CN110953073A - Integrated gas bearing, rotor system and micro gas turbine generator set - Google Patents

Integrated gas bearing, rotor system and micro gas turbine generator set Download PDF

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Publication number
CN110953073A
CN110953073A CN201911354025.0A CN201911354025A CN110953073A CN 110953073 A CN110953073 A CN 110953073A CN 201911354025 A CN201911354025 A CN 201911354025A CN 110953073 A CN110953073 A CN 110953073A
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CN
China
Prior art keywords
bearing
thrust
bearing body
air cavity
radial
Prior art date
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Pending
Application number
CN201911354025.0A
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Chinese (zh)
Inventor
靳普
刘慕华
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Yongxu Tengfeng New Energy Power Technology Development Co ltd
Zhiyue Tengfeng Technology Group Co ltd
Original Assignee
Xunling Tengfeng Automotive Power Technology Beijing Co ltd
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Application filed by Xunling Tengfeng Automotive Power Technology Beijing Co ltd filed Critical Xunling Tengfeng Automotive Power Technology Beijing Co ltd
Priority to CN201911354025.0A priority Critical patent/CN110953073A/en
Publication of CN110953073A publication Critical patent/CN110953073A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/166—Sliding contact bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/22—Lubricating arrangements using working-fluid or other gaseous fluid as lubricant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C32/00—Bearings not otherwise provided for
    • F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
    • F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Abstract

The invention provides an integrated gas bearing, a rotor system and a micro gas turbine generator set, wherein the gas bearing is used for being arranged on a rotating shaft and comprises: the thrust disc is fixedly connected with the rotating shaft or integrally formed; the first bearing body and the second bearing body are sleeved on the rotating shaft and positioned on two sides of the thrust disc; wherein the first bearing body has a radial bearing portion and a thrust bearing portion which are integrally formed, the radial bearing portion has a predetermined radial clearance with the rotating shaft in the radial direction, and the thrust bearing portion is installed opposite to the thrust disk in the axial direction and has a predetermined first axial clearance; the second bearing body is mounted axially opposite the thrust disc with a predetermined second axial clearance. The integrated gas bearing can simultaneously support the rotating shaft in the radial direction and the axial direction, is simple to process, high in processing precision, low in assembly precision requirement, low in manufacturing cost and economical and practical.

