CN109139253B - Miniature gas turbine - Google Patents
Miniature gas turbine Download PDFInfo
- Publication number
- CN109139253B CN109139253B CN201810878347.4A CN201810878347A CN109139253B CN 109139253 B CN109139253 B CN 109139253B CN 201810878347 A CN201810878347 A CN 201810878347A CN 109139253 B CN109139253 B CN 109139253B
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- gas
- diffuser
- collecting device
- combustion chamber
- pressure
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 59
- 238000010276 construction Methods 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 14
- 230000008569 process Effects 0.000 abstract description 13
- 239000012080 ambient air Substances 0.000 abstract description 4
- 238000005381 potential energy Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 140
- 239000003570 air Substances 0.000 description 18
- 239000002737 fuel gas Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
-
- 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
-
- 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
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the technical field of micro gas turbines, and discloses a micro gas turbine which comprises a gas compressor, a combustion chamber and a gas collecting device positioned between the gas compressor and the combustion chamber, wherein the gas compressor comprises an impeller and a diffuser arranged at an outlet of the impeller, an inlet of the gas collecting device is communicated with the diffuser, an outlet of the gas collecting device is communicated with the combustion chamber, and the gas collecting device is used for guiding high-pressure gas generated by the diffuser into the combustion chamber. In the above embodiment, the ambient air at normal temperature and normal pressure first enters the impeller rotating at high speed, the mechanical work absorbed from the impeller rotating at high speed is converted into pressure (potential energy) and speed (kinetic energy), the pressure of the high-pressure gas is reduced in the diffuser after flowing out of the impeller, the pressure is continuously increased, and the high-pressure gas enters the gas collecting device from the diffuser, and the gas collecting device has the function of collecting the high-pressure gas and guiding the high-pressure gas into the combustion chamber, so that the purpose of reducing the pressure loss of the high-pressure gas in the circulation process is achieved.
Description
Technical Field
The invention relates to the technical field of micro gas turbines, in particular to a micro gas turbine.
Background
The whole structure of the existing micro gas turbine is shown in fig. 1, and mainly comprises a gas compressor, a combustion chamber 3, a turbine and the like, wherein the gas compressor comprises an impeller 1 and a diffuser 2, the impeller 1 rotates at a high speed to apply work to air, the air is compressed and conveyed into the diffuser 2, the diffuser 2 is arranged at the outlet position of the impeller 1 and is used for continuously improving the pressure of high-pressure gas flowing out of the impeller 1, the other end of the diffuser 2 is communicated with the inside of a casing 4, the high-pressure gas enters the casing 4 through the diffuser 2, two outlets are formed in two sides of the casing 4, and the high-pressure gas flows out from the outlets and is led into the combustion chamber 3 through an external pipeline 5.
With continued reference to fig. 1, the flowing process of the gas working medium is shown by an arrow in the figure, external air at normal temperature and normal pressure enters the impeller 1 rotating at high speed, the pressure is increased after flowing out of the impeller 1, then enters the diffuser 2, the speed of the high-pressure gas in the diffuser 2 is reduced, the pressure is continuously increased, the high-pressure gas enters the casing 4 from the diffuser 2, finally flows into the combustion chamber 3 through the external pipeline 5, and high-temperature and high-pressure gas generated in the combustion chamber 3 is led into the turbine blade grid from the volute 6, and pushes the turbine to apply work, so that heat energy is converted into mechanical energy. In this process, because there is a large space in the casing 4, the components and pipes of various sizes in the space are distributed in a complicated way, and when air flows through the casing 4, a large pressure loss is caused; and, after the high-pressure air passes through the casing 4, the high-pressure air can be introduced into the combustion chamber 3 through the external pipeline 5, and a part of pressure energy of the high-pressure air is lost, so that the work output of the micro gas turbine and the working efficiency of the whole machine are reduced finally.
Disclosure of Invention
The invention provides a miniature gas turbine which is used for solving the problem of pressure loss generated in the process of introducing high-pressure gas into a combustion chamber in the prior art.
The embodiment of the invention provides a miniature gas turbine, which comprises a gas compressor, a combustion chamber and a gas collecting device positioned between the gas compressor and the combustion chamber, wherein,
The gas compressor comprises an impeller and a diffuser arranged at the outlet of the impeller, an inlet of the gas collecting device is communicated with the diffuser, an outlet of the gas collecting device is communicated with the combustion chamber, and the gas collecting device is used for guiding high-pressure gas in the diffuser into the combustion chamber.
