TWI676735B - Small micro gas turbine generator - Google Patents

Abstract

The invention discloses a small miniature gas turbine generator, which comprises a turbine, a compressor, a motor, two radial bearings, a thrust bearing and a combustion chamber. The radial bearing is a hybrid dynamic pressure gas radial bearing The thrust bearing is a 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 bearing sleeve is set on the outer shaft on the right end and is located on the outer end side of the radial bearing on the right end. The invention can realize ultra-high speed and stable operation in the air-floating state. For the same power requirements, the volume of the gas turbine generator can be increased. Significant reduction in miniaturization.

Description

Small miniature gas turbine generator

The invention relates to a small miniature gas turbine generator and belongs to the technical field of high precision machinery.

A gas turbine generator is an internal combustion power machine that uses a continuously flowing gas as a working substance to drive the impeller to rotate at high speed and converts the energy of fuel into useful work. It is a rotary impeller heat engine. It consists of a gas turbine and a generator. Used in oilfields, power plants, telecommunication buildings, high-rise buildings, hotels, living communities, shopping malls, hospitals, military, conference centers, remote areas, islands and other important places, as a backup power source and as a necessary mobile power source for emergencies, field operations, etc. , Can also be used as ship power, power peak shaving.

With the global demand for energy and power, miniature gas turbine generators using air bearings have small size, light weight, strong fuel adaptability, low fuel consumption, low noise, low vibration, low pollution emissions, and maintenance. A series of advanced technical features such as low cost and no need for water cooling have begun to be applied in military and civil transportation (hybrid electric vehicles) and land and sea defense, and have received great attention and attention from the United States, Russia and other countries. However, the existing air bearings mainly have the following problems: complicated structure, not suitable for industrialization; poor reliability, easy to instability or even stuck at high speed operation; heat generated at high speed operation cannot be efficiently exported, and can not work continuously for a long time; larger volume , Can not meet today's miniaturization development requirements.

In view of the above problems existing in the conventional technology, an object of the present invention is to provide a small micro gas turbine generator that can stably operate.

To achieve the above objective, the technical solution adopted by the present invention is as follows:

A small miniature gas turbine generator comprising a turbine, a compressor, a motor, two radial bearings, a thrust bearing and a combustion chamber. The turbine includes a turbine, a turbine deflector and a turbine deflector housing. The compressor includes a compressor wheel, a compressor housing, and a compressor diffuser, and the motor includes a rotor, a stator, an inner shaft, an outer shaft, and a motor housing; the radial bearing is a hybrid type A dynamic pressure gas radial bearing includes a bearing outer sleeve, a bearing inner sleeve, and a foil-type elastic member provided between the bearing outer sleeve and the inner sleeve; the thrust bearing is a hybrid dynamic pressure gas thrust bearing including two side disks And a middle plate sandwiched between two side plates, and a foil-type elastic member is provided between each side plate and the middle plate; the rotor is sleeved in the middle of the inner shaft, and 2 radial bearings are sleeved in The thrust bearings are located on the outer shafts at the left and right ends of the rotor, and the thrust bearings are sleeved on the outer shafts at the right ends, and are located on the outer end side of the radial bearings at the right ends.

In one embodiment, the turbine and the compressor are respectively disposed at both ends of the inner shaft, and the combustion chamber is disposed at the turbine end.

In another embodiment, the combustion chamber is disposed at the middle of the inner shaft, and the turbine and the compressor are disposed at both ends of the inner shaft or back-to-back at one end of the inner shaft, respectively.

As a further embodiment, the small miniature gas turbine generator further includes a left radial bearing sleeve and a left bearing chamber end cover, the turbine deflector housing is fixedly connected to the left bearing chamber end cover, and the left bearing chamber end cover and the The left radial bearing sleeve is fixedly connected, the casing of the combustion chamber is fixedly connected with the left radial bearing sleeve, and the left radial bearing sleeve is fixedly connected with the motor housing.

