A rotor system and a micro gas turbine generator set

Abstract

The present invention provides a rotor system and a micro gas turbine generator set. The rotor system includes: a rotating shaft, which is an integrally formed structure; and a thrust bearing, a first radial bearing, a motor, a second radial bearing, a compressor, and a turbine that are sequentially arranged on the rotating shaft. Among them, a motor rotor core accommodating cavity is provided on the rotating shaft. The motor includes a motor rotor core installed in the motor rotor core accommodating cavity and a motor stator sleeved on the rotating shaft. The motor stator includes a stator core and a stator winding, and the stator winding is wound around the stator core. The first radial bearing and the second radial bearing are sleeved radially between the stator winding and the rotating shaft. The present invention uses an integral rotating shaft to connect the micro gas turbine rotor and the generator rotor, and arranges the thrust bearing at the end where the generator is located, solving the technical problem that the installation position of the thrust bearing in the prior art is restricted.

Description

Technical Field

[0001] The present invention relates to the technical field of rotor dynamics, and particularly to a rotor system and a micro gas turbine generator set. Background Art

[0002] A micro gas turbine is a newly developed small thermal engine, with a single-unit power range of 25 - 300 kW. Its basic technical features are the adoption of a radial flow turbomachine and a regenerative cycle. A micro gas turbine mainly includes three major components: a compressor, a combustion chamber, and a turbine. After air enters the compressor, it is compressed into high-temperature and high-pressure air, and then supplied to the combustion chamber to be mixed with fuel for combustion. The high-temperature and high-pressure gas generated by the combustion expands and does work in the turbine. When the rotor rotates at a high speed, the rotor will be subjected to forces in the radial direction and the axial direction. In order to limit the radial and axial movement of the rotating shaft, radial bearings and thrust bearings need to be installed in the rotor system. Traditional radial bearings and thrust bearings are both ordinary contact bearings. With the increase in the rotor speed, especially when the rotor speed exceeds 40,000 revolutions per minute, ordinary contact bearings cannot meet the requirements of the operating speed due to the large mechanical wear.

[0003] For a micro gas turbine generator set, the rotation of the generator rotor is driven by the high-speed rotation of the micro gas turbine rotor to generate electricity. In the prior art, a coupling is usually used to connect the micro gas turbine rotor and the generator rotor. The setting of the coupling limits the setting position of the thrust bearing. This is because with the increase in the rotor speed, the axial force on the rotor will further increase. If the thrust bearing is set between the compressor and the turbine, the center of gravity of the entire rotor system will shift towards the turbine side, resulting in poor stability of the rotor system. If the thrust bearing is set on the side of the coupling towards the generator, the axial force of the rotor will act entirely on the coupling, easily causing damage to the coupling.

[0004] It can be seen that there is an urgent need to provide a new rotor system to solve the above problems existing in the existing micro gas turbine generator set. Summary of the Invention

[0005] In order to solve the above technical problems, an object of the present invention is to provide a rotor system and a micro gas turbine generator set, which connect the micro gas turbine rotor and the generator rotor by an integrated rotating shaft, and set the thrust bearing at the end where the generator is located, solving the technical problem that the setting position of the thrust bearing in the prior art is restricted.

[0006] The technical solution of the present invention is as follows:

[0007] According to one aspect of the present invention, a rotor system is provided, including:

[0008] A rotating shaft, and the rotating shaft is an integrally formed structure;

[0009] And, a thrust bearing, a first radial bearing, a motor, a second radial bearing, a compressor, and a turbine that are sequentially arranged on the rotating shaft;

[0010] Wherein, a motor rotor core accommodating cavity is provided on the rotating shaft, the motor includes a motor rotor core installed in the motor rotor core accommodating cavity and a motor stator sleeved on the rotating shaft, the motor stator includes a stator core and a stator winding, and the stator winding is wound around the stator core;

[0011] The first radial bearing and the second radial bearing are sleeved between the stator winding and the rotating shaft in the radial direction.

[0012] Further, the rotating shaft includes a first shaft section and a second shaft section, the diameter of the first shaft section is larger than that of the second shaft section, and a stepped surface is formed at the transition between the first shaft section and the second shaft section;

[0013] Wherein, the thrust bearing, the first radial bearing, the motor, and the second radial bearing are arranged on the first shaft section, the compressor and the turbine are arranged on the second shaft section, and one end of the compressor abuts against the stepped surface.

[0014] Further, the first radial bearing, the second radial bearing, and the thrust bearing are all gas bearings, and any one of a hydrodynamic bearing, a hydrostatic bearing, or a hybrid hydrodynamic and hydrostatic bearing.

[0015] Further, a first radial bearing clearance is provided between the first radial bearing and the rotating shaft, and a second radial bearing clearance is provided between the second radial bearing and the rotating shaft;

[0016] A first annular air cavity is provided on the outer peripheral surface of the first radial bearing, and a plurality of bearing air holes are provided at the bottom of the first annular air cavity to communicate the first annular air cavity with the first radial bearing clearance, and a first air inlet passage for communicating the first annular air cavity with an external air source is provided on the stator winding;

[0017] A second annular air cavity is provided on the outer peripheral surface of the second radial bearing, and a plurality of bearing air holes are provided at the bottom of the second annular air cavity to communicate the second annular air cavity with the second radial bearing clearance, and a second air inlet passage for communicating the second annular air cavity with an external air source is provided on the stator winding.

