CN111022185A - Turbine and rotor system with gland - Google Patents
Turbine and rotor system with gland Download PDFInfo
- Publication number
- CN111022185A CN111022185A CN201911353086.5A CN201911353086A CN111022185A CN 111022185 A CN111022185 A CN 111022185A CN 201911353086 A CN201911353086 A CN 201911353086A CN 111022185 A CN111022185 A CN 111022185A
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- Prior art keywords
- turbine
- gland
- wheel body
- nickel
- shaft section
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Links
- 210000004907 gland Anatomy 0.000 title claims abstract description 52
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 46
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 36
- 239000004917 carbon fiber Substances 0.000 claims description 36
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 25
- 229910052759 nickel Inorganic materials 0.000 claims description 23
- 239000002131 composite material Substances 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 7
- 239000013585 weight reducing agent Substances 0.000 claims description 5
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 4
- 238000002844 melting Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 230000008018 melting Effects 0.000 claims description 3
- 238000007747 plating Methods 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 4
- 230000002093 peripheral effect Effects 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 10
- 230000007547 defect Effects 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 208000016261 weight loss Diseases 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 238000010923 batch production Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001465 metallisation Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- 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
-
- 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
- F01D25/005—Selecting particular materials
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a turbine and a rotor system with a gland, wherein the turbine comprises a conical wheel body and blades, a first weight-reducing notch is formed in the peripheral edge of the large end face of the wheel body, the turbine also comprises the gland arranged on the turbine, the gland comprises an annular body and a cylindrical body, one end of the annular body is vertically formed into a whole with the cylindrical body, a connecting part is arranged at the other end of the annular body, and the gland is fixedly connected with the large end face of the wheel body through the connecting part and covers the first weight-reducing notch wholly or partially. According to the invention, through the arrangement of the turbine gland, the overall aerodynamic efficiency is not influenced while the weight of the turbine is reduced, and the total efficiency of the combustion engine is improved.
Description
Technical Field
The invention relates to the technical field of micro gas turbines, in particular to a turbine with a gland and a rotor system.
Background
The micro gas turbine uses continuously flowing gas as working medium to drive the impeller to rotate at high speed, and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. The device mainly comprises three parts of a gas compressor, a combustion chamber and a turbine: the air compressor sucks air from the external atmospheric environment, and compresses the air step by step to pressurize the air, and meanwhile, the air temperature is correspondingly increased; compressed air is pumped into a combustion chamber and is mixed with injected fuel to be combusted to generate high-temperature and high-pressure gas; then the gas or liquid fuel enters a turbine to do work through expansion, the turbine is pushed to drive the gas compressor and the external load rotor to rotate at a high speed, the chemical energy of the gas or liquid fuel is partially converted into mechanical work, and the mechanical work can be output by connecting a generator.
However, the micro gas turbine generator set in the prior art has the following defects:
in the prior art, a turbine is an integrated part, the turbine is made of nickel, the weight is large, when the high-speed working condition of a rotor system of a micro gas turbine is borne, grooves, holes and holes are needed to be arranged to reduce the weight so as to reduce the centrifugal force load, but the mode can seriously influence the pneumatic efficiency at the same time, so that the loss of two points is caused, and as a core power part of the micro gas turbine, the pneumatic efficiency loss of the turbine is close to the efficiency loss of the whole machine, and the efficiency loss of the whole machine can also be caused; in addition, the turbine also needs strength for rotation, the requirement on temperature resistance is high, the size cannot be changed, and the weight of the turbine cannot be easily reduced.
The metal-based carbon fiber composite material is mainly used for manufacturing parts working at high temperature and high rotating speed, is the most promising application material for the parts of a gas turbine engine, but has the defects of large surface inertia, low surface energy, lack of chemical bonds with chemical activity, low reaction activity, poor bonding force with a matrix and more defects on the surface, directly influences the mechanical property of the composite material and limits the exertion of the high performance of the carbon fiber. In addition, the carbon fiber for the micro gas turbine has high application temperature, high possibility of reaction between the reinforcement and the matrix and high manufacturing difficulty, and a plurality of effective attempts and researches are made on a carbon fiber metallization method in the prior art, but the existing methods have certain defects, and the composite carbon fiber material has uneven quality and low universality.
Disclosure of Invention
In order to solve the above-described problems, an object of the present invention is to provide a turbine and a rotor system having a gland, which can reduce the weight of the turbine, do not affect the overall aerodynamic efficiency, and can be easily manufactured in a mass production manner.
The technical scheme of the invention is as follows:
according to one aspect of the invention, the turbine with the gland is provided, the turbine comprises a conical wheel body and blades, a first lightening notch is formed in the peripheral edge of the large end face of the wheel body, the turbine is installed on a rotating shaft, the gland is installed on the turbine and comprises an annular body and a cylindrical body, one end of the annular body is vertically formed into a whole with the cylindrical body, the other end of the annular body is provided with a connecting portion, and the gland is fixedly connected with the large end face of the wheel body through the connecting portion and covers the first lightening notch wholly or partially.
Further, the gland material is nickel-based carbon fiber.
Further, the manufacturing method of the gland comprises the following steps: gradually winding carbon fibers into a disc, and carrying out nickel plating on the carbon fiber disc until nickel on each circle of carbon fibers is fused together, or after each circle of carbon fibers is plated with nickel, integrally heating the carbon fibers to a nickel melting point, so that the nickel on each circle layer is fused together after being slightly melted, and forming an initial disc which is rough in surface, uneven in surface and covered with nickel alloy; and carrying out finish machining on the initial disc in a grinding mode to obtain a smooth fine disc with the size meeting the assembly precision requirement.
Furthermore, the connecting portion of gland is lug or shrinkage pool, the big terminal surface of wheel body is provided with connecting portion complex shrinkage pool or lug.
Furthermore, the gland and the wheel body are fixedly connected through welding or bonding at the connecting part.
Furthermore, a second weight-reducing notch is axially formed in the large end face of the wheel body, and carbon fiber composite materials are filled in the second weight-reducing notch.
Further, the second weight-reducing notch is a bell mouth, and an arc line of the bell mouth is matched with a shape line of the turbine.
Further, the wheel body is made of carbon fiber composite materials.
Furthermore, a stepped hole is formed in the end portion of the small end face of the wheel body, and the assembling end of the rotating shaft extends into the large hole of the stepped hole; the turbine is assembled on the rotating shaft by extruding the step surface of the stepped hole through a nut which is screwed on the rotating shaft and is sunk into the large hole of the stepped hole.
Further, a gap capable of accommodating an assembling tool is formed between the large hole of the stepped hole and the nut in the radial direction.
According to another aspect of the present invention, there is provided a rotor system comprising: a rotating shaft, a gas compressor and the turbine;
the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, 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 position of the first shaft section and the second shaft section;
the compressor and the turbine are arranged on the second shaft section, one end of the compressor is abutted to the step surface, the other end of the compressor is abutted to one end of the gland, and the other end of the gland is fixedly connected with the turbine.
Compared with the prior art, the invention has the following beneficial effects:
1. the turbine wheel body is provided with the gland, and the overall pneumatic efficiency is not influenced while the weight of the turbine is reduced through the matching of the wheel body and the gland, so that the total efficiency of the combustion engine is improved; the composite material of the gland can bear high-temperature working environment, and can bear stress far higher than working stress; the gland production method and the gland production material provided by the invention can ensure the quality of the gland, are low in cost and are convenient for batch production.
2. The stepped hole is arranged at the end part of the small end of the turbine, so that the wheelbase is shortened, the rigidity of the shaft is improved, and the weight of the turbine is reduced by arranging the stepped hole at the end part of the small end of the turbine; the large end of the turbine is provided with the concave hole matched with the gland, so that the weight is greatly reduced, and meanwhile, the gland is made of carbon fiber composite materials, so that the stress meeting the load requirement can be borne in the radial direction; the whole turbine is made of carbon fiber composite materials, so that the turbine can radially bear stress meeting load requirements, and simultaneously meets the requirements of rotor dynamics.