Description

Integrated gas bearing, rotor system and micro gas turbine generator set
Technical Field
The invention relates to the technical field of bearings, in particular to an integrated gas bearing, a rotor system and a micro gas turbine generator set.
Background
Non-contact bearings are generally selected for the rotor system of ultra-high speed rotating machinery. At present, non-contact bearings generally comprise magnetic bearings and air bearings, and the air bearings rely on a pressure air film in a bearing gap to realize the support of a rotor system. Therefore, the processing precision of the bearing clearance has great influence on the performance of the air bearing; meanwhile, a thrust bearing is simultaneously used for a rotor system generating an axial force in the rotating process; in a rotor system which is simultaneously provided with a radial bearing and a thrust bearing, the precision of a bearing gap not only depends on the processing precision of the bearing, but also is influenced by the combined installation precision of the radial bearing and the thrust bearing after the radial bearing and the thrust bearing are installed in place; i.e. the perpendicularity between the thrust bearing support surface and the radial bearing support surface. Therefore, the rotor system puts higher requirements on the processing precision and the installation precision of the radial bearing and the thrust bearing, so that the manufacturing cost of the whole rotor system is greatly increased.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide an integrated gas bearing, a rotor system and a micro gas turbine generator set, wherein the integrated gas bearing can simultaneously realize radial and axial support on a rotating shaft, is simple to process, has high processing precision, low requirement on assembly precision and low manufacturing cost, and is economical and practical.
The technical scheme of the invention is as follows:
according to an aspect of the present invention, there is provided an integrated gas bearing for mounting on a rotating shaft, comprising:
the thrust disc is fixedly connected with the rotating shaft or integrally formed;
the first bearing body and the second bearing body are sleeved on the rotating shaft and positioned on two sides of the thrust disc;
wherein the first bearing body has a radial bearing portion and a thrust bearing portion which are integrally formed, the radial bearing portion has a predetermined radial clearance with the rotating shaft in the radial direction, and the thrust bearing portion is installed opposite to the thrust disk in the axial direction and has a predetermined first axial clearance;
the second bearing body is mounted axially opposite the thrust disc with a predetermined second axial clearance.
Further, the method also comprises the following steps: the bearing shell covers the peripheries of the first bearing body, the thrust disc and the second bearing body;
and the bearing end cover is arranged at one end of the second bearing body of the rotating shaft and is used for fixing the second bearing body in the axial direction.
Further, the integrated gas bearing is a hydrostatic gas bearing;
a first annular air cavity is arranged between the periphery of the radial bearing part of the first bearing body and the bearing shell, and a first through hole penetrating through the first annular air cavity and the radial gap is formed in the bottom of the first annular air cavity; a second annular air cavity is arranged between the thrust bearing part of the first bearing body and the bearing shell, and a second through hole penetrating through the second annular air cavity and the first axial gap is formed in the bottom of the second annular air cavity;
a third annular air cavity is arranged between the second bearing body and the bearing end cover, and a third through hole penetrating through the third annular air cavity and the second axial gap is formed in the bottom of the third annular air cavity;
the bearing shell is provided with a first air inlet and a second air inlet which are used for communicating the first annular air cavity and the second annular air cavity with an external air source, and the bearing end cover is provided with a third air inlet which is used for communicating the third annular air cavity with the external air source.
Further, the integrated gas bearing is a dynamic pressure gas bearing;
the inner diameter surface of the radial bearing part of the first bearing body or the part of the rotating shaft, which is provided with the radial bearing part, is provided with a dynamic pressure generating groove;
the thrust bearing part of the first bearing body faces to the end face of the thrust disc or the end face of the thrust disc faces to the thrust bearing part is provided with a dynamic pressure generating groove;
and the end surface of the second bearing body facing the thrust disc or the end surface of the thrust disc facing the second bearing body is provided with a dynamic pressure generating groove.
Further, the integrated gas bearing is a hybrid gas bearing;
a first annular air cavity is arranged between the periphery of the radial bearing part of the first bearing body and the bearing shell, and a first through hole penetrating through the first annular air cavity and the radial gap is formed in the bottom of the first annular air cavity; a second annular air cavity is arranged between the thrust bearing part of the first bearing body and the bearing shell, and a second through hole penetrating through the second annular air cavity and the first axial gap is formed in the bottom of the second annular air cavity; a third annular air cavity is arranged between the second bearing body and the bearing end cover, and a third through hole penetrating through the third annular air cavity and the second axial gap is formed in the bottom of the third annular air cavity; the bearing shell is provided with a first air inlet and a second air inlet which are used for communicating the first annular air cavity and the second annular air cavity with an external air source, and the bearing end cover is provided with a third air inlet which is used for communicating the third annular air cavity with the external air source;
