CN112324569A - Turbine disc with self-lubricating structure for miniature gas turbine - Google Patents
Turbine disc with self-lubricating structure for miniature gas turbine Download PDFInfo
- Publication number
- CN112324569A CN112324569A CN202010978790.6A CN202010978790A CN112324569A CN 112324569 A CN112324569 A CN 112324569A CN 202010978790 A CN202010978790 A CN 202010978790A CN 112324569 A CN112324569 A CN 112324569A
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- China
- Prior art keywords
- wall
- gas turbine
- rotating shaft
- shell
- blade
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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
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- 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
- F01D25/30—Exhaust heads, chambers, or the like
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- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Abstract
The invention discloses a micro turbine disc with a self-lubricating structure for a gas turbine, which comprises a gas turbine shell, a first rotating shaft, a motor, a first limiting disc, a first rotating hole, a second rotating shaft, a first blade, a driving gear, a third rotating shaft, a second blade, a driven gear, a second limiting disc, an inner gear, an air inlet, a combustion chamber, a fuel nozzle, an igniter, a turbine disc body, an exhaust pipe, a heat exchanger, an exhaust port and a filter screen, wherein the first rotating shaft is arranged on the gas turbine shell; the air flow control device is simple in structure and convenient to use, and the purposes of controlling the air flow and compressing the air are achieved by finely adjusting the angles of the first blade and the second blade through the matching of the motor, the first limiting disc, the second rotating shaft, the first blade, the driving gear, the third rotating shaft, the second blade, the driven gear, the second limiting disc and the internal gear; through the cooperation of blast pipe, heat exchanger, gas vent and filter screen, reduced the influence to external environment, facilitate the use.
Description
Technical Field
The invention relates to the technical field of micro gas turbine equipment, in particular to a turbine disc with a self-lubricating structure for a micro gas turbine.
Background
The micro gas turbine as a small-sized thermal power generator which is newly developed has excellent application prospect, and is considered to possibly start up the technological innovation trend of 'small and decentralized power supply', so that the micro gas turbine becomes the mainstream of the energy technology in the 21 st century, and therefore, certain requirements are made on the micro gas turbine in the market; however, the existing micro gas turbine has a complex structure and is difficult to use, and the air compression equipment in the existing micro gas turbine cannot control the air flow and the air compression, so that the use is influenced; in addition, most of the fuel oil in the existing micro gas turbine is discharged after passing through a simple heat exchanger after being combusted, and certain influence is generated on the environment, so that the invention is very necessary for inventing the turbine disc for the micro gas turbine with the self-lubricating structure.
Disclosure of Invention
The invention aims to provide a turbine disc with a self-lubricating structure for a micro gas turbine, so as to solve the problems in the background technology.
In order to solve the technical problems, the invention provides the following technical scheme: a turbine disc with a self-lubricating structure for a micro gas turbine comprises a gas turbine base, a gas turbine shell, an air inlet, a first bearing, a first rotating shaft, a fan, a motor, a first limiting disc, a first rotating hole, a second rotating shaft, a first blade, a driving gear, a third rotating shaft, a second blade, a driven gear, a second limiting disc, an inner gear, an air inlet, a combustion shell, a combustion chamber, a fuel nozzle, an igniter, an air outlet, a turbine disc body, a second bearing, a second rotating hole, an exhaust pipe, a heat exchanger, an exhaust port and a filter screen, wherein the gas turbine shell is fixedly connected to the outer wall of the top end of the gas turbine base, the air inlet is formed in the outer wall of one side of the gas turbine shell, the first bearing is fixedly installed on the inner wall of one side of the gas turbine shell, the first rotating shaft is rotatably connected to the inner wall of one side of, a fan is fixedly connected to the outer wall of one end of the first rotating shaft, a motor is symmetrically embedded and connected to the inner wall of one side of the gas turbine shell, a first limiting disc is rotatably connected to the outer wall of one end of the first rotating shaft, first rotating holes are symmetrically formed in the outer wall of one side of the first limiting disc, a driving gear is fixedly connected to the outer wall of one end of the motor output shaft, a second rotating shaft is fixedly connected to the outer wall of one end of the motor output shaft, first blades are fixedly connected to the outer wall of one side of the second rotating shaft, a driving gear is fixedly connected to one side of the outer wall of one side of the second rotating shaft, corresponding to the first blades, a third rotating shaft is rotatably connected to the outer wall of one side of the first limiting disc in a distributed manner, second blades are fixedly connected to the outer wall of one side of the third rotating shaft, and a driven gear is fixedly connected to one side of the outer wall of one end of the third rotating, the outer wall of one side of the first limiting disc is sleeved with a second limiting disc, the outer wall of one side of the second limiting disc is fixedly connected to the inner wall of one side of the gas turbine shell, the inner wall of one side of the second limiting disc is fixedly connected with an inner gear, the outer wall of one side of the driven gear is meshed and connected to the outer wall of one side of the inner gear, the inner wall of one side of the gas turbine shell is symmetrically provided with air inlets in a penetrating manner, the outer wall of one side of the gas turbine shell is sleeved with a combustion shell corresponding to the air inlets, the inner wall of one side of the combustion shell is provided with air outlets in a penetrating manner, the inner wall of one side of the combustion shell is provided with a combustion chamber, the inner wall of one side of the combustion shell is inserted and connected with a fuel nozzle, the outer wall of one side of the first rotating shaft is fixedly connected with a, the second rotating hole is fixedly connected with a second bearing, the outer wall of one side of the first rotating shaft is connected with the inner wall of one side of the second bearing in an inserting mode, an exhaust pipe is arranged on the outer wall of one side of the shell, and an exhaust port is formed in one end of the exhaust pipe.
According to the technical scheme, the first bearing is an air bearing.
According to the technical scheme, the outer wall of one side of the driving gear is connected to the outer wall of one side of the internal gear in a meshed mode.
According to the technical scheme, the number of the driven gears is eight.
According to the technical scheme, the igniter is fixedly connected to the inner wall of one side of the combustion shell.
According to the technical scheme, the heat exchangers are symmetrically and fixedly installed on the inner wall of one side of the exhaust pipe.
According to the technical scheme, the inner wall of one side of the exhaust port is embedded and connected with the filter screen.
Compared with the prior art, the invention has the following beneficial effects: the turbine disc with the self-lubricating structure for the micro gas turbine is simple in structure and convenient to use, is simple in structure through matching of the motor, the first limiting disc, the second rotating shaft, the first blade, the driving gear, the third rotating shaft, the second blade, the driven gear, the second limiting disc and the inner gear, and achieves the purpose of controlling air flow and compressing air through fine adjustment of angles of the first blade and the second blade; the expansion force is increased by fully combusting the fuel through the matching of the air inlet, the combustion chamber, the fuel nozzle and the igniter, the utilization rate of the fuel is improved, and the use is convenient; through the cooperation of blast pipe, heat exchanger, gas vent and filter screen, reduced the influence to external environment, facilitate the use.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic overall perspective view of the present invention;
FIG. 2 is a schematic perspective view of a turbine disk body according to the present invention;
FIG. 3 is a schematic overall front cut-away construction of the present invention;
FIG. 4 is a schematic front view of a first limiting plate according to the present invention;
FIG. 5 is a schematic rear view of the first limiting plate according to the present invention;
FIG. 6 is an enlarged view of the structure of the area A in FIG. 3 according to the present invention;
in the figure: 1. a gas turbine engine base; 2. a gas turbine casing; 3. an air inlet; 4. a first bearing; 5. a first rotating shaft; 6. a fan; 7. a motor; 8. a first limiting disc; 9. a first rotation hole; 10. a second rotating shaft; 11. a first blade; 12. a driving gear; 13. a third rotating shaft; 14. a second blade; 15. a driven gear; 16. a second limiting disc; 17. an internal gear; 18. an air inlet; 19. a combustion housing; 20. a combustion chamber; 21. a fuel nozzle; 22. an igniter; 23. an air outlet; 24. a turbine disk body; 25. a second bearing; 26. a second rotation hole; 27. an exhaust pipe; 28. a heat exchanger; 29. an exhaust port; 30. and (4) a filter screen.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, the present invention provides a technical solution: a turbine disk for a micro gas turbine with a self-lubricating structure comprises a gas turbine base 1, a gas turbine shell 2, an air inlet 3, a first bearing 4, a first rotating shaft 5, a fan 6, a motor 7, a first limiting disk 8, a first rotating hole 9, a second rotating shaft 10, a first blade 11, a driving gear 12, a third rotating shaft 13, a second blade 14, a driven gear 15, a second limiting disk 16, an internal gear 17, an air inlet 18, a combustion shell 19, a combustion chamber 20, a fuel nozzle 21, an igniter 22, an air outlet 23, a turbine disk body 24, a second bearing 25, a second rotating hole 26, an exhaust pipe 27, a heat exchanger 28, an exhaust port 29 and a filter screen 30, wherein the gas turbine shell 2 is fixedly connected to the outer wall of the top end of the gas turbine base 1, the air inlet 3 is formed in the outer wall of one side of the gas turbine shell 2, the first bearing 4 is fixedly installed on the inner wall of one side of the gas turbine shell, the first bearing 4 is an air bearing, the use of the air bearing is convenient for self-lubrication, high temperature resistance and convenient use, a first rotating shaft 5 is rotatably connected on one side inner wall of the first bearing 4, a fan 6 is fixedly connected on one end outer wall of the first rotating shaft 5, a motor 7 is symmetrically embedded and connected on one side inner wall of the gas turbine shell 2, a first limiting disc 8 is rotatably connected on one end outer wall of the first rotating shaft 5, a first rotating hole 9 is symmetrically formed on one side outer wall of the first limiting disc 8, and one end outer wall of an output shaft of the motor 7 is rotatably connected on one side inner wall of the first rotating hole 9, a second rotating shaft 10 is fixedly connected on one end outer wall of the output shaft of the motor 7, a first blade 11 is fixedly connected on one side outer wall of the second rotating shaft 10, a driving gear 12 is fixedly connected on one side outer wall of the second rotating shaft 10 corresponding to the first blade 11, a third rotating shaft 13 is distributed on the outer wall of one side of the first limiting disc 8 and is rotatably connected with the first limiting disc, a second blade 14 is fixedly connected with the outer wall of one side of the third rotating shaft 13, a driven gear 15 is fixedly connected with one side of the outer wall of one end of the third rotating shaft 13, which corresponds to the second blade 14, a second limiting disc 16 is sleeved on the outer wall of one side of the first limiting disc 8, the outer wall of one side of the second limiting disc 16 is fixedly connected with the inner wall of one side of the gas turbine shell 2, an inner gear 17 is fixedly connected with the inner wall of one side of the second limiting disc 16, the outer wall of one side of the driving gear 12 is meshed and connected with the outer wall of one side of the inner gear 17, the inner gear 17 is conveniently driven to rotate, the first blade 11 and the second blade 14 are driven to synchronously rotate, the air inlet amount is conveniently adjusted, the outer wall of one side of the, the matching of a plurality of driven gears 15 is further convenient for adjusting the angle of the second blade 14, an air inlet 18 is symmetrically perforated on the inner wall of one side of the gas turbine casing 2, a combustion casing 19 is sleeved on one side of the outer wall of one side of the gas turbine casing 2 corresponding to the air inlet 18, an air outlet 23 is perforated on the inner wall of one side of the combustion casing 19, a combustion chamber 20 is arranged on the inner wall of one side of the combustion casing 19, a fuel nozzle 21 is spliced on the inner wall of one side of the combustion casing 19, an igniter 22 is fixedly connected on the inner wall of one side of the combustion casing 19 for ignition and combustion, a turbine disc body 24 is fixedly connected on the outer wall of one side of the first rotating shaft 5, a second rotating hole 26 is perforated on the inner wall of one side of the gas turbine casing 2, a second bearing 25 is fixedly connected with the second rotating hole 26, and the outer wall of one side of the, an exhaust pipe 27 is arranged on the outer wall of one side of the gas turbine shell 2, a heat exchanger 28 is symmetrically and fixedly mounted on the inner wall of one side of the exhaust pipe 27, heat exchange is facilitated, an exhaust port 29 is formed in one end of the exhaust pipe 27, and a filter screen 30 is connected to the inner wall of one side of the exhaust port 29 in an embedded mode, so that filtering is facilitated, and air pollution is reduced.
When the turbine disk with the self-lubricating structure for the micro gas turbine is used, air enters the gas turbine shell 2 from the air inlet 3 through the fan 6, the motor 7 is started to drive the second rotating shaft 10 to rotate, and then the first blade 11 is driven to rotate, the driving gear 12 is driven under the action of the second rotating shaft 10, and then the internal gear 17 is driven to rotate under the action of the driving gear 12, the driven gear 15 is driven to rotate under the action of the internal gear 17, and then the second blade 14 is driven to rotate, the rotating angles of the first blade 11 and the second blade 14 are adjusted through the motor 7, so that the first blade 11 and the second blade 14 are finely adjusted, the flow of the air and the compressed air are controlled to enter the combustion chamber 20, fuel oil atomization and air are mixed through the fuel oil nozzle 21, the igniter 22 is started to enable the fuel oil to be fully combusted and expanded, and then drive turbine disc body 24 and rotate, and the abandonment after the burning is discharged after filtering through filter screen 30 through blast pipe 27 and heat exchanger 28, has realized the purpose that reduces environmental pollution.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A turbine disc with a self-lubricating structure for a micro gas turbine comprises a gas turbine base (1), a gas turbine shell (2), an air inlet (3), a first bearing (4), a first rotating shaft (5), a fan (6), a motor (7), a first limiting disc (8), a first rotating hole (9), a second rotating shaft (10), a first blade (11), a driving gear (12), a third rotating shaft (13), a second blade (14), a driven gear (15), a second limiting disc (16), an internal gear (17), an air inlet (18), a combustion shell (19), a combustion chamber (20), a fuel nozzle (21), an igniter (22), an air outlet (23), a turbine disc body (24), a second bearing (25), a second rotating hole (26), an exhaust pipe (27), a heat exchanger (28), an exhaust port (29) and a filter screen (30), the method is characterized in that: the gas turbine engine base is characterized in that a gas turbine outer shell (2) is fixedly connected to the outer wall of the top end of the gas turbine engine base (1), an air inlet (3) is formed in the outer wall of one side of the gas turbine outer shell (2), a first bearing (4) is fixedly mounted on the inner wall of one side of the gas turbine outer shell (2), a first rotating shaft (5) is rotatably connected to the inner wall of one side of the first bearing (4), a fan (6) is fixedly connected to the outer wall of one end of the first rotating shaft (5), a motor (7) is symmetrically embedded and connected to the inner wall of one side of the gas turbine outer shell (2), a first limiting disc (8) is rotatably connected to the outer wall of one end of the first rotating shaft (5), a first rotating hole (9) is symmetrically formed in the outer wall of one side of the first limiting disc (8), and the outer wall of one end of an output shaft of the motor (, a second rotating shaft (10) is fixedly connected to the outer wall of one end of an output shaft of the motor (7), a first blade (11) is fixedly connected to the outer wall of one side of the second rotating shaft (10), a driving gear (12) is fixedly connected to the outer wall of one side of the second rotating shaft (10) corresponding to the first blade (11), a third rotating shaft (13) is rotatably connected to the outer wall of one side of the first limiting disc (8) in a distributed manner, a second blade (14) is fixedly connected to the outer wall of one side of the third rotating shaft (13), a driven gear (15) is fixedly connected to the outer wall of one end of the third rotating shaft (13) corresponding to the second blade (14), a second limiting disc (16) is sleeved on the outer wall of one side of the first limiting disc (8), and the outer wall of one side of the second limiting disc (16) is fixedly connected to the inner wall of one side of the gas turbine housing (2), an inner gear (17) is fixedly connected to the inner wall of one side of the second limiting disc (16), the outer wall of one side of the driven gear (15) is connected to the outer wall of one side of the inner gear (17) in a meshed mode, air inlets (18) are symmetrically formed in the inner wall of one side of the gas turbine shell (2) in a penetrating mode, a combustion shell (19) is sleeved on one side, corresponding to the air inlets (18), of the outer wall of one side of the gas turbine shell (2), air outlets (23) are formed in the inner wall of one side of the combustion shell (19) in a penetrating mode, a combustion chamber (20) is arranged on the inner wall of one side of the combustion shell (19), a fuel nozzle (21) is connected to the inner wall of one side of the combustion shell (19) in an inserting mode, a turbine disc body (24) is fixedly connected to the outer wall of one side of the first rotating shaft (5), and, the second rotating hole (26) is fixedly connected with a second bearing (25), the outer wall of one side of the first rotating shaft (5) is connected to the inner wall of one side of the second bearing (25) in an inserting mode, an exhaust pipe (27) is arranged on the outer wall of one side of the gas turbine shell (2), and an exhaust port (29) is formed in one end of the exhaust pipe (27).
2. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: the first bearing (4) is an air bearing.
3. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: and the outer wall of one side of the driving gear (12) is meshed and connected with the outer wall of one side of the inner gear (17).
4. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: the number of the driven gears (15) is eight.
5. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: an igniter (22) is fixedly connected to the inner wall of one side of the combustion shell (19).
6. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: and a heat exchanger (28) is symmetrically and fixedly arranged on the inner wall of one side of the exhaust pipe (27).
7. A turbine disk for a micro gas turbine with a self-lubricating structure as claimed in claim 1, wherein: and a filter screen (30) is embedded and connected on the inner wall of one side of the exhaust port (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010978790.6A CN112324569A (en) | 2020-09-17 | 2020-09-17 | Turbine disc with self-lubricating structure for miniature gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010978790.6A CN112324569A (en) | 2020-09-17 | 2020-09-17 | Turbine disc with self-lubricating structure for miniature gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN112324569A true CN112324569A (en) | 2021-02-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010978790.6A Pending CN112324569A (en) | 2020-09-17 | 2020-09-17 | Turbine disc with self-lubricating structure for miniature gas turbine |
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| CN (1) | CN112324569A (en) |
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| CN103459832A (en) * | 2011-04-28 | 2013-12-18 | 裴明淳 | Multipurpose rotary device, and generating system including same |
| CN103582742A (en) * | 2011-06-01 | 2014-02-12 | 涡轮梅坎公司 | Variable-pitch nozzle for a radial flow turbine, in particular for a turbine of an auxiliary power source |
| CN203603984U (en) * | 2013-12-10 | 2014-05-21 | 中国南方航空工业(集团)有限公司 | Turbocharger |
| CN109268141A (en) * | 2018-10-30 | 2019-01-25 | 常胜 | Multifuel engine |
| EP3540184A1 (en) * | 2018-03-14 | 2019-09-18 | Nuovo Pignone Technologie S.r.l. | Radial - axial turboexpander |
| CN110273758A (en) * | 2019-06-04 | 2019-09-24 | 湖南航翔燃气轮机有限公司 | Miniature gas turbine generating set |
| JP6597689B2 (en) * | 2016-03-28 | 2019-10-30 | 株式会社豊田自動織機 | Variable nozzle mechanism |
| CN210564758U (en) * | 2019-09-07 | 2020-05-19 | 重庆搏帆涡轮动力设备有限公司 | Mixed-flow turbocharger of adjustable nozzle ring |
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2020
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Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011127530A (en) * | 2009-12-18 | 2011-06-30 | Mitsubishi Heavy Ind Ltd | Nozzle blade drive device for turbocharger |
| CN103459832A (en) * | 2011-04-28 | 2013-12-18 | 裴明淳 | Multipurpose rotary device, and generating system including same |
| CN103582742A (en) * | 2011-06-01 | 2014-02-12 | 涡轮梅坎公司 | Variable-pitch nozzle for a radial flow turbine, in particular for a turbine of an auxiliary power source |
| EP2650490A2 (en) * | 2012-04-10 | 2013-10-16 | Rolls-Royce Deutschland Ltd & Co KG | Turbine vane adjustment device for a gas turbine |
| CN203603984U (en) * | 2013-12-10 | 2014-05-21 | 中国南方航空工业(集团)有限公司 | Turbocharger |
| JP6597689B2 (en) * | 2016-03-28 | 2019-10-30 | 株式会社豊田自動織機 | Variable nozzle mechanism |
| EP3540184A1 (en) * | 2018-03-14 | 2019-09-18 | Nuovo Pignone Technologie S.r.l. | Radial - axial turboexpander |
| CN109268141A (en) * | 2018-10-30 | 2019-01-25 | 常胜 | Multifuel engine |
| CN110273758A (en) * | 2019-06-04 | 2019-09-24 | 湖南航翔燃气轮机有限公司 | Miniature gas turbine generating set |
| CN210564758U (en) * | 2019-09-07 | 2020-05-19 | 重庆搏帆涡轮动力设备有限公司 | Mixed-flow turbocharger of adjustable nozzle ring |
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