CN215804840U

CN215804840U - Magnetic suspension outer rotor starting integrated motor for gas turbine

Info

Publication number: CN215804840U
Application number: CN202122000853.3U
Authority: CN
Inventors: 袁军; 钟仁志
Original assignee: Xinlei Compressor Co Ltd
Current assignee: Xinlei Compressor Co Ltd
Priority date: 2021-08-24
Filing date: 2021-08-24
Publication date: 2022-02-11
Anticipated expiration: 2031-08-24

Abstract

The utility model relates to the field of gas turbines, in particular to a magnetic suspension outer rotor starting integrated motor for a gas turbine. The motor comprises a motor shaft and an outer rotor of the turbine; the outer wall of the motor shaft is fixedly sleeved with a motor stator, a radial magnetic bearing and an axial magnetic bearing, and a plurality of radial magnetic bearings are respectively arranged at two ends of the motor shaft; the outer rotor of the turbine is provided with an outer rotor inner hole, and the inner wall of the outer rotor inner hole is fixedly embedded with a motor rotor, a radial bearing rotor and a thrust disc; the outer rotor of the turbine comprises a compression section, a combustion section and an expansion section, wherein the outer wall of the compression section is fixedly provided with a plurality of compression impellers, the combustion section is used for containing fuel of the gas turbine, and the outer wall of the expansion section is fixedly provided with a plurality of expansion impellers; the combustion section is communicated with the compression section and the expansion section at two ends respectively, and the compression section is communicated with the outside air. The motor enables the gas turbine to be compact in structure, reduces occupied space and ensures that the gas turbine is free of maintenance.

Description

Magnetic suspension outer rotor starting integrated motor for gas turbine

Technical Field

The utility model relates to the field of gas turbines, in particular to a magnetic suspension outer rotor starting integrated motor for a gas turbine.

Background

The gas turbine generator set drives a generator by a micro gas turbine, and the generator generates electricity and outputs electric power. The gas turbine generator set comprises a generator rotor and a gas turbine rotor, the generator set rotor is long, the number of mutually associated structural members is large, the rotor runs at high speed of tens of thousands of revolutions per minute, the critical rotating speed is large, and the vibration mode is complex.

The Chinese invention patent application (publication No. CN110645097B, published: 20201009) discloses a gas turbine generator set rotor component and a gas turbine generator set, which comprise a generator rotor, a gas turbine rotor and a supporting structure for supporting the generator rotor and the gas turbine rotor, wherein the gas turbine rotor comprises a centrifugal impeller and a centripetal turbine, and a floating drum-shaped spline coupling for only transmitting torque is arranged between the generator rotor and the gas turbine rotor; the gas turbine rotor also comprises a main shaft which is used for connecting the centrifugal impeller and the centripetal turbine and transmitting torque, and the centrifugal impeller, the main shaft and the centripetal turbine are coaxially and sequentially arranged; the supporting structure comprises a first supporting piece, a second supporting piece, a third supporting piece and a fourth supporting piece, wherein the first supporting piece and the second supporting piece are respectively arranged on a first journal and a second journal of the generator rotor, and the third supporting piece and the fourth supporting piece are arranged on the main shaft. The rotor assembly of the gas turbine generator set adopts a four-pivot supporting scheme, so that a large cantilever structure of the conventional rotor is avoided.

The prior art has the following defects: the motor for the traditional gas turbine is arranged at the front end of the compression section, and a shaft coupling is needed to connect a gas turbine shaft system and a motor shaft system; namely, the gas turbine shaft system and the electric machine shaft system are separated into two parts, so that the structure of the gas turbine is complicated, the space is wasted, and the step of assembling the two parts together is also increased. Meanwhile, the bearings of the motor shaft system adopt sliding bearings, mechanical abrasion is generated, oil is needed for lubrication, and the maintenance-free performance of the gas turbine is not facilitated.

Disclosure of Invention

The purpose of the utility model is: aiming at the problems, the motor shaft system and the outer rotor of the turbine are combined into a whole, so that the gas turbine has a compact structure and occupies less space; meanwhile, the magnetic bearing is adopted to support the outer rotor of the turbine, so that mechanical abrasion is avoided, oil is not needed for lubrication, and the maintenance-free magnetic suspension outer rotor starting integrated motor for the gas turbine is ensured.

In order to achieve the purpose, the utility model adopts the following technical scheme:

a magnetic suspension outer rotor starting integrated motor for a gas turbine comprises a motor shaft and a turbine outer rotor; the outer wall of the motor shaft is fixedly sleeved with a motor stator, a radial magnetic bearing and an axial magnetic bearing, and a plurality of radial magnetic bearings are respectively arranged at two ends of the motor shaft; the outer rotor of the turbine is provided with an outer rotor inner hole, and the inner wall of the outer rotor inner hole is fixedly embedded with a motor rotor, a radial bearing rotor and a thrust disc; the motor rotor and the radial bearing rotor respectively correspond to the motor stator and the radial magnetic bearing, and the limiting parts of the axial magnetic bearing are respectively positioned at two axial sides of the thrust disc; the outer rotor of the turbine comprises a compression section, a combustion section and an expansion section, wherein the outer wall of the compression section is fixedly provided with a plurality of compression impellers, the combustion section is used for containing fuel of the gas turbine, and the outer wall of the expansion section is fixedly provided with a plurality of expansion impellers; the combustion section is communicated with the compression section and the expansion section at two ends respectively, and the compression section is communicated with the outside air.

Preferably, the combustion section is radially concave in shape.

Preferably, a protective bearing seat is fixedly embedded in the inner wall of the inner hole of the outer rotor, and a protective bearing is fixedly sleeved on the outer wall of the motor shaft; the inner ring of the protection bearing is in interference fit with the outer wall of the motor shaft, and a gap exists between the outer ring of the protection bearing and the protection bearing seat.

Preferably, the motor rotor comprises a plurality of axially-stacked silicon steel sheets and a plurality of magnetic steels; the silicon steel sheet is provided with a magnetic steel inner hole, the plurality of magnetic steels are fixedly embedded in the magnetic steel inner hole in the circumferential direction, and the plurality of magnetic steels correspond to the motor stator in position.

Preferably, an inlet fairing is fixedly arranged at one end of the outer rotor of the turbine, a guide vane fairing is fixedly arranged on a motor shaft at one end of the outer rotor of the turbine, and an outlet fairing is fixedly arranged at the other end of the outer rotor of the turbine; the guide vane fairing and the inlet fairing are used for rectifying the airflow at the inlet of the motor, and the outlet fairing is used for rectifying the airflow at the outlet of the motor.

Preferably, the guide vane fairing is fixedly provided with an axial sensor, and the sensing end of the axial sensor is aligned with the end surface of the outer rotor of the turbine; the axial sensor is used for detecting the axial position of the outer rotor of the turbine; a radial sensor is fixedly arranged on the motor shaft, and the sensing end of the radial sensor is aligned with the radial inner surface of the protective bearing seat; the radial sensor is used for detecting the radial position of the outer rotor of the turbine.

Preferably, the guide vane fairing is further fixedly provided with inlet guide vanes, and the plurality of inlet guide vanes are distributed along the circumferential direction.

Preferably, the inner wall of the inner hole of the outer rotor is provided with a heat insulation sleeve, the outer wall of the heat insulation sleeve is fixedly embedded in the inner wall of the inner hole of the outer rotor, and the motor rotor, the radial bearing rotor and the thrust disc are fixedly embedded in the inner hole of the heat insulation sleeve.

Preferably, the guide vane fairing is provided with a first channel communicated with the outside, the axial magnetic bearing is provided with a second channel which penetrates through the axial direction, and a third channel is arranged between the thrust disc and the outer wall of the motor shaft; a fourth channel is arranged between the radial magnetic bearing and the radial bearing rotor, the motor rotor is provided with a fifth channel which penetrates through the motor rotor in the axial direction, and the outlet fairing is provided with a sixth channel which penetrates through the motor rotor in the axial direction and is communicated with the outside of the motor; the first channel, the gap between the outer ring of the protection bearing and the protection bearing seat, the second channel, the third channel, the fourth channel, the fifth channel and the sixth channel are communicated through the inner hole of the outer rotor to form a heat dissipation channel.