As a further embodiment, the small miniature gas turbine generator 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, and the right bearing chamber end cover and the right diameter It is fixedly connected to the bearing sleeve, and the right radial bearing sleeve is fixedly connected to the motor casing.

As a preferred solution, a surface of the inner shaft is provided with a heat dissipation spiral groove to facilitate heat dissipation of the rotating shaft and the bearing chamber.

As a preferred solution, a plurality of opening slots are provided on the inner wall peripheral side of the motor casing, and a plurality of vent holes are provided on an end surface of the motor casing, and the opening slots are communicated with the vent holes 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 realizes air supply to the bearing chamber.

As a preferred solution, both the outer circumferential surface and both end surfaces of the bearing inner sleeve have a grooved pattern with a regular shape.

As a further preferred solution, 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 axial contour of the groove pattern on the outer circumferential surface and the groove pattern on both end faces are The radial contour lines all form a one-to-one correspondence and intersect with each other.

As a further preferred solution, the axial high-level lines in the grooved pattern on the outer circumferential surface of the bearing inner sleeve correspond to the radial high-level lines in the grooved pattern on both end surfaces and intersect each other before the end face circumferential chamfer. ; The axial median line in the grooved pattern on the outer circumferential surface and the radial median line in the grooved pattern on both end surfaces correspond and intersect with each other before the end face circumferential chamfer; the grooved pattern on the outer circumferential surface The axial low-level lines in the middle correspond to the radial low-level lines in the groove pattern on the two end surfaces, and they intersect with each other before the end face circumferential chamfer.

As a further preferred solution, a wear-resistant coating is provided on a mating surface of the foil-type elastic member matching the outer circumferential surface of the bearing inner sleeve.

As a further preferred solution, a matching clearance between the foil-shaped elastic member and the bearing inner sleeve is 0.003 to 0.008 mm.

As a further preferred solution, both ends of the foil-type elastic member are fixed on the inner circumferential wall of the bearing housing.

As a further preferred solution, there are a plurality of foil-type elastic members, and they are evenly distributed along the inner circumferential wall of the bearing housing.

As a further preferred solution, a clamping groove for fixing the foil-type elastic member is provided on an inner circumferential wall of the bearing housing.

As a further preferred solution, stop rings are provided at both ends of the bearing housing.

As a preferred solution, both end surfaces of the middle plate are provided with a groove pattern with a regular shape, and the groove pattern on one end face and the groove pattern on the other end face are mirror-symmetrical.

As a preferred solution, 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 the same as the shape of the groove pattern on both end faces, and the shaft of the groove pattern on the outer circumferential surface The contour lines form a one-to-one correspondence with the radial contour lines of the groove pattern on both end surfaces and intersect with each other.

As a further preferred solution, the axial high-level lines in the grooved pattern on the outer circumferential surface of the center plate correspond to the radial high-level lines in the grooved pattern on both end surfaces and intersect with each other before the end face circumferential chamfer; the outer circumferential surface The axial median line in the grooved pattern of the corresponding to the radial median line in the grooved pattern on both end faces and intersects each other before the end face circumferential chamfer; the axial direction in the grooved pattern on the outer circumferential surface The low-level lines correspond to the radial low-level lines in the groove pattern on both end surfaces, and intersect with each other before the end faces are chamfered circumferentially.

As a further preferred solution, a wear-resistant coating is provided on a mating surface of the foil-type elastic member matched with the middle plate.

As a further preferred solution, a matching gap between the foil-shaped elastic member and the middle plate is 0.003 to 0.008 mm.

As a further preferred solution, at least one end of the foil-type elastic member is fixed on an inner end surface of the corresponding side plate.

As a further preferred solution, 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.

As a further preferred solution, 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.

As a further preferred solution, a clamping groove for fixing the foil-type elastic member is provided on an inner end surface of the side plate.

As an embodiment, the foil-type elastic member is composed of a wave foil and a flat foil, and an arc-shaped convex top of the wave foil is in contact with the flat foil.

As another embodiment, the foil-type elastic member is composed of a wave foil and a flat foil, and the bottom edge of the wave arch transition between the wave foil and the flat foil is attached.

As another embodiment, the foil-type elastic member is composed of two flat foils.

The above-mentioned groove patterns are all impeller shapes.

The aforementioned foil-type elastic member is preferably subjected to a surface heat treatment.

As a preferred solution, the rotor includes a rotor base, a magnetic steel, and a magnetic steel protective sleeve, the rotor base is sleeved on an inner shaft, the magnetic steel sleeve is disposed at a center portion of the rotor base, and the magnetic steel protection sleeve is sleeved On magnetic steel.

As a preferred solution, the stator includes an iron core and a winding, the iron core is fixed on an inner wall of a motor housing located above the rotor, and the winding is disposed on the iron core.

As a preferred solution, the iron core includes a stator lamination formed by a plurality of punching sheets stacked on top of each other and end pressure plates fixed on both sides of the stator lamination.

As a further preferred solution, the punching sheet has a circular ring shape, and a plurality of cup-shaped perforations are provided at intervals in the ring portion. The perforated cup mouth portion is closed and the bottom of the cup foot is open.

As a preferred solution, the winding is a three-phase star connection, and the center line is not led out, and only three ends of A, B, and C are led out.

As a further preferred solution, each phase winding is two coils, and each coil is continuously wound by enameled copper wire.

Compared with the conventional technology, the present invention has the following beneficial effects:

Because the gas turbine generator provided by the present invention uses gas as a lubricant for bearings, it not only has many advantages such as no pollution, low friction loss, long use time, wide application range, energy saving and environmental protection, etc., but also adopts the structure , The heat dissipation effect is good, can guarantee stable operation for a long time; especially, because the air bearing of the structure can achieve ultra-high speed and stable operation in the air-floating state (after testing, it can reach the limit speed of 100,000 to 450,000 rpm), so For the same power requirements, the invention can significantly reduce the volume of gas turbine generators to achieve miniaturization, has the advantages of small space occupation, convenient use, etc., and has important value for promoting the development of miniaturized high-tech. Compared with the conventional technology Significant progress.

Example 1

As shown in FIG. 1: a small miniature gas turbine generator provided in this embodiment includes a turbine 1, a compressor 2, a motor 3, two radial bearings 4, a thrust bearing 5, and a combustion chamber 6. The turbine 1 includes a turbine 11, a turbine deflector 12, and a turbine deflector housing 13. The compressor 2 includes a pressure wheel 21, a compressor housing 22, and a compressor diffuser 23. The motor 3 includes a rotor. 31. Stator 32, inner shaft 33, outer shaft 34, and motor housing 35; the radial bearing 4 is a hybrid dynamic pressure gas radial bearing, and includes a bearing outer sleeve 41, a bearing inner sleeve 42 and a bearing outer sleeve 41 The foil type elastic member 45 between the inner sleeve 42 and the 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 52 sandwiched between the two side plates. A foil-type elastic member 53 is provided between each side plate 51 and the middle plate 52; the rotor 31 is sleeved in the middle of the inner shaft 33, and two radial bearings 4 are sleeved outside the left and right ends of the rotor 31, respectively On the shaft 34, 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.

In one embodiment, the turbine 1 and the compressor 2 are disposed at both ends of the inner shaft 33, and the combustion chamber 6 is disposed at the end of the turbine 1 (as shown in FIG. 1); however, the following structure may also be adopted:

The combustion chamber 6 is disposed in the middle of the inner shaft 33, and the turbine 1 and the compressor 2 are disposed at both ends of the inner shaft 33 or back-to-back at one end of the inner shaft 33, respectively.

The small miniature gas turbine generator further includes a left radial bearing sleeve 7a, a left bearing chamber end cover 8a, a right radial bearing sleeve 7b, and a right bearing chamber end cover 8b. The turbine deflector housing 13 and the left bearing The end cover 8a of the chamber is fixedly connected, the end cover 8a of the left bearing is fixedly connected to the left radial bearing sleeve 7a, the casing 61 of the combustion chamber 6 is fixedly connected to the left radial bearing sleeve 7a, and the left radial bearing sleeve 7a is connected to the motor casing. The body 35 is fixedly connected, the compressor housing 22 is fixedly connected to the right bearing housing end cover 8b, the right bearing room end cover 8b is fixedly connected to the right radial bearing housing 7b, and the right radial bearing housing 7b is fixedly connected to the motor housing 35 .

As shown in combination with 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, and the grooves in this embodiment). The pattern is 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 and the groove pattern 433 on the right end form a mirror symmetry and an outer circumference. The axial contour line of the groove pattern 431 on the surface and the radial contour lines of the groove 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 impeller-shaped groove pattern on both sides. The pressurized gas produced by (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 stronger gas film required to support the high-speed running bearing, and The gas film is used as a lubricant of the dynamic pressure gas radial bearing, so it is beneficial to realize 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.

As shown in combination with FIG. 6 and FIG. 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, and the wave-shaped protrusion 4511 of the wave foil 451 The top end of the wave foil is attached to the flat foil 452, and the wave arch transition bottom edge 4512 of the wave foil 451 is attached to 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: a 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 453, in order to further reduce the wear of the bearing inner sleeve 42 on the foil-shaped elastic member 45 at a high speed, 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 plates 51, a middle plate 52 is sandwiched between the two side plates 51, and each side plate 51 A foil-shaped elastic member 53 is provided between the middle plate 52 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.

10a and 10b, it can be seen that a mirror symmetry is formed between the groove pattern 521 on the left end face of the middle plate 52 and the groove pattern 522 on the right end face, and the radial contour of the groove pattern 521 on the left end face and the right end face The radial contour lines of the groove pattern 522 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.

11a and 11b further, it can be seen that the foil-shaped elastic member 53 is fixed on the inner end surface of the corresponding side plate 51 (for example, the left-side disk 511 to which the foil-type elastic member 53a is fixed as shown in FIG. 11a and the The right side plate 512 of the foil type elastic member 53b 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 surface of the left end surface are formed. The grooved pattern 522 forms a mirror symmetry, thus obtaining both the rigid characteristics of the high limit 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. Flexible dynamic hybrid gas thrust bearing; because the wedge-shaped space is formed between the foil-shaped elastic member 53 and the middle plate 52, when the middle plate 52 rotates, the gas is driven by its own viscosity and compressed into the wedge-shaped space. As a result, the axial dynamic pressure can be significantly enhanced. Compared with the existing simple foil type dynamic pressure gas thrust bearing, it can have a limit speed that doubles under the same load. At the same time, due to the addition of the foil-type elastic member 53, Under its elasticity, it can also significantly improve the bearing's load capacity, impact resistance, and ability to suppress shaft whirl. Compared with the existing simple groove type dynamic pressure gas thrust bearings, Double the 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 composed of wave foils 451/531 and flat foils 452/532, and the arc-shaped protrusions 4511 of the wave foils 451/531 The top of / 5311 fits flat foil 452/532.

Example 2

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 peripheral wall of the bearing housing 41. The bottom 4512 of the wave-to-arch transition of the wave foil 451 is attached to the flat foil 452.

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

Example 3

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

Example 4

With reference to Figs. 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 Embodiment 1 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 they 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 (see 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 of 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.

An engaging groove 513 (as shown in FIG. 18) for fixing the foil-type elastic member 53 is provided on an inner end surface of the side plate 51.

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.

Example 5

1 and FIG. 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 on the rotor. At the center of the base 311, the magnetic steel protective sleeve 313 is sleeved on the magnetic steel 312 to better meet ultra-high speed rotation.

