CN113175438A - Multi-channel compressor air-entraining circulating device of turboshaft engine and control method - Google Patents
Multi-channel compressor air-entraining circulating device of turboshaft engine and control method Download PDFInfo
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- CN113175438A CN113175438A CN202110293360.5A CN202110293360A CN113175438A CN 113175438 A CN113175438 A CN 113175438A CN 202110293360 A CN202110293360 A CN 202110293360A CN 113175438 A CN113175438 A CN 113175438A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0253—Surge control by throttling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4226—Fan casings
- F04D29/4233—Fan casings with volutes extending mainly in axial or radially inward direction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
Abstract
The invention discloses a multi-channel compressor air-entraining circulating device of a turboshaft engine, which comprises a compressor air inlet channel, a compressor casing, a compressor impeller, a compressor exhaust volute, a compressor main blade, a compressor splitter blade, a compressor diffuser, a channel air suction hole, a channel return pipeline, a channel exhaust hole, a two-channel air suction hole, a two-channel return pipeline, a two-channel exhaust hole, a three-channel air suction hole, a three-channel return pipeline and a three-channel exhaust hole.
Description
Technical Field
The invention relates to the technical field of centrifugal compressors of turboshaft engines, in particular to an air-entraining circulating device of a multichannel compressor of a turboshaft engine.
Background
The centrifugal compressor is widely applied to a scroll type aircraft engine, and along with the increasing requirements on the power performance of the engine, the working rotating speed and the pressure ratio of the compressor are increased, so that the working range of the compressor is closer to a surge boundary, and the engine is easy to surge. Three methods are commonly used for solving the engine surge problem, the first method is to change the angle of an air inlet guide vane and improve the air flow separation phenomenon of air flow at the back of a compressor blade, but the air inlet guide vane is complex in processing and installation and angle control, high in cost and not wide in application range; the second one adopts a multi-rotor structure, when surging occurs, the gas compressor and the power turbine are allowed to run asynchronously, so that the difference value occurs in the rotating speed, and the surging phenomenon is eliminated, but the processing technology of the multi-rotor is very complex and difficult to realize; and the third method is to use the air compressor to discharge air with high pressure out of the engine to eliminate surge, which is also the most common method, but the method can cause air leakage of the engine, reduce the air input of a combustion chamber, cause insufficient combustion of the engine, reduce the working efficiency of the engine and increase the pollutant emission.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides an air-entraining circulating device and a control method for a multi-channel compressor of a turboshaft engine, which can improve the surge margin and the working range of a centrifugal compressor of the turboshaft engine under the conditions of high pressure ratio and low pressure ratio, improve the power of the engine and reduce the emission of pollutants.
The technical scheme of the invention is as follows:
the multi-channel compressor air-entraining circulating device of the scroll engine comprises a compressor air inlet channel 1, a compressor casing 2, a compressor impeller 3, a compressor exhaust volute 4, a compressor main blade 5, a compressor splitter blade 6, a compressor diffuser 7, a channel air pumping hole 8, a channel return pipeline 9, a channel air exhaust hole 10, a two-channel air pumping hole 11, a two-channel return pipeline 12, a two-channel air exhaust hole 13, a three-channel air pumping hole 14, a three-channel return pipeline 15 and a three-channel air exhaust hole 16, wherein the compressor casing 2 is provided with the compressor exhaust volute 4 communicated with a combustion chamber, the compressor impeller 3 is arranged inside the compressor casing 2, the compressor air inlet channel 1 is formed between the compressor impeller 3 and the compressor casing 2, the compressor air inlet channel 1 is communicated with the exhaust volute 4, and the compressor main blade 5, The compressor splitter blade 6 is arranged inside the compressor inlet channel 1, and the compressor diffuser 7 is arranged at the inlet of the compressor exhaust volute 4;
a channel air suction hole 8 is arranged between the compressor main blade 5 and the compressor splitter blade 6, a channel exhaust hole 10 is arranged on the inner side wall of the inlet of the compressor air inlet 1, the channel air suction hole 8 and the channel exhaust hole 10 are both positioned on the compressor casing 2, the channel exhaust hole 10 is positioned at the front end of the compressor main blade 5, and a channel return pipeline 9 is also arranged in the compressor casing 2 and is respectively communicated with the channel air suction hole 8 and the channel exhaust hole 10;
a two-channel air exhaust hole 11 is arranged between the outlet of the compressor impeller 3 and the compressor diffuser 7, a two-channel air exhaust hole 13 is arranged on the inner side wall of the inlet of the compressor air inlet 1, the two-channel air exhaust hole 11 and the two-channel air exhaust hole 13 are both positioned on the compressor casing 2, the two-channel air exhaust hole 13 is positioned at the front end of the compressor main blade 5, and a two-channel return pipeline 12 is also arranged in the compressor casing 2 and is respectively communicated with the two-channel air exhaust hole 11 and the two-channel air exhaust hole 13;
a three-channel air exhaust hole 14 is arranged between the one-channel air exhaust hole 8 and the two-channel air exhaust hole 11, a three-channel air exhaust hole 16 is arranged between the one-channel air exhaust hole 10 and the two-channel air exhaust hole 13, the three-channel air exhaust hole 16 is positioned at the front end of the compressor main blade 5, and a three-channel return pipeline 15 is respectively communicated with the three-channel air exhaust hole 14 and the three-channel air exhaust hole 16.
Furthermore, the diameters of the one-channel return pipeline 9, the two-channel return pipeline 12 and the three-channel return pipeline 15 are 1-10 cm.
Furthermore, an electric control valve is arranged on the channel return pipeline 9.
Further, an electric control valve is arranged on the two-way return pipeline 12.
Further, an electric control valve is arranged on the three-channel return pipeline 15.
According to the control method of the air-entraining circulation device of the multi-channel compressor of the turboshaft engine, when the engine is in a high working condition state, the air speed and the air pressure at the outlet of the impeller 3 of the compressor are high, at the moment, the electric control valves on the return pipeline 9 of the first channel and the return pipeline 15 of the three channel are in a closed state, the electric control valve on the return pipeline 12 of the two channel is opened, the air at the outlet of the impeller 3 of the compressor is led back to the air inlet channel 1 of the compressor through the return pipeline 12 of the two channel and the exhaust hole 13 of the two channel, and the working range and the surge margin of the compressor are improved under the high working condition state.
When the engine is in a low working condition state, the air speed and the air pressure at the rear end of the front edge of the main blade 5 of the compressor are lower, at the moment, the electric control valves on the two-channel return pipeline 12 and the three-channel return pipeline 15 are in a closed state, the electric control valve on the channel return pipeline 9 is opened, the air at the rear end of the front edge of the main blade 5 of the compressor is led back to the air inlet channel 1 of the compressor through the channel return pipeline 9 and the channel exhaust hole 10, and the working range and the surge margin of the compressor are improved in the low working condition state.
When the engine is in a partial load state, at the moment, the electric control valves on the two-channel return pipeline 12 and the one-channel return pipeline 9 are in a closed state, the electric control valve on the three-channel return pipeline 15 is opened, air after the splitter blades 6 of the compressor is led back to the air inlet 1 of the compressor through the three-channel return pipeline 15 and the three-channel exhaust hole 16, and the working range and the surge margin of the compressor are improved in the partial load state.
The invention has the beneficial effects that:
the invention provides an air-entraining circulating device and a control method for a multi-channel compressor of a turboshaft engine.
Drawings
FIG. 1 is a schematic structural view of the present invention;
wherein: 1. the compressor comprises a compressor inlet channel, 2, a compressor casing, 3, a compressor impeller, 4, a compressor exhaust volute, 5, a compressor main blade, 6, a compressor splitter blade, 7, a compressor diffuser, 8, a channel exhaust hole, 9, a channel return line, 10, a channel exhaust hole, 11, a two-channel exhaust hole, 12, a two-channel return line, 13, a two-channel exhaust hole, 14, a three-channel exhaust hole, 15, a three-channel return line, 16 and a three-channel exhaust hole.
Detailed Description
The following detailed description of the embodiments of the present invention, such as the shapes, configurations, mutual positions and connection relationships of the components, the functions and operating principles of the components, the manufacturing processes and the operation and use methods thereof, will be further described in detail with reference to the accompanying drawings, so as to help those skilled in the art to more completely, accurately and deeply understand the concept and technical solutions of the present invention:
as shown in fig. 1, the multi-channel compressor bleed air circulation device of the turboshaft engine comprises a compressor air inlet channel 1, a compressor casing 2, a compressor impeller 3, a compressor exhaust volute 4, a compressor main blade 5, a compressor splitter blade 6, a compressor diffuser 7, a channel air suction hole 8, a channel return pipeline 9, a channel exhaust hole 10, a two-channel air suction hole 11, a two-channel return pipeline 12, a two-channel exhaust hole 13, a three-channel air suction hole 14, a three-channel return pipeline 15 and a three-channel exhaust hole 16;
the compressor impeller 3 is arranged inside the compressor casing 2, the compressor casing 2 is provided with a compressor exhaust volute 4 communicated with the combustion chamber, a compressor air inlet 1 is formed between the compressor impeller 3 and the inner wall surface of the compressor casing 2, the aperture of the opening of the compressor air inlet 1 is large, the aperture of the compressor air inlet gradually decreases towards the extension aperture of the exhaust volute, the air inlet channel 1 is communicated with an air compressor exhaust volute 4, the air compressor main blade 5 and the air compressor splitter blade 6 are arranged inside the air compressor air inlet channel 1, the air compressor main blade 5 is positioned at the front end of the air compressor splitter blade 6, the compressor diffuser 7 is arranged at the inlet of the compressor exhaust volute 4 and used for increasing the pressure of the air flow flowing into the compressor exhaust volute 4 from the compressor air inlet 1.
As shown in fig. 1, a passage air suction hole 8 is arranged between a compressor main blade 5 and a splitter blade 6, a passage exhaust hole 10 is arranged on the inner side wall of the inlet of the compressor air inlet 1, the passage air suction hole 8 and the passage exhaust hole 10 are both positioned on a compressor casing 2, the passage exhaust hole 10 is positioned at the front end of the compressor main blade 5, and a passage return pipeline 9 is also arranged in the compressor casing 2 and is respectively communicated with the passage air suction hole 8 and the passage exhaust hole 10.
A two-channel air exhaust hole 11 is arranged between the outlet of the impeller 3 and the compressor diffuser 7, a two-channel air exhaust hole 13 is arranged on the inner side wall of the inlet of the compressor air inlet 1, the two-channel air exhaust hole 11 and the two-channel air exhaust hole 13 are both positioned on the compressor casing 2, the two-channel air exhaust hole 13 is positioned at the front end of the compressor main blade 5, and a two-channel return pipeline 12 is also arranged in the compressor casing 2 and is respectively communicated with the two-channel air exhaust hole 11 and the two-channel air exhaust hole 13.
A three-channel air exhaust hole 14 is arranged between the one-channel air exhaust hole 8 and the two-channel air exhaust hole 11, a three-channel air exhaust hole 16 is arranged between the one-channel air exhaust hole 10 and the two-channel air exhaust hole 13, the three-channel air exhaust hole 16 is positioned at the front end of the compressor main blade 5, and a three-channel return pipeline 15 is respectively communicated with the three-channel air exhaust hole 14 and the three-channel air exhaust hole 16.
The diameters of the first channel return pipeline 9, the second channel return pipeline 12 and the third channel return pipeline 15 are 1-10 cm, the gas flow demand can be met, and meanwhile, the first channel return pipeline 9, the second channel return pipeline 12 and the third channel return pipeline 15 are provided with electric control valves for controlling the on-off of gas flows in the three pipelines.
A control method of a multi-channel compressor bleed air circulating device of a turboshaft engine,
when the engine is in a high working condition state, the air speed and the air pressure at the outlet of the compressor impeller 3 are high, at the moment, the electric control valves on the first channel return pipeline 9 and the third channel return pipeline 15 are in a closed state, the electric control valve on the second channel return pipeline 12 is opened, the air at the outlet of the compressor impeller 3 is led back to the compressor air inlet 1 through the second channel return pipeline 12 and the second channel exhaust hole 13, and the working range and the surge margin of the compressor are improved under the high working condition state.
When the engine is in a low working condition state, the air speed and the air pressure at the rear end of the front edge of the main blade 5 of the compressor are lower, at the moment, the electric control valves on the two-channel return pipeline 12 and the three-channel return pipeline 15 are in a closed state, the electric control valve on the channel return pipeline 9 is opened, the air at the rear end of the front edge of the main blade 5 of the compressor is led back to the air inlet channel 1 of the compressor through the channel return pipeline 9 and the channel exhaust hole 10, and the working range and the surge margin of the compressor are improved in the low working condition state.
When the engine is in a partial load state, at the moment, the electric control valves on the two-channel return pipeline 12 and the one-channel return pipeline 9 are in a closed state, the electric control valve on the three-channel return pipeline 15 is opened, air after the splitter blade 6 is led back to the air inlet 1 of the compressor through the three-channel return pipeline 15 and the three-channel exhaust hole 16, and the working range and the surge margin of the compressor are improved in the partial load state.
The invention is mainly characterized in that a channel air suction hole 8 is arranged between the front edge 5 of the main blade of the compressor and the front edge 6 of the splitter blade of the compressor, and the air at the position can be led back to the air inlet channel 1 of the compressor through a channel return pipeline 9 and a channel air discharge hole 10.
And a two-channel air extraction hole 11 is arranged between the outlet of the compressor impeller 3 and the diffuser 7, so that the air at the position can be led back to the air inlet channel of the compressor through a two-channel return pipeline 12 and a two-channel exhaust hole 13, the air is compressed by the impeller at the position, the air pressure and the speed are higher, the working range and the surge margin of the compressor can be improved in a high-rotating-speed state, and the improvement effect is common in a low-rotating-speed state and a middle-rotating-speed state.
And finally, a three-channel air exhaust hole 14, a three-channel return pipeline 15 and a three-channel air exhaust hole 16 are arranged between the first channel and the second channel, the principle is similar to that of the first channel and the second channel, and the three-channel air exhaust design widens the working range and the surge margin of the compressor under low, medium and high rotating speeds (low working condition, partial load state and high working condition). Meanwhile, because the compressed air is circulated, air bleeding of the air compressor caused by engine surge is reduced, the air behind the air compressor is fully utilized, the pressure ratio is increased, the combustion efficiency is improved, and the power of the engine is increased, the oil consumption rate and the pollutant discharge are reduced.
The invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.
Claims (8)
1. Turbo shaft engine multichannel compressor bleed air circulating device, its characterized in that: the device comprises a gas compressor inlet channel (1), a gas compressor casing (2), a gas compressor impeller (3), a gas compressor exhaust volute (4), a gas compressor main blade (5), a gas compressor splitter blade (6), a gas compressor diffuser (7), a channel air exhaust hole (8), a channel return pipeline (9), a channel exhaust hole (10), a two-channel air exhaust hole (11), a two-channel return pipeline (12), a two-channel exhaust hole (13), a three-channel air exhaust hole (14), a three-channel return pipeline (15) and a three-channel exhaust hole (16), wherein the gas compressor exhaust volute (4) communicated with a combustion chamber is arranged on the gas compressor casing (2), the gas compressor impeller (3) is arranged inside the gas compressor casing (2), the gas compressor inlet channel (1) is formed between the gas compressor impeller (3) and the casing (2), the air compressor inlet channel (1) is communicated with an air compressor exhaust volute (4), the air compressor main blade (5) and the air compressor splitter blade (6) are arranged inside the air compressor inlet channel (1), and the air compressor diffuser (7) is arranged at the inlet of the air compressor exhaust volute (4);
a channel air suction hole (8) is arranged between the compressor main blade (5) and the compressor splitter blade (6), a channel exhaust hole (10) is arranged on the inner side wall of the inlet of the compressor air inlet (1), the channel air suction hole (8) and the channel exhaust hole (10) are both positioned on the compressor casing (2), the channel exhaust hole (10) is positioned at the front end of the compressor main blade (5), and a channel return pipeline (9) is also arranged in the compressor casing (2) and is respectively communicated with the channel air suction hole (8) and the channel exhaust hole (10);
a two-channel air exhaust hole (11) is arranged between an outlet of a compressor impeller (3) and a compressor diffuser (7), a two-channel air exhaust hole (13) is arranged on the inner side wall of an inlet of a compressor air inlet (1), the two-channel air exhaust hole (11) and the two-channel air exhaust hole (13) are both positioned on a compressor casing (2), the two-channel air exhaust hole (13) is positioned at the front end of a compressor main blade (5), and a two-channel return pipeline (12) is also arranged in the compressor casing (2) and is respectively communicated with the two-channel air exhaust hole (11) and the two-channel air exhaust hole (13);
a three-channel air exhaust hole (14) is formed between the one-channel air exhaust hole (8) and the two-channel air exhaust hole (11), a three-channel air exhaust hole (16) is formed between the one-channel air exhaust hole (10) and the two-channel air exhaust hole (13), the three-channel air exhaust hole (16) is located at the front end of the compressor main blade (5), and a three-channel return pipeline (15) is respectively communicated with the three-channel air exhaust hole (14) and the three-channel air exhaust hole (16).
2. The multi-channel compressor bleed air circulation device of the turboshaft engine according to claim 1, characterized in that: the diameters of the one-channel return pipeline (9), the two-channel return pipeline (12) and the three-channel return pipeline (15) are 1-10 cm.
3. The multi-channel compressor bleed air circulation device of the turboshaft engine according to claim 2, characterized in that: an electric control valve is arranged on the channel return pipeline (9).
4. The multi-channel compressor bleed air circulation device of the turboshaft engine according to claim 2, characterized in that: an electric control valve is arranged on the two-channel return pipeline (12).
5. The multi-channel compressor bleed air circulation device of the turboshaft engine according to claim 2, characterized in that: an electric control valve is arranged on the three-channel return pipeline (15).
6. The method for controlling the bleed air circulation device of the multi-channel compressor of the turboshaft engine as defined in any one of claims 1 to 5, wherein:
when the engine is in a high working condition state, the air speed and the air pressure at the outlet of the compressor impeller (3) are high, at the moment, the electric control valves on the one-channel return pipeline (9) and the three-channel return pipeline (15) are in a closed state, the electric control valves on the two-channel return pipeline (12) are opened, the air at the outlet of the compressor impeller (3) is led back to the compressor air inlet (1) through the two-channel return pipeline (12) and the two-channel exhaust hole (13), and the working range and the surge margin of the compressor are improved under the high working condition state.
7. The method for controlling the bleed air circulation device of the multi-channel compressor of the turboshaft engine as defined in any one of claims 1 to 5, wherein:
when the engine is in a low working condition state, the air speed and the air pressure at the rear end of the front edge of the main blade (5) of the compressor are low, at the moment, the electric control valves on the two-channel return pipeline (12) and the three-channel return pipeline (15) are in a closed state, the electric control valve on the one-channel return pipeline (9) is opened, the air at the rear end of the front edge of the main blade (5) of the compressor is led back to the air inlet channel (1) of the compressor through the one-channel return pipeline (9) and the one-channel exhaust hole (10), and the working range and the surge margin of the compressor are improved in the low working condition state.
8. The method for controlling the bleed air circulation device of the multi-channel compressor of the turboshaft engine as defined in any one of claims 1 to 5, wherein:
when the engine is in a partial load state, at the moment, the electric control valves on the two-channel return pipeline (12) and the one-channel return pipeline (9) are in a closed state, the electric control valve on the three-channel return pipeline (15) is opened, air after the splitter blades (6) of the compressor is led back to the air inlet channel (1) of the compressor through the three-channel return pipeline (15) and the three-channel exhaust hole (16), and the working range and the surge margin of the compressor are improved in the partial load state.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110293360.5A CN113175438A (en) | 2021-03-16 | 2021-03-16 | Multi-channel compressor air-entraining circulating device of turboshaft engine and control method |
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| CN202110293360.5A CN113175438A (en) | 2021-03-16 | 2021-03-16 | Multi-channel compressor air-entraining circulating device of turboshaft engine and control method |
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| CN114183401A (en) * | 2021-12-10 | 2022-03-15 | 哈尔滨工程大学 | Adjustable casing bleed air recirculation structure of centrifugal compressor and control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114183401A (en) * | 2021-12-10 | 2022-03-15 | 哈尔滨工程大学 | Adjustable casing bleed air recirculation structure of centrifugal compressor and control method |
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