CN212429023U - Fixed-gap rotor system and micro gas turbine generator set - Google Patents
Fixed-gap rotor system and micro gas turbine generator set Download PDFInfo
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- CN212429023U CN212429023U CN202020120455.8U CN202020120455U CN212429023U CN 212429023 U CN212429023 U CN 212429023U CN 202020120455 U CN202020120455 U CN 202020120455U CN 212429023 U CN212429023 U CN 212429023U
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Abstract
The utility model provides a decide crack formula rotor system and miniature gas turbine generating set, rotor system include the pivot, set gradually in changeing epaxial motor, compressor and turbine, miniature gas turbine machine casket is established to the periphery cover of compressor and turbine, the motor both ends set up air bearing, and the air bearing and the miniature gas turbine machine casket that are close to compressor one end are through deciding crack dish fixed connection. The utility model discloses with the cartridge receiver through rigid structure such as fixed gap part directly continuous with the bearing, can be so that the rotor drives the bearing displacement when, whole cartridge receiver moves along with the bearing, the displacement of rotor and impeller is constant amplitude and synchronous, the displacement of bearing and cartridge receiver also is constant amplitude and synchronous, clearance between impeller and the cartridge receiver can be done very little like this, greatly is favorable to controlling the pneumatic leakage loss of apex, improves the efficiency of impeller.
Description
Technical Field
The utility model relates to a rotor dynamics technical field, concretely relates to decide crack formula rotor system and miniature gas turbine generating set.
Background
In the field of micro gas turbine power generation, a micro gas turbine power generator set generally includes a coaxially mounted generator and a micro gas turbine. Specifically, the micro gas turbine mainly comprises three parts, namely a compressor, a combustion chamber and a turbine. The air is compressed into high-temperature and high-pressure air after entering the air compressor, then the high-temperature and high-pressure air is supplied to the combustion chamber to be mixed and combusted with fuel, the generated high-temperature and high-pressure gas expands in the turbine to do work, the turbine is pushed to rotate, and the generator is driven to generate electricity.
For a rotor system of a micro gas turbine, the rotor is mostly high in rotating speed of more than 40000 revolutions per minute, a common contact type bearing has large mechanical abrasion and cannot meet the requirement of working rotating speed, and a non-contact type radial bearing and a thrust bearing are adopted to limit the rotating shaft to move in the radial direction and the axial direction. For the non-contact bearing, the bearing is connected with the damper, the damper is connected with the stator, and the damper has a certain thickness, so that the gap between the bearing and the stator is formed, when the rotor is provided with the impeller, the gap of the damper is often as small as or even smaller than the gap of the blade tip of the impeller, if the tilting angle under the condition of the cantilever of the impeller is added, the displacement is often unacceptable for the gap of the blade tip, the stator and the bearing are required to have extremely high processing precision and assembly precision, otherwise, the phenomena of impeller collision and clamping are easily generated, or the bearing is abraded and damaged.
Disclosure of Invention
In order to solve the technical problem, an object of the utility model is to provide a decide crack formula rotor system and miniature gas turbine generating set.
The technical scheme of the utility model as follows:
according to the utility model discloses an aspect provides a fixed-gap rotor system, include the pivot, set gradually in changeing epaxial motor, compressor and turbine, miniature gas turbine machine casket is established to the periphery cover of compressor and turbine, the motor both ends set up air bearing, and the air bearing who is close to compressor one end passes through rigidity piece fixed connection with miniature gas turbine machine casket.
Furthermore, elastic pieces are arranged on the outer wall of the air bearing and the micro gas turbine casing.
Further, the elastic part is a damper, the damper is a metal or nonmetal damper, and the damper is annular;
the metal damper is a foil damper or a spring damper; the nonmetal damper is an O-ring or hollow cylindrical rubber or rubber damper.
Further, the rigid part is a fixed-gap disc, the fixed-gap disc is provided with a first connecting body and a second connecting body, the first connecting body and the second connecting body are integrally formed through a transition body, the first connecting body is fixedly connected with an air bearing close to one end of the gas compressor, and the second connecting body is fixedly connected with the micro gas turbine casing.
Furthermore, the first connecting body and the second connecting body are both annular, and an inner ring of the annular first connecting body is sleeved with the outer diameter of the air bearing, or the non-transitional end face of the annular first connecting body is attached to the end face of the air bearing;
the inner ring of the annular second connector surrounds the inlet of the gas compressor, and the non-transition end face of the second connector is attached to the end face of the micro gas turbine casing.
Furthermore, when the inner ring of the annular first connecting body is sleeved with the outer diameter of the air bearing, the inner ring of the first connecting body is in interference fit with the outer diameter of the air bearing, or when the non-transitional end face of the annular first connecting body is attached to the end face of the air bearing, the inner ring of the first connecting body is equal to the inner diameter of the air bearing;
and the outer ring of the annular second connecting body is close to the outer ring of the micro gas turbine casing.