[0018] Further, a second anti-rotation member is provided between the first radial bearing and the stator winding, and / or between the second radial bearing and the stator winding, and the second anti-rotation member is used for circumferentially fixing the first radial bearing and / or the second radial bearing.

[0019] Further, the thrust bearing includes a thrust disk fixedly connected or integrally formed with the rotating shaft, and a first stator and a second stator located on both sides of the thrust disk. There is a first axial gap between the first stator and the thrust disk, and a second axial gap between the second stator and the thrust disk;

[0020] Both the first axial gap and the second axial gap are communicated with an external air source.

[0021] Further, the thrust bearing further includes a bearing housing and a bearing end cover. The bearing housing covers the outer periphery of the first stator and the second stator, and the bearing end cover presses the first stator and the bearing housing from the end face of the first stator away from the thrust disk.

[0022] Further, a third annular air cavity is provided on the end face of the first stator away from the thrust disk, a third air inlet channel is provided on the bearing end cover, and a fourth air inlet channel is provided on the first stator. The third annular air cavity is communicated with the external air source through the third air inlet channel and is communicated with the first axial gap through the fourth air inlet channel;

[0023] A fourth annular air cavity is provided on the end face of the second stator away from the thrust disk, a fifth air inlet channel is provided on the bearing housing, and a sixth air inlet channel is provided on the second stator. The fourth annular air cavity is communicated with the external air source through the fifth air inlet channel and is communicated with the second axial gap through the sixth air inlet channel.

[0024] Further, the fourth air inlet channels are provided in plurality and are evenly distributed around the rotating shaft on the first stator;

[0025] The sixth air inlet channels are provided in plurality and are evenly distributed around the rotating shaft on the second stator.

[0026] Further, a first anti-rotation member is provided between the first stator and the bearing housing, and / or between the second stator and the bearing housing. The first anti-rotation member is used for fixing the first stator and / or the second stator in the circumferential direction.

[0027] Further, a ventilation hole extending along the axial direction of the rotating shaft is provided at the central position of the end of the rotating shaft away from the turbine. A through hole extending along the radial direction of the rotating shaft is provided at the bottom of the ventilation hole. The ventilation hole is communicated with the through hole, and the through hole is communicated with the bearing clearance of the radial bearing and / or the bearing clearance of the thrust bearing.

[0028] Further, a first air groove for realizing gas diversion is provided in the thrust bearing;

[0029] A second air groove for realizing gas diversion is provided on the inner wall of the first radial bearing along the circumferential direction or on the circumferential surface of the rotating shaft corresponding to the installation of the first radial bearing part, and on the inner wall of the second radial bearing along the circumferential direction or on the circumferential surface of the rotating shaft corresponding to the installation of the second radial bearing part.

[0030] Furthermore, a reinforcing ring is provided between the compressor and the turbine.

[0031] According to another aspect of the present invention, there is provided a micro gas turbine generator set, including a motor casing, a micro gas turbine casing, a combustion chamber, and the above-mentioned rotor system;

[0032] Wherein, the motor casing covers the outer periphery of the motor, the micro gas turbine casing covers the outer periphery of the compressor and the turbine, and is connected to the motor casing, the combustion chamber is connected to the micro gas turbine casing, and the air inlet of the combustion chamber is connected to the exhaust port of the compressor, and the exhaust port of the combustion chamber is connected to the air inlet of the turbine;

[0033] An air inlet passage of the compressor, an air inlet passage of the first radial bearing, and an air inlet passage of the second radial bearing are provided on the motor casing.

[0034] Furthermore, a diffuser is provided between the exhaust port of the compressor and the air inlet of the combustion.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] 1. In the present invention, the thrust bearing is arranged at the leftmost end of the entire rotor system, and its arrangement does not block the air inlet of the compressor. At the same time, the two radial bearings are arranged on both sides of the motor. When the mass of the motor is large, it will not affect the running stability of the entire rotor system; the layout of the rotor system is compact, the axial length of the rotating shaft is short, and the running stability of the rotor system at high speed is good.

[0037] 2. The rotor system of the present invention uses non-contact bearings, has a high rotational speed, and anti-rotation members are provided for both the radial bearing and the thrust bearing, which is safe and reliable and has a long service life.

[0038] 3. The present invention reduces the machining accuracy and assembly accuracy of the micro gas turbine generator set, reduces the cost, and is suitable for engineering batch production. Description of the Drawings

[0039] Figure 1 It is a structural diagram of the rotor system of the present invention.

[0040] Figure 2 It is the anti-rotation member structure of the thrust bearing of the present invention Figure 1 .

[0041] Figure 3 It is Figure 2 The cross-sectional view taken along A-A in

[0042] Figure 4 It is the anti-rotation member structure of the thrust bearing of the present invention Figure 2 .

[0043] Figure 5 It isFigure 4 Cross-sectional view along A-A in

[0044] Figure 6 Anti-rotation component structure of the thrust bearing of the present invention Figure 3 .

[0045] Figure 7 is Figure 6 Cross-sectional view along A-A in

[0046] Figure 8 Anti-rotation component structure of the thrust bearing of the present invention Figure 4 .

[0047] Figure 9 is Figure 8 Cross-sectional view along A-A in

[0048] Figure 10 Anti-rotation component structure of the thrust bearing of the present invention Figure 5 .

[0049] Figure 11 is Figure 10 Cross-sectional view along A-A in

[0050] Figure 12 Anti-rotation component structure of the thrust bearing of the present invention Figure 6 .