Preferably, the motor shaft is provided with a first wire outlet hole and a plurality of radial second wire outlet holes, wherein the first wire outlet hole penetrates through the motor shaft in the axial direction, and the first wire outlet hole is communicated with the radial outer part of the motor shaft through the second wire outlet holes; the guide vane fairing is provided with a third wire outlet hole communicated with the outside, and the first wire outlet hole is communicated with the axial outside of the motor shaft through the third wire outlet hole.

The magnetic suspension outer rotor starting integrated motor for the gas turbine adopting the technical scheme has the advantages that:

when in work: 1) the motor stator is electrified to drive the motor rotor to rotate so as to drive the external rotor of the motor to rotate, at the moment, the radial magnetic bearing supports the external rotor of the wheel through supporting the radial bearing rotor, and the axial magnetic bearing controls the axial position of the thrust disc so as to axially limit the external rotor of the wheel; 2) the compression impeller continuously sucks air from the atmosphere and compresses the air; 3) the compressed air enters a combustion section, is mixed with the injected fuel and then is combusted to form high-temperature fuel gas; 4) the high-temperature fuel gas flows into the expansion section to do work through expansion, the expansion impeller is pushed to rotate, and the expansion impeller rotates to drive the compression impeller to rotate to complete the working process. In this way, the power-producing capability of the heated high-temperature gas is significantly improved, so that the expansion impeller drives the compression impeller to rotate, and simultaneously, the residual power is used as the output mechanical power of the gas turbine. When the gas turbine is started from a static state, the magnetic suspension outer rotor starting integrated motor is required to rotate, and after the gas turbine is accelerated to be capable of operating independently, the magnetic suspension outer rotor starting integrated motor is changed into a generator to continuously generate power to supply power to other positions of the system; the mode combines the motor shaft system and the outer rotor of the turbine into a whole, has two functions of starting and generating electricity at the same time, and does not need to use a coupling for connection, so that the gas turbine has a compact structure, and the occupied space is reduced. Meanwhile, the radial and axial supporting and limiting of the outer rotor of the turbine are respectively controlled by a radial magnetic bearing and an axial magnetic bearing, and the magnetic bearings are free of mechanical wear and do not need oil for lubrication, so that the maintenance-free performance of the gas turbine is ensured.

Drawings

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a schematic structural diagram of an outer rotor of a turbine.

Fig. 3 and 4 are schematic structural diagrams of the motor rotor.

Fig. 5 is a schematic view of the structure of the motor shaft.

FIGS. 6-9 are schematic views of vane fairings.

Fig. 10 and 11 are schematic structural views of an axial magnetic bearing.

Detailed Description

The following describes in detail embodiments of the present invention with reference to the drawings.

Example 1

The magnetic suspension outer rotor starting integrated motor for the gas turbine as shown in the figures 1 and 2 comprises a motor shaft 1 and a turbine outer rotor 2; the outer wall of the motor shaft 1 is fixedly sleeved with a motor stator 3, a radial magnetic bearing 4 and an axial magnetic bearing 5, and the plurality of radial magnetic bearings 4 are respectively arranged at two ends of the motor shaft 1; the outer rotor 2 of the turbine is provided with an inner bore of the outer rotor, and the inner wall of the inner bore of the outer rotor is fixedly embedded with a motor rotor 21, a radial bearing rotor 22 and a thrust disc 23; the motor rotor 21 and the radial bearing rotor 22 correspond to the motor stator 3 and the radial magnetic bearing 4 respectively, and the limiting parts of the axial magnetic bearing 5 are respectively positioned at two axial sides of the thrust disc 23; the turbine outer rotor 2 comprises a compression section 24, a combustion section 25 and an expansion section 26, wherein the outer wall of the compression section 24 is fixedly provided with a plurality of compression impellers 241, the combustion section 25 is used for containing fuel of the gas turbine, and the outer wall of the expansion section 26 is fixedly provided with a plurality of expansion impellers 261; the combustion section 25 communicates at both ends with the compression section 24 and the expansion section 26, respectively, and the compression section 24 communicates with the outside air. When in work: 1) the motor stator 3 is electrified to drive the motor rotor 21 to rotate so as to drive the wheel external rotor 2 to rotate, at the moment, the radial magnetic bearing 4 supports the wheel external rotor 2 in a radial direction by supporting the radial bearing rotor 22, and the axial magnetic bearing 5 controls the axial position of the thrust disc 23 so as to axially limit the wheel external rotor 2; 2) the compression impeller 241 continuously sucks air from the atmosphere and compresses it; 3) the compressed air enters the combustion section 25, and is mixed with the injected fuel and then is combusted to form high-temperature fuel gas; 4) the high-temperature fuel gas flows into the expansion section 26 to do work through expansion, the expansion impeller 261 is pushed to rotate, and the expansion impeller 261 rotates to drive the compression impeller 241 to rotate to complete the working process. In this way, the power-generating capacity of the heated high-temperature combustion gas is significantly improved, and therefore, the expansion impeller 261 drives the compression impeller 241 to rotate, and at the same time, the remaining power is used as the output mechanical power of the gas turbine. When the gas turbine is started from a static state, the magnetic suspension outer rotor starting integrated motor is required to rotate, and after the gas turbine is accelerated to be capable of operating independently, the magnetic suspension outer rotor starting integrated motor is changed into a generator to continuously generate power to supply power to other positions of the system; the mode combines the motor shaft system and the outer rotor of the turbine into a whole, has two functions of starting and generating electricity at the same time, and does not need to use a coupling for connection, so that the gas turbine has a compact structure, and the occupied space is reduced. Meanwhile, the radial and axial supporting and limiting of the outer rotor 2 of the turbine are respectively controlled by a radial magnetic bearing 4 and an axial magnetic bearing 5, and the magnetic bearings are free from mechanical wear and do not need oil for lubrication, so that the maintenance-free performance of the gas turbine is ensured.

The combustion section 25 is concave in the radial direction.

A protective bearing seat 27 is fixedly embedded in the inner wall of the inner hole of the outer rotor, and a protective bearing 11 is fixedly sleeved on the outer wall of the motor shaft 1; the inner ring of the protection bearing 11 is in interference fit with the outer wall of the motor shaft 1, and a gap exists between the outer ring of the protection bearing 11 and the protection bearing seat 27. When the equipment is suddenly powered off or stopped, the radial magnetic bearing 4 and the axial magnetic bearing 5 lose magnetic force and can not support and limit the outer rotor 2 of the turbine, and at the moment, the outer rotor 2 of the turbine falls down and is in contact with the outer ring of the protective bearing 11 and supported by the protective bearing 11; thereby avoiding the damage of important parts such as the radial magnetic bearing 4 and the axial magnetic bearing 5 caused by the sudden power failure of the motor or the sudden falling of the outer rotor 2 of the turbine when the motor is stopped.

As shown in fig. 3 and 4, the motor rotor 21 includes a plurality of silicon steel sheets 211 and a plurality of magnetic steels 212 stacked axially one on another; silicon steel sheet 211 is provided with the magnet steel hole, and a plurality of magnet steel 212 are fixed to be inlayed in the magnet steel hole in the circumferencial direction to a plurality of magnet steel 212 are corresponding with motor stator 3's position. The motor stator 3 controls the magnetic steel 212 to rotate through magnetic force so as to drive the motor rotor 21 to rotate.

As shown in fig. 1, an inlet fairing 14 is fixedly arranged at one end of the outer rotor 2 of the turbine, a guide vane fairing 12 is fixedly arranged on the motor shaft 1 at one end of the outer rotor 2 of the turbine, and an outlet fairing 13 is fixedly arranged at the other end of the outer rotor 2 of the turbine; the guide vane fairing 12 and the inlet fairing 14 are used to rectify the airflow at the inlet of the motor, and the outlet fairing 13 is used to rectify the airflow at the outlet of the motor.

As shown in fig. 1 and 5, the guide vane fairing 12 is fixedly provided with an axial sensor 121, and an induction end of the axial sensor 121 is aligned with an end surface of the outer rotor 2 of the turbine; the axial sensor 121 is used for detecting the axial position of the outer rotor 2 of the turbine; a radial sensor 122 is fixedly arranged on the motor shaft 1, and the sensing end of the radial sensor 122 is aligned with the radial inner surface of the protective bearing seat 27; the radial sensor 122 is used to detect the radial position of the turbine outer rotor 2. The guide vane fairing 12 is further fixedly provided with inlet guide vanes 120, and a plurality of inlet guide vanes 120 are distributed along the circumferential direction.

The inner wall of the inner hole of the outer rotor is provided with a heat insulation sleeve 6, the outer wall of the heat insulation sleeve 6 is fixedly embedded in the inner wall of the inner hole of the outer rotor, and the motor rotor 21, the radial bearing rotor 22 and the thrust disc 23 are fixedly embedded in the inner hole of the heat insulation sleeve 6. The heat insulation sleeve 6 is made of a high-strength composite material with extremely low heat conduction coefficient, has small thermal deformation at high temperature, stable performance and excellent heat insulation performance, and can ensure the mechanical performance while playing a role in heat insulation.

As shown in fig. 1, the guide vane fairing 12 is provided with a first passage 123 communicating with the outside, the axial magnetic bearing 5 is provided with a second passage 51 penetrating axially, and a third passage 231 is provided between the thrust disc 23 and the outer wall of the motor shaft 1; a fourth channel 232 is arranged between the radial magnetic bearing 4 and the radial bearing rotor 22, the motor rotor 21 is provided with a fifth channel 213 which axially penetrates, and the outlet fairing 13 is provided with a sixth channel 131 which axially penetrates and is communicated with the outside of the motor; the first channel 123, the gap between the outer ring of the protection bearing 11 and the protection bearing seat 27, the second channel 51, the third channel 231, the fourth channel 232, the fifth channel 213 and the sixth channel 131 are communicated through the inner hole of the outer rotor to form a heat dissipation channel so as to prevent the gas turbine from being damaged due to overheating.

As shown in fig. 1 and 5, the motor shaft 1 is provided with a first outlet hole 101 penetrating axially and a plurality of second outlet holes 102 penetrating radially, and the first outlet hole 101 is communicated with the radially outer part of the motor shaft 1 through the second outlet holes 102; the guide vane fairing 12 is provided with a third outlet hole 103 communicated with the outside, and the first outlet hole 101 is communicated with the axial outside of the motor shaft 1 through the third outlet hole 103. The lines of the motor stator 3, the radial magnetic bearing 4 and the axial magnetic bearing 5 are collected to the first outlet hole 101 through the second outlet hole 102, and then are led out of the gas turbine through the third outlet hole 103.

Claims

1. A magnetic suspension outer rotor starting integrated motor for a gas turbine is characterized by comprising a motor shaft (1) and a turbine outer rotor (2); the outer wall of the motor shaft (1) is fixedly sleeved with a motor stator (3), a radial magnetic bearing (4) and an axial magnetic bearing (5), and the plurality of radial magnetic bearings (4) are respectively arranged at two ends of the motor shaft (1); the outer rotor (2) of the turbine is provided with an inner bore of the outer rotor, and the inner wall of the inner bore of the outer rotor is fixedly embedded with a motor rotor (21), a radial bearing rotor (22) and a thrust disc (23); the motor rotor (21) and the radial bearing rotor (22) respectively correspond to the motor stator (3) and the radial magnetic bearing (4), and the limiting parts of the axial magnetic bearing (5) are respectively positioned at two axial sides of the thrust disc (23); the outer rotor (2) of the turbine comprises a compression section (24), a combustion section (25) and an expansion section (26), wherein a plurality of compression impellers (241) are fixedly arranged on the outer wall of the compression section (24), the combustion section (25) is used for containing fuel of the gas turbine, and a plurality of expansion impellers (261) are fixedly arranged on the outer wall of the expansion section (26); the combustion section (25) communicates at both ends with the compression section (24) and the expansion section (26), respectively, and the compression section (24) communicates with the outside air.

2. Magnetic levitation outer rotor heuristic one-piece electrical machine for gas turbines according to claim 1, characterized by the fact that the combustion section (25) is concave in shape in radial direction.