Further, the first connecting body and the air bearing are fixedly connected in a welding, riveting or interference sleeving manner;
the second connector is fixedly connected with the micro gas turbine casing in a welding, riveting or fastener mode.
Furthermore, the transition body is formed into a conical shape or a barrel shape, and a vent groove is formed in the end face of the conical shape or the barrel shape; the air channel is a plurality of, and the air channel distributes along axle center central symmetry formula.
According to the utility model discloses an on the other hand provides a miniature gas turbine generating set, including foretell fixed-gap formula rotor system, motor machine casket and combustion chamber, the periphery of motor is located to the motor machine casket cover and is connected with miniature gas turbine machine casket, the combustion chamber is connected with miniature gas and turbine machine casket and the air inlet of combustion chamber is connected with the gas vent of compressor, and the gas vent of combustion chamber is connected with the air inlet of turbine.
Furthermore, the miniature gas turbine machine casket passes through perpendicular terminal surface and the butt joint of motor flange, and the miniature gas turbine machine casket cup joints in the combustion chamber through outer periphery, the attenuator set up with motor complex on the perpendicular terminal surface, and/or with the outer periphery of combustion chamber complex, pass through fastener fixed connection between miniature gas turbine machine casket and the motor and miniature gas turbine machine casket and the combustion chamber.
The utility model has the advantages that:
1. the utility model discloses a with structures such as spiral case or machine casket, through rigid structure such as fixed gap part directly links to each other with the bearing, and make the follow-up machine casket with the real shell body or the stator machine casket that will fix and use the attenuator the same or similar clearance with the bearing outside the machine casket, can make when the rotor drives the bearing displacement, whole machine casket moves along with the bearing, the displacement of rotor and impeller is constant amplitude and synchronous, the bearing also is constant amplitude and synchronous with the displacement of machine casket, clearance between impeller and the machine casket can be done very little like this, greatly be favorable to controlling the pneumatic leakage loss of apex, improve the efficiency of impeller.
2. The utility model discloses an integrative rigid coupling structure can balance the resonance that arouses when excitation frequency that the unbalanced force of rotor produced is unanimous with the natural frequency of rotor and supporting system to make rotor system pass through the resonance mode fast safely, reduce the disturbance that causes rotor system, very big improvement the work efficiency of turbine with the compressor.
Drawings
FIG. 1 is a schematic structural view of a gap-fixed rotor system.
Fig. 2 is an enlarged view of a portion a in fig. 1.
Fig. 3 is a first structural schematic diagram of a fixed-gap disk of a gap-fixed rotor system.
Fig. 4 is a schematic structural diagram of a fixed-gap disk of a gap-fixed rotor system.
Detailed Description
In order to better understand the technical solution of the present invention, the present invention will be further explained with reference to the following specific embodiments and the accompanying drawings.
According to an aspect of the present invention, the embodiment of the present invention provides a fixed gap type rotor system.
As shown in fig. 1, the gas turbine comprises a rotating shaft 2, wherein the rotating shaft 2 is provided with 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, a step surface is formed at the transition position of the first shaft section and the second shaft section, a motor 3, a gas compressor 4 and a turbine 5 are sequentially arranged on the rotating shaft 2, the motor 3 is arranged on the first shaft section through an air bearing 1, the gas compressor 4 and the turbine 5 are arranged on the second shaft section, one end of the gas compressor 4 is abutted against the step surface, the air bearing 1 is arranged at two ends of the motor 3, and the air bearing 1 close to one end of the gas compressor 4 is fixedly connected with a micro gas turbine casing 7 sleeved on the peripheries of the gas compressor.
Preferably, a damper 10 is disposed on an outer wall of the air bearing 1.
Preferably, as shown in fig. 2, the micro gas turbine casing 7 is further provided with a damper 10.
Preferably, the damper 10 may be a metal or nonmetal damper, and the damper 10 is configured in a ring shape.
Preferably, the metal damper is a foil damper or a spring damper; the nonmetal damper is an O-ring or hollow cylindrical rubber or rubber damper.
In the embodiment, the air bearing 1 is connected with the micro gas turbine casing 7 through the rigid fixed-gap disc 9, the micro gas turbine casing 7 and the dampers with the same or similar gaps are arranged at the air bearing 1 to be made into follow-up casings, so that when the rotating shaft 2 drives the air bearing 1 to move, the whole casing moves along with the bearing, the displacements of the rotating shaft and the impeller are in equal amplitude and synchronous, and the displacements of the air bearing 1 and the micro gas turbine casing 7 are also in equal amplitude and synchronous, therefore, the gap between the impeller and the micro gas turbine casing 7 can be made to be very small, the pneumatic leakage loss of the blade tip can be controlled greatly, and the efficiency of the impeller is improved.
