CN114060094A - High-pressure gas driven turbine mechanism - Google Patents
High-pressure gas driven turbine mechanism Download PDFInfo
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- CN114060094A CN114060094A CN202111356737.3A CN202111356737A CN114060094A CN 114060094 A CN114060094 A CN 114060094A CN 202111356737 A CN202111356737 A CN 202111356737A CN 114060094 A CN114060094 A CN 114060094A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 71
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 238000005381 potential energy Methods 0.000 abstract description 8
- 239000003921 oil Substances 0.000 description 8
- 230000006872 improvement Effects 0.000 description 7
- 230000000694 effects Effects 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000010687 lubricating oil Substances 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011946 reduction process Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
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Classifications
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
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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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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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
- F01D25/18—Lubricating arrangements
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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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
- F01D5/12—Blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a high-pressure gas driven turbine mechanism which comprises a high-pressure turbine mechanism main body, a high-pressure turbine outer cover, an impeller outer cover and a main shaft structure, wherein the high-pressure turbine mechanism main body is provided with a high-pressure turbine main body; the high-pressure turbine mechanism comprises a main shaft structure, an impeller outer cover, a high-pressure turbine outer cover and a main shaft structure, wherein the impeller outer cover is provided with an impeller air suction port and a pressurization exhaust port; the high-pressure turbine outer cover is of a bulge structure with a bulged middle section, an annular cavity structure is further arranged at one end close to the high-pressure turbine mechanism main body, the high-pressure air inlet is arranged at one side of the annular cavity structure, and the turbine air outlet is arranged at one end, far away from the high-pressure turbine mechanism main body, of the high-pressure turbine outer cover; and the high-pressure turbine outer cover and the impeller outer cover are respectively arranged at two ends of the main body of the high-pressure turbine mechanism. The high-pressure gas driven turbine mechanism provided by the invention can convert potential energy of high-pressure gas into mechanical energy and then into air energy, and improves the utilization efficiency of energy.
Description
Technical Field
The invention relates to the field of turbine mechanisms, in particular to a high-pressure gas driven turbine mechanism.
Background
The turbine mechanism is a mechanical mechanism capable of extracting kinetic energy, potential energy or internal energy of fluid to be changed into mechanical energy, the traditional turbine mechanism is generally composed of a connecting shaft and a turbine, the other end of the connecting shaft is connected with a device capable of transmitting the mechanical energy, and the turbine mechanism plays an important role in the field of energy sustainable circulation industry.
The invention designs a green circulation air conditioner, which comprises an indoor exchanger, an air filter box, a heat energy boosting box, a pneumatic energy collecting mechanism, a high-pressure turbine mechanism, an airflow valve, an electric control flow valve, a motor and a one-way transmission structure, wherein the air conditioner takes high-pressure air as a heat exchange carrier, and an energy circulation system is used for recycling redundant heat, so that the air conditioner maintains the whole-process running with lower energy consumption; because there is not the high-pressure turbine mechanism with green circulation air conditioner assorted at present, consequently need design a high-pressure turbine mechanism that is used for specially supporting with green circulation air conditioner.
Disclosure of Invention
The invention aims to provide a high-pressure gas driven turbine mechanism which can convert potential energy of high-pressure gas into mechanical energy and then into air energy, and improve the utilization efficiency of energy.
In order to achieve the above object, the present invention provides a high-pressure gas driven turbine mechanism, which comprises a high-pressure turbine mechanism main body, a high-pressure turbine housing, an impeller housing and a main shaft structure; the high-pressure turbine mechanism comprises a main shaft structure, an impeller outer cover, a high-pressure turbine outer cover and a main shaft structure, wherein the impeller outer cover is provided with an impeller air suction port and a pressurization exhaust port; the high-pressure turbine outer cover is of a bulge structure with a bulged middle section, an annular cavity structure is further arranged at one end close to the high-pressure turbine mechanism main body, the high-pressure air inlet is arranged at one side of the annular cavity structure, and the turbine air outlet is arranged at one end, far away from the high-pressure turbine mechanism main body, of the high-pressure turbine outer cover; and the high-pressure turbine outer cover and the impeller outer cover are respectively arranged at two ends of the main body of the high-pressure turbine mechanism.
As a further improvement of the invention, the main shaft structure comprises a high-pressure connecting shaft, a high-pressure turbine and a driven impeller; the high-pressure turbine mechanism is characterized in that a high-pressure turbine and a driven impeller are fixed at two ends of the high-pressure connecting shaft respectively, the high-pressure connecting shaft is in coaxial rotation fit with the high-pressure turbine mechanism body, a high-pressure turbine outer cover is in clearance fit with the high-pressure turbine, and an impeller outer cover is in clearance fit with the driven impeller.