Example 6

As shown in combination with 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 housing 35 located above the rotor 31, and the winding 322 is provided on the iron On the 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 winding 322 is connected by a three-phase star, and the center line is not led out, but only three terminals A, B, and C are drawn out; each phase winding is 2 coils, and each coil is made of enameled copper wire Continuously wound.

Example 7

As shown in FIG. 27 and FIG. 28 in combination, a heat dissipation spiral groove 331 is provided on the surface of the inner shaft 33 to facilitate heat dissipation of the rotating shaft and the bearing chamber.

Example 8

As shown in combination with FIG. 29 and FIG. 30, a plurality of opening grooves 351 are provided on the inner wall peripheral side of the motor housing 35, and a plurality of ventilation holes 352 are provided on an end surface of the motor housing. The opening grooves 351 and the ventilation holes 352 are provided. It is connected 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 the limit speed of 100,000 to 450,000 rpm in the air-floating state. Therefore, according to the same power requirement, the present invention can significantly reduce the volume of the gas turbine generator, achieve miniaturization, and promote miniaturization. The development of high-tech technology has important value.

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. Some non-essential improvements and adjustments belong to the protection scope of the present invention.

1‧‧‧ Turbine

11‧‧‧ Turbine

12‧‧‧ Turbine deflector

13‧‧‧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

331‧‧‧cooling spiral groove

34‧‧‧Outer shaft

35‧‧‧Motor housing

351‧‧‧open slot

352‧‧‧Vent

4‧‧‧ Hybrid dynamic pressure gas radial bearing

4a‧‧‧Left end radial bearing

4b‧‧‧Right end radial bearing

41‧‧‧bearing jacket

411‧‧‧card slot

42‧‧‧bearing inner sleeve

43‧‧‧Slot pattern

431, 523‧‧‧Groove pattern on the outer circumferential surface

4311, 5231‧‧‧ axial high line

4312, 5232‧‧‧ axial median line

4313, 5233‧‧‧ axial low line

432, 521‧‧‧Groove pattern on the left end

4321, 4311, 5121, 5221‧‧‧ radial high line

4322, 4322, 5122, 5222‧‧‧ radial median

4323, 4333, 5213, 5223‧‧‧ radial low line

433, 522‧‧‧Groove pattern on the right end face

44‧‧‧ Stop ring

45‧‧‧Foil Elastic

451, 531‧‧‧wave foil

4511, 5311‧‧‧arc convex

4512, 5312 ‧‧‧ wave arch transition bottom

452, 532‧‧‧ flat foil

453‧‧‧Abrasion resistant coating

5‧‧‧ Hybrid dynamic pressure gas thrust bearing

51‧‧‧Side plate

511‧‧‧Left plate

512‧‧‧Right disk

513‧‧‧Card slot

52‧‧‧ Midday

53‧‧‧Foil Elastic

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

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

6‧‧‧combustion chamber

61‧‧‧Combustion chamber housing

7a‧‧‧left radial bearing sleeve

7b‧‧‧Right radial bearing sleeve

8a‧‧‧End cover of left bearing chamber

8b‧‧‧Rear bearing housing end cover

1 is a schematic cross-sectional structure diagram of a small miniature gas turbine generator provided in Embodiment 1; FIG. 2 is a left-view perspective structural diagram of a partial division of the hybrid dynamic pressure gas radial bearing provided in Embodiment 1; FIG. 3 is 2 is an enlarged view of part A in FIG. 4; FIG. 4 is a schematic diagram of a right-handed three-dimensional structure of a partial division of the hybrid dynamic pressure gas radial bearing provided in Embodiment 1; FIG. 5 is a partially enlarged view of B in FIG. 4; 7 is a schematic sectional view of a hybrid dynamic pressure gas radial bearing provided in Embodiment 1; FIG. 7 is a partially enlarged view of C in FIG. 6; FIG. 8 is a partially enlarged view of D in FIG. 7; Schematic sectional view of the hybrid dynamic pressure gas thrust bearing; FIG. 10a is a left side view of the middle plate described in Embodiment 1; FIG. 10b is a right side view of the middle plate described in Embodiment 1; FIG. 11a is described in Embodiment 1 Right side view of the left side plate with the foil type elastic member fixed; FIG. 11b is a left side view of the right side plate with the foil type elastic member fixed in Embodiment 1; FIG. 12 is a view of the foil type elastic member provided in the first embodiment; Schematic cross-sectional structure; Figure 13 is the foil-type elasticity provided by Example 1 14 is a schematic sectional view of a hybrid dynamic pressure gas radial bearing provided in Embodiment 2; FIG. 15 is a schematic structural view of a wave foil in FIG. 14; FIG. 16 is a hybrid provided in Embodiment 3 Figure 17a is a left-hand perspective view of a hybrid dynamic pressure gas thrust bearing provided in Embodiment 4; and Fig. 17b is a hybrid dynamic pressure gas bearing provided in Embodiment 4 Schematic diagram of the right-hand perspective structure of the thrust bearing; FIG. 18 is a schematic diagram of the partially divided three-dimensional structure of the hybrid dynamic pressure gas thrust bearing provided in Embodiment 4; 20 is a partially enlarged view of E in FIG. 19; FIG. 21 is a schematic view of a right-handed three-dimensional structure of the middle plate described in Embodiment 4; FIG. 22 is a partially enlarged view of F in FIG. 21; and FIG. 23 is a rotor provided in Embodiment 5 24 is a schematic diagram of a core structure provided in Embodiment 6; FIG. 25 is a schematic diagram of a punch plate described in Embodiment 6; FIG. 26 is a schematic diagram of a winding structure provided in Embodiment 6; Schematic diagram of the inner shaft structure provided in Example 7; FIG. 28 is a partially enlarged view of G in FIG. 27; FIG. 29 is a perspective structural diagram of the motor housing provided in Embodiment 8; FIG. 30 is a partially enlarged view of H in FIG. Illustration.

The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

Claims (22)