As shown in fig. 3 and 4, the two kinds of fixed-gap disks of the gap-fixed rotor system according to the embodiment of the present invention are schematically shown. The fixed-gap disc 9 is provided with a first connecting body and a second connecting body, the first connecting body and the second connecting body are integrally formed through a transition body, the first connecting body is fixedly connected with the air bearing 1 close to one end of the gas compressor 4, and the second connecting body is fixedly connected with the micro gas turbine casing 7.
Preferably, the first connecting body and the second connecting body are both annular, the inner ring of the annular first connecting body is sleeved with the outer diameter of the air bearing 1 or the non-transition end face of the annular first connecting body is attached to the end face of the air bearing 1, the inner ring of the annular second connecting body surrounds the inlet of the air compressor 4, and the non-transition end face of the second connecting body is attached to the end face of the micro gas turbine casing 7.
Preferably, when the inner ring of the annular first connecting body is sleeved with the outer diameter of the air bearing 1, the inner ring of the first connecting body is in interference fit with the outer diameter of the air bearing 1, or when the non-transitional end face of the annular first connecting body is attached to the end face of the air bearing 1, the inner ring of the first connecting body is equal to the inner diameter of the air bearing 1, and the outer ring of the annular second connecting body is close to the outer ring of the micro gas turbine casing 7, so that the air intake efficiency is improved on the basis of increasing the air intake amount.
Preferably, the first connecting body is fixedly connected with the air bearing 1 by welding, riveting or interference sleeve, and the second connecting body is fixedly connected with the micro gas turbine casing 7 by welding, riveting or fastening.
Preferably, the transition body is formed into a conical shape or a barrel shape, and the conical surface or the barrel-shaped end surface is provided with a vent groove.
Preferably, the number of the vent grooves is multiple, the vent grooves are distributed along the center of the axis in a symmetrical mode, and the air inlet channel area of the vent grooves can ensure the air inlet efficiency of the micro gas turbine.
According to the utility model discloses an on the other hand, the embodiment of the utility model provides a still provide a miniature gas turbine generating set, this generator unit includes: the rotor system comprises a motor casing 6, a micro gas turbine casing 7 and a combustion chamber 8, wherein the motor casing 6 covers the periphery of the motor 3, the micro gas turbine casing 7 covers the peripheries of the compressor 4 and the turbine 5 and is connected with the motor casing 6, the combustion chamber 8 is connected with the micro gas turbine casing 7, an air inlet of the combustion chamber 8 is connected with an air outlet of the compressor 4, and an air outlet of the combustion chamber 8 is connected with an air inlet of the turbine 5.
Preferably, as shown in fig. 2, the micro gas turbine casing 7 is in flange joint with the electric motor 3 through a vertical end surface, the micro gas turbine casing 7 is sleeved in the combustion chamber 8 through an outer circumferential surface, the damper 10 is arranged on the vertical end surface matched with the electric motor 3 and/or the outer circumferential surface matched with the combustion chamber 8, and the micro gas turbine casing 7 and the electric motor 3, and the micro gas turbine casing 7 and the combustion chamber 8 are fixed through fasteners.
Preferably, a diffuser is disposed between the exhaust port of the compressor 4 and the intake port of the combustion chamber 8 to further increase the pressure of the high-temperature and high-pressure gas entering the turbine 5 to perform work.
In the gas turbine generator set of this embodiment, the bearing sets up in motor machine casket 6, only need guarantee like this in this machine casket be used for setting up the machining precision of the position of bearing stator can, the position that is used for connecting the bearing stator in this machine casket can be accomplished through the processing of once installing the card when the assembly, and it is thus clear that this embodiment has reduced gas turbine generator set's machining precision and assembly precision, and the cost is reduced is fit for engineering batch production.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be understood by those skilled in the art that the scope of the present invention is not limited to the specific combination of the above-mentioned features, but also covers other embodiments formed by any combination of the above-mentioned features or their equivalents without departing from the spirit of the present invention. For example, the features described above have similar functions to (but are not limited to) those disclosed in this application.
Claims (10)
1. The utility model provides a decide clearance formula rotor system, its characterized in that includes the pivot, sets gradually in epaxial motor, compressor and turbine, miniature gas turbine machine casket is established to the periphery cover of compressor and turbine, the motor both ends set up air bearing, and the air bearing and the miniature gas turbine machine casket that are close to compressor one end pass through rigid component fixed connection.
2. The fixed clearance rotor system of claim 1, wherein a resilient member is disposed on both the outer air bearing wall and the micro gas turbine case.
