A magnetically levitated outer rotor inspired integrated motor for a gas turbine

Abstract

The present invention relates to the field of gas turbines, and particularly to a magnetically levitated outer rotor integrated motor for a gas turbine. The motor includes a motor shaft and a turbine outer rotor; a motor stator, a radial magnetic bearing, and an axial magnetic bearing are fixedly sleeved on the outer wall of the motor shaft, and a plurality of radial magnetic bearings are respectively arranged at both ends of the motor shaft; the turbine outer rotor is provided with an inner hole of the outer rotor, and a motor rotor, a radial bearing rotor, and a thrust disk are fixedly embedded on the inner wall of the inner hole of the outer rotor; the turbine outer rotor includes a compression section, a combustion section, and an expansion section. A plurality of compression impellers are fixedly arranged on the outer wall of the compression section, the combustion section is used to accommodate the fuel of the gas turbine, and a plurality of expansion impellers are fixedly arranged on the outer wall of the expansion section; both ends of the combustion section are respectively communicated with the compression section and the expansion section, and the compression section is communicated with external air. This motor makes the gas turbine structure compact, reduces the occupied space, and ensures that the gas turbine is maintenance-free.

Description

Technical Field

[0001] The present invention relates to the field of gas turbines, and in particular to a magnetically levitated outer rotor integrated motor for a gas turbine. Background Art

[0002] A gas turbine generator set is driven by a micro gas turbine to drive a generator, and the generator generates electricity and outputs electric power. The gas turbine generator set includes a generator rotor and a gas turbine rotor. The rotor of the unit is long, there are many interrelated structural components, and the rotor rotates at a high speed of tens of thousands of revolutions per minute, with multiple critical speeds and complex vibration modes.

[0003] Chinese Patent Application (Publication No. CN110645097B, Publication Date: 20201009) discloses a rotor assembly of a gas turbine generator set and a gas turbine generator set, including a generator rotor, a gas turbine rotor, and a support structure for supporting the generator rotor and the gas turbine rotor. The gas turbine rotor includes a centrifugal impeller and a centripetal turbine. A floating drum spline coupling for only torque transmission is arranged between the generator rotor and the gas turbine rotor; the gas turbine rotor further includes a main shaft for connecting the centrifugal impeller and the centripetal turbine and transmitting torque, and the centrifugal impeller, the main shaft, and the centripetal turbine are arranged coaxially in sequence; the support structure includes a first support member, a second support member, a third support member, and a fourth support member. The first support member and the second support member are respectively arranged on the first journal and the second journal of the generator rotor, and the third support member and the fourth support member are arranged on the main shaft. The rotor assembly of the gas turbine generator set of the present invention adopts a four-point support scheme, avoiding the large cantilever structure of the existing rotor.

[0004] The prior art has the following deficiencies: The motor used in a traditional gas turbine is placed at the front end of the compression section, and a coupling is required to connect the gas turbine shafting and the motor shafting; that is, the gas turbine shafting and the motor shafting are two separate parts, resulting in a complex structure of the gas turbine, wasting space, and also increasing the steps of assembling the two parts together. At the same time, the bearings of the motor shafting use sliding bearings, which will cause mechanical wear and require oil for lubrication, making it difficult for the gas turbine to achieve maintenance-free operation. Summary of the Invention

[0005] The object of the present invention is: In view of the above problems, to propose a magnetically levitated outer rotor integrated motor for a gas turbine that combines the motor shafting and the outer rotor of the turbine, making the gas turbine structure compact and reducing the occupied space; at the same time, using magnetic bearings to support the outer rotor of the turbine, avoiding mechanical wear and not requiring oil for lubrication, ensuring that the gas turbine can achieve maintenance-free operation.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A magnetically levitated outer rotor inspired integrated motor for a gas turbine, the motor comprising a motor shaft and a turbine outer rotor; a motor stator, a radial magnetic bearing, and an axial magnetic bearing are fixedly sleeved on the outer wall of the motor shaft, and a plurality of radial magnetic bearings are respectively arranged at both ends of the motor shaft; the turbine outer rotor is provided with an inner hole of the outer rotor, and a motor rotor, a radial bearing rotor, and a thrust disk are fixedly embedded on the inner wall of the inner hole of the outer rotor; the motor rotor and the radial bearing rotor respectively correspond to the positions of the motor stator and the radial magnetic bearing, and the limiting parts of the axial magnetic bearing are respectively located on both axial sides of the thrust disk; the turbine outer rotor includes a compression section, a combustion section, and an expansion section, a plurality of compression impellers are fixedly arranged on the outer wall of the compression section, the combustion section is used to accommodate the fuel of the gas turbine, and a plurality of expansion impellers are fixedly arranged on the outer wall of the expansion section; both ends of the combustion section are respectively communicated with the compression section and the expansion section, and the compression section is communicated with the external air.

[0008] Preferably, the combustion section is concave in the radial direction.

[0009] Preferably, a protective bearing seat is also fixedly embedded on the inner wall of the inner hole of the outer rotor, and a protective bearing is also fixedly sleeved on the outer wall of the motor shaft; the inner ring of the protective bearing is in interference fit with the outer wall of the motor shaft, and there is a gap between the outer ring of the protective bearing and the protective bearing seat.

[0010] Preferably, the motor rotor includes a plurality of silicon steel sheets stacked axially and a plurality of permanent magnets; the silicon steel sheets are provided with inner holes for permanent magnets, and a plurality of permanent magnets are fixedly embedded in the inner holes for permanent magnets in the circumferential direction, and the plurality of permanent magnets correspond to the position of the motor stator.

[0011] Preferably, an inlet fairing is fixedly arranged at one end of the turbine outer rotor, a guide vane fairing is fixedly arranged on the motor shaft at one end of the turbine outer rotor, and an outlet fairing is fixedly arranged at the other end of the turbine outer rotor; the guide vane fairing and the inlet fairing are used to rectify the air flow at the inlet of the motor, and the outlet fairing is used to rectify the air flow at the outlet of the motor.

[0012] Preferably, an axial sensor is fixedly arranged on the guide vane fairing, and the sensing end of the axial sensor is aligned with the end face of the turbine outer rotor; the axial sensor is used to detect the axial position of the turbine outer rotor; 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 to detect the radial position of the turbine outer rotor.

[0013] Preferably, the guide vane fairing is also fixedly provided with inlet guide vanes, and a plurality of inlet guide vanes are distributed along the circumferential direction.

[0014] Preferably, a heat insulation sleeve is arranged on the inner wall of the inner hole of the outer rotor, the outer wall of the heat insulation sleeve is fixedly embedded on the inner wall of the inner hole of the outer rotor, and the motor rotor, the radial bearing rotor, and the thrust disk are all fixedly embedded in the inner hole of the heat insulation sleeve.

[0015] Preferably, the guide vane fairing is provided with a first channel communicating with the outside, the axial magnetic bearing is provided with a second channel axially penetrating therethrough, a third channel is provided between the thrust disk and the outer wall of the motor shaft; a fourth channel is provided between the radial magnetic bearing and the radial bearing rotor, the motor rotor is provided with a fifth channel axially penetrating therethrough, and the outlet fairing is provided with a sixth channel axially penetrating and communicating 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.

[0016] Preferably, the motor shaft is provided with a first wire outlet hole axially penetrating therethrough and a plurality of radial second wire outlet holes, and the first wire outlet hole is communicated with the outside of the motor shaft radially through the second wire outlet holes; the guide vane fairing is provided with a third wire outlet hole communicating with the outside, and the first wire outlet hole is communicated with the outside of the motor shaft axially through the third wire outlet hole.

[0017] The advantages of a magnetically levitated outer rotor induction integrated motor for a gas turbine using the above technical solutions of the present invention are:

[0018] During operation: 1) The motor stator is energized to drive the motor rotor to rotate, and then drive the outer rotor of the turbine to rotate. At this time, the radial magnetic bearing radially supports the outer rotor of the turbine by supporting the radial bearing rotor, and the axial magnetic bearing axially limits the outer rotor of the turbine by controlling the axial position of the thrust disk; 2) The compression impeller continuously sucks air from the atmosphere and compresses it; 3) The compressed air enters the combustion section, mixes with the injected fuel and burns to become high-temperature gas; 4) The high-temperature gas flows into the expansion section to expand and do work, driving the expansion impeller to rotate, and the rotation of the expansion impeller drives the compression impeller to rotate to complete the working process. In this way, the work capacity of the heated high-temperature gas is significantly improved. Therefore, while the expansion impeller drives the compression impeller to rotate, there is still surplus work as the output mechanical work of the gas turbine. That is, when the gas turbine starts from a standstill, it needs to be rotated by the magnetically levitated outer rotor induction integrated motor. After accelerating to be able to operate independently, the magnetically levitated outer rotor induction integrated motor becomes a generator to continuously generate electricity and supply power to other positions of the system; that is, this method combines the motor shaft system and the outer rotor of the turbine into one, and has two functions of starting and generating electricity at the same time and does not require a coupling connection, making the gas turbine structure compact and reducing the occupied space. At the same time, the radial and axial support and limit of the outer rotor of the turbine are controlled by the radial magnetic bearing and the axial magnetic bearing respectively, and the magnetic bearing does not show mechanical wear and does not require oil lubrication, ensuring that the gas turbine is maintenance-free. Brief Description of the Drawings