[0051] Figure 13 is Figure 12 Cross-sectional view along A-A in

[0052] Figure 14 Anti-rotation component structure of the radial bearing of the present invention Figure 1 .

[0053] Figure 15 is Figure 14 Cross-sectional view along A-A in

[0054] Figure 16 Anti-rotation component structure of the radial bearing of the present invention Figure 2 .

[0055] Figure 17 is Figure 16 Cross-sectional view along A-A in

[0056] Figure 18 Anti-rotation component structure of the radial bearing of the present invention Figure 3 .

[0057] Figure 19 is Figure 18 Cross-sectional view along A-A in

[0058] Figure 20 Anti-rotation component structure of the radial bearing of the present inventionFigure 4 。

[0059] Figure 21 is Figure 20 a sectional view taken along A-A in

[0060] Figure 22 the anti-rotation member structure of the radial bearing of the present invention Figure 5 。

[0061] Figure 23 is Figure 22 a sectional view taken along A-A in

[0062] Figure 24 the anti-rotation member structure of the radial bearing of the present invention Figure 6 。

[0063] Figure 25 is Figure 24 a sectional view taken along A-A in

[0064] Figure 26 the structure diagram of the first air groove of the present invention

[0065] Figure 27 the structure diagram of the second air groove of the present invention

[0066] Figure 28 the structure diagram of the micro gas turbine generator set of the present invention Detailed implementation manners

[0067] In order to better understand the technical solution of the present invention, the present invention will be further described below in conjunction with specific embodiments and the accompanying drawings of the specification.

[0068] According to one aspect of the present invention, a rotor system is provided.

[0069] As Figure 1 shown, it includes:

[0070] a rotating shaft 100, the rotating shaft 100 includes an integrally formed first shaft section 110 and a second shaft section 120, the diameter of the first shaft section 110 is greater than that of the second shaft section 120, and a stepped surface 130 is formed at the transition between the first shaft section 110 and the second shaft section 120;

[0071] a thrust bearing 200, a first radial bearing 300, a motor 400, a second radial bearing 500, a compressor 600, and a turbine 700 sequentially arranged on the rotating shaft 100; wherein, the thrust bearing 200, the first radial bearing 300, the motor 400, and the second radial bearing 500 are arranged on the first shaft section 110, the compressor 600 and the turbine 700 are arranged on the second shaft section 120, and one end of the compressor 500 abuts against the stepped surface 130;

[0072] The first shaft section 110 is provided with a motor rotor core accommodating cavity 113. The motor 400 includes a motor rotor core 410 installed in the motor rotor core accommodating cavity 113 and a motor stator 420 sleeved on the first shaft section 110. The motor stator 420 includes a stator core 421 and a stator winding 422, and the stator winding 422 is wound around the stator core 421. The first radial bearing 300 and the second radial bearing 500 are sleeved radially between the stator winding 422 and the first shaft section 110.

[0073] In the present invention, by using an integrated rotating shaft to connect the micro gas turbine rotor and the generator rotor, the technical problem in the prior art that the thrust bearing cannot be installed on the motor side is avoided. At the same time, the above rotor system has a compact layout, the axial length of the rotating shaft 100 is short, and the rotor system has good stability during high-speed operation.

[0074] In the layout of the above rotor system, the thrust bearing is arranged at the leftmost end of the entire rotor system, and its arrangement will not block the intake of the compressor 600. At the same time, the two radial bearings are arranged on both sides of the motor. When the mass of the motor is large, it will not affect the running stability of the entire rotor system.

[0075] Preferably, the first radial bearing 300, the second radial bearing 500 and the thrust bearing 200 are non-contact bearings.

[0076] Preferably, the first radial bearing 300, the second radial bearing 500 and the thrust bearing 200 are gas bearings. Specifically, it can be any one of a hydrodynamic bearing, a hydrostatic bearing or a hybrid hydrodynamic and hydrostatic bearing.

[0077] There is a first radial bearing clearance between the first radial bearing 300 and the rotating shaft 100, and there is a second radial bearing clearance between the second radial bearing 500 and the rotating shaft 100.

[0078] Preferably, a first annular air cavity 310 is provided on the outer peripheral surface of the first radial bearing 300. A plurality of bearing air holes (not shown in the figure) for communicating the first annular air cavity 310 with the first radial bearing clearance are provided at the bottom of the first annular air cavity 310. A first air inlet passage 423 for communicating the first annular air cavity 310 with an external air source is provided on the stator winding 422.

[0079] A second annular air cavity 510 is provided on the outer peripheral surface of the second radial bearing 500. A plurality of bearing air holes (not shown in the figure) for communicating the second annular air cavity 510 with the second radial bearing clearance are provided at the bottom of the second annular air cavity 510. A second air inlet passage 424 for communicating the second annular air cavity 510 with an external air source is provided on the stator winding 422.

[0080] The thrust bearing 200 includes a thrust disk 210 integrally formed with the rotating shaft 100, and a first stator 220 and a second stator 230 located on both sides of the thrust disk 210. There is a first axial gap between the first stator 220 and the thrust disk 210, and a second axial gap between the second stator 230 and the thrust disk 210. Both the first axial gap and the second axial gap are communicated with an external air source.

[0081] Preferably, the thrust bearing 200 further includes a bearing housing 240 and a bearing end cover 250. The bearing housing 240 covers the outer periphery of the first stator 220 and the second stator 230, and the bearing end cover 250 presses the first stator 220 and the bearing housing 240 from the end face of the first stator 220 away from the thrust disk 210.

[0082] Preferably, a third annular air cavity 221 is provided on the end face of the first stator 220 away from the thrust disk 210. A third air inlet passage 251 is provided on the bearing end cover 250, and a fourth air inlet passage 222 is provided on the first stator 220. The third annular air cavity 221 is communicated with the external air source through the third air inlet passage 251 and is communicated with the first axial gap through the fourth air inlet passage 222;

[0083] Among them, the fourth air inlet passage 222 can be provided in multiple numbers and is evenly distributed around the rotating shaft 100 on the first stator 220, so that the support of the first stator 220 for the thrust disk 210 is more stable.

[0084] A fourth annular air cavity 231 is provided on the end face of the second stator 230 away from the thrust disk 210. A fifth air inlet passage 241 is provided on the bearing housing 240, and a sixth air inlet passage 232 is provided on the second stator 230. The fourth annular air cavity 231 is communicated with the external air source through the fifth air inlet passage 241 and is communicated with the second axial gap through the sixth air inlet passage 232;

[0085] Among them, the sixth air inlet passage 232 can be provided in multiple numbers and is evenly distributed around the rotating shaft 100 on the second stator 230, so that the support of the second stator 230 for the thrust disk 210 is more stable.

[0086] Preferably, a ventilation hole 111 extending along the axial direction of the rotating shaft 100 is provided at the central position of one end of the first shaft section 110 away from the second shaft section 120. A through hole 112 extending along the radial direction of the rotating shaft 100 is provided at the bottom of the ventilation hole 111. The ventilation hole 111 is communicated with the through hole 112, and the through hole 112 is communicated with the bearing clearance of the thrust bearing 200 and the bearing clearance of the radial bearing. In this way, during the operation of the rotor system, the excess gas can be discharged through the ventilation hole 111 to prevent air from being trapped between the bearing and the rotating shaft, affecting the normal operation of the rotor system.

[0087] As a preferred embodiment of the present invention, in the present invention, the thrust bearing 200 adopts an anti-rotation bearing. Specifically: The thrust bearing 200 further includes a first bearing housing 240 and a first bearing end cover 250. The first bearing housing 240 covers the outer periphery of the first stator 220 and the second stator 230. The first bearing end cover 250 presses the first stator 220 and the first bearing housing 240 from the end face of the first stator 220 away from the thrust disk 210. A first anti-rotation member 260 is provided between the first bearing housing 240 and the first stator 220, and / or between the first bearing housing 240 and the second stator 230. The first anti-rotation member 260 is used to fix the first stator 220 relative to the first bearing housing 240 and / or the second stator 230 relative to the first bearing housing 240 in the circumferential direction.

[0088] Specifically, one end of the first anti-rotation member 260 is fixedly connected or integrally formed with the first bearing housing 240, and the other end of the first anti-rotation member 260 is detachably connected to the first stator 220 or the second stator 230; alternatively, one end of the first anti-rotation member 260 is detachably connected to the first bearing housing 240, and the other end of the first anti-rotation member 260 is fixedly connected or integrally formed with the first stator 220 or the second stator 230; the first anti-rotation member 260 can be provided as one or more.

[0089] In the above, the connection of the first anti-rotation member 260 to the bearing can be connected to the second stator 230 or the first stator 210. Since the second stator 230 and the first stator 220 are fixedly connected, therefore, no matter which bearing stator the first anti-rotation member 260 is connected to, it can prevent the bearing stator from rotating circumferentially.

[0090] Next, a further explanation will be given for the specific structure of the first anti-rotation member 260 of the present invention.

[0091] As shown in Figure 2 、 3 , the first anti-rotation member 260 can be provided as a pin and fixedly installed on the end face of the second stator 230, and a corresponding first receiving hole 261 is provided on the first bearing housing 240.

[0092] Or, as shown in Figure 4 、 5 , the first anti-rotation member 260 can be provided as a pin and fixedly installed on the end face of the first bearing housing 240 facing the second stator 230, and a corresponding second receiving hole 262 is provided on the second stator 230.

[0093] Or, as shown in Figure 6 、 7As shown, the first anti-rotation member 260 can be set as a pin or a dowel pin. The first anti-rotation member 260 is installed radially along the outer periphery of the first bearing housing 240. One end of the first anti-rotation member 260 is fixed to the first bearing housing 240, and the other end is inserted into the outer periphery of the second stator 230. A corresponding third receiving hole 263 is provided on the outer periphery of the second stator 230.

[0094] Alternatively, as Figure 8 、 9 shown, the first anti-rotation member 260 can be set as a key and fixedly installed on the end face of the second stator 230 or integrally formed with an end face of the second stator 230. A corresponding first keyway 264 is provided on the first bearing housing 240.

[0095] Alternatively, as Figure 10 、 11 shown, the first anti-rotation member 260 can be set as a key and fixedly installed on the inner diameter surface of the bearing housing 240 or integrally formed with the inner diameter surface of the bearing housing 240. A corresponding second keyway 265 is provided on the second stator 230.

[0096] Alternatively, as Figure 12 、 13 shown, the first anti-rotation member 260 can be set as a spherical body and fixedly installed on the end face of the second stator 230. A corresponding hemispherical groove is provided on the first bearing housing 240.

[0097] Alternatively, as Figure 12 、 13 shown, the anti-rotation member 260 can be set as a spherical body and fixedly installed on the end face of the first bearing housing 240 facing the second stator 230. A corresponding hemispherical groove is provided on the second stator 230.

[0098] This thrust bearing 200 is provided with an anti-rotation member, and the bearing stator will not rotate with the rotating shaft, having a long service life and stable operation.

[0099] As a preferred embodiment of the present invention, in the present invention, both the first radial bearing 300 and the second radial bearing 500 adopt anti-rotation bearings. Specifically: both the first radial bearing 300 and the second radial bearing include a bearing body 320, a second bearing housing 330, a second bearing end cap 340, and a second anti-rotation member 350. The bearing body 320 is sleeved on the rotating shaft 100 and maintains a predetermined gap with the rotating shaft 100. The second bearing housing 330 covers one axial end face and the outer periphery of the bearing body 320. The second bearing end cap 340 is sleeved on the rotating shaft 100 and abuts against one end face of the second bearing housing 330. The second anti-rotation member 350 is disposed between the second bearing housing 330 and the bearing body 320 and connects the two to fix the bearing body 320 in the circumferential direction. In this embodiment, the second bearing housing 330 and the second bearing end cap 340 can be disposed on the stator winding 422 or directly formed by the stator winding 422.

[0100] In this structure, one end of the second anti-rotation member 350 is fixedly connected or integrally formed with the second bearing housing 330, and the other end of the second anti-rotation member 350 is detachably connected to the third bearing body 320;

[0101] Alternatively, one end of the second anti-rotation member 350 is detachably connected to the second bearing housing 330, and the other end of the second anti-rotation member 350 is fixedly connected or integrally formed with the third bearing body 320. This connection manner of the second anti-rotation member 350 enables the installation of the second anti-rotation member 350 to be very convenient.

[0102] Specifically, the second anti-rotation member 350 can be provided as one or more.

[0103] For this anti-rotation radial bearing structure, several exemplary structures of the second anti-rotation member 350 are provided as follows.

[0104] As shown in Figure 14 and 15 , the second anti-rotation member 350 is provided as a pin and fixedly installed on the end face of the bearing body 320. A corresponding first receiving hole 331 is provided on the second bearing housing 330, and the circumferential positioning of the bearing body 320 is achieved through the pin.

[0105] Alternatively, as shown in Figure 16 and 17 , the second anti-rotation member 350 is provided as a pin and fixedly installed on the end face of the second bearing housing 330 facing the bearing body 320. A corresponding second receiving hole 321 is provided on the bearing body 320, and the circumferential positioning of the bearing body 320 is achieved through the pin.

[0106] Alternatively, as shown in Figure 18 and 19As shown, the second anti-rotation member 350 is set as a pin or a dowel pin. The second anti-rotation member 350 is installed radially along the outer circumference of the second bearing housing 330. One end of the second anti-rotation member 350 is fixed to the second bearing housing 330, and the other end is inserted into the outer circumference of the bearing body 320. A corresponding third receiving hole 322 is provided on the outer circumference of the bearing body 320, and the circumferential positioning of the bearing body 320 is achieved through the pin or the dowel pin.

[0107] Alternatively, as Figure 20 、 21 shown, the second anti-rotation member 350 is set as a key and is fixedly installed on the end face of the bearing body 320 or integrally formed with one end face of the bearing body 320. A corresponding first keyway 332 is provided on the second bearing housing 330, and the circumferential positioning of the bearing body 320 is achieved through the key.

[0108] Alternatively, as Figure 22 、 23 shown, the second anti-rotation member 350 is set as a key and is fixedly installed on the inner diameter surface of the second bearing housing 330 or integrally formed with the inner diameter surface of the second bearing housing 330. A corresponding second keyway 323 is provided on the bearing body 320, and the circumferential positioning of the bearing body 320 is achieved through the key.

[0109] Alternatively, as Figure 24 、 25 shown, the second anti-rotation member 350 is set as a spherical body and is fixedly installed on the end face of the bearing body 320. A corresponding hemispherical groove is provided on the second bearing housing 330, and the circumferential positioning of the bearing body 320 is achieved through the spherical body.

[0110] Alternatively, as Figure 24 、 25 shown, the second anti-rotation member 350 can be set as a spherical body and is fixedly installed on the end face of the second bearing housing 330 facing the bearing body 320. A corresponding hemispherical groove is provided on the bearing body 320, and the circumferential positioning of the bearing body 320 is achieved through the spherical body.

[0111] During the operation of the rotor, through the anti-rotation structure of the radial bearing, the bearing body works stably, does not rotate with the increase of the rotating speed of the rotating shaft, has reliable performance, long service life, and simple structure.

[0112] As a preferred embodiment of the present invention, as Figure 26 、 27 shown,

[0113] On one side of the first stator 220 facing the thrust disk 210 or on one side of the thrust disk 210 facing the first stator 220, and on one side of the second stator 230 facing the thrust disk 210 or on one side of the thrust disk 210 facing the second stator 230, a first air groove 270 is provided.

[0114] On the inner wall of the first radial bearing 300 along the circumferential direction or on the circumferential surface of the first radial bearing part 300 corresponding to the rotation shaft 100, and on the inner wall of the second radial bearing 500 along the circumferential direction or on the circumferential surface of the second radial bearing 500 part corresponding to the rotation shaft, a second air groove 360 for realizing gas diversion is provided to improve the air diversion rate. When the rotation shaft 100 rotates and gradually accelerates, the flowing gas existing in the bearing clearance is pressed into the second air groove 360 and flows quickly along the second air groove 360, thereby realizing the directional high-speed flow of the gas. Under the condition of satisfying the air pressure load of the bearing, the rotation shaft 100 and the air bearing can dissipate heat and conduct air better.