3. The rotor system provided by the invention can meet the requirement on the rigidity of the rotor through the gland between the gas compressor and the turbine.
Drawings
FIG. 1 is a schematic view of the construction of a turbine with gland according to the present invention;
FIG. 2 is a schematic view of a turbine wheel and blade according to the present invention;
FIG. 3 is a schematic view of the gland of the present invention;
FIG. 4 is a schematic view of the turbine with a stepped bore according to the present invention.
FIG. 5 is a schematic view of the turbine with a second weight-reduction notch according to the present invention;
fig. 6 is a schematic structural view of the rotor system of the present invention.
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 invention, an embodiment of the invention provides a turbine with a gland, shown in fig. 1, 2, 3. Fig. 1 is a schematic structural diagram of a turbine with a gland according to the present invention. In fig. 2, (a) is a right side view of the wheel body and the blade, (b) is a front view, and (c) is a left side view, and in fig. 3, (a) is a right side view of the cover, (b) is a front view, and (c) is a left side view.
The turbine 2 comprises a conical wheel body and blades, a first weight reduction notch 21 is formed in the peripheral edge of the large end face of the wheel body, the turbine 2 is installed on a rotating shaft, the pressing cover 3 is installed on the turbine 2 and comprises an annular body and a cylindrical body, one end of the annular body and the cylindrical body are vertically formed into a whole, a connecting portion 31 is formed in the other end of the annular body, the pressing cover 3 is fixedly connected with the large end face of the wheel body through the connecting portion 31 and covers the first weight reduction notch 21 wholly or partially, and therefore pneumatic efficiency is guaranteed while weight reduction of the turbine 2 is achieved.
Preferably, the material of the gland 3 is nickel-based carbon fiber. In the metal-based carbon fiber composite material, the nickel-based composite material is manufactured by taking nickel and nickel alloy as a matrix, and the gland 3 made of the nickel-based carbon fiber can meet the use requirement of the micro gas turbine wheel body due to the excellent high-temperature performance of the nickel.
The embodiment of the invention also provides a manufacturing method of the gland 3, which comprises the steps of 1, winding carbon fibers into a disc one by one, wherein the disc has the size capable of covering the compressor 1 or the turbine 2, and plating nickel on the carbon fiber disc with the thickness of 10-dozens of micrometers until the nickel on each circle of carbon fibers is fused together; or after each circle of carbon fiber is plated with nickel, the whole carbon fiber is heated to the nickel melting point, so that the nickel of each circle layer is melted together after micro-melting to form an initial disc with rough and uneven surface and covered with nickel alloy;
and 2, carrying out finish machining on the initial disc in a grinding mode to obtain a smooth fine disc with the size reaching the requirement of the assembly precision, wherein the density is 3-3.5(2-5), and the packing stress is 700-800 MPa. The gland 3 manufactured by the method can ensure the mechanical property of the gland 3 and is beneficial to batch manufacturing.
Preferably, the connecting portion 31 of the gland 3 is a bump or a concave hole, and the large end surface of the wheel body of the turbine 2 is provided with a concave hole or a bump matched with the connecting portion 31. The gland 3 is in clearance fit or transition fit with the shaft surface of the rotating shaft.
Preferably, after the large end of the wheel body is lightened, the connecting part 31 and the gland 3 are fixedly connected in a welding or bonding mode, the combined structure of the turbine 2 and the gland 3 can reduce the weight of the turbine 2, does not influence the overall pneumatic efficiency, and improves the dynamic performance of a rotor system, thereby improving the total efficiency of the micro gas turbine.
Embodiments of the present invention also provide a structure for reducing weight of the turbine 2.
As shown in fig. 4, a stepped hole is arranged at the end of the small end of the wheel body, and the assembling end of the rotating shaft extends into the large hole of the stepped hole; the wheel body is assembled on the rotating shaft by extruding the step surface of the stepped hole through the nut 4 which is screwed on the rotating shaft and is sunk into the large hole of the stepped hole. Since in the conventional manner the turbine 2 usually extends out of the shaft at the mounting end, the turbine 2 is tightly mounted on the shaft by pressing the small end of the turbine 2 at the mounting end by tightening the nut. And the small end of the turbine 2 bears a smaller radial load and has a lower strength requirement, so that the weight of the turbine 2 can be further reduced by arranging the stepped holes (stepped holes and counter bores) at the end part of the small end of the turbine 2, the axle distance is shortened, and the axle rigidity is improved.
