TWI676734B - Small and micro electric power generation turbocharger - Google Patents

Abstract

The invention provides a small miniature electric power generating turbocharging device, which includes a turbine, a compressor, a motor, two radial bearings and a thrust bearing. The radial bearing is a hybrid dynamic pressure gas radial bearing. The thrust bearing is Hybrid dynamic pressure gas thrust bearing. The rotor is sleeved in the middle of the inner shaft. Two radial bearings are sleeved on the outer shafts at the left and right ends of the rotor. The thrust bearing is sleeved on the outer shaft at the right end and located in On the outer end side of the right-end radial bearing, a turbine and a compressor are provided at both ends of the inner shaft, respectively. The invention can achieve ultra-high-speed stable operation in an air-floating state. Under the requirement of the same power, the volume of an electric power generating turbocharging device can be significantly reduced to achieve miniaturization.

Description

Small miniature electric power generating turbocharger

The invention relates to a turbocharger for electric power generation, in particular to a turbocharger for small and micro electric power generation.

Turbocharging is one of the most important technical measures for strengthening, energy saving and environmental protection of internal combustion engines. The engine turbocharger uses the exhaust gas energy from the engine to drive the turbine and the turbine to drive the coaxial compressor to perform work on the air and send the compressed air into the engine cylinder. Without increasing the volume of the engine cylinder, the air filling coefficient is increased so that The engine injects more fuel to increase the engine's output and combustion, thereby strengthening the engine. However, the turbocharged engine has a "turbine lag" phenomenon during acceleration. Therefore, in order to improve the transient characteristics of the turbocharged engine, an electric-assisted turbocharger system that relies on the motor to drive the turbocharger shaft to improve acceleration performance is used. In recent years, more and more attention has been paid.

At present, there are mainly three layout methods that rely on electric motors to drive the turbocharger rotor to improve its performance: the first is called an electric assisted turbocharger, and its motor is only used as a motor to drive the supercharger rotor; the second is a turbine Generating supercharger, that is, when the engine exhaust gas energy is excessive, the surplus exhaust energy drives the turbine to drive the generator to generate electricity, which improves the exhaust gas energy utilization rate and improves the engine economy; the third type is the electric generating turbocharger, which is to integrate the former two As a whole, the generator / motor of the electric power generation turbocharger is used as a motor under the condition of the turbocharger rotor at low (load) speed; under the condition of high (load) speed, it is used as a generator mode to generate electricity and store energy. The electric power generation turbocharger has both electric assistance and power generation functions, and has obvious advantages. However, when the motor generator rotor and the turbo compressor rotor are integrated and assembled as a whole, the quality of the entire rotor system is increased, and the inertia is increased, which makes the acceleration performance of the rotor worse, and it is difficult to adapt to high-speed conditions. Quality rotors also consume more exhaust energy. This is one of the reasons why the electric turbocharger has not been widely used so far, although the advantages are obvious.

Therefore, in order to solve the above-mentioned problems, an object of the present invention is to provide a small micro electric power generating turbocharging device capable of stable high-speed operation.

The technical means adopted by the present invention to solve the problems of the conventional technology is to provide a small and miniature electric power generating turbocharging device, including: a turbine, a compressor, an electric motor, two radial bearings and a thrust bearing. The turbine includes a turbine, a turbine casing, a turbine deflector, and a turbine deflector casing. The compressor includes a pressure wheel, a compressor casing, and a compressor diffuser. The motor includes a A rotor, a stator, an inner shaft, an outer shaft, and a motor housing; the radial bearing is a hybrid dynamic pressure gas radial bearing, including a bearing outer sleeve, a bearing inner sleeve, and the bearing outer sleeve and A foil-type elastic member between the bearing inner sleeves; the thrust bearing is a hybrid dynamic pressure gas thrust bearing, which includes two side plates and a middle plate sandwiched between the two side plates. The foil-shaped elastic member is provided between each of the side plate and the middle plate; the rotor is sleeved in the middle of the inner shaft, and two radial bearings are respectively sleeved on the outer shaft at the left and right ends of the rotor, The thrust bearing is sleeved on the outer shaft at the right end, At the right end of the radially outer end of the bearing, the turbine and the compressor are provided at both ends of the inner shaft.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The turbine is disposed at the left end of the inner shaft, and the compressor is disposed at the right end of the inner shaft.

According to an embodiment of the present invention, a small and miniature electric power generating turbocharging device is further provided, which further includes a left radial bearing sleeve and a left bearing chamber end cover. The turbine housing is fixedly connected to the left radial bearing sleeve, and the turbine guides the flow. The housing is fixedly connected to the left bearing room end cover, the left bearing room end cover is fixedly connected to the left radial bearing sleeve, and the left radial bearing cover is fixedly connected to the motor housing.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is further provided, which further includes a right radial bearing sleeve and a right bearing chamber end cover. The compressor housing is fixedly connected to the right bearing chamber end cover. The right bearing chamber The end cover is fixedly connected to the right radial bearing sleeve, and the right radial bearing sleeve is fixedly connected to the motor housing.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. A plurality of opening grooves are provided on an inner wall peripheral side of the motor housing, and a plurality of opening grooves are provided on an end surface of the motor housing. The vent hole, the open slot communicates with the vent hole to facilitate the introduction and export of gas. On the one hand, it achieves rapid heat dissipation and exhaust, and on the other hand, it supplies air to the bearing chamber.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. The outer circumferential surface and both end surfaces of the inner sleeve of the bearing have a regular groove-shaped pattern.

In one embodiment of the present invention, a small micro electric power generating turbocharging device is provided. The groove pattern on one end face of the bearing inner sleeve forms a mirror symmetry with the groove pattern on the other end face, and the groove pattern on the outer circumferential surface. The axial contour lines of the pattern and the radial contour lines of the groove pattern on both end surfaces form a one-to-one correspondence and cross each other.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. The axial high line in the grooved pattern on the outer circumferential surface of the bearing inner sleeve and the radial high position in the grooved pattern on both end surfaces are provided. The lines correspond to each other and intersect with each other before the end face is chamfered; the axial median lines in the groove pattern on the outer circumferential surface correspond to the radial median lines in the groove pattern on both end surfaces and fall on the end surface circumference. The front corners meet each other; the axial low-level lines in the grooved pattern on the outer circumferential surface correspond to the radial low-level lines in the grooved pattern on both end surfaces and intersect with each other before the end surface is chamfered.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided, and a wear-resistant coating is provided on a mating surface of a foil-type elastic member matched with an outer circumferential surface of a bearing inner sleeve.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. A matching clearance between the foil-shaped elastic member and a bearing inner sleeve is 0.003 to 0.008 mm.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and both ends of the foil-type elastic member are fixed on an inner circumferential wall of a bearing housing.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The foil-shaped elastic members are multiple and are evenly distributed along the inner circumferential wall of the bearing housing.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. An inner circumferential wall of a bearing housing is provided with a clamping slot for fixing a foil-type elastic member.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and a stop ring is provided at both ends of a bearing housing.

In one embodiment of the present invention, a small micro electric power generating turbocharging device is provided. Both end surfaces of the middle plate are provided with a groove pattern of a regular shape, and the groove pattern on one end face and the groove pattern on the other end face. Form mirror symmetry.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. A groove pattern is also provided on the outer circumferential surface of the middle plate, and the shape of the groove pattern on the outer circumferential surface and the groove pattern on both end surfaces are provided. The shapes of the patterns are the same, and the axial contour lines of the groove pattern on the outer circumferential surface and the radial contour lines of the groove pattern on both end surfaces form a one-to-one correspondence and cross each other.

In one embodiment of the present invention, a small micro electric power generating turbocharging device is provided. The axial high-level lines in the groove pattern on the outer circumferential surface of the middle plate and the radial high-level lines in the groove pattern on both end surfaces are both provided. Correspond to each other and meet each other before the chamfer on the end face; the axial median line in the groove pattern on the outer circumferential surface corresponds to the radial median line in the groove pattern on both end faces and before the chamfer on the end surface. Intersecting each other; the axial low-level lines in the grooved pattern on the outer circumferential surface correspond to the radial low-level lines in the grooved pattern on both end surfaces and intersect each other before the end surface is chamfered.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The foil-type elastic member fixed on one of the side plates is formed with the foil-type elastic member fixed on the other side plate. Mirror symmetry.

In one embodiment of the present invention, a small micro electric power generating turbocharging device is provided, and a wear-resistant coating is provided on a mating surface of a foil-type elastic member matched with a middle plate.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and the matching gap between the foil-shaped elastic member and the center plate is 0.003 to 0.008 mm.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. At least one end of the foil-type elastic member is fixed on an inner end surface of a corresponding side plate.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. There are a plurality of foil-type elastic members on each side plate, and they are evenly distributed along the inner end surface of the side plate.

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. A foil-type elastic member fixed on one side plate and a foil-type elastic member fixed on the other side plate are mirror-symmetrical.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and an inner surface of a side plate is provided with a clamping slot for fixing a foil-type elastic member.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The foil-type elastic member is composed of a wave foil and a flat foil, and the curved convex top of the wave foil is attached to the flat foil. .

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The foil-type elastic member is composed of a wave foil and a flat foil, and the bottom edge of the wave foil transition between the wave foil and the flat foil is attached to the flat foil. Together.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The foil-type elastic member is composed of two flat foils.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and the groove patterns are all in the shape of an impeller.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided, and the foil-type elastic member is preferably subjected to a surface heat treatment.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The rotor includes a rotor base, a magnetic steel, and a magnetic steel protective sleeve. The rotor base is sleeved on the inner shaft. A steel sleeve is disposed at a center portion of the rotor base, and the magnetic steel protective sleeve is sleeved on the magnetic steel.

According to an embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The stator includes an iron core and a winding, and the iron core is fixed on the inner wall of the motor casing located above the rotor. The winding is disposed on the core.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The iron core includes a plurality of stator laminations formed by stacking a plurality of punches on top of each other, and one end pressing plates fixed on both sides of the stator lamination. .