In the embodiment, the pressure of the external air at normal temperature and normal pressure is increased after the external air sequentially passes through the impeller and the diffuser, and the high-pressure air is directly led into the combustion chamber through the air collecting device, so that the pressure loss generated in the conveying process of the high-pressure air is avoided, and the work output of the micro gas turbine and the improvement of the working efficiency of the whole machine are facilitated.
In a specific embodiment, the gas collecting device comprises an inner wall and an outer wall, wherein the inner wall is annularly arranged, the outer wall is sleeved on the inner wall, and the inner wall and the outer wall form an inlet of the gas collecting device at one end facing the diffuser and are connected at one end far away from the diffuser;
The inner wall is provided with a first outlet at one side facing the combustion chamber, the outer wall is provided with a second outlet at a corresponding position, and a channel between the first outlet and the second outlet forms an outlet of the gas collecting device. A channel for gas circulation is formed between the inner wall and the outer wall of the annular arrangement, so that high-pressure gas in the diffuser can smoothly flow into the gas collecting device, and sudden expansion loss generated in the circulation process is avoided.
When the gas collecting device is specifically arranged, an annular flow guiding device is further arranged between the gas collecting device and the combustion chamber, the flow guiding device comprises an inner cylinder and an outer cylinder sleeved on the inner cylinder, and the flow guiding device is used for guiding high-pressure gas in the gas collecting device into the combustion chamber through a gap between the inner cylinder and the outer cylinder.
When the device is specifically arranged, the device also comprises a volute and a turbine, wherein the volute is positioned in the cavity of the inner wall of the gas collecting device, an inlet of the volute is communicated with the inner cylinder of the flow guiding device, an outlet of the volute is communicated with the turbine, and the volute is used for conveying high-temperature gas generated by the combustion chamber into the turbine.
Preferably, the diffuser comprises a radial diffuser and an axial diffuser, wherein the radial diffuser is communicated with a blade runner of the impeller, and the axial diffuser is respectively communicated with the radial diffuser and an inlet of the gas collecting device.
Preferably, the axial diffuser is connected with the inlet of the gas collecting device through a flange plate.
Preferably, the gas collecting device is of an integrally formed structure.
Drawings
FIG. 1 is a cross-sectional view of a prior art micro gas turbine;
FIG. 2 is a cross-sectional view of a micro gas turbine provided in an embodiment of the present invention;
Fig. 3 is a schematic structural view of the gas collecting device shown in fig. 2;
fig. 4 is a cross-sectional view of the gas collecting device shown in fig. 3.
Reference numerals:
1-impeller 2-diffuser 3-combustion chamber 4-casing 5-external pipeline 6-volute
10-Impeller 20-diffuser 30-combustion chamber 40-casing
50-Gas collector 501-inner wall 502-outer wall 51-inlet 52-outlet
60-Deflector 70-volute
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The miniature gas turbine is a rotary power machine which uses flowing gas as working medium and converts heat energy into mechanical energy, and is mainly composed of three large components of gas compressor, combustion chamber and turbine. The compressor comprises an impeller and a diffuser, wherein the impeller is a part for improving air pressure by using blades rotating at high speed to apply work to air, and the diffuser is a part for converting kinetic energy obtained by gas in the impeller into pressure energy as much as possible by using the difference of flow sectional areas; the combustion chamber is a component for mixing high-pressure air with fuel and burning to generate high-temperature high-pressure fuel gas, and the high-temperature high-pressure fuel gas is discharged from the combustion chamber and pushes the turbine to apply work so as to convert heat energy into mechanical energy.
In the prior art, a diffuser is communicated with a casing of a micro gas turbine, and high-pressure gas flowing out of a gas compressor enters the inside of the casing and then enters a combustion chamber through an external pipeline communicated with the casing; in the process, high-pressure gas generates pressure loss when flowing in the casing and the external pipeline, so that the work output of the micro gas turbine and the working efficiency of the whole machine are reduced.
In order to avoid pressure loss of high-pressure gas during the process of introducing the high-pressure gas into the combustion chamber, the embodiment of the invention provides a miniature gas turbine, which comprises a gas compressor, a combustion chamber and a gas collecting device positioned between the gas compressor and the combustion chamber, wherein,
The compressor comprises an impeller and a diffuser arranged at the outlet of the impeller, the inlet of the gas collecting device is communicated with the diffuser, the outlet of the gas collecting device is communicated with the combustion chamber, and the gas collecting device is used for guiding high-pressure gas generated by the diffuser into the combustion chamber.
In the above embodiment, the ambient air at normal temperature and normal pressure first enters the impeller rotating at high speed, the mechanical work absorbed from the impeller rotating at high speed is converted into pressure (potential energy) and speed (kinetic energy), the pressure of the high-pressure gas is reduced in the diffuser after flowing out of the impeller, the pressure is continuously increased, and the high-pressure gas enters the gas collecting device from the diffuser, and the gas collecting device has the function of collecting the high-pressure gas and guiding the high-pressure gas into the combustion chamber, so that the purpose of reducing the pressure loss of the high-pressure gas in the circulation process is achieved.
In order to facilitate an understanding of the micro gas turbine provided by the embodiments of the present invention, the following detailed description of the structure thereof is provided with reference to the specific drawings and embodiments.
As shown in fig. 2, the micro gas turbine comprises a compressor and a combustion chamber 30, wherein the compressor adopts a centrifugal compressor, and comprises an impeller 10 and a diffuser 20 arranged at the outlet of the impeller 10, the impeller 10 is composed of a wheel disc and blades arranged on the wheel disc, blade flow passages for gas circulation are formed among the blades, and after ambient air at normal temperature and normal pressure enters the impeller 10, mechanical work absorbed from the impeller 10 rotating at high speed is converted into pressure (potential energy) and speed (kinetic energy) and flows out of the blade flow passages; the diffuser 20 is communicated with the vane flow passage of the impeller 10, after the high-pressure gas enters the diffuser 20 from the impeller 10, the speed is reduced, the pressure is continuously increased, the diffuser 20 converts the kinetic energy obtained by the gas in the impeller 10 into pressure energy as much as possible, and the pressure of the gas is further increased. In order to reduce the pressure loss generated during the entry of the high-pressure air exiting from the diffuser 20 into the combustion chamber 30, the micro gas turbine further comprises a gas collecting device 50 arranged between the compressor and the combustion chamber 30, the inlet 51 of the gas collecting device 50 being in communication with the diffuser 20 and the outlet 52 being in communication with the combustion chamber 30, the gas collecting device 50 being adapted to introduce the high-pressure gas in the diffuser 20 into the combustion chamber 30. In this way, in the whole process, the high-pressure gas is directly led into the combustion chamber 30 through the connection function of the gas collecting device 50, so that the purpose of reducing the pressure loss of the high-pressure gas in the circulation process is achieved, and the work output of the micro gas turbine and the improvement of the working efficiency of the whole machine are facilitated.
In a specific arrangement, referring to fig. 3 and fig. 4, the gas collecting device 50 includes an inner wall 501 disposed in a ring shape and an outer wall 502 sleeved on the inner wall 501, and a channel for gas circulation is formed between the inner wall 501 and the outer wall 502, so as to minimize the loss along the path generated when high-pressure gas flows in the structure, and both the inner wall 501 and the outer wall 502 have smooth surface structures; the inner wall 501 and the outer wall 502 form the inlet 51 of the gas collecting device 50 at the end facing the diffuser 20 and are connected at the end facing away from the diffuser 20, e.g. the gas collecting device 50 is flanged to the diffuser 20 at the inlet 51; in addition, the inner wall 501 of the gas collecting device 50 is provided with a first outlet at the side facing the combustion chamber 30, and the outer wall 502 thereof is provided with a second outlet at a corresponding position, the passage between the first outlet and the second outlet forming the outlet 52 of the gas collecting device 50. In the preparation process, the gas collecting device 50 can be integrally formed by an integral casting method, or can be split into two parts or even more parts, respectively formed by stamping, and finally welded into an integral whole. When in use, the gas collecting device 50 directly collects the high-pressure gas flowing out of the diffuser 20 and guides the high-pressure gas into the combustion chamber 30 in a countercurrent mode, so that on one hand, the sudden expansion loss generated when the high-pressure gas is directly discharged into the inner space of the casing 40 from the diffuser 20 can be effectively reduced, the accumulation of the high-pressure gas in the casing 40 is avoided, and meanwhile, the risk of leakage of the high-pressure gas at the flange assembling position in the casing 40 is also reduced to a great extent; on the other hand, the pressure loss generated by the high-pressure gas in the external pipeline 5 is avoided, and finally the purposes of improving the work output and the overall efficiency of the micro gas turbine are achieved. The gas collecting device 50 is shown in a cross-sectional view in fig. 4, wherein both the first outlet and the second outlet have edges extending upwards, thereby facilitating the introduction of high pressure gas into the combustion chamber 30.
In particular, the diffuser 20 comprises a radial diffuser 21 and an axial diffuser 22, the radial diffuser 21 being in communication with the outlet 52 of the impeller 10, and the axial diffuser 22 being in communication with the radial diffuser 21 and with the inlet 51 of the gas collecting device 50, respectively. The high-pressure gas flowing out of the impeller 10 sequentially passes through the radial diffuser 21 and the axial diffuser 22 to enter the gas collecting device 50, and the axial diffuser 22 is used for further improving the static pressure energy of the gas and converting the flow direction of the gas from radial to axial. In the micro gas turbine shown in fig. 2, an annular flow guiding device 60 is further disposed between the gas collecting device 50 and the combustion chamber 30, the flow guiding device 60 includes an inner cylinder and an outer cylinder sleeved on the inner cylinder, and the flow guiding device 60 is used for guiding high-pressure gas in the gas collecting device 50 into the combustion chamber 30 through a gap between the inner cylinder and the outer cylinder. As shown in fig. 2, the flow guiding device 60 is connected with the gas collecting device 50 through a flange, that is, the inner cylinder of the flow guiding device 60 is connected with the inner wall 501 of the gas collecting device 50 through a flange correspondingly, the outer cylinder of the flow guiding device 60 is connected with the outer wall 502 of the gas collecting device 50 through a flange, and the arrangement of the flow guiding device 60 is beneficial to further adjusting the flow direction of the high-pressure gas, so that the high-pressure gas flows upwards in a countercurrent manner to enter the combustion chamber 30 and is fully mixed with fuel.
The micro gas turbine also comprises a volute 70 and a turbine, wherein the volute 70 is positioned in a cavity of the inner wall 501 of the gas collecting device 50, an inlet of the volute 70 is communicated with an inner cylinder of the flow guiding device 60, an outlet of the volute 70 is communicated with the turbine, the volute 70 is used for conveying high-temperature gas generated by the combustion chamber 30 into the turbine, and the turbine further converts heat energy into mechanical energy.
In the working process of the micro gas turbine, the flowing direction of a gas working medium is shown by an arrow in fig. 2, ambient air at normal temperature and pressure enters an impeller 10, the impeller 10 rotates at a high speed to apply work to the air, the air is compressed and conveyed to a radial diffuser 21 and an axial diffuser 22, the radial diffuser 21 and the axial diffuser 22 convert kinetic energy obtained by the high-pressure gas in the impeller 10 into pressure energy as much as possible, the pressure of the gas is further improved, and the axial diffuser 22 converts the flowing direction of the gas from radial to axial and leads the gas into a gas collecting device 50; the high-pressure gas flows in from the inlet 51 of the gas collecting device 50, flows out from the outlet 52 through the gap between the inner wall 501 and the outer wall 502, and the outlets arranged on the inner wall 501 and the outer wall 502 are provided with edges extending upwards so as to be beneficial to smoothly guiding the high-pressure gas into the flow guiding device 60; the flow guiding device 60 is arranged along the vertical direction, and further guides high-pressure gas into the combustion chamber 30, the high-pressure gas and fuel are mixed in the combustion chamber 30 and combusted to generate high-temperature and high-pressure fuel gas, the high-temperature and high-pressure fuel gas is led into the volute 70 from the combustion chamber 30 and finally guided into the turbine blade cascade to push the turbine to apply work, and heat energy is converted into mechanical energy.
As can be seen from the above description, in the embodiment of the present invention, by arranging the gas collecting device 50 between the gas compressor and the combustion chamber 30, the high-pressure gas formed after passing through the impeller 10 and the diffuser 20 in sequence can be directly introduced into the combustion chamber 30, so that the pressure loss generated in the circulation process of the high-pressure gas is reduced, the risk of leakage of the high-pressure gas inside the casing 40 is reduced, and the work output and the working efficiency of the complete machine of the micro gas turbine are improved.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (6)
1. A miniature gas turbine is characterized by comprising a gas compressor, a combustion chamber and a gas collecting device positioned between the gas compressor and the combustion chamber, wherein,
The gas compressor comprises an impeller and a diffuser arranged at the outlet of the impeller, the inlet of the gas collecting device is communicated with the diffuser, the outlet of the gas collecting device is communicated with the combustion chamber, and the gas collecting device is used for guiding high-pressure gas in the diffuser into the combustion chamber;
the combustion chambers are distributed on the side parts of the air compressor along the central axis direction of the air compressor;
The gas collecting device comprises an annular inner wall and an outer wall sleeved on the inner wall, wherein the inner wall and the outer wall form an inlet of the gas collecting device at one end facing the diffuser and are connected at one end far away from the diffuser;
The inner wall is provided with a first outlet at one side facing the combustion chamber, the outer wall is provided with a second outlet at a corresponding position, and a channel between the first outlet and the second outlet forms an outlet of the gas collecting device.
2. The micro gas turbine as set forth in claim 1, wherein an annular flow guiding device is further provided between the gas collecting device and the combustion chamber, the flow guiding device comprises an inner cylinder and an outer cylinder sleeved on the inner cylinder, and the flow guiding device is used for guiding high-pressure gas in the gas collecting device into the combustion chamber through a gap between the inner cylinder and the outer cylinder.
3. The micro gas turbine as set forth in claim 2, further comprising a scroll housing and a turbine, said scroll housing being located in an inner wall cavity of said gas collecting device, an inlet of said scroll housing being in communication with an inner barrel of said flow guiding device, an outlet of said scroll housing being in communication with said turbine, said scroll housing being for delivering high temperature gas generated by said combustion chamber into said turbine.
4. A micro gas turbine according to any one of claims 1 to 3, wherein the diffuser comprises a radial diffuser in communication with the outlet of the impeller and an axial diffuser in communication with the radial diffuser and the inlet of the gas collector, respectively.
5. The micro gas turbine as set forth in claim 4, wherein said axial diffuser is connected to an inlet of said gas collector by a flange.
6. The micro gas turbine as set forth in claim 1, wherein said gas collecting means is of unitary construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810878347.4A CN109139253B (en) | 2018-08-03 | 2018-08-03 | Miniature gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810878347.4A CN109139253B (en) | 2018-08-03 | 2018-08-03 | Miniature gas turbine |
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| CN109139253A CN109139253A (en) | 2019-01-04 |
| CN109139253B true CN109139253B (en) | 2024-06-04 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109854383A (en) * | 2019-04-10 | 2019-06-07 | 武汉福赛尔新能源科技有限公司 | A kind of miniature gas turbine system based on technology for Turbocharger Manufacturing exploitation |
| CN112746904A (en) * | 2020-12-24 | 2021-05-04 | 北航（四川）西部国际创新港科技有限公司 | Micro gas turbine |
| CN113107679B (en) * | 2021-04-23 | 2023-09-19 | 浙江浙能技术研究院有限公司 | Transition section component of composite tangential air inlet of small-sized gas turbine |
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| GB981848A (en) * | 1962-11-14 | 1965-01-27 | Saurer Ag Adolph | Gas turbine plant |
| CN201896664U (en) * | 2010-12-01 | 2011-07-13 | 哈尔滨东安发动机（集团）有限公司 | Electricity generating device of miniature gas turbine |
| CN107120192A (en) * | 2017-04-27 | 2017-09-01 | 上海泛智能源装备有限公司 | A kind of scroll casing type collection chamber and gas turbine |
| CN208749448U (en) * | 2018-08-03 | 2019-04-16 | 新奥能源动力科技（上海）有限公司 | A kind of miniature gas turbine |
-
2018
- 2018-08-03 CN CN201810878347.4A patent/CN109139253B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB981848A (en) * | 1962-11-14 | 1965-01-27 | Saurer Ag Adolph | Gas turbine plant |
| CN201896664U (en) * | 2010-12-01 | 2011-07-13 | 哈尔滨东安发动机（集团）有限公司 | Electricity generating device of miniature gas turbine |
| CN107120192A (en) * | 2017-04-27 | 2017-09-01 | 上海泛智能源装备有限公司 | A kind of scroll casing type collection chamber and gas turbine |
| CN208749448U (en) * | 2018-08-03 | 2019-04-16 | 新奥能源动力科技（上海）有限公司 | A kind of miniature gas turbine |
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