the inner diameter surface of the radial bearing part of the first bearing body or the part of the rotating shaft, which is provided with the radial bearing part, is provided with a dynamic pressure generating groove; the thrust bearing part of the first bearing body faces the end face of the thrust disc or the end face of the thrust disc facing the thrust bearing part is provided with a dynamic pressure generating groove; and the end surface of the second bearing body facing the thrust disc or the end surface of the thrust disc facing the second bearing body is provided with a dynamic pressure generating groove.
Furthermore, the first through hole is a stepped hole with a large diameter at one side far away from the gap and a small diameter at one side close to the gap;
and/or the second through hole is a stepped hole with a large diameter at one side far away from the gap and a small diameter at one side close to the gap;
and/or the third through hole is a stepped hole with a large diameter at one side far away from the gap and a small diameter at one side close to the gap.
Further, an annular groove is circumferentially formed in the inner wall of the radial bearing portion of the first bearing body, and the first through hole intersects with the annular groove portion or the whole.
Furthermore, the first through holes are uniformly distributed along the circumferential direction of the radial bearing part;
and/or the first through holes are distributed along the axial direction of the radial bearing part;
and/or a plurality of second through holes are uniformly distributed on the end surface of the thrust bearing part by taking the axis of the rotating shaft as the center;
and/or the third through holes are distributed uniformly on the end surface of the second bearing body by taking the axis of the rotating shaft as the center.
Furthermore, a first air groove for guiding air is formed in one side, facing the thrust disc, of the thrust bearing part, or one side, facing the thrust bearing part, of the thrust disc, or one side, facing the thrust disc, of the second bearing body, or one side, facing the second bearing body, of the thrust disc;
and a second air groove for guiding air is arranged on the inner wall of the radial bearing part along the circumferential direction or on the circumferential surface of the radial bearing part corresponding to the rotating shaft.
Further, an anti-rotation member is arranged between the bearing housing and the first bearing body, and/or between the bearing housing and the second bearing body, and the anti-rotation member is used for fixing the first bearing body relative to the bearing housing and/or the second bearing body relative to the bearing housing in the circumferential direction.
Furthermore, the one end that first bearing body is close to the thrust dish is equipped with thrust dish holding tank, the thrust dish sets up in thrust dish holding tank, the terminal surface of second bearing body and the terminal surface butt of thrust dish holding tank.
According to another aspect of the present invention, there is provided a rotor system comprising: the integrated gas bearing described above.
According to another aspect of the invention, a micro gas turbine generator set is provided, comprising the rotor system described above.
Compared with the prior art, the invention has the following beneficial effects:
1. the integrated gas bearing can simultaneously support the rotating shaft in the radial direction and the axial direction, has simple and easy-to-operate processing technology and high processing precision, does not need to consider the precision of combined assembly in the assembly process, and has low manufacturing cost and high practicability.
2. The integrated gas bearing structure design of the invention ensures that the pressure gas film of the bearing is uniform, and the gas inlet through hole is not easy to block.
3. The integrated gas bearing is provided with the anti-rotation component, so that the bearing body cannot rotate along with the rotating shaft, the service life is long, and the stability is high.
4. The rotor system and the micro gas turbine generator set provided by the invention are low in manufacturing cost and good in operation stability.
Drawings
Fig. 1 is a structural view of an integrated gas bearing according to the present invention.
Fig. 2 is a front view of the first bearing body of the present invention.
Fig. 3 is a left side view of the first bearing body of the present invention.
Fig. 4 is a view showing the structure of the ring groove of the present invention.
Fig. 5 is a structural view of a first air tank of the present invention.
Fig. 6 is a structural view of a second air tank of the present invention.
FIG. 7 is a first view of the anti-rotation member of the present invention.
Fig. 8 is a cross-sectional view taken along a-a in fig. 7.
FIG. 9 is a second structure of the anti-rotation component of the present invention.
Fig. 10 is a cross-sectional view taken along a-a in fig. 9.
FIG. 11 is a third view of the anti-rotation member of the present invention.
Fig. 12 is a cross-sectional view taken along a-a in fig. 11.
FIG. 13 is a fourth structural view of an anti-rotation member of the present invention.
Fig. 14 is a cross-sectional view taken along a-a in fig. 13.
FIG. 15 is a fifth structural view of an anti-rotation member of the present invention.
Fig. 16 is a cross-sectional view taken along a-a in fig. 15.
FIG. 17 is a sixth view showing the construction of an anti-rotation member according to the present invention.
Fig. 18 is a cross-sectional view taken along a-a in fig. 17.
Detailed Description
In order to better understand the technical scheme of the invention, the invention is further explained by combining the specific embodiment and the attached drawings of the specification.
According to one aspect of the present invention, an integrated gas bearing is provided.
