of the flow field in the span direction of the impeller outlet caused by the excessive curvature of the impeller flange, and use the radial flow outlet to balance the backflow at the hub of the diffuser inlet caused by improper setting of the oblique flow outlet Through the effective combination of the inclined flow outlet and the outlet, the flow field distribution at the inlet of the vaneless diffuser is ideal, and the working efficiency of the compressor is improved.

The detailed structure of the present utility model will be further described below in conjunction with the accompanying drawings and specific embodiments.

Description of drawings

Accompanying drawing 1 is the structural representation of existing turbocharger;

Accompanying drawing 2 is the enlarged view of part I in accompanying drawing 1;

Accompanying drawing 3 is the structural representation of existing radial flow impeller;

Accompanying drawing 4 is A-A sectional view among accompanying drawing 3;

Accompanying drawing 5 is the structural schematic diagram of the turbocharger with radial oblique flow impeller of band compressor;

Accompanying drawing 6 is the structural representation of radial oblique flow impeller;

Accompanying drawing 7 is B-B sectional view among accompanying drawing 6;

Accompanying drawing 8 is II part enlarged view among 7.

Detailed ways

A turbocharger with a radial oblique flow impeller of a compressor, comprising a turbine case 1, a bearing body 2, a compressor casing 3, a rotor shaft 4, a turbine rotor 5, a thrust vane 6, a compressor impeller 13, a thrust Bearing 8, sealing sleeve 9, heat shield 10, oil sealing cover 11, sealing ring 12.

The turbine box 1 is connected to the bearing body 2 through a collar sleeve, the heat shield 10 is installed between the end plane of the turbine box 1 and the bearing body 2, the turbine rotor 5 is fixedly installed on one end of the rotor shaft 4, and the rotor shaft 4 is installed on the bearing body The inner ring of the sliding bearing on 2, the thrust plate 6, the sealing sleeve 9 and the compressor impeller 13 are installed on the other end of the rotor shaft 4 in sequence, and are fixed on the rotor shaft 4 by nuts, and the thrust bearing 8 is installed on the sealing sleeve 9 and fixed on the bearing body 2 by screws, the pressure end sealing ring 12 is installed on the round boss of the sealing sleeve 9, the oil sealing cover 11 is set on the sealing sleeve 9 and fixed in the bearing body 2, and the compressed air The machine pressure shell 3 is connected with the bearing body 2 through screws and pressure plates.

Described compressor impeller adopts radial oblique flow impeller, and radial oblique flow impeller 13 comprises hub 13-1, five long blades 13-2 and five short blades 13-3, long blade 13-2 and short blade 13-3 Evenly distributed on the hub 13-1 in a staggered shape, the top of the air outlet of the long blade 13-2 and the top of the air outlet of the short blade 13-3 adopt a structure combining radial flow and oblique flow, and the oblique flow outlet of the long blade 13-2 The hypotenuse 13-2-1 and the hypotenuse 13-3-1 of the oblique flow outlet of the short blade 13-3 are 30° with the axis angle a of the hub 13-1, and the oblique side of the oblique flow outlet of the long blade 13-2 13-2-1 and the oblique edge 13-3-1 of the oblique flow outlet of the short blade 13-3 have a blade tip outer circle diameter of D1, and the sideline 13-2-2 of the long blade 13-2 runoff outlet and the short blade 13 The diameter of the outer circle of the sideline 13-3-2 of the -3 runoff outlet is D2, D2 is less than D1, the sideline 13-2-2 of the long blade 13-2 runoff outlet and the sideline 13-3 of the short blade 13-3 runoff outlet -2 is parallel to the center line of the hub 13-1, and the intersection of the inclined edge of the oblique flow outlet and the edge of the runoff outlet adopts a circular arc transition to reduce the stress concentration at the intersection. The diameter of the outer circle contour is the same.

Claims (1)

1. A turbocharger with a radial oblique flow impeller of a compressor, comprising a turbine case, a bearing body, a compressor casing, a rotor shaft, a turbine rotor, a thrust vane, a compressor impeller, a thrust bearing, a sealing sleeve, Heat shield, oil seal cover, sealing ring; The turbine box is connected with the bearing body through a collar sleeve, the heat shield is installed between the turbine box and the end plane of the bearing body, the turbine rotor is fixedly installed at one end of the rotor shaft, and the rotor shaft is installed on the inner ring of the sliding bearing on the bearing body, and the The push piece, sealing sleeve and compressor impeller are installed on the other end of the rotor shaft in sequence, and are fixed on the rotor shaft by nuts. The thrust bearing is installed on the outer circle of the sealing sleeve, and is fixed on the bearing body by screws. The pressure end The sealing ring is installed on the circular boss of the sealing sleeve, the oil sealing cover is set on the sealing sleeve and fixed in the bearing body, and the compressor pressure shell is connected with the bearing body through screws and pressure plates; It is characterized in that: the compressor impeller adopts a radial-slant flow impeller, and the radial-slant flow impeller includes a hub, four to six long blades and four to six short blades, the number of long blades and short blades is the same, and the number of long blades and short blades is the same. The blades are evenly distributed on the hub in a staggered shape. The top of the air outlet of the long blade and the top of the air outlet of the short blade adopt a combination of radial flow and oblique flow. The oblique edge of the oblique outlet of the long blade and the oblique outlet of the short blade The axis angle a between the side and the hub is 15°～70°, the diameter of the tip outer circle of the oblique outlet of the long blade oblique outlet and the oblique outlet of the short blade is D1, the sideline of the long blade radial outlet and the short blade The diameter of the outer circle of the sideline of the runoff outlet is D2, and D2 is smaller than D1. The sidelines of the long-blade runoff outlet and the short-blade runoff outlet are parallel to the centerline of the wheel hub. Arc transition to reduce stress concentration at the intersection, and the diameter of the outer circle of the hub is consistent with the diameter of the outer circle of the runoff outlet.