[0115] Preferably, the first air groove 270 is an arc-shaped groove. The arc-shaped grooves are circumferentially evenly distributed and centrosymmetric. One end of the arc-shaped groove is adjacent to the center of the circle, and the other end is adjacent to or intersects with the circumference. The number of arc-shaped grooves is set according to the rotation speed of the rotation shaft 100 so that the air flow velocity and pressure reach a reasonable ratio. When the rotation shaft 100 rotates forward or backward, the stiffness and load capacity of the bearing can be maintained, and the air flow is smooth, which can prevent air from being blocked in the flow channel.

[0116] Preferably, when viewed from the air inlet direction, when the rotation shaft 100 rotates clockwise, the arc-shaped grooves on the end faces of the first stator 220 and the second stator 230 are left concave arcs, and the arc-shaped grooves on the end face of the thrust disk 210 are right concave arcs. When the rotation shaft 100 rotates counterclockwise, the arc-shaped grooves on the end faces of the first stator 220 and the second stator 230 are right concave arcs, and the arc-shaped grooves on the end face of the thrust disk 210 are left concave arcs, so as to realize the air flow axially from left to right.

[0117] Preferably, the first air groove 270 can be formed by forging, rolling, etching or stamping; at the same time, the thrust disk 210 can be made of stainless steel material, which is convenient for the processing of the first air groove 270.

[0118] Preferably, the shape of the second air groove 360 is a parallel inclined groove or a spiral groove. Compared with the parallel inclined groove, the flow capacity of the spiral groove is smaller than that of the parallel inclined groove, but it can increase the axial damping. During the air flow process, when the pitch is small, the air flow will decelerate and increase pressure, and when the pitch is large, the air flow will accelerate and decrease pressure. Therefore, the parameters of the spiral groove can be set according to the rotation speed of the rotating shaft. When the rotation speed of the rotating shaft is high, the spiral groove is set with a large pitch and the spiral line gap is loose. When the rotation speed of the rotating shaft is low, the spiral groove is set with a small pitch and the spiral line gap is dense.

[0119] Preferably, the parallel inclined grooves are continuous or discontinuous; the lead angle of the spiral groove is α, the pitch is P, the depth of the spiral groove is HL, the diameter of the rotating shaft is DL, 30° < α < 60°, 1 / 2DL < P < 5DL; P = 3DL, α = 45°; the spiral groove winds around the shaft for half a turn or 1 / 3 of a turn.

[0120] The position of the parallel inclined grooves or the spiral grooves is set such that, when the rotating shaft rotates forward or backward, the stiffness and load capacity of the bearing can be maintained, the air flow is smooth, and air blockage in the flow channel can be prevented.

[0121] Preferably, the second air groove 360 is provided in the middle part of the position corresponding to the inner wall of the bearing body 320 where the rotating shaft 100 is installed, or is provided as two independent parts symmetrically distributed on both sides of the middle part.

[0122] Preferably, when viewed from the air inlet direction, when the rotating shaft 100 rotates clockwise, the inclination direction of the parallel inclined grooves or the spiral grooves is leftward inclination, and when the rotating shaft 100 rotates counterclockwise, the inclination direction of the parallel inclined grooves or the spiral grooves is rightward inclination, so as to realize the axial air flow from left to right.

[0123] Preferably, the shape of the second air groove 360 also includes a herringbone shape, a figure-eight shape, a V shape. The figure-eight groove, the herringbone groove or the V-shaped groove is set such that, when the rotating shaft 100 rotates forward or backward, the bearing can support the rotating shaft 100 in a non-contact manner in a desired manner, and has a high load capacity and good stability; the figure-eight groove, the herringbone groove or the V-shaped groove is provided at a position where the load of the rotating shaft 100 is large or the stiffness is insufficient, and the parallel inclined grooves or the spiral grooves are provided at a position where the air flow is insufficient. The figure-eight groove, the herringbone groove, the V-shaped groove and / or the parallel inclined grooves, the spiral grooves are arranged at intervals.

[0124] The ventilation efficiency of the second air groove 360 varies with the angle, groove width, number of grooves, length, depth and flatness of the second air groove 360. The ventilation speed is related to the rotation speed of the rotating shaft 100 and the bearing clearance. In addition, in reality, the cross-section of the rotating shaft 100 cannot be an ideal circle. When the out-of-roundness affects the pressure of the air film during rotation, the radial distribution of the clearance between the rotating shaft 100 and the bearing body 320 is uneven, the pressure in the space with a small clearance becomes larger, and the pressure in the place with a large clearance decreases. The second air groove 360 can be matched and set according to the actual working conditions.

[0125] Preferably, the air grooves in the same direction are engraved on the thrust disk 210, the rotating shaft 100 or the bearing surface. Preferably, the air grooves are engraved on the rotating shaft 100. Since the rotating shaft 100 is relatively hard and wear-resistant, when it is impacted, the air grooves are not easily deformed and worn. Among them, the air grooves are engraved at one end, both ends or specific positions of the rotating shaft 100.