As shown in fig. 1, the integrated gas bearing of the present invention is mounted to a rotating shaft 100; it includes: a first bearing body 200, a thrust disc 300, a second bearing body 400; the thrust disc 300 is fixedly connected with the rotating shaft 100 or integrally formed; the first bearing body 200 and the second bearing body 400 are both sleeved on the rotating shaft 100 and located at two sides of the thrust disc 300; the first bearing body 200 includes a radial bearing portion 210 and a thrust bearing portion 220 which are integrally formed, the radial bearing portion 210 and the rotating shaft 100 have a predetermined radial gap S1 in the radial direction, and the thrust bearing portion 220 and the thrust disk 300 are mounted opposite to each other in the axial direction and have a predetermined first axial gap S2; the second bearing body 400 is mounted axially opposite the thrust disc 300 with a predetermined second axial gap S3.
As a preferable aspect of the present invention, the integrated gas bearing of the present invention further includes a bearing housing 500 and a bearing cap 600, the bearing housing 500 is covered on the outer peripheries of the first bearing body 200, the thrust disc 300 and the second bearing body 400, the bearing cap 600 is mounted on one end of the second bearing body 400 of the rotating shaft 100, fixes the second bearing body 400 in the axial direction, and is in transition fit with the bearing housing 500.
Specifically, the integrated gas bearing of the present invention may be any one of a static pressure gas bearing, a dynamic pressure gas bearing, or a hybrid dynamic and static pressure gas bearing.
When it is provided as a static pressure gas bearing, a first annular air chamber 230 is provided between the outer circumference of the radial bearing portion 210 of the first bearing body 200 and the bearing housing 500, and a first through hole 240 penetrating the first annular air chamber 230 and the radial gap S1 is provided at the bottom of the first annular air chamber 230.
A second annular air chamber 250 is provided between the thrust bearing portion 220 of the first bearing body 200 and the bearing housing 500, and a second through hole 260 penetrating the second annular air chamber 250 and the first axial gap S2 is provided at the bottom of the second annular air chamber 250.
A third annular air chamber 270 is arranged between the second bearing body 400 and the bearing end cover 600, and a third through hole 280 penetrating through the third annular air chamber 270 and the second axial gap S3 is arranged at the bottom of the third annular air chamber 270.
Meanwhile, the bearing housing 500 is also provided with a first air inlet 510 and a second air inlet 520 which communicate the first annular air chamber 230 and the second annular air chamber 250 with an external air source, and the bearing end cover 600 is provided with a third air inlet 610 which communicates the third annular air chamber 270 with the external air source.
Preferably, as shown in fig. 2, in the present invention, the first through hole 240, the second through hole 260, and the third through hole 280 are provided as stepped holes, specifically: the diameter of one side of the stepped hole, which is far away from the gap, is large, the diameter of one side of the stepped hole, which is close to the gap, is small, and the section of the reducing part of the stepped hole can be funnel-shaped or conical. This facilitates machining without affecting the gas pressure in the gap. Because the aperture of the air inlet hole needs to be smaller than a certain value in order to satisfy the air pressure in the gap, the air inlet hole with a small diameter is difficult to process and is easy to block.
Meanwhile, as shown in fig. 3, an annular groove 241 is circumferentially provided at an inner wall of the first bearing body 200 of the present invention, and the first through hole 240 partially or entirely intersects with the annular groove 241.
Preferably, the width W of the annular groove 241 is larger than the diameter D of the first through hole 240, the first through hole 240 is located in the annular groove 241, or the first through hole 240 is tangent to one side of the annular groove 241, or the first through hole 240 partially intersects the annular groove 241.
Preferably, the width W of the annular groove 241 is equal to the diameter D of the first through hole 240, and the first through hole 240 is tangent to both sides of the annular groove 241.
Preferably, the annular groove 241 has a width W < the diameter D of the first through hole 240, and the first through hole 240 partially intersects the annular groove 241.
Preferably, the depth H of the annular groove 241 is larger than or equal to the diameter D of the first through hole 240.
Because the first through holes 240 of the invention are partially or completely sunk into the annular groove 241, when the shaft and the inner wall of the radial bearing generate friction, the first through holes 240 in the annular groove 241 cannot be worn, so that the first through holes 240 are prevented from being blocked, and the pneumatic lubrication effect is improved; the annular groove 241 can increase the position clearance of the throttling hole, and the throttling hole oxidation caused by high temperature is effectively avoided while the rigidity of the whole bearing is ensured.
Preferably, the first through holes 240 of the present invention are provided in plural numbers, and are uniformly distributed in the circumferential direction of the radial bearing portion 210, so as to form a stable pressure air film in the circumferential direction of the rotating shaft 100, and to support the rotating shaft 100 more smoothly in the circumferential direction.
Preferably, the first through holes 240 of the present invention are provided in plurality, and are uniformly distributed in the axial direction of the radial bearing portion 210, so as to form a stable pressure air film in the axial direction of the rotating shaft 100, and to more smoothly support the rotating shaft 100 in the axial direction.