As a further improvement of the invention, the impeller housing is of a volute structure as a whole, the middle part of the volute structure is provided with an impeller air suction port, the outer side of the volute structure is provided with a pressurizing air exhaust port, and an air compression channel is arranged between the middle part of the volute structure and the outer side of the volute structure.
As a further improvement of the invention, the section of the driven impeller along the axial tail end of the high-pressure connecting shaft is in a trapezoid shape with a larger part and a smaller part, the unfolded surface of the driven impeller is in an oblique gear tooth structure with a certain angle with the central axis, and the whole driven impeller is in clearance fit with the middle of the worm-shaped structure.
As a further improvement of the invention, the length of the annular cavity structure is 1/8-1/4 of the length of the bulge structure, and the length of the turbine exhaust port is 1/6-1/3 of the length of the bulge structure.
As a further improvement of the invention, the whole high-pressure turbine is in a bud-shaped structure with two small ends and a middle bulge, the expansion surface of the high-pressure turbine is a combined structure of a bevel wheel blade and an axial wheel blade which form a certain angle with the central axis, the appearance of the bevel wheel blade is in clearance fit with the bulge structure of the high-pressure turbine housing, and the appearance of the axial wheel blade is in clearance fit with the annular cavity structure of the high-pressure turbine housing.
As a further improvement of the present invention, a bearing is further included; and a bearing is coaxially fixed between the high-pressure connecting shaft and the high-pressure turbine mechanism main body.
As a further improvement of the invention, the oil-saving device also comprises an oil cavity; the oil chamber is arranged on one side of the bearing.
Advantageous effects
Compared with the prior art, the high-pressure gas driven turbine mechanism has the advantages that:
1. the main shaft structure is divided into the high-pressure turbine and the driven impeller which can be assembled, so that the maintenance cost can be reduced, the difficulty of the manufacturing process is reduced, the standard production is facilitated, and the high-pressure turbine outer cover and the impeller outer cover are separated from the main body of the high-pressure turbine mechanism and have similar effects; the high-pressure turbine outer cover main body mainly comprises a bulge structure and an annular cavity structure, a high-pressure air inlet enters from the annular cavity structure and impacts the high-pressure turbine to enable the high-pressure turbine to rotate, the air flow outputs the air flow from a turbine exhaust port at the tail end along a gear tooth structure of the high-pressure turbine after acting, and the bulge structure is in clearance fit with the high-pressure turbine and can efficiently convert potential energy of the high-pressure gas into mechanical energy to drive the high-pressure turbine.
2. The air flow pipeline of the impeller outer cover in a vortex structure is wound from the maximum pipe diameter at the outer side to the middle part and gradually becomes smaller, so that the air flow sucked from the impeller air suction port can be gradually pressurized and stabilized through the air channel, and the pressurized air flow meeting the requirements is output from the pressurized air outlet.
3. The driven impeller is in a trapezoid shape with a larger part and a smaller part along the whole section of the tail end of the shaft, the air flow outside the volute structure can be guided to be output from the pressurizing exhaust port in the middle of the volute structure, and the air flow flows along the gear tooth structure with the tail end gradually reduced, so that the function of pressurizing the air flow is also achieved.
4. The high-pressure turbine outer cover main body mainly comprises a bulge structure and an annular cavity structure, a high-pressure air inlet enters from the annular cavity structure and impacts the high-pressure turbine to enable the high-pressure turbine to rotate, the air flow outputs the air flow from a turbine exhaust port at the tail end along a gear tooth structure of the high-pressure turbine after acting, and the bulge structure is in clearance fit with the high-pressure turbine and can efficiently convert potential energy of the high-pressure gas into mechanical energy to drive the high-pressure turbine.
5. The length proportions of the annular cavity structure, the bulge structure and the turbine exhaust port can be properly adjusted according to the air pressure of the air flow and the use requirement.
6. The high-pressure turbine is a combined structure of axial vanes and inclined vanes which form a certain angle with the central axis along the expansion surface at the tail end of the shaft, and the axial vanes drive the high-pressure turbine to rotate under the impact of high-pressure airflow and guide the airflow to do secondary work on the inclined vanes, so that the utilization rate of high-pressure gas potential energy can be improved.
7. The bearing can support the main shaft structure and keep the rotation precision of the main shaft structure, the main shaft structure is prevented from directly contacting and rotating with the main body of the high-pressure turbine mechanism, and the service life of the main shaft structure can be prolonged.