[0019] Figure 1 It is a schematic structural diagram of the present invention.

[0020] Figure 2 It is a schematic structural diagram of the outer rotor of the turbine.

[0021] Figure 3 、 Figure 4 is a schematic structural view of a motor rotor.

[0022] Figure 5 is a schematic structural view of a motor shaft.

[0023] Figures 6 - 9 is a schematic structural view of a guide vane fairing.

[0024] Figure 10 、 Figure 11 is a schematic structural view of an axial magnetic bearing. Detailed Embodiments

[0025] The following will explain in detail the detailed embodiments of the present invention with reference to the accompanying drawings.

[0026] Embodiment 1

[0027] As Figure 1 、 Figure 2A kind of magnetic levitation outer rotor inspired integrated motor for a gas turbine is shown. The motor includes a motor shaft 1 and a turbine outer rotor 2; a motor stator 3, a radial magnetic bearing 4 and an axial magnetic bearing 5 are fixedly sleeved on the outer wall of the motor shaft 1, and a plurality of radial magnetic bearings 4 are respectively arranged at both ends of the motor shaft 1; the turbine outer rotor 2 is provided with an inner hole of the outer rotor, and a motor rotor 21, a radial bearing rotor 22 and a thrust disk 23 are fixedly embedded on the inner wall of the inner hole of the outer rotor; the motor rotor 21 and the radial bearing rotor 22 correspond to the positions of the motor stator 3 and the radial magnetic bearing 4 respectively, and the limiting parts of the axial magnetic bearing 5 are respectively located on both axial sides of the thrust disk 23; the turbine outer rotor 2 includes a compression section 24, a combustion section 25 and an expansion section 26, a plurality of compression impellers 241 are fixedly arranged on the outer wall of the compression section 24, the combustion section 25 is used to accommodate the fuel of the gas turbine, and a plurality of expansion impellers 261 are fixedly arranged on the outer wall of the expansion section 26; both ends of the combustion section 25 are respectively communicated with the compression section 24 and the expansion section 26, and the compression section 24 is communicated with the external air. When working: 1) The motor stator 3 is energized to drive the motor rotor 21 to rotate, and then drive the turbine outer rotor 2 to rotate. At this time, the radial magnetic bearing 4 radially supports the turbine outer rotor 2 by supporting the radial bearing rotor 22, and the axial magnetic bearing 5 axially limits the turbine outer rotor 2 by controlling the axial position of the thrust disk 23; 2) The compression impellers 241 continuously suck air from the atmosphere and compress it; 3) The compressed air enters the combustion section 25, mixes with the injected fuel and burns to become high-temperature gas; 4) The high-temperature gas flows into the expansion section 26 to expand and do work, pushing the expansion impellers 261 to rotate, and the rotation of the expansion impellers 261 drives the compression impellers 241 to rotate to complete the working process. In this way, the work capacity of the heated high-temperature gas is significantly improved. Therefore, while the expansion impellers 261 drive the compression impellers 241 to rotate, there is still surplus work as the output mechanical work of the gas turbine. That is, when the gas turbine starts from rest, it needs to be rotated by the magnetic levitation outer rotor inspired integrated motor. After accelerating to be able to operate independently, the magnetic levitation outer rotor inspired integrated motor becomes a generator to continuously generate electricity and supply power to other positions of the system; that is, this method combines the motor shaft system and the turbine outer rotor into one, and has two functions of starting and generating electricity at the same time and does not require a coupling connection, making the gas turbine structure compact and reducing the occupied space. At the same time, the radial and axial support and limit of the turbine outer rotor 2 are respectively controlled by the radial magnetic bearing 4 and the axial magnetic bearing 5, and the magnetic bearing does not have mechanical wear and does not require oil lubrication, ensuring that the gas turbine is maintenance-free.