According to an embodiment of the present invention, a small micro electric power generating turbocharging device is provided. The punching sheet has a circular ring shape, and a plurality of cup-shaped perforations are arranged at an annular portion. The cup-shaped perforated cup mouth portion is closed. The bottom of the cup feet is open.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. The winding is a three-phase star connection. The center line is not led out, and only three terminals A, B and C are led out.

In one embodiment of the present invention, a small miniature electric power generating turbocharging device is provided. Each phase winding is two coils, and each coil is continuously wound by an enameled copper wire.

Compared with the prior art, the present invention has the following beneficial effects: Because the electric power generating turbocharging device provided by the present invention uses gas as a bearing lubricant, it not only has no pollution, low friction loss, long use time, and is applicable. It has many advantages such as wide range, energy saving and environmental protection, and adopts the structure, which has good heat dissipation effect and can guarantee stable operation for a long time. In particular, the air bearing of the structure can achieve ultra-high speed and stable operation in the air-floating state. The test can reach the limit speed of 100,000 ～ 450,000rpm). Therefore, under the requirement of the same power, the invention can significantly reduce the volume of the electric power generation turbocharger device to achieve miniaturization, and has the advantages of small space occupation and convenient use. It has important value to promote the development of miniaturized high-tech, and it has significant progress compared with the previous technology.

The specific embodiments used in the present invention will be further explained by the following embodiments and accompanying drawings.

Hereinafter, embodiments of the present invention will be described with reference to FIGS. 1 to 28. This description is not intended to limit the embodiment of the present invention, but is an example of the embodiment of the present invention.

First embodiment

As shown in FIG. 1: a small miniature electric power generating turbocharging device provided in this embodiment includes a turbine 1, a compressor 2, a motor 3, two radial bearings 4 and a thrust bearing 5, and the turbine 1 The compressor 2 includes a turbine 11, a turbine casing 12, a turbine deflector 13, and a turbine deflector casing 14. The compressor 2 includes a pressure wheel 21, a compressor casing 22, and a compressor diffuser 23. The motor 3 includes a rotor 31, a stator 32, an inner shaft 33, an outer shaft 34, and a motor housing 35; the radial bearing 4 is a hybrid dynamic pressure gas radial bearing, including a bearing outer sleeve 41, a bearing inner sleeve 42 and A foil-type elastic member 45 between a bearing outer sleeve 41 and an inner sleeve 42; the thrust bearing 5 is a hybrid dynamic pressure gas thrust bearing, and includes two side plates 51 and a middle plate sandwiched between the two side plates 52, a foil-type elastic member 53 is provided between each side disk 51 and the middle disk 52; the rotor 31 is sleeved in the middle of the inner shaft 33, and two radial bearings 4 are sleeved on the left, On the outer shaft 34 on the right end, the thrust bearing 5 is sleeved on the outer shaft 34 on the right end and is located on the outer end side of the right end radial bearing 4b, Said turbine 1 and the compressor 2 are provided at both ends of the inner shaft 33 (left end in Example 1 is provided in the inner of the turbine shaft 33 of the present embodiment, the right end of the compressor 2 provided in the inner shaft 33).

The small miniature electric power generating turbocharging device further includes a left radial bearing sleeve 6a, a right radial bearing sleeve 6b, a left bearing chamber end cover 7a, and a right bearing chamber end cover 7b. The turbine casing 12 and the left radial direction The bearing sleeve 6a is fixedly connected, the turbine deflector housing 14 is fixedly connected to the left bearing chamber end cover 7a, the left bearing room end cover 7a is fixedly connected to the left radial bearing sleeve 6a, and the left radial bearing sleeve 6a is connected to the motor housing 35 is fixedly connected, the compressor housing 22 is fixedly connected to the right bearing housing end cover 7b, the right bearing room end cover 7b is fixedly connected to the right radial bearing housing 6b, and the right radial bearing housing 6b is fixedly connected to the motor housing 35.

With reference to FIGS. 2 to 5, the outer circumferential surface and the left and right end surfaces of the bearing inner sleeve 42 each have a regular groove pattern 43 (such as 431, 432, and 433 in the figure. In this embodiment, (The groove patterns are all in the shape of an impeller), and the groove pattern 432 on the left end face and the groove pattern 433 on the right end face are mirror-symmetrical. The axial contours of the grooved pattern 431 on the outer circumferential surface of the bearing inner sleeve 42 and the radial contours of the grooved patterns (432 and 433) on the left and right end surfaces form a one-to-one correspondence and intersect with each other, that is, the outer The axial high-level lines 4311 in the grooved pattern 431 on the circumferential surface correspond to the radial high-level lines (4321 and 4331) in the grooved patterns (432 and 433) on the left and right end faces, and before the end face circumferential chamfer Intersecting each other; the axial median line 4312 in the grooved pattern 431 on the outer circumferential surface corresponds to the radial median lines (4322 and 4332) in the grooved pattern (432 and 433) on the left and right end faces, and Intersect each other before chamfering on the end face; the axial low line 4313 in the groove pattern 431 on the outer circumferential surface and the radial low line (4323 and 4333) in the groove pattern (432 and 433) on the left and right end faces are both Correspond to each other and meet each other before chamfering the circumference of the end face.