Preferably, the second through holes 260 of the present invention are provided in plural numbers, and are uniformly distributed on the end surface of the thrust bearing part 220 with the axis of the rotating shaft 100 as the center, so as to more smoothly support the rotating shaft 100 and the rotor system in the axial direction. As shown in fig. 4. Fig. 4 is a left side view of the first bearing body 200.
Preferably, the plurality of third through holes 280 of the present invention are provided and uniformly distributed on the end surface of the second bearing body 400 centering on the axis of the rotating shaft 100, so as to more stably support the rotating shaft 100 and the rotor system in the axial direction.
When the integrated gas bearing of the present invention is configured as a dynamic pressure bearing, a dynamic pressure generating groove is provided on an inner diameter surface of the radial bearing portion 210 of the first bearing body 200 or a portion of the rotating shaft 100 where the radial bearing portion 210 is installed; a dynamic pressure generating groove is provided on an end surface of the thrust bearing portion 220 of the first bearing body 200 facing the thrust disk 300 or an end surface of the thrust disk surface 300 facing the thrust bearing portion 220; a dynamic pressure generating groove is provided on an end surface of the second bearing body 400 facing the thrust disk 300 or an end surface of the thrust disk 300 facing the second bearing body 400.
Preferably, as shown in fig. 5 and 6, in the present invention, the first air groove 700 is provided on the side of the thrust bearing portion 220 facing the thrust disk 300, on the side of the thrust disk 300 facing the thrust bearing portion 220, on the side of the second bearing body 400 facing the thrust disk 300, or on the side of the thrust disk 300 facing the second bearing body 400; the inner wall of the radial bearing portion 210 is provided with a second air groove 800 along the circumferential direction or the circumferential surface of the rotating shaft 100 corresponding to the radial bearing portion 210, so as to increase the air flow rate. When the rotating shaft 100 rotates and gradually accelerates, the flowing gas existing in the bearing gap is pressed into the second air groove 800 and rapidly flows through the second air groove 800, so that the directional high-speed circulation of the gas is realized, and under the condition of meeting the bearing air pressure load, the rotating shaft 100 and the air bearing can better dissipate heat and guide flow.
Preferably, the first air grooves 700 are arc-shaped grooves which are uniformly distributed in the circumferential direction and are centrosymmetric, one end of each arc-shaped groove is adjacent to the circle center, and the other end of each arc-shaped groove is adjacent to or intersected with the circumference. The number of the arc-shaped grooves is set according to the rotating speed of the rotating shaft 100, so that the air flow rate and the pressure reach reasonable proportion, the rigidity and the load capacity of the bearing can be kept to be high under the condition that the rotating shaft 100 rotates in the forward direction or in the reverse direction, the air through flow is smooth, and the air can be prevented from being blocked in the flow channel.
Preferably, when the rotating shaft 100 rotates clockwise as viewed from the air intake direction, the arc-shaped grooves on the end surfaces of the second bearing body 400 and the thrust bearing portion 220 are left concave arcs, the arc-shaped grooves on the end surface of the thrust disc 300 are right concave arcs, and when the rotating shaft 100 rotates counterclockwise, the arc-shaped grooves on the end surfaces of the second bearing body 400 and the thrust bearing portion 220 are right concave arcs, and the arc-shaped grooves on the end surface of the thrust disc 300 are left concave arcs, so that air flows through from left to right along the axial direction.
Preferably, the first air groove 700 may be formed by forging, rolling, etching, or stamping; meanwhile, the thrust disc 300 may be made of a stainless material, which facilitates the machining of the first air groove 700.
Preferably, the second air groove 800 is shaped as a parallel diagonal groove or a spiral groove having a smaller flow capacity than the parallel diagonal groove but capable of increasing axial damping compared to the parallel diagonal groove. The circulation of air in-process, when the pitch is less, the air flow can the pressure boost that slows down, and when the pitch is great, the air flow can the acceleration rate step-down, therefore can set up the helicla flute parameter according to the rotation axis rotational speed, when the rotation axis rotational speed is high, sets up the helicla flute and be coarse pitch, and the helix clearance is loose, and when the rotation axis rotational speed was low, it is little pitch to set up the helicla flute, and the helix clearance is fine and close.
Preferably, the parallel inclined grooves are continuous or discontinuous, the lift angle of the spiral groove is α, the pitch of the spiral groove is P, the depth of the spiral groove is HL, the diameter of the rotating shaft is DL, 30 degrees < α <60 degrees, 1/2DL < P <5DL, P is 3DL, and &lTtT translation = α "&gTt α &lTt/T &gTt ═ 45 degrees, and the spiral groove is in a half-turn around the shaft or 1/3 turns.
The parallel chute or the spiral groove is arranged in a position which can keep the rigidity and the load capacity of the bearing to be strong under the condition that the rotating shaft rotates in the positive direction or the reverse direction, the air can flow smoothly, and the air can be prevented from being blocked in the flow channel.
Preferably, the second air grooves 800 in the radial bearing portion 210 are provided in the middle portion of the rotating shaft 100 corresponding to the position where the inner wall of the radial bearing portion 210 is mounted, or in two independent portions symmetrically distributed on both sides of the middle portion.
Preferably, the inlet end of the parallel inclined groove or spiral groove on the rotating shaft 100 is adjacent to the annular groove 241.