8. The oil cavity arranged on one side of the bearing can store certain lubricating oil, and abrasion caused by friction resistance when the bearing rotates can be reduced.
The invention will become more apparent from the following description when taken in conjunction with the accompanying drawings, which illustrate embodiments of the invention.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a front cross-sectional view of a high pressure turbine mechanism;
fig. 2 is a front view of the spindle structure.
Detailed Description
Embodiments of the present invention will now be described with reference to the accompanying drawings.
Examples
Detailed description of the inventionas shown in fig. 1 to 2, a high-pressure gas driven turbine mechanism includes a high-pressure turbine mechanism main body 51, a high-pressure turbine housing 52, an impeller housing 53, and a main shaft structure; the impeller outer cover 53 is provided with an impeller suction port 531 and a pressurization exhaust port 532, the high-pressure turbine outer cover 52 is provided with a high-pressure air inlet 521 and a turbine exhaust port 522, and the main shaft structure is in running fit with the high-pressure turbine mechanism main body 51; the high-pressure turbine housing 52 is of a bulge structure with a bulged middle section, an annular cavity structure is further arranged at one end close to the high-pressure turbine mechanism main body 51, the high-pressure air inlet 521 is arranged at one side of the annular cavity structure, and the turbine air outlet 522 is arranged at one end, far away from the high-pressure turbine mechanism main body 51, of the high-pressure turbine housing 52; the high-pressure turbine housing 52 and the impeller housing 53 are respectively installed at both ends of the high-pressure turbine mechanism body 51. In this embodiment, the high-pressure turbine mechanism main body 51 is integrally in a hollow tubular structure, the bearings 57 are arranged at two ends of the high-pressure connecting shaft 54 and coaxially and rotatably matched with the high-pressure turbine mechanism main body 51, and structures which are respectively in concave-convex fit with the high-pressure turbine outer cover 52 and the impeller outer cover 53 are arranged at two ends of the high-pressure turbine mechanism main body 51 and are fixed through bolts; the high-pressure turbine outer cover main body mainly comprises a bulge structure and an annular cavity structure, a high-pressure air inlet enters from the annular cavity structure and impacts the high-pressure turbine to enable the high-pressure turbine to rotate, the air flow outputs from a turbine exhaust port at the tail end along a gear tooth structure of the high-pressure turbine after acting, and the bulge structure is in clearance fit with the high-pressure turbine and can efficiently convert potential energy of the high-pressure gas into mechanical energy to drive the high-pressure turbine.
The main shaft structure of the high-pressure gas drive turbine mechanism comprises a high-pressure connecting shaft 54, a high-pressure turbine 55 and a driven impeller 56; the high-pressure turbine mechanism is characterized in that a high-pressure turbine 55 and a driven impeller 56 are respectively fixed at two ends of the high-pressure connecting shaft 54, the high-pressure connecting shaft 54 is coaxially and rotationally matched with the high-pressure turbine mechanism main body 51, the high-pressure turbine outer cover 52 is in clearance fit with the high-pressure turbine 55, and the impeller outer cover 53 is in clearance fit with the driven impeller 56. In this embodiment, the main shaft structure is divided into the high-pressure turbine 55 and the driven impeller 56 which can be assembled, so that the maintenance cost can be reduced, the difficulty of the manufacturing process can be reduced, and the standardized production is facilitated, and the high-pressure turbine housing 52 and the impeller housing 53 are separated from the high-pressure turbine mechanism main body 51, and the similar effects can be achieved.
The impeller outer cover 53 of the high-pressure gas driven turbine mechanism is integrally in a volute structure, an impeller air suction port 531 is arranged in the middle of the volute structure, a pressurization exhaust port 532 is arranged on the outer side of the volute structure, and an air compression channel 533 is further arranged between the middle of the volute structure and the outer side of the volute structure. In this embodiment, the airflow duct of the volute structure of the impeller housing 53 is wound and gradually reduced from the maximum outside diameter to the middle, and can gradually pressurize the airflow sucked from the impeller air suction port 531 and stabilize the airflow through the air compression passage 533, and output the pressurized airflow meeting the requirement from the pressurized air discharge port 532.
The section of the driven impeller 56 of the high-pressure gas drive turbine mechanism along the axial tail end of the high-pressure connecting shaft 54 is in a trapezoid shape with a larger part and a smaller part, the unfolded surface of the driven impeller is in an oblique gear tooth structure with a certain angle with the central axis, and the whole driven impeller 56 is in clearance fit with the middle of the volute structure. In this embodiment, the driven impeller 56 has a trapezoid cross section with a larger end and a smaller end along the whole end of the shaft, so that the air flow outside the volute structure can be guided to be output from the pressurizing exhaust port 532 at the middle of the volute structure, and the air flow flows along the gear tooth structure with the smaller end, and the function of pressurizing the air flow is also provided.