3. The magnetic suspension outer rotor starting integrated motor for the gas turbine is characterized in that a protective bearing seat (27) is fixedly embedded in the inner wall of an inner hole of the outer rotor, and a protective bearing (11) is fixedly sleeved on the outer wall of the motor shaft (1); the inner ring of the protection bearing (11) is in interference fit with the outer wall of the motor shaft (1), and a gap exists between the outer ring of the protection bearing (11) and the protection bearing seat (27).

4. Magnetic levitation external rotor heuristic integrated electrical machine for gas turbine according to claim 1, characterized in that the electrical machine rotor (21) comprises a plurality of silicon steel sheets (211) and a plurality of magnetic steels (212) axially stacked on each other; silicon steel sheet (211) are provided with the magnet steel hole, and a plurality of magnet steel (212) are fixed to be inlayed in the magnet steel hole in circumferencial direction to a plurality of magnet steel (212) are corresponding with motor stator (3)'s position.

5. The magnetic suspension outer rotor starting integrated motor for the gas turbine is characterized in that an inlet fairing (14) is fixedly arranged at one end of the outer rotor (2) of the turbine, a guide vane fairing (12) is fixedly arranged on a motor shaft (1) at one end of the outer rotor (2) of the turbine, and an outlet fairing (13) is fixedly arranged at the other end of the outer rotor (2) of the turbine; the guide vane fairing (12) and the inlet fairing (14) are used for rectifying the airflow at the inlet of the motor, and the outlet fairing (13) is used for rectifying the airflow at the outlet of the motor.

6. The magnetic suspension outer rotor starting integrated motor for the gas turbine is characterized in that an axial sensor (121) is fixedly arranged on the guide vane fairing (12), and the sensing end of the axial sensor (121) is aligned with the end surface of the outer rotor (2) of the turbine; the axial sensor (121) is used for detecting the axial position of the outer rotor (2) of the turbine; a radial sensor (122) is fixedly arranged on the motor shaft (1), and the sensing end of the radial sensor (122) is aligned with the radial inner surface of the protective bearing seat (27); the radial sensor (122) is used for detecting the radial position of the outer rotor (2) of the turbine.

7. The magnetic levitation outer rotor starting integrated motor for a gas turbine as recited in claim 5, wherein the guide vane cowling (12) is further fixedly provided with inlet guide vanes (120), and a plurality of inlet guide vanes (120) are distributed along a circumferential direction.

8. The magnetic suspension outer rotor starting integrated motor for the gas turbine is characterized in that a heat insulation sleeve (6) is arranged on the inner wall of an inner hole of an outer rotor, the outer wall of the heat insulation sleeve (6) is fixedly embedded in the inner wall of the inner hole of the outer rotor, and a motor rotor (21), a radial bearing rotor (22) and a thrust disc (23) are fixedly embedded in the inner hole of the heat insulation sleeve (6).

9. The magnetic levitation outer rotor heuristic integrated motor for gas turbine according to claim 3 or 5, characterized in that the guide vane fairing (12) is provided with a first channel (123) communicating with the outside, the axial magnetic bearing (5) is provided with a second channel (51) passing through axially, a third channel (231) is provided between the thrust disc (23) and the outer wall of the motor shaft (1); a fourth channel (232) is arranged between the radial magnetic bearing (4) and the radial bearing rotor (22), the motor rotor (21) is provided with a fifth channel (213) which axially penetrates, and the outlet fairing (13) is provided with a sixth channel (131) which axially penetrates and is communicated with the outside of the motor; the heat dissipation channel is formed by communicating a first channel (123), a gap between the outer ring of the protection bearing (11) and the protection bearing seat (27), a second channel (51), a third channel (231), a fourth channel (232), a fifth channel (213) and a sixth channel (131) through an inner hole of the outer rotor.

10. The magnetic suspension outer rotor heuristic integrated motor for gas turbine according to claim 5, characterized in that the motor shaft (1) is provided with a first outlet hole (101) axially through and a plurality of second outlet holes (102) radially, the first outlet hole (101) communicating with the radially outer part of the motor shaft (1) through the second outlet holes (102); the guide vane fairing (12) is provided with a third wire outlet hole (103) communicated with the outside, and the first wire outlet hole (101) is communicated with the axial outside of the motor shaft (1) through the third wire outlet hole (103).