Preferably, the nut 4 is a polygonal nut, in particular an outer hexagonal nut.
Meanwhile, a gap capable of accommodating an assembling tool is formed between the large hole of the stepped hole and the nut 4 in the radial direction, so that the wheel body can be assembled and disassembled by screwing or loosening the nut 4 through the tool.
The embodiment of the invention also provides a structure for reducing weight of the turbine.
As shown in fig. 5, a second lightening recess 22 is provided in the large end surface of the wheel body, and the second lightening recess 22 is filled with a carbon fiber composite material, thereby further realizing the lightening of the turbine 2.
Preferably, the second lightening recess 22 may be provided as a bell mouth, through which the arc line matches the shape line of the wheel body, so as to guarantee the mechanical properties of the turbine 2.
The embodiment of the invention also provides a structure for reducing weight of the turbine.
In this embodiment, the entire wheel body of the wheel body may be made of a carbon fiber composite material. The wheel body made of the carbon fiber composite material can radially bear stress meeting load requirements, and simultaneously meets the requirements of rotor dynamics. During wheel body manufacturing, the carbon fiber wheel disc with the turbine 2 wheel disc shaped into the end face with the large end provided with the first weight-reducing notch 21 is wound by carbon fibers, and blades are cast or welded on the periphery of the turbine 2 wheel disc to form the wheel body.
The embodiment of the invention also provides a rotor system.
As shown in fig. 6, the rotor system includes a rotating shaft 5, a compressor 1 and the turbine 2;
the rotating shaft 5 comprises a first shaft section 51 and a second shaft section 52 which are integrally formed, the diameter of the first shaft section 51 is larger than that of the second shaft section 52, and a step surface is formed at the transition position of the first shaft section 51 and the second shaft section 52; the wheel bodies of the compressor 1 and the turbine 2 are fixed on the second shaft section 52, one end of the compressor 1 is abutted against the step surface, the other end of the compressor 1 is abutted against one end of the gland 3, and the other end of the gland 3 is fixedly connected with the turbine 2. For rotor dynamics, the shaft 5 is lighter and lighter, and the smaller the diameter of the shaft 5, the lighter the shaft 5, but during high speed rotation of the rotor system, the higher the strength of the shaft 5. In order to simultaneously consider the rotor dynamics and the strength of the rotating shaft 5, the shaft diameter of the second shaft section 52 is set to be thin in the embodiment, and the gland 3 is installed between the compressor 1 and the turbine 2 at the same time so as to meet the requirement of the rotor rigidity.
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 set of system only has one moving part, the running reliability of the whole set of system is as high as 99.996%, the average annual shutdown maintenance time is not more than 2 hours, and the rotor system can be used for miniature gas turbines of 10-100 KW models, such as 15/30/45KW models.
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 (11)
1. The turbine with the gland is characterized by further comprising a gland arranged on the turbine, wherein the gland comprises an annular body and a cylindrical body, one end of the annular body is vertically formed into a whole with the cylindrical body, the other end of the annular body is provided with a connecting part, and the gland is fixedly connected with the large end face of the wheel body through the connecting part and covers the first weight reduction notch wholly or partially.
2. The turbine of claim 1 wherein the capping material is nickel-based carbon fiber.
3. The turbine of claim 2, wherein the gland is fabricated by a method comprising the steps of:
gradually winding carbon fibers into a disc, and carrying out nickel plating on the carbon fiber disc until nickel on each circle of carbon fibers is fused together, or after each circle of carbon fibers is plated with nickel, integrally heating the carbon fibers to a nickel melting point, so that the nickel on each circle layer is fused together after being slightly melted, and forming an initial disc which is rough in surface, uneven in surface and covered with nickel alloy;
and carrying out finish machining on the initial disc in a grinding mode to obtain a smooth fine disc with the size meeting the assembly precision requirement.
4. The turbine of claim 1, wherein the connecting portion of the gland is a projection or a recess, and the large end surface of the wheel body is provided with a recess or a projection which is matched with the connecting portion.
5. The turbine of claim 1, wherein the gland and the wheel body are fixedly connected at a connecting portion by welding or bonding.
6. The turbine of claim 1, wherein the large end surface of the wheel body is axially provided with a second weight-reducing recess filled with carbon fiber composite material.
7. The turbine of claim 6, wherein the second weight-reducing notch is a flare, the camber line of which matches the shape line of the turbine.
8. The turbine of claim 1 wherein the wheel body material is a carbon fiber composite material.
9. The turbine of claim 1, wherein the small end surface of the wheel body is provided with a stepped hole, and the assembling end of the rotating shaft extends into the large hole of the stepped hole;
the turbine is assembled on the rotating shaft by extruding the step surface of the stepped hole through a nut which is screwed on the rotating shaft and is sunk into the large hole of the stepped hole.
10. The turbine of claim 9, wherein the large bore of the stepped bore and the nut have a clearance therebetween in a radial direction that is capable of receiving an assembly tool.
11. A rotor system, comprising:
a shaft, a compressor and a turbine according to any one of claims 1 to 10;
the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, 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 position of the first shaft section and the second shaft section;
the compressor and the turbine are arranged on the second shaft section, one end of the compressor is abutted to the step surface, the other end of the compressor is abutted to one end of the gland, and the other end of the gland is fixedly connected with the turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911353086.5A CN111022185A (en) | 2019-12-25 | 2019-12-25 | Turbine and rotor system with gland |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911353086.5A CN111022185A (en) | 2019-12-25 | 2019-12-25 | Turbine and rotor system with gland |
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| Publication Number | Publication Date |
|---|---|
| CN111022185A true CN111022185A (en) | 2020-04-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911353086.5A Pending CN111022185A (en) | 2019-12-25 | 2019-12-25 | Turbine and rotor system with gland |
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| CN (1) | CN111022185A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01111102U (en) * | 1988-01-21 | 1989-07-26 | ||
| CN203362235U (en) * | 2013-07-01 | 2013-12-25 | 刘世华 | Weight reducing structure of booster turbine rotor |
| CN107076163A (en) * | 2014-11-25 | 2017-08-18 | 三菱重工业株式会社 | Impeller and rotating machinery |
| CN109267332A (en) * | 2018-08-22 | 2019-01-25 | 至玥腾风科技投资集团有限公司 | A kind of metal-based carbon fiber composite material and ceramic preparation method |
| CN110332018A (en) * | 2019-07-18 | 2019-10-15 | 北京动力机械研究所 | A kind of high compact closed cycle radial-flow turbine electricity generation system rotor |
| CN211343127U (en) * | 2019-12-25 | 2020-08-25 | 迅玲腾风汽车动力科技(北京)有限公司 | Turbine and rotor system with gland |
-
2019
- 2019-12-25 CN CN201911353086.5A patent/CN111022185A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01111102U (en) * | 1988-01-21 | 1989-07-26 | ||
| CN203362235U (en) * | 2013-07-01 | 2013-12-25 | 刘世华 | Weight reducing structure of booster turbine rotor |
| CN107076163A (en) * | 2014-11-25 | 2017-08-18 | 三菱重工业株式会社 | Impeller and rotating machinery |
| CN109267332A (en) * | 2018-08-22 | 2019-01-25 | 至玥腾风科技投资集团有限公司 | A kind of metal-based carbon fiber composite material and ceramic preparation method |
| CN110332018A (en) * | 2019-07-18 | 2019-10-15 | 北京动力机械研究所 | A kind of high compact closed cycle radial-flow turbine electricity generation system rotor |
| CN211343127U (en) * | 2019-12-25 | 2020-08-25 | 迅玲腾风汽车动力科技(北京)有限公司 | Turbine and rotor system with gland |
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