The length of the annular cavity structure of the high-pressure gas driven turbine mechanism is 1/8-1/4 of the length of the bulge structure, and the length of the turbine exhaust opening 522 is 1/6-1/3 of the length of the bulge structure. In this embodiment, the length ratios of the ring cavity structure, the bulge structure and the turbine exhaust outlet 522 can be adjusted according to the air pressure of the air flow and the use requirement.
The high-pressure turbine 55 of the high-pressure gas driven turbine mechanism is integrally in a bud-shaped structure with two small ends and a middle bulge, the expansion surface of the high-pressure turbine is a combined structure of a bevel wheel blade 551 and an axial wheel blade 552 which form a certain angle with the central axis, the appearance of the bevel wheel blade 551 is in clearance fit with the bulge structure of the high-pressure turbine housing 52, and the appearance of the axial wheel blade 552 is in clearance fit with the annular cavity structure of the high-pressure turbine housing 52. In this embodiment, the expanded surface of the high-pressure turbine 5 along the end of the shaft is a combined structure of an axial vane 552 and an oblique vane 551 which sequentially form a certain angle with the central axis, the axial vane 552 drives the high-pressure turbine 55 to rotate under the impact of high-pressure air flow and guides the air flow to perform secondary work on the oblique vane 551, when 50MPa high-pressure air impacts the axial vane 552 through the high-pressure air inlet 521, the air pressure is released for the first time, the air pressure is reduced to about 4MPa, then the air is fully expanded in the annular cavity, then the air flows along the structure of the axial vane 552 and is sprayed to the oblique vane 551, the air pressure is reduced to about 0.2MPa again, the two-stage pressure reduction process is a process of pressure release expansion and cooling of the air volume, and the two-stage pressure reduction process has the effects of improving the air potential energy conversion rate and eliminating local heat accumulation caused by the impact of the high-pressure air on the main body 51 of the high-pressure turbine mechanism. The high-pressure turbine housing 52 and the impeller housing 53 have the matching and rectifying functions, and the gas outlets of the high-pressure turbine housing and the impeller housing are designed to be closed to achieve the effect of maximum efficient utilization of gas tail pressure.
The high pressure gas driven turbine mechanism further comprises a bearing 57; a bearing 57 is coaxially fixed between the high-pressure connecting shaft 54 and the high-pressure turbine mechanism main body 51. In this embodiment, the bearing 57 can support the main shaft structure and maintain the rotation precision thereof, thereby preventing the main shaft structure from directly contacting and rotating with the high-pressure turbine mechanism main body 51, and improving the service life of the main shaft structure.
The high pressure gas driven turbine mechanism further includes an oil chamber 58; the oil chamber 58 is provided on the bearing 57 side. In this embodiment, the oil chamber 58 provided on the bearing 57 side can store a certain amount of lubricating oil, and can reduce wear due to frictional resistance when the bearing 57 rotates, and the oil chamber 58 is further provided with an oil filler 581 for periodically adding lubricating oil.
The present invention has been described in connection with the preferred embodiments, but the present invention is not limited to the embodiments disclosed above, and is intended to cover various modifications, equivalent combinations, which are made in accordance with the spirit of the present invention.
Claims (8)
1. A high-pressure gas driven turbine mechanism is characterized by comprising a high-pressure turbine mechanism main body (51), a high-pressure turbine housing (52), an impeller housing (53) and a main shaft structure; the high-pressure turbine mechanism is characterized in that the impeller housing (53) is provided with an impeller suction port (531) and a pressurization exhaust port (532), the high-pressure turbine housing (52) is provided with a high-pressure air inlet (521) and a turbine exhaust port (522), and the main shaft structure is in running fit with the high-pressure turbine mechanism main body (51); the high-pressure turbine outer cover (52) is of a bulge structure with a bulged middle section, an annular cavity structure is further arranged at one end close to the high-pressure turbine mechanism main body (51), the high-pressure air inlet (521) is arranged at one side of the annular cavity structure, and the turbine air outlet (522) is arranged at one end, far away from the high-pressure turbine mechanism main body (51), of the high-pressure turbine outer cover (52); the high-pressure turbine housing (52) and the impeller housing (53) are respectively arranged at two ends of the high-pressure turbine mechanism main body (51).