By making the outer circumferential surface and both end surfaces of the bearing inner sleeve 42 with a regular groove pattern (431, 432, and 433), the groove pattern 432 on the left end face and the groove pattern 433 on the right end face form a mirror symmetry and an outer shape. The axial contour of the grooved pattern 431 on the circumferential surface and the radial contours of the grooved patterns (432 and 433) on the left and right end surfaces form a one-to-one correspondence and intersect with each other, which can ensure the shape of the impeller in both ends. The pressurized gas generated by the pattern (432 and 433) is continuously transmitted from the shaft center in the radial direction to the groove channel formed by the groove pattern 431 on the outer circumferential surface, so as to form a gas film required to support the bearing at higher speeds. The gas film is used as a lubricant of the dynamic pressure gas radial bearing, so it is beneficial to achieve the high-speed and stable operation of the hybrid dynamic pressure gas radial bearing 4 in an air floating state.

In addition, when retaining rings 44 are respectively provided at both ends of the bearing housing 41, a self-sealing effect can be generated between both end surfaces of the bearing inner sleeve 42 and the retaining rings 44 driven by a high-speed rotary shaft, so that the groove pattern is continuous. The generated dynamic pressure gas can be perfectly sealed and stored in the entire fitting gap of the bearing, which fully guarantees the lubrication needs of the high-speed running dynamic pressure gas radial bearing.

With reference to FIGS. 6 and 7, the foil-shaped elastic member 45 is disposed between the bearing outer sleeve 41 and the inner sleeve 42, and is composed of a wave foil 451 and a flat foil 452. The top of the riser 4511 is in contact with the flat foil 452, and the bottom 4512 between the wave arches of the wave foil 451 is in contact with the inner circumferential wall of the bearing housing 41. The inner circumferential wall of the bearing housing 41 is provided with locking grooves 411 for fixing both ends of the foil-shaped elastic member 45. The number of the grooves 411 corresponds to the number of the foil-shaped elastic members 45 and is uniform along the inner circumferential wall of the bearing housing 41. distributed.

As shown in FIG. 8: the mating surface of the foil-type elastic member 45 (that is, the inner surface of the flat foil 452 constituting the foil-type elastic member 45) that is matched with the outer circumferential surface of the bearing inner sleeve 42 is provided with a wear-resistant coating. Layer 453 to further reduce the abrasion of the foil-shaped elastic member 45 by the high-speed running bearing inner sleeve 42 and extend the service life of the bearing.

The matching clearance between the foil-shaped elastic member 45 and the bearing inner sleeve 42 is preferably 0.003 to 0.008 mm to further ensure the reliability and stability of the high-speed operation of the bearing.

As shown in FIG. 9: A hybrid dynamic pressure gas thrust bearing 5 provided in this embodiment includes: two side disks 51, a middle disk 52 is sandwiched between the two side disks 51, and each side disk A foil-type elastic member 53 is provided between 51 and the middle plate 52; a left end surface of the middle plate 52 is provided with a regular groove pattern 521, and a right end surface is provided with a regular groove pattern 522.

With reference to Figures 10A and 10B, it can be seen that a mirror symmetry is formed between the groove pattern 521 on the left end face and the groove pattern 522 on the right end face of the middle plate 52, and the radial contour of the groove pattern 521 on the left end face and the right end The radial contour lines of the groove pattern 522 of the surface form a one-to-one correspondence.

The shapes of the groove patterns 521 and 522 are the same, and in this embodiment, they are both impeller shapes.

By further combining FIG. 11A and FIG. 11B, it can be seen that the foil-shaped elastic member 53 is fixed to the inner end surface of the corresponding side plate 51 (for example, the left-side disk 511 and the 11B of the foil-shaped elastic member 53a are fixed as shown in FIG. 11A). The right side plate 512 of the foil type elastic member 53b shown in the figure is fixed, and the foil type elastic member 53a fixed on the left side plate 511 and the foil type elastic member 53b fixed on the right side plate 512 are mirror-symmetrical. There can be multiple foil-type elastic members on each side plate (four are shown in the figure), and they are evenly distributed along the inner end surface of the side plate.

By providing a foil-shaped elastic member 53 between the side plate 51 and the center plate 52, regular-shaped groove patterns (521 and 522) are provided on the left and right end surfaces of the center plate 52, and the groove pattern 521 and the right end of the left end surface are formed. The groove pattern 522 on the surface forms a mirror symmetry, so that it has both the rigid characteristics of the high limiting speed of the grooved dynamic pressure gas thrust bearing and the high impact resistance and load capacity of the foil type dynamic pressure gas thrust bearing. Hybrid dynamic pressure gas thrust bearing with flexible characteristics; because the foil-shaped elastic member 53 and the middle plate 52 form a wedge-shaped space, when the middle plate 52 rotates, the gas is driven by its own viscosity and is compressed into the wedge-shaped space , So that the axial dynamic pressure can be significantly enhanced. Compared with the simple foil type dynamic pressure gas thrust bearing of the prior art, it can have a limit speed that doubles under the same load; at the same time, due to the addition of foil-type elastic members 53. Under its elasticity, it can also significantly improve the bearing's load capacity, impact resistance, and ability to suppress shaft eddy. Compared with the simple groove dynamic pressure gas thrust bearing of the prior art, It has multiple impact resistance and load capacity at the same speed.

In order to further reduce the wear of the foil-shaped elastic member 53 at the high-speed running of the middle plate 52 to extend the service life of the bearing, it is best to provide a wear-resistant coating on the mating surface of the foil-shaped elastic member 53 that matches the middle plate 52 (the figure Not shown).

As shown in FIG. 12 and FIG. 13: The foil-type elastic members 45/53 described in this embodiment are each composed of a wave foil 451/531 and a flat foil 452/532, and the arc-shaped protrusions of the wave foil 451/531 The top of the 4511/5311 fits with the flat foil 452/532.

Second embodiment

As shown in FIG. 14, the foil-type elastic member 45 according to this embodiment is composed of a wave foil 451 and a flat foil 452, and the top end of the arc-shaped protrusion 4511 of the wave foil 451 is in contact with the inner circumferential wall of the bearing housing 41. The bottom 4512 between the wave arches of the wave foil 451 and the flat foil 452 fit together.

FIG. 15 is a schematic diagram showing the structure of the wave foil 451.

Third embodiment

As shown in FIG. 16, the foil-type elastic member 45 according to this embodiment is composed of two flat foils 452.

Fourth embodiment

With reference to Figures 17A, 17B, and 18 to 22, it can be seen that the hybrid dynamic pressure gas thrust bearing provided in this embodiment is different from the first embodiment only in that:

A groove pattern 523 is also provided on the outer circumferential surface of the middle plate 52, and the shape of the groove pattern 523 on the outer circumferential surface is the same as that of the groove patterns (521 and 522) on the left and right end faces (in this embodiment) (Both impeller shapes), and the axial contour lines of the groove pattern 523 on the outer circumferential surface and the radial contour lines of the groove patterns (521 and 522) on the left and right end faces form a one-to-one correspondence and intersect with each other; namely:

The axial high-line 5231 in the groove pattern 523 on the outer circumferential surface and the radial high-line 5211 in the groove pattern 521 on the left end surface correspond to each other and intersect with each other before the end surface is chamfered; The axial median line 5232 in the pattern 523 corresponds to the radial median line 5212 in the grooved pattern 521 on the left end face and intersects with each other before the end face circumferential chamfer; The axial low-level lines 5233 correspond to the radial low-level lines 5213 in the groove pattern 521 on the left end face and intersect with each other before the end face circumferential chamfer (as shown in FIG. 20);

The axial high line 5231 in the groove pattern 523 on the outer circumferential surface corresponds to the radial high line 5221 in the groove pattern 522 on the right end face and intersects with each other before the end face circumferential chamfer; the groove type on the outer circumferential surface The axial median line 5232 in the pattern 523 corresponds to the radial median line 5222 in the grooved pattern 522 on the right end face and intersects with each other before the end face is chamfered. The axial low-level lines 5233 correspond to the radial low-level lines 5223 in the groove pattern 522 on the right end face and intersect with each other before the end face circumferential chamfer (as shown in FIG. 22).

When a groove pattern is also provided on the outer circumferential surface of the middle plate 52, and the shape of the groove pattern 523 on the outer circumferential surface is the same as that of the groove patterns (521 and 522) on the left and right end faces, and the outer circumference When the axial contour lines of the groove pattern 523 on the surface and the radial contour lines of the groove patterns (521 and 522) on the left and right end faces are formed in a one-to-one correspondence with each other, the groove patterns ( 521 and 522) The pressurized gas generated from the axis is continuously conveyed in the groove channel formed by the groove pattern 523 on the outer circumferential surface in the radial direction, so that the gas film required to support the high-speed running bearing is stronger, and the gas The film is used as a lubricant for the dynamic pressure gas thrust bearing, so it can further ensure the high-speed and stable operation of the hybrid dynamic pressure gas thrust bearing in an air-floating state, and further guarantee the high limit speed of the motor.

The inner surface of the side plate 51 is provided with a clamping groove 513 (as shown in FIG. 18) for fixing the foil-type elastic member 53.

The matching clearance between the foil-shaped elastic member 53 and the middle plate 52 is preferably 0.003 to 0.008 mm, so as to further ensure the reliability and stability of the high-speed operation of the bearing.

In order to better meet the performance requirements for high-speed operation, the foil-type elastic member 53 is preferably subjected to a surface heat treatment.

It should also be noted that the composition structure of the foil-type elastic member 53 according to the present invention is not limited to that described in the above embodiment, and can also be composed of a wave foil and a flat foil. The flat foils are fitted together, or two flat foils are directly used, or other existing structures are used.

Fifth Embodiment

As shown in Figures 1 and 23, the rotor 31 includes a rotor base 311, a magnetic steel 312, and a magnetic steel protective sleeve 313. The rotor base 311 is sleeved on the inner shaft 33, and the magnetic steel 312 is sleeved. At the center of the rotor base 311, the magnetic steel protective sleeve 313 is sleeved on the magnetic steel 312 to better meet ultra-high speed rotation.

Sixth embodiment

As shown in FIG. 1 and FIG. 24, the stator 32 includes an iron core 321 and a winding 322. The iron core 321 is fixed on an inner wall of a motor casing 35 located above the rotor 31, and the winding 322 is provided. On the iron core 321, the iron core 321 includes a stator lamination piece 3212 formed by a plurality of punching pieces 3211 stacked on top of each other, and end pressure plates 3213 fixed on both sides of the stator lamination piece 3212.

As shown in FIG. 25, the punching piece 3211 has a circular ring shape, and a plurality of cup-shaped perforations 32111 are provided at intervals in the ring portion. The cup mouth portion 32111a of the perforation 32111 is closed, and the bottom of the cup leg 32111b is open.

As shown in Figure 26: the windings 322 are connected by three-phase star, and the center line is not drawn, only three ends of A, B, and C are drawn out; each winding is two coils, and each coil is made of enameled copper The wire is continuously wound.

Seventh embodiment

With reference to FIGS. 27 and 28, a plurality of opening slots 351 are provided on the inner wall peripheral side of the motor casing 35, and a plurality of vent holes 352 are provided on an end surface of the motor casing. The air holes 352 communicate with each other to facilitate the introduction and export of gas. On the one hand, it realizes rapid heat dissipation and exhaustion, and on the other hand, it supplies air in the bearing chamber.

After testing, the bearing provided by the present invention can reach a limit speed of 100,000 to 450,000 rpm in the air-floating state. Therefore, under the same power requirement, the present invention can significantly reduce the volume of the electric power generating turbocharging device to achieve miniaturization. It has important value to promote the development of miniaturized high technology.

Finally, it is necessary to point out that: the above content is only used to further describe the technical solution of the present invention in detail, and cannot be understood as a limitation on the protection scope of the present invention. The essential improvements and adjustments belong to the protection scope of the present invention.

The above descriptions and descriptions are merely illustrations of the preferred embodiments of the present invention. Those with ordinary knowledge of this technology may make other modifications based on the scope of the patent application defined below and the above description, but these modifications should still be made. It is the spirit of the present invention and is within the scope of the present invention.

1‧‧‧ Turbine

11‧‧‧ Turbine

12‧‧‧Turbine casing

13‧‧‧Turbine deflector

14‧‧‧Turbine deflector housing

2‧‧‧compressor

21‧‧‧Press roller

22‧‧‧compressor housing

23‧‧‧Compressor diffuser

3‧‧‧motor

31‧‧‧rotor

311‧‧‧rotor base

312‧‧‧Magnetic steel

313‧‧‧Magnetic steel protective sleeve

32‧‧‧ stator

321‧‧‧ iron core

3211‧‧‧ Punch

32111‧‧‧cup-shaped perforation

32111a‧‧‧ Mouth

32111b‧‧‧cup feet

3212‧‧‧Stator lamination

3213‧‧‧End plate

322‧‧‧winding

33‧‧‧Inner shaft

34‧‧‧Outer shaft

35‧‧‧Motor housing

351‧‧‧open slot

352‧‧‧Vent

4‧‧‧ Hybrid dynamic pressure gas radial bearing

41‧‧‧bearing jacket

411‧‧‧card slot

42‧‧‧bearing inner sleeve

43‧‧‧Slot pattern

431‧‧‧ Groove pattern on the outer circumferential surface

4311‧‧‧Axial high line

4312‧‧‧Axial median line

4313‧‧‧Axial low line

432‧‧‧Groove pattern on the left end

4321‧‧‧Radial High Line

4322‧‧‧Radial median line

4323‧‧‧Radial low line

433‧‧‧Groove pattern on right end

4331‧‧‧Radial high line

4332‧‧‧Radial median line

4333‧‧‧Radial low line

44‧‧‧ Stop ring

45‧‧‧Foil Elastic

451‧‧‧wave foil

4511‧‧‧arc convex

4512‧‧‧ Wave bottom transition

452‧‧‧Foil

453‧‧‧Abrasion resistant coating

4a‧‧‧left radial bearing

4b‧‧‧right radial bearing

5‧‧‧ Hybrid dynamic pressure gas thrust bearing

51‧‧‧Side plate

511‧‧‧Left plate

512‧‧‧Right disk

513‧‧‧Card slot

52‧‧‧ Midday

521‧‧‧Groove pattern on the left end

5211‧‧‧Radial High Line

5212‧‧‧ Radial Median

5213‧‧‧Radial low line

522‧‧‧Groove pattern on right end

5221‧‧‧Radial high line

5222‧‧‧Radial median

5223‧‧‧Radial low line

523‧‧‧ Groove pattern on the outer circumferential surface

5231‧‧‧Axial high line

5232‧‧‧Axial median line

5233‧‧‧Axial low line

53‧‧‧Foil Elastic

531‧‧‧wave foil

5311‧‧‧arc convex

532‧‧‧flat foil

53a‧‧‧Foil type elastic member fixed on the left side plate

53b‧‧‧Foil-shaped elastic member fixed on the right side plate

6a‧‧‧left radial bearing sleeve

6b‧‧‧Right radial bearing sleeve

7a‧‧‧Left bearing housing end cap

7b‧‧‧Rear bearing housing end cover

FIG. 1 is a schematic cross-sectional structure diagram of a small micro electric power generating turbocharging device according to a first embodiment of the present invention. FIG. 2 is a schematic left-view three-dimensional structure diagram showing a partial division of a hybrid dynamic pressure gas radial bearing according to an embodiment of the present invention. FIG. 3 is a partially enlarged view showing A in FIG. 2. FIG. 4 is a schematic diagram of a three-dimensional structure of the right side of a partially divided hybrid dynamic pressure gas radial bearing according to an embodiment of the present invention. FIG. 5 is a partial enlarged view showing B in FIG. 4. FIG. 6 is a schematic cross-sectional structure view of a hybrid dynamic pressure gas radial bearing according to an embodiment of the present invention. Fig. 7 is a partial enlarged view showing C in Fig. 4. FIG. 8 is a partial enlarged view showing D in FIG. 4. FIG. 9 is a schematic cross-sectional structure view of a hybrid dynamic pressure gas thrust bearing according to an embodiment of the present invention. FIG. 10A is a left side view showing a center plate according to an embodiment of the present invention. FIG. 10B is a right side view showing a center plate according to an embodiment of the present invention. Fig. 11A is a right side view showing a left side plate to which a foil-type elastic member is fixed according to an embodiment of the present invention. FIG. 11B is a left side view showing a right side plate to which a foil-type elastic member is fixed according to an embodiment of the present invention. FIG. 12 is a schematic cross-sectional structure view of a foil-type elastic member according to an embodiment of the present invention. FIG. 13 is a schematic diagram showing a three-dimensional structure of a foil-type elastic member according to an embodiment of the present invention. FIG. 14 is a schematic sectional view showing a hybrid dynamic pressure gas radial bearing according to a second embodiment of the present invention. FIG. 15 is a schematic diagram showing the structure of the wave foil in FIG. 14. FIG. 16 is a schematic sectional view showing a hybrid dynamic pressure gas radial bearing according to a third embodiment of the present invention. FIG. 17A is a left-view perspective structural view showing a hybrid dynamic pressure gas thrust bearing according to a fourth embodiment of the present invention. FIG. 17B is a right-side perspective structural view showing a hybrid dynamic pressure gas thrust bearing according to an embodiment of the present invention. FIG. 18 is a schematic diagram showing a partially divided three-dimensional structure of a hybrid dynamic pressure gas thrust bearing according to an embodiment of the present invention. FIG. 19 is a schematic left-view three-dimensional structure diagram of a center plate according to an embodiment of the present invention. FIG. 20 is a partial enlarged view showing E in FIG. 19. FIG. 21 is a schematic diagram showing a right-side three-dimensional structure of a center plate according to an embodiment of the present invention. Fig. 22 is a partially enlarged view showing F in Fig. 21; Fig. 23 is a schematic diagram showing a rotor structure according to a fifth embodiment of the present invention. FIG. 24 is a schematic diagram showing a core structure according to a sixth embodiment of the present invention. FIG. 25 is a schematic diagram showing a structure of a punch according to an embodiment of the present invention. FIG. 26 is a schematic diagram showing a winding structure according to an embodiment of the present invention. FIG. 27 is a schematic diagram showing a three-dimensional structure of a motor case according to a seventh embodiment of the present invention. FIG. 28 is a partially enlarged view showing G in FIG. 27.

Claims (18)

A small miniature electric power generating turbocharging device includes: a turbine, a compressor, a motor, two radial bearings and a thrust bearing. The turbine includes a turbine, a turbine casing, and a turbine guide. And a turbine deflector casing, the compressor includes a pressure wheel, a compressor casing, and a compressor diffuser, and the motor includes a rotor, a stator, an inner shaft, and a motor casing The rotor is sleeved in the middle of the inner shaft, and the turbine and the compressor are respectively provided at both ends of the inner shaft; characterized in that the motor further includes an outer shaft, and two radial bearings are sleeved respectively The thrust bearings are located on the outer shafts on the left and right ends of the rotor, and the thrust bearings are sleeved on the outer shafts on the right end and on the outer end side of the radial bearings on the right end; the radial bearings are a hybrid dynamic pressure gas radial bearing, including A bearing outer sleeve, a bearing inner sleeve, and a foil-type elastic member provided between the bearing outer sleeve and the bearing inner sleeve; the thrust bearing is a hybrid dynamic pressure gas thrust bearing, and includes two sides Plate and one sandwiched between two side plates Disc, between each side of the disc and the disc has a foil-type elastic member; circumferential side of the inner wall of the motor housing defines a plurality of open slots in the end face of the motor housing defines a plurality of vent holes. The small micro electric power generating turbocharging device according to claim 1, wherein the turbine is disposed at a left end of the inner shaft, and the compressor is disposed at a right end of the inner shaft. The small micro-electric power generation turbocharging device according to claim 1, wherein the outer circumferential surface and both end surfaces of the bearing inner sleeve have a regular-shaped groove pattern. The small micro electric power generating turbocharging device according to claim 3, wherein the groove pattern on one end surface of the bearing inner sleeve forms a mirror symmetry with the groove pattern on the other end surface, and the groove pattern on the outer circumferential surface The axial contour lines and the radial contour lines of the groove pattern on both end surfaces form a one-to-one correspondence and intersect with each other. The small micro electric power generating turbocharging device according to claim 4, wherein the axial high-level lines in the grooved pattern on the outer circumferential surface of the bearing inner sleeve and the radial high-level lines in the grooved pattern on both end surfaces are both Correspond to each other and meet each other before the chamfer on the end face; the axial median line in the groove pattern on the outer circumferential surface corresponds to the radial median line in the groove pattern on both end faces and before the chamfer on the end surface. Intersecting each other; the axial low-level lines in the grooved pattern on the outer circumferential surface correspond to the radial low-level lines in the grooved pattern on both end surfaces and intersect each other before the end surface is chamfered. The small micro electric power generating turbocharging device according to claim 1, wherein both end surfaces of the middle plate are provided with a groove pattern of a regular shape, and the groove pattern on one end surface and the groove pattern on the other end surface form a mirror image. symmetry. The small micro electric power generating turbocharging device according to claim 6, wherein a groove pattern is also provided on the outer circumferential surface of the middle plate, and the shape of the groove pattern on the outer circumferential surface is different from that of the groove patterns on both end surfaces. The axial contour lines of the groove pattern of the same shape and the outer circumferential surface and the radial contour lines of the groove pattern of the both end surfaces form a one-to-one correspondence and intersect with each other. The small micro electric power generating turbocharging device according to claim 7, wherein the axial high-level lines in the grooved pattern on the outer circumferential surface of the middle plate correspond to the radial high-level lines in the grooved pattern on both end surfaces and The end faces circumferentially intersect each other before chamfering; the axial median lines in the groove pattern on the outer circumferential surface correspond to the radial neutral lines in the grooved patterns on both end surfaces and intersect each other before the end face circumferential chamfering; The axial low-level lines in the grooved pattern on the circumferential surface correspond to the radial low-level lines in the grooved pattern on both end surfaces and intersect with each other before the end surface is chamfered. The small micro electric power generating turbocharging device according to claim 1, wherein the foil-type elastic member fixed on one side plate and the foil-type elastic member fixed on the other side plate form a mirror symmetry. The small miniature electric power generating turbocharging device according to claim 1 or claim 9, wherein the foil-type elastic member is composed of a wave foil and a flat foil, and the curved convex top of the wave foil is in phase with the flat foil. fit. The small micro electric power generating turbocharging device according to claim 1 or claim 9, wherein the foil-type elastic member is composed of a wave foil and a flat foil, and the bottom edge of the wave foil transition between the wave foil and the flat foil Phase fit. The small micro electric power generating turbocharging device according to claim 1 or claim 9, wherein the foil-type elastic member is composed of two flat foils. The small micro electric power generating turbocharging device according to claim 1, wherein the rotor includes a rotor base, a magnetic steel, and a magnetic steel protective sleeve, the rotor base is sleeved on the inner shaft, and the magnetic steel sleeve The magnetic steel protective sleeve is sleeved on the magnetic steel. The small miniature electric power generating turbocharging device according to claim 1, wherein the stator includes an iron core and a winding, and the iron core is fixed on the inner wall of the motor casing located above the rotor, and the winding Set on this core. The small micro-electric power generating turbocharging device according to claim 14, wherein the iron core includes a plurality of stator laminations formed by stacking a plurality of punches on top of each other, and one end pressing plates fixed on both sides of the stator lamination. The small micro-electric power generating turbocharging device according to claim 15, wherein the punching sheet has a circular ring shape, and a plurality of cup-shaped perforations are arranged at an annular portion, and the cup-shaped perforated cup mouth portion is closed, and the cup The bottom of the foot is open. The small miniature electric power generating turbocharging device according to claim 14, wherein the winding is a three-phase star connection, and the center line is not led out, and only three terminals A, B, and C are led out. The small micro electric power generating turbocharging device according to claim 17, wherein each phase winding is two coils, and each coil is continuously wound by an enameled copper wire.