[0126] When the rotor system is at low speed, the longer the shaft length, the greater the zero stiffness at low speed crossing. When at high speed, the longer the shaft length, the greater the resistance, increasing exponentially. Therefore, after grooving, the shaft stiffness is not affected at low speed and the thrust remains unchanged. At high speed, the dynamic pressure working ability decreases, the air will flow into the air grooves, the stiffness decreases, and the actual working length of the dynamic pressure is the shaft length minus the groove length, and the resistance becomes smaller, so the shaft length can be increased; it realizes guiding the flow without reducing the shaft stiffness. After setting the air grooves, the gas is guided to form a directional flow at low speed. When switching to dynamic pressure at high speed, the air flow still flows directionally and no impact air flow will be formed; at the same time, after setting the air grooves on the bearing, the ability of the rotor to resist the disturbance of eccentric wall collision can be improved, thereby also improving the bearing capacity of the bearing.

[0127] As a preferred embodiment of the present invention, in order to reduce the influence of the heat conduction of the hot end of the turbine on the efficiency of the compressor 600, the turbine of the turbine 700 can be made of a ceramic turbine material or other materials with a lower thermal conductivity.

[0128] As a preferred embodiment of the present invention, a reinforcing ring 900 is provided between the compressor 600 and the turbine 700.

[0129] Considering the rotor dynamics performance, the lighter the weight of the rotating shaft 100, the better. And the smaller the diameter of the rotating shaft 100, the lighter the weight. However, during the high-speed rotation of the rotor system, there are very high requirements for the strength of the rotating shaft 100. In order to consider both the rotor dynamics characteristics and the strength of the rotating shaft 100, the shaft diameter of the second shaft section 120 can be set thinner, and at the same time, a reinforcing ring 900 is installed between the compressor 600 and the turbine 700 to meet the requirements for the rotor stiffness.

[0130] According to another aspect of the present invention, the present invention also provides a micro gas turbine generator set using the above rotor system, see Figure 28 . The generator set includes:

[0131] The above rotor system, the motor casing 810, the micro gas turbine casing 820 and the combustion chamber 830; the motor casing 810 covers the outer periphery of the motor 400, the micro gas turbine casing 820 covers the outer periphery of the compressor 600 and the turbine 700, and is connected to the motor casing 810. The combustion chamber 830 is connected to the micro gas turbine casing 820, and the intake port of the combustion chamber 830 is connected to the exhaust port of the compressor 600, and the exhaust port of the combustion chamber 830 is connected to the intake port of the turbine 700.

[0132] The motor casing 810 is provided with the seventh intake passage 811 of the compressor 700, the seventh intake passage 812 of the first radial bearing 300, and the seventh intake passage 813 of the second radial bearing 500.

[0133] Preferably, a diffuser 840 is provided between the exhaust port of the compressor 600 and the intake port of the combustion chamber 830 to further increase the pressure of the high-temperature and high-pressure gas entering the turbine 700 for work.

[0134] In the micro gas turbine generator set of the present invention, all bearings are arranged inside the motor casing 810. Thus, it is only necessary to ensure the machining accuracy of the part inside the casing for arranging the bearing stator. During assembly, the part inside the casing for connecting the bearing stator can be completed through one-time clamping and machining. It can be seen that the present invention reduces the machining accuracy and assembly accuracy of the micro gas turbine generator set, reduces the cost, and is suitable for engineering batch production. At the same time, the micro gas turbine generator set of the present invention has a compact layout, the axial length of the rotating shaft 100 is short, and the rotor system has good stability during high-speed operation.

[0135] The micro gas turbine of the present invention has a simple and very compact structure, saves installation space, is convenient for quick installation and handling, and can well meet the small-scale and decentralized demands of distributed power supply; it has few moving parts and a simple and compact structure, so it has good reliability, low manufacturing cost and maintenance cost; it has the advantages of good environmental adaptability and high power supply quality.

[0136] The whole system has only one moving part and uses an air bearing, and its operation reliability rate is as high as 99.996%. The average annual shutdown and maintenance time does not exceed 2 hours. The rotor system of the present invention can be used in micro gas turbines with a capacity of 10 - 100 KW, such as 15 / 30 / 45 KW models.

[0137] Single micro gas turbine:

[0138] The 15KW micro gas turbine with a recuperator has a rotational speed of 0 - 140000 RPM. When the fuel is kerosene, the fuel consumption is 50 g / kWh - 600 g / kWh; when the fuel is natural gas, the natural gas consumption is 0.15 m 3 / kWh - 0.5 m 3 / kWh. The 15KW micro gas turbine without a recuperator has a rotational speed of 0 - 140000 RPM. When the fuel is kerosene, the fuel consumption is 400 g / kWh - 1000 g / kWh; when the fuel is natural gas, the natural gas consumption is 0.4 m 3 / kWh - 1 m 3 / kWh.

[0139] The 45KW micro gas turbine with a recuperator has a rotational speed of 0 - 80000 RPM. When the fuel is kerosene, the fuel consumption is 200 g / kWh - 500 g / kWh; when the fuel is natural gas, the natural gas consumption is 0.2 m 3 / kWh - 0.5 m 3 / kWh. The rotational speed of a 45KW micro gas turbine without a recuperator is 0 - 80,000 RPM. When the fuel is kerosene, the fuel consumption is 400g / kWh - 900g / kWh; when the fuel is natural gas, the natural gas consumption is 0.5m 3 / kWh - 1m 3 / kWh.

[0140] The above description is only the preferred embodiment of the present application and the explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solutions formed by the specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features have similar functions to those disclosed in the present application (but not limited to).