A small miniature gas turbine generator includes a turbine, a compressor, a motor, two radial bearings, a thrust bearing and a combustion chamber. The turbine includes a turbine, a turbine deflector, and a turbine deflector housing. The compressor includes a compressor wheel, a compressor housing, and a compressor diffuser, and the motor includes a rotor, a stator, an inner shaft, an outer shaft, and a motor housing; wherein the radial bearing is a hybrid dynamic pressure gas diameter Directional bearing, including bearing outer sleeve, bearing inner sleeve and foil-type elastic member arranged between bearing outer sleeve and inner sleeve; the thrust bearing is a hybrid dynamic pressure gas thrust bearing, including two side disks and sandwiched between The middle plate between the two side plates is provided with a foil-type elastic member between each side plate and the middle plate; the rotor is sleeved in the middle of the inner shaft, and two radial bearings are sleeved on the left and On the right end outer shaft, the thrust bearing is sleeved on the right end outer shaft and located on the outer end side of the right end radial bearing. The small miniature gas turbine generator according to claim 1, wherein the turbine and the compressor are respectively provided at both ends of the inner shaft, and the combustion chamber is provided at the turbine end. The small miniature gas turbine generator according to claim 1, wherein the combustion chamber is provided in the middle of the inner shaft, the turbine and the compressor are respectively provided at different ends of the inner shaft, or the turbine and the compressor are back-to-back Set on the same end of the inner shaft. The small miniature gas turbine generator according to any one of claims 1 to 3, wherein the small miniature gas turbine generator further includes a left radial bearing sleeve and a left bearing chamber end cover, and a turbine deflector. The housing is fixedly connected to the left bearing housing end cover, the left bearing room end cover is fixedly connected to the left radial bearing sleeve, the combustion chamber housing is fixedly connected to the left radial bearing sleeve, and the left radial bearing cover is fixed to the motor housing connection. The small miniature gas turbine generator according to claim 4, wherein the small miniature gas turbine generator further comprises a right radial bearing sleeve and a right bearing chamber end cover, a compressor housing and a right bearing chamber end cover Fixed connection. The right bearing housing end cover is fixedly connected to the right radial bearing sleeve, and the right radial bearing sleeve is fixedly connected to the motor housing. The small miniature gas turbine generator according to claim 1, wherein a surface of the inner shaft is provided with a heat dissipation spiral groove. The small miniature gas turbine generator according to claim 1, wherein a plurality of opening grooves are provided on the inner wall peripheral side of the motor housing, and a plurality of vent holes are provided on the end surface of the motor housing. The vents communicate. The small miniature gas turbine generator 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 miniature gas turbine generator according to claim 8, wherein the grooved pattern on one end face of the bearing inner sleeve forms a mirror-symmetrical relationship with the grooved pattern on the other end face, and the shaft of the grooved pattern on the outer circumferential surface The contour lines form a one-to-one correspondence with the radial contour lines of the groove pattern on both end surfaces and intersect with each other. The small miniature gas turbine generator according to claim 9, wherein the axial high-level lines in the grooved pattern on the outer circumferential surface of the bearing inner sleeve are homogeneous with the radial high-level lines in the grooved pattern on both end surfaces. Correspond to and intersect each other before the chamfer on the end face; 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 chamfer on the end surface circumference The axially low lines in the grooved pattern on the outer circumferential surface correspond to the radial lows in the grooved pattern on both end surfaces, and they meet each other before the end face is chamfered. The small miniature gas turbine generator according to claim 1, wherein both end surfaces of the middle plate are provided with a groove pattern with a regular shape, and the groove pattern on one end face is mirror-symmetrical with the groove pattern on the other end face . The small miniature gas turbine generator according to claim 11, wherein a groove pattern is also provided on an outer circumferential surface of the middle plate, and a shape of the groove pattern on the outer circumferential surface and a shape of the groove pattern on both end surfaces are provided. Similarly, 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 intersect with each other. The small miniature gas turbine generator according to claim 12, 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 outer circumferential surface correspond to the radial low-level lines in the grooved pattern on both end surfaces, and they intersect with each other before the end face circumferential chamfer. The small miniature gas turbine generator 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 are mirror-symmetrical. The small miniature gas turbine generator according to claim 1 or 14, wherein the foil-type elastic member is composed of a wave foil and a flat foil, and an arcuate convex top of the wave foil is attached to the flat foil. The small miniature gas turbine generator according to claim 1 or 14, wherein the foil-type elastic member is composed of a wave foil and a flat foil, and the bottom edge of the wave-to-arch transition of the wave foil is attached to the flat foil. The small miniature gas turbine generator according to claim 1 or 14, wherein the foil-type elastic member is composed of two flat foils. The small miniature gas turbine generator 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 is sleeved on the rotor At the center of the base, the magnetic steel protective sleeve is sleeved on the magnetic steel. The small miniature gas turbine generator according to claim 1, wherein the stator includes an iron core and a winding, the iron core is fixed on an inner wall of a motor casing located above the rotor, and the winding is provided on the iron On the core. The small miniature gas turbine generator according to claim 19, wherein the iron core includes a stator lamination formed by a plurality of punches stacked on top of each other and end pressure plates fixed on both sides of the stator lamination; In a circular ring shape, a plurality of cup-shaped perforations are provided at intervals in the ring portion. The perforated cup mouth portion is closed, and the bottom of the cup feet is open. The small miniature gas turbine generator according to claim 19, 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 miniature gas turbine generator according to claim 21, wherein each phase winding is two coils, and each coil is continuously wound by enameled copper wire.