Preferably, when the rotating shaft 100 rotates clockwise as viewed from the air intake direction, the inclined direction of the parallel diagonal grooves or the helical grooves is inclined to the left, and when the rotating shaft 100 rotates counterclockwise, the inclined direction of the parallel diagonal grooves or the helical grooves is inclined to the right, so that air flows through the rotating shaft from the left to the right in the axial direction.
Preferably, the shape of the second air groove 800 further includes a herringbone shape, a V-shape, and a herringbone shape groove, or a V-shape groove is set such that the bearing can support the rotating shaft 100 in a non-contact manner in a desired manner under the condition that the rotating shaft 100 rotates in the forward direction or in the reverse direction, and has high load capacity and good stability; splayed grooves, herringbone grooves or V-shaped grooves are arranged at the positions of the rotating shaft 100 with larger load or insufficient rigidity, parallel inclined grooves or spiral grooves are arranged at the positions with insufficient through-flow, and the splayed grooves, the herringbone grooves, the V-shaped grooves and/or the parallel inclined grooves and the spiral grooves are arranged at intervals.
The ventilation efficiency of the second air groove 800 varies depending on the angle, the groove width, the number of grooves, the length, the depth, and the flatness of the second air groove 800, and the ventilation speed is related to the rotation speed of the rotation shaft 100 and the bearing gap. In addition, in reality, the cross section of the rotating shaft 100 may not be an ideal circle, and when the out-of-roundness affects the pressure of the air film during rotation, the radial distribution of the gap between the rotating shaft 100 and the radial bearing portion 210 is not uniform, the pressure of the space with a small gap becomes large and the pressure of the place with a large gap becomes small. The second air groove 800 and the annular groove 241 may be arranged in a matching manner according to actual conditions.
Preferably, the air grooves are engraved on the thrust plate 300, the rotating shaft 100 or the bearing surface in the same direction, and preferably, the air grooves are engraved on the rotating shaft 100, and since the rotating shaft 100 is hard and relatively wear-resistant, the air grooves are not easily deformed and worn when receiving an impact, wherein the air grooves are engraved at one end, both ends or a specific position of the rotating shaft 100.
Because the shaft length is longer when the rotor system is at low speed, the low-speed zero-crossing rigidity is larger, and the shaft length is longer when the rotor system is at high speed, the resistance is larger and multiplied, after grooving, the shaft rigidity is not influenced at low speed, the thrust is unchanged, the dynamic pressure working capacity is reduced when the rotor system is at high speed, air can flow to an air groove, the rigidity is reduced, the dynamic pressure actual working length is the length of the shaft minus the length of the groove, the resistance is reduced, and the length of the shaft can be increased; the flow guide is realized without reducing the rigidity of the shaft, after the air grooves are arranged, the air is guided to form directional flow at low speed, and the airflow still flows directionally when the dynamic pressure is switched at high speed, so that the impact airflow is not formed; meanwhile, after the bearing is provided with the air groove, the capacity of resisting the rotor from being disturbed and eccentrically colliding with the wall can be improved, and therefore the bearing capacity of the bearing is also improved.
When the integrated gas bearing of the present invention is configured as a hybrid bearing, it has both the features of a hydrostatic bearing and a hydrodynamic bearing.
In the present invention, since the first bearing body 200 has both the radial bearing portion 210 and the thrust bearing portion 220, it is only necessary to machine the thrust bearing portion 220 with the axial direction as a reference in the machining process, and ensure the perpendicularity between the axial direction and the action surface of the thrust bearing portion 220 or machine the inner diameter of the radial bearing portion 210 with the action surface of the thrust bearing portion 220 as a reference, and ensure the perpendicularity between the action surface of the thrust bearing portion 220 and the axial direction. The processing technology is simple and easy to operate, the processing precision is high, meanwhile, the precision of combined assembly is not required to be considered in the assembly process, and the assembly technology is simple.
As a preferred aspect of the present invention, one end of the first bearing body 200 adjacent to the thrust disc 200 is provided with a thrust disc receiving groove 290, see fig. 2. When mounted, the thrust disk 200 is placed in the thrust disk receiving groove 290, and the end surface of the second bearing body 400 abuts against the end surface of the thrust disk receiving groove 290. The design of this kind of structure, the installation of being convenient for, and installation accuracy is high.
As a preferable aspect of the present invention, an anti-rotation member 900 is disposed between the bearing housing 500 and the first bearing body 200, and/or between the bearing housing 500 and the second bearing body 400, and the anti-rotation member 900 is used for fixing the first bearing body 200 relative to the bearing housing 500 and/or the second bearing body 200 relative to the bearing housing 500 in the circumferential direction.
Specifically, one end of the anti-rotation member 900 is fixedly connected or integrally formed with the bearing housing 500, and the other end of the anti-rotation member 900 is detachably connected with the first bearing body 200 or the second bearing body 400; or, one end of the anti-rotation member 900 is detachably connected to the bearing housing 500, and the other end of the anti-rotation member 900 is fixedly connected to the first bearing body 200 or the second bearing body 400 or integrally formed therewith; the anti-rotation member 900 may be provided in one or more.