[0028] The combustion section 25 is concave in shape radially.

[0029] A protective bearing seat 27 is also fixedly embedded in the inner wall of the inner hole of the outer rotor, and a protective bearing 11 is also fixedly sleeved on the outer wall of the motor shaft 1; the inner ring of the protective bearing 11 is in interference fit with the outer wall of the motor shaft 1, and there is a gap between the outer ring of the protective bearing 11 and the protective bearing seat 27. When the equipment suddenly loses power or stops, the radial magnetic bearing 4 and the axial magnetic bearing 5 lose their magnetic force and cannot support and limit the outer rotor 2 of the turbine. At this time, the outer rotor 2 of the turbine drops and contacts the outer ring of the protective bearing 11 and is supported by the protective bearing 11; thus, damage to important parts such as the radial magnetic bearing 4 and the axial magnetic bearing 5 caused by the sudden drop of the outer rotor 2 of the turbine when the motor suddenly loses power or stops is avoided.

[0030] As Figure 3 , Figure 4 shown, the motor rotor 21 includes a plurality of silicon steel sheets 211 stacked axially and a plurality of permanent magnets 212; the silicon steel sheets 211 are provided with inner holes for permanent magnets, and the plurality of permanent magnets 212 are fixedly embedded in the inner holes for permanent magnets in the circumferential direction, and the plurality of permanent magnets 212 correspond to the position of the motor stator 3. The motor stator 3 controls the rotation of the permanent magnets 212 through magnetic force and then drives the motor rotor 21 to rotate.

[0031] As Figure 1 shown, an inlet fairing 14 is fixedly provided at one end of the outer rotor 2 of the turbine, a guide vane fairing 12 is fixedly provided on the motor shaft 1 at one end of the outer rotor 2 of the turbine, and an outlet fairing 13 is fixedly provided 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 air flow at the motor inlet, and the outlet fairing 13 is used for rectifying the air flow at the motor outlet.

[0032] As Figure 1 , Figure 5 shown, an axial sensor 121 is fixedly provided on the guide vane fairing 12, and the sensing end of the axial sensor 121 is aligned with the end face of the outer rotor 2 of the turbine; the axial sensor 121 is used to detect the axial position of the outer rotor 2 of the turbine; a radial sensor 122 is fixedly provided 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 outer rotor 2 of the turbine. The guide vane fairing 12 is also fixedly provided with inlet guide vanes 120, and the plurality of inlet guide vanes 120 are distributed along the circumferential direction.

[0033] A heat insulation sleeve 6 is provided on the inner wall of the inner hole of the 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. The motor rotor 21, the radial bearing rotor 22, and the thrust disk 23 are all 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 an extremely low thermal conductivity. It has small thermal deformation, stable performance, and excellent heat insulation performance at high temperatures. While playing a role in heat insulation, it can also ensure mechanical properties.

[0034] As Figure 1As shown, the guide vane fairing 12 is provided with a first channel 123 communicating with the outside, the axial magnetic bearing 5 is provided with an axially penetrating second channel 51, a third channel 231 is provided between the thrust disk 23 and the outer wall of the motor shaft 1; a fourth channel 232 is provided between the radial magnetic bearing 4 and the radial bearing rotor 22, the motor rotor 21 is provided with an axially penetrating fifth channel 213, and the outlet fairing 13 is provided with a sixth channel 131 axially penetrating and communicating with the outside of the motor; the first channel 123, the gap between the outer ring of the protective bearing 11 and the protective 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 to prevent the gas turbine from being damaged due to overheating.

[0035] As Figure 1 , Figure 5 shown, the motor shaft 1 is provided with an axially penetrating first wire outlet hole 101 and a plurality of radial second wire outlet holes 102, and the first wire outlet hole 101 is communicated with the outside of the motor shaft 1 radially through the second wire outlet holes 102; the guide vane fairing 12 is provided with a third wire outlet hole 103 communicating with the outside, and the first wire outlet hole 101 is communicated with the outside of the motor shaft 1 axially through the third wire outlet hole 103. The circuits of the motor stator 3, the radial magnetic bearing 4 and the axial magnetic bearing 5 are collected to the first wire outlet hole 101 through the second wire outlet holes 102, and then led out of the gas turbine through the third wire outlet hole 103.