Claims

1. A rotor system, characterized in that, it includes: a rotating shaft, and the rotating shaft is an integrally formed structure; and, a thrust bearing, a first radial bearing, a motor, a second radial bearing, a compressor, and a turbine sequentially arranged on the rotating shaft; wherein, a motor rotor core accommodating cavity is provided on the rotating shaft, the motor includes a motor rotor core installed in the motor rotor core accommodating cavity and a motor stator sleeved on the rotating shaft, the motor stator includes a stator core and a stator winding, and the stator winding is wound around the stator core; the first radial bearing and the second radial bearing are sleeved between the stator winding and the rotating shaft in the radial direction; the first radial bearing, the second radial bearing, and the thrust bearing are all gas bearings, and any one of them is a hydrodynamic bearing, a hydrostatic bearing, or a hybrid hydrodynamic and hydrostatic bearing; a ventilation hole extending axially along the rotating shaft is provided at the central position of one end of the rotating shaft away from the turbine, a through hole extending radially along the rotating shaft is provided at the bottom of the ventilation hole, the ventilation hole communicates with the through hole, and the through hole communicates with the bearing clearance of the radial bearing and / or the bearing clearance of the thrust bearing.

2. The rotor system according to claim 1, characterized in that, the rotating shaft includes a first shaft section and a second shaft section, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition between the first shaft section and the second shaft section; wherein, the thrust bearing, the first radial bearing, the motor, and the second radial bearing are arranged on the first shaft section, the compressor and the turbine are arranged on the second shaft section, and one end of the compressor abuts against the step surface.

3. The rotor system according to claim 1, characterized in that, a first radial bearing clearance exists between the first radial bearing and the rotating shaft, and a second radial bearing clearance exists between the second radial bearing and the rotating shaft; a first annular air cavity is provided on the outer peripheral surface of the first radial bearing, and a plurality of bearing air holes connecting the first annular air cavity with the first radial bearing clearance are provided at the bottom of the first annular air cavity, and a first air inlet passage connecting the first annular air cavity with an external air source is provided on the stator winding; a second annular air cavity is provided on the outer peripheral surface of the second radial bearing, and a plurality of bearing air holes connecting the second annular air cavity with the second radial bearing clearance are provided at the bottom of the second annular air cavity, and a second air inlet passage connecting the second annular air cavity with an external air source is provided on the stator winding.

4. The rotor system according to claim 1, characterized in that, a second anti-rotation member is provided between the first radial bearing and the stator winding, and / or between the second radial bearing and the stator winding, and the second anti-rotation member is used for fixing the first radial bearing and / or the second radial bearing in the circumferential direction.

5. The rotor system according to claim 1, characterized in that, the thrust bearing includes a thrust disk fixedly connected or integrally formed with the rotating shaft and a first stator and a second stator located on both sides of the thrust disk, a first axial clearance exists between the first stator and the thrust disk, and a second axial clearance exists between the second stator and the thrust disk; both the first axial clearance and the second axial clearance communicate with an external air source.

6. The rotor system according to claim 5, characterized in that, The thrust bearing further includes a bearing housing and a bearing end cover. The bearing housing covers the outer peripheries of the first stator and the second stator, and the bearing end cover presses the first stator and the bearing housing from the end face of the first stator away from the thrust disk.

7. The rotor system according to claim 6, wherein, a third annular air chamber is provided on the end face of the first stator away from the thrust disk, a third air inlet passage is provided on the bearing end cover, a fourth air inlet passage is provided on the first stator, and the third annular air chamber is communicated with an external air source through the third air inlet passage and is communicated with the first axial gap through the fourth air inlet passage; a fourth annular air chamber is provided on the end face of the second stator away from the thrust disk, a fifth air inlet passage is provided on the bearing housing, a sixth air inlet passage is provided on the second stator, and the fourth annular air chamber is communicated with an external air source through the fifth air inlet passage and is communicated with the second axial gap through the sixth air inlet passage.

8. The rotor system according to claim 7, wherein, the fourth air inlet passages are provided in plurality and are evenly distributed around the rotating shaft on the first stator; the sixth air inlet passages are provided in plurality and are evenly distributed around the rotating shaft on the second stator.

9. The rotor system according to claim 6, wherein, a first anti-rotation member is provided between the first stator and the bearing housing, and / or between the second stator and the bearing housing, and the first anti-rotation member is used for fixing the first stator and / or the second stator in the circumferential direction.

10. The rotor system according to claim 1, wherein, a first air groove for realizing gas diversion is provided in the thrust bearing; a second air groove for realizing gas diversion is provided on the inner wall of the first radial bearing along the circumferential direction or on the circumferential surface of the rotating shaft corresponding to the installation of the first radial bearing portion, and on the inner wall of the second radial bearing along the circumferential direction or on the circumferential surface of the rotating shaft corresponding to the installation of the second radial bearing portion.

11. The rotor system according to claim 1, wherein, a reinforcing ring is provided between the compressor and the turbine.

12. A micro gas turbine generator set, wherein, comprising a motor casing, a micro gas turbine casing, a combustion chamber, and the rotor system according to any one of claims 1-11; wherein, the motor casing covers the outer periphery of the motor, the micro gas turbine casing covers the outer peripheries of the compressor and the turbine and is connected to the motor casing, the combustion chamber is connected to the micro gas turbine casing, and the air inlet of the combustion chamber is connected to the exhaust port of the compressor, and the exhaust port of the combustion chamber is connected to the air inlet of the turbine; an air inlet passage of the compressor, an air inlet passage of the first radial bearing, and an air inlet passage of the second radial bearing are provided on the motor casing.

13. The micro gas turbine generator set according to claim 12, wherein, a diffuser is provided between the exhaust port of the compressor and the air inlet of the combustion.

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