2. A high pressure gas driven turbo mechanism according to claim 1, wherein said main shaft structure comprises a high pressure connecting shaft (54), a high pressure turbine (55) and a driven impeller (56); the high-pressure turbine mechanism is characterized in that a high-pressure turbine (55) and a driven impeller (56) are respectively fixed at two ends of the high-pressure connecting shaft (54), the high-pressure connecting shaft (54) is in coaxial rotation fit with the high-pressure turbine mechanism main body (51), a high-pressure turbine outer cover (52) is in clearance fit with the high-pressure turbine (55), and an impeller outer cover (53) is in clearance fit with the driven impeller (56).
3. The high-pressure gas driven turbine mechanism as claimed in claim 2, wherein the impeller housing (53) is formed as a whole in a spiral structure, an impeller suction port (531) is formed in the middle of the spiral structure, a pressurizing exhaust port (532) is formed on the outer side of the spiral structure, and a gas compression passage (533) is formed between the middle of the spiral structure and the outer side of the spiral structure.
4. A high pressure gas driven turbine according to claim 3, wherein the driven impeller (56) has a trapezoidal cross section from the first larger to the second smaller along the axial end of the high pressure connecting shaft (54), the developed surface thereof is a helical gear tooth structure with a certain angle to the central axis, and the driven impeller (56) is integrally clearance-fitted with the middle of the worm-shaped structure.
5. The high pressure gas driven turbine engine as claimed in claim 1, wherein the length of the torus structure is 1/8-1/4 of the length of the bulge structure, and the length of the turbine exhaust outlet (522) is 1/6-1/3 of the length of the bulge structure.
6. The high-pressure gas driven turbine mechanism as claimed in claim 1, wherein the high-pressure turbine (55) is a whole body of a flower-bud-shaped structure with two small ends and a middle bulge, the development surface of the high-pressure turbine is a combined structure of a helical blade (551) and an axial blade (552) which form a certain angle with the central axis, the shape of the helical blade (551) is in clearance fit with the bulge structure of the high-pressure turbine housing (52), and the shape of the axial blade (552) is in clearance fit with the annular cavity structure of the high-pressure turbine housing (52).
7. A high pressure gas driven turbo mechanism according to claim 2, further comprising a bearing (57); and a bearing (57) is coaxially fixed between the high-pressure connecting shaft (54) and the high-pressure turbine mechanism main body (51).
8. The high pressure gas driven turbomachinery mechanism of claim 2, further comprising an oil chamber (58); the oil chamber (58) is arranged on one side of the bearing (57).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111356737.3A CN114060094A (en) | 2021-11-16 | 2021-11-16 | High-pressure gas driven turbine mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111356737.3A CN114060094A (en) | 2021-11-16 | 2021-11-16 | High-pressure gas driven turbine mechanism |
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| CN114060094A true CN114060094A (en) | 2022-02-18 |
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| CN202111356737.3A Pending CN114060094A (en) | 2021-11-16 | 2021-11-16 | High-pressure gas driven turbine mechanism |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110206500A1 (en) * | 2008-11-05 | 2011-08-25 | Kenichi Nagao | Turbocharger |
| CN106593650A (en) * | 2015-10-16 | 2017-04-26 | 谭佑军 | Detonation turbine engine |
| CN113606160A (en) * | 2021-08-02 | 2021-11-05 | 鑫磊压缩机股份有限公司 | Residual pressure recovery energy-saving compressor |
| CN114017135A (en) * | 2021-11-16 | 2022-02-08 | 曾昭达 | Heat source cooling and waste heat regeneration power system |
| CN219472163U (en) * | 2021-11-16 | 2023-08-04 | 曾昭达 | High-pressure gas driven turbine mechanism |
| CN219691604U (en) * | 2021-11-16 | 2023-09-15 | 曾昭达 | Heat source cooling and waste heat regeneration power system thereof |
-
2021
- 2021-11-16 CN CN202111356737.3A patent/CN114060094A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110206500A1 (en) * | 2008-11-05 | 2011-08-25 | Kenichi Nagao | Turbocharger |
| CN106593650A (en) * | 2015-10-16 | 2017-04-26 | 谭佑军 | Detonation turbine engine |
| CN113606160A (en) * | 2021-08-02 | 2021-11-05 | 鑫磊压缩机股份有限公司 | Residual pressure recovery energy-saving compressor |
| CN114017135A (en) * | 2021-11-16 | 2022-02-08 | 曾昭达 | Heat source cooling and waste heat regeneration power system |
| CN219472163U (en) * | 2021-11-16 | 2023-08-04 | 曾昭达 | High-pressure gas driven turbine mechanism |
| CN219691604U (en) * | 2021-11-16 | 2023-09-15 | 曾昭达 | Heat source cooling and waste heat regeneration power system thereof |
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