Claims

1. A magnetic levitation outer rotor inspired integrated motor for a gas turbine, characterized in that, The motor includes a motor shaft (1) and a turbine outer rotor (2); a motor stator (3), a radial magnetic bearing (4), and an axial magnetic bearing (5) are fixedly sleeved on the outer wall of the motor shaft (1), and a plurality of radial magnetic bearings (4) are respectively arranged at both ends of the motor shaft (1); the turbine outer rotor (2) is provided with an inner hole of the outer rotor, and a motor rotor (21), a radial bearing rotor (22), and a thrust disk (23) are fixedly embedded on the inner wall of the inner hole of the outer rotor; the positions of the motor rotor (21) and the radial bearing rotor (22) correspond to those of the motor stator (3) and the radial magnetic bearing (4) respectively, and the limiting parts of the axial magnetic bearing (5) are respectively located on both axial sides of the thrust disk (23); the turbine outer rotor (2) includes a compression section (24), a combustion section (25), and an expansion section (26), a plurality of compression impellers (241) are fixedly arranged on the outer wall of the compression section (24), the combustion section (25) is used to accommodate the fuel of the gas turbine, and a plurality of expansion impellers (261) are fixedly arranged on the outer wall of the expansion section (26); both ends of the combustion section (25) are respectively communicated with the compression section (24) and the expansion section (26), and the compression section (24) is communicated with the external air; An inlet fairing (14) is fixedly arranged at one end of the turbine outer rotor (2), a guide vane fairing (12) is fixedly arranged on the motor shaft (1) at one end of the turbine outer rotor (2), and an outlet fairing (13) is fixedly arranged at the other end of the turbine outer rotor (2); the guide vane fairing (12) and the inlet fairing (14) are used for rectifying the air flow at the motor inlet, and the outlet fairing (13) is used for rectifying the air flow at the motor outlet; 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 face of the turbine outer rotor (2); the axial sensor (121) is used to detect the axial position of the turbine outer rotor (2); 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 provided with a first channel (123) communicated with the outside, the axial magnetic bearing (5) is provided with a second channel (51) axially penetrating, and a third channel (231) is arranged between the thrust disk (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) axially penetrating, and the outlet fairing (13) is provided with a sixth channel (131) axially penetrating and communicated with the outside of the motor; the first channel (123), the gap between the outer ring of the protective bearing (11) and the protective 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; The motor shaft (1) is provided with an axially penetrating first wire outlet hole (101) and a plurality of radial second wire outlet holes (102). The first wire outlet hole (101) is communicated with the radially outer part of the motor shaft (1) through the second wire 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 axially outer part of the motor shaft (1) through the third wire outlet hole (103).

2. The magnetically levitated outer rotor inspired integrated motor for a gas turbine according to claim 1, characterized in that, The combustion section (25) is concave in the radial direction.

3. The integrated motor inspired by magnetic levitation outer rotor for a gas turbine according to claim 1, characterized in that, A protective bearing seat (27) is also fixedly embedded in the inner wall of the inner hole of the outer rotor, and a protective bearing (11) is also fixedly sleeved on the outer wall of the motor shaft (1); the inner ring of the protective bearing (11) is in interference fit with the outer wall of the motor shaft (1), and there is a gap between the outer ring of the protective bearing (11) and the protective bearing seat (27).

4. The integrated motor with magnetic levitation outer rotor inspiration for a gas turbine according to claim 1, characterized in that, The motor rotor (21) includes a plurality of silicon steel sheets (211) axially stacked with each other and a plurality of permanent magnets (212); the silicon steel sheets (211) are provided with permanent magnet inner holes, and a plurality of permanent magnets (212) are fixedly embedded in the permanent magnet inner holes in the circumferential direction, and the plurality of permanent magnets (212) correspond to the positions of the motor stator (3).

5. The integrated motor with magnetic levitation outer rotor inspiration for a gas turbine according to claim 1, characterized in that, The guide vane fairing (12) is also fixedly provided with inlet guide vanes (120), and a plurality of inlet guide vanes (120) are distributed along the circumferential direction.

6. The integrated motor inspired by magnetic levitation outer rotor for a gas turbine according to claim 1, characterized in that, 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 all fixedly embedded in the inner hole of the heat insulation sleeve (6).

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