The connection between the anti-rotation member 900 and the bearing may be with the first bearing body 200 or the second bearing body 400, and because the first bearing body 200 and the second bearing body 400 are fixedly connected, the anti-rotation member 900 can prevent the bearing body from rotating circumferentially regardless of which bearing body is connected.
The specific structure of the anti-rotation member 900 of the present invention will be further explained below, and the description will be given only to the thrust bearing portion of the present integrated gas bearing, and it will be understood by those skilled in the art that the specific structure of the anti-rotation member 900 is also applicable to the radial bearing portion of the integrated gas bearing.
As shown in fig. 7 and 8, the rotation preventing member 900 may be configured as a pin and fixedly mounted on the end surface of the first bearing body 200, and the bearing housing 500 is provided with a corresponding first receiving hole 910.
Alternatively, as shown in fig. 9 and 10, the rotation preventing member 900 may be provided as a pin and fixedly mounted on an end surface of the bearing housing 500 facing the first bearing body 200, and the first bearing body 200 is provided with a corresponding second receiving hole 920.
Alternatively, as shown in fig. 11 and 12, the rotation preventing member 900 may be provided as a pin or a dowel, the rotation preventing member 900 is installed from the outer circumference of the bearing housing 500 in the radial direction of the bearing housing 500, one end of the rotation preventing member 900 is fixed to the bearing housing 500, the other end is inserted into the outer circumference of the first bearing body 200, and the outer circumference of the first bearing body 200 is provided with a corresponding third receiving hole 930.
Alternatively, as shown in fig. 13 and 14, the rotation preventing member 900 may be provided as a key and fixedly mounted on the end surface of the first bearing body 200 or integrally formed with one end surface of the first bearing body 200, and the bearing housing 500 is provided with a corresponding first key groove 940.
Alternatively, as shown in fig. 15 and 16, the rotation preventing member 900 may be a key and fixedly mounted on the inner diameter surface of the bearing housing 500, or integrally formed with the inner diameter surface of the bearing housing 500, and the first bearing body 200 is provided with a corresponding second key groove 950.
Alternatively, as shown in fig. 17 and 18, the rotation preventing member 900 may be provided with a spherical body and fixedly mounted on the end surface of the first bearing body 200, and the bearing housing 550 is provided with a corresponding hemispherical groove.
Alternatively, as shown in fig. 17 and 18, the rotation preventing member 900 may be provided with a spherical body and fixedly mounted on the end surface of the bearing housing 500 facing the first bearing body 200, and the first bearing body 200 is provided with a corresponding semi-spherical groove.
The bearing is provided with prevents changeing the component, and the bearing body can not be along with the pivot is rotatory, long service life, operation stability.
According to another aspect of the invention, the rotor system and the micro gas turbine generator set using the integrated air bearing are further provided, and the rotor system and the micro gas turbine generator set have the advantages of convenience in installation, high radial and axial verticality and good operation stability.
The micro gas turbine is a small heat engine which is newly developed, the single-machine power range of the micro gas turbine is 25-300 kW, and the basic technical characteristics are that a radial-flow impeller machine and a regenerative cycle are adopted. The micro gas turbine has a simple and compact structure, saves the installation space, is convenient for quick installation and transportation, and can well meet the small-scale and distributed requirements of distributed power supply; the moving parts are few, the structure is simple and compact, and therefore the reliability is good, and the manufacturing cost and the maintenance cost are low; good environmental adaptability and high power supply quality.
The whole system only has one moving part and adopts an air bearing, the operation reliability of the system is as high as 99.996%, and the average annual downtime and overhaul time is not more than 2 hours.
The bearing/rotor system of the invention can be used in miniature gas turbines of 10-100 KW models, such as 15/30/45KW models.
Single micro gas turbine:
the rotating speed of a 15KW micro-combustion engine with a heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 50-600 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.15m3/kWh～0.5m3/kWh. The rotating speed of a 15KW micro-combustion engine without a heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 400-1000 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.4m3/kWh～1m3/kWh。
The rotating speed of a 45KW micro-combustion engine with a heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 200-500 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.2m3/kWh～0.5m3/kWh. The rotating speed of a 45KW micro-combustion engine without a heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 400-900 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.5m3/kWh～1m3/kWh。
The foregoing description is only exemplary of the preferred embodiments of the invention and is illustrative of the principles of the technology employed. It will be appreciated by those skilled in the art that the scope of the invention herein disclosed is not limited to the particular combination of features described above, but also encompasses other arrangements formed by any combination of the above features or their equivalents without departing from the spirit of the invention. For example, the above features have similar functions to (but not limited to) those disclosed in the present invention.

Claims (13)

1. Integral type gas bearing for install in the pivot, its characterized in that includes:
the thrust disc is fixedly connected with the rotating shaft or integrally formed;
the first bearing body and the second bearing body are sleeved on the rotating shaft and positioned on two sides of the thrust disc;
wherein the first bearing body has a radial bearing portion and a thrust bearing portion which are integrally formed, the radial bearing portion has a predetermined radial clearance with the rotating shaft in the radial direction, and the thrust bearing portion is installed opposite to the thrust disk in the axial direction and has a predetermined first axial clearance;
the second bearing body is mounted axially opposite the thrust disc with a predetermined second axial clearance.
2. The integrated gas bearing of claim 1, further comprising:
the bearing shell covers the peripheries of the first bearing body, the thrust disc and the second bearing body;
and the bearing end cover is arranged at one end of the second bearing body of the rotating shaft and is used for fixing the second bearing body in the axial direction.
3. The integrated gas bearing of claim 2, wherein the integrated gas bearing is a hydrostatic gas bearing;
a first annular air cavity is arranged between the periphery of the radial bearing part of the first bearing body and the bearing shell, and a first through hole penetrating through the first annular air cavity and the radial gap is formed in the bottom of the first annular air cavity; a second annular air cavity is arranged between the thrust bearing part of the first bearing body and the bearing shell, and a second through hole penetrating through the second annular air cavity and the first axial gap is formed in the bottom of the second annular air cavity;
a third annular air cavity is arranged between the second bearing body and the bearing end cover, and a third through hole penetrating through the third annular air cavity and the second axial gap is formed in the bottom of the third annular air cavity;
the bearing shell is provided with a first air inlet and a second air inlet which are used for communicating the first annular air cavity and the second annular air cavity with an external air source, and the bearing end cover is provided with a third air inlet which is used for communicating the third annular air cavity with the external air source.
4. The integrated gas bearing according to claim 2, wherein the integrated gas bearing is a hydrodynamic gas bearing;
the inner diameter surface of the radial bearing part of the first bearing body or the part of the rotating shaft, which is provided with the radial bearing part, is provided with a dynamic pressure generating groove;
the thrust bearing part of the first bearing body faces to the end face of the thrust disc or the end face of the thrust disc faces to the thrust bearing part is provided with a dynamic pressure generating groove;
and the end surface of the second bearing body facing the thrust disc or the end surface of the thrust disc facing the second bearing body is provided with a dynamic pressure generating groove.
5. The one-piece gas bearing according to claim 2,
the integrated gas bearing is a dynamic and static pressure mixed gas bearing;
a first annular air cavity is arranged between the periphery of the radial bearing part of the first bearing body and the bearing shell, and a first through hole penetrating through the first annular air cavity and the radial gap is formed in the bottom of the first annular air cavity; a second annular air cavity is arranged between the thrust bearing part of the first bearing body and the bearing shell, and a second through hole penetrating through the second annular air cavity and the first axial gap is formed in the bottom of the second annular air cavity; a third annular air cavity is arranged between the second bearing body and the bearing end cover, and a third through hole penetrating through the third annular air cavity and the second axial gap is formed in the bottom of the third annular air cavity; the bearing shell is provided with a first air inlet and a second air inlet which are used for communicating the first annular air cavity and the second annular air cavity with an external air source, and the bearing end cover is provided with a third air inlet which is used for communicating the third annular air cavity with the external air source;
the inner diameter surface of the radial bearing part of the first bearing body or the part of the rotating shaft, which is provided with the radial bearing part, is provided with a dynamic pressure generating groove; the thrust bearing part of the first bearing body faces the end face of the thrust disc or the end face of the thrust disc facing the thrust bearing part is provided with a dynamic pressure generating groove; and the end surface of the second bearing body facing the thrust disc or the end surface of the thrust disc facing the second bearing body is provided with a dynamic pressure generating groove.
6. The integrated gas bearing according to claim 3 or 5, wherein the first through hole is a stepped hole having a large diameter on a side away from the gap and a small diameter on a side close to the gap;
and/or the second through hole is a stepped hole with a large diameter at one side far away from the gap and a small diameter at one side close to the gap;
and/or the third through hole is a stepped hole with a large diameter at one side far away from the gap and a small diameter at one side close to the gap.
7. The integrated gas bearing according to claim 6, wherein an annular groove is circumferentially provided on an inner wall of the radial bearing portion of the first bearing body, and the first through hole intersects with the annular groove portion or integrally.
8. The integrated gas bearing according to claim 3 or 5, wherein the first through-holes are plural and are uniformly distributed in a circumferential direction of the radial bearing portion;
and/or the first through holes are distributed along the axial direction of the radial bearing part;
and/or a plurality of second through holes are uniformly distributed on the end surface of the thrust bearing part by taking the axis of the rotating shaft as the center;
and/or the third through holes are distributed uniformly on the end surface of the second bearing body by taking the axis of the rotating shaft as the center.
9. The integrated gas bearing according to claim 4 or 5, wherein the thrust bearing portion side toward the thrust disk or the thrust disk side toward the thrust bearing portion, the second bearing body side toward the thrust disk or the thrust disk side toward the second bearing body is provided with a first air groove for guiding gas;
and a second air groove for guiding air is arranged on the inner wall of the radial bearing part along the circumferential direction or on the circumferential surface of the radial bearing part corresponding to the rotating shaft.
10. The integrated gas bearing according to claim 2, wherein an anti-rotation member is provided between the bearing housing and the first bearing body, and/or between the bearing housing and the second bearing body, for circumferentially fixing the first bearing body relative to the bearing housing and/or the second bearing body relative to the bearing housing.
11. The integrated gas bearing according to claim 1, wherein the first bearing body has a thrust disk receiving groove formed at an end thereof adjacent to the thrust disk, the thrust disk being disposed in the thrust disk receiving groove, and wherein the end surface of the second bearing body abuts against the end surface of the thrust disk receiving groove.
12. A rotor system, comprising: an integral gas bearing as claimed in any one of claims 1 to 11.
13. A micro gas turbine power plant comprising the rotor system of claim 12.
CN201911354025.0A 2019-12-25 2019-12-25 Integrated gas bearing, rotor system and micro gas turbine generator set Pending CN110953073A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911354025.0A CN110953073A (en) 2019-12-25 2019-12-25 Integrated gas bearing, rotor system and micro gas turbine generator set

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911354025.0A CN110953073A (en) 2019-12-25 2019-12-25 Integrated gas bearing, rotor system and micro gas turbine generator set

Publications (1)

Publication Number Publication Date
CN110953073A true CN110953073A (en) 2020-04-03

Family

ID=69983963

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911354025.0A Pending CN110953073A (en) 2019-12-25 2019-12-25 Integrated gas bearing, rotor system and micro gas turbine generator set

Country Status (1)

Country Link
CN (1) CN110953073A (en)

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