3. The fixed-gap rotor system as claimed in claim 2, wherein the elastic member is a damper, the damper is a metal or non-metal damper, and the damper is provided in a ring shape;
the metal damper is a foil damper or a spring damper; the nonmetal damper is an O-ring or hollow cylindrical rubber or rubber damper.
4. The constant gap rotor system as claimed in claim 1, wherein the rigid member is a constant gap disk having a first connecting body and a second connecting body integrally formed with each other through a transition body, the first connecting body is fixedly connected to an air bearing near one end of the compressor, and the second connecting body is fixedly connected to the micro gas turbine casing.
5. The constant gap rotor system as claimed in claim 4, wherein the first connecting body and the second connecting body are both annular, and the inner ring of the annular first connecting body is sleeved with the outer diameter of the air bearing, or the non-transitional end face of the annular first connecting body is attached to the end face of the air bearing;
the inner ring of the annular second connector surrounds the inlet of the gas compressor, and the non-transition end face of the second connector is attached to the end face of the micro gas turbine casing.
6. The constant gap rotor system as claimed in claim 5, wherein the inner race of the first annular connecting body is in interference fit with the outer diameter of the air bearing when the inner race of the first annular connecting body is sleeved with the outer diameter of the air bearing, or the inner race of the first annular connecting body is equal to the inner diameter of the air bearing when the non-transitional end face of the first annular connecting body is attached to the end face of the air bearing;
and the outer ring of the annular second connecting body is close to the outer ring of the micro gas turbine casing.
7. The fixed-gap rotor system as claimed in claim 4, wherein the first connecting body is fixedly connected with the air bearing by welding, riveting or interference fit;
the second connector is fixedly connected with the micro gas turbine casing in a welding, riveting or fastener mode.
8. The fixed-gap rotor system as claimed in claim 4, wherein the transition body is formed in a conical or barrel shape, and a vent groove is provided on the conical surface or barrel end surface; the air channel is a plurality of, and the air channel distributes along axle center central symmetry formula.
9. A micro gas turbine generator set is characterized by comprising the fixed-gap rotor system, a motor casing and a combustion chamber according to any one of claims 1 to 8, wherein the motor casing is covered on the periphery of a motor and is connected with the micro gas turbine casing, the combustion chamber is connected with the micro gas turbine and the turbine casing, an air inlet of the combustion chamber is connected with an air outlet of an air compressor, and an air outlet of the combustion chamber is connected with an air inlet of a turbine.
10. A micro gas turbine generator set, characterized by comprising the fixed-gap rotor system, the motor casing and the combustion chamber of claim 3, wherein the motor casing is covered on the periphery of the motor and is connected with the micro gas turbine casing, the combustion chamber is connected with the micro gas turbine and the turbine casing, the air inlet of the combustion chamber is connected with the air outlet of the air compressor, and the air outlet of the combustion chamber is connected with the air inlet of the turbine;
the miniature gas turbine machine casket passes through perpendicular terminal surface and motor flange butt joint, and the miniature gas turbine machine casket cup joints in the combustion chamber through outer periphery, the attenuator set up with motor complex on the perpendicular terminal surface, and/or with the outer periphery of combustion chamber complex, pass through fastener fixed connection between miniature gas turbine machine casket and the motor and miniature gas turbine machine casket and the combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020120455.8U CN212429023U (en) | 2020-01-19 | 2020-01-19 | Fixed-gap rotor system and micro gas turbine generator set |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020120455.8U CN212429023U (en) | 2020-01-19 | 2020-01-19 | Fixed-gap rotor system and micro gas turbine generator set |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212429023U true CN212429023U (en) | 2021-01-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020120455.8U Active CN212429023U (en) | 2020-01-19 | 2020-01-19 | Fixed-gap rotor system and micro gas turbine generator set |
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|---|---|
| CN (1) | CN212429023U (en) |
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- 2020-01-19 CN CN202020120455.8U patent/CN212429023U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210322 Address after: 100176 room 1202a, block B, Chaolin Plaza, No.19, Ronghua Middle Road, economic and Technological Development Zone, Daxing District, Beijing Patentee after: Jin Pu Address before: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Patentee before: Zhiyue Tengfeng Technology Group Co.,Ltd. Patentee before: XUNLING TENGFENG AUTOMOTIVE POWER TECHNOLOGY (BEIJING) Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230426 Address after: 518063 10 Nanshan District Road, Gaoxin south, Nanshan District, Shenzhen, Guangdong. Patentee after: Liu Muhua Address before: 100176 room 1202a, block B, Chaolin Plaza, No.19, Ronghua Middle Road, economic and Technological Development Zone, Daxing District, Beijing Patentee before: Jin Pu |