CN112377307A - Curved tube type vortex reducing system with high-radius outlet - Google Patents
Curved tube type vortex reducing system with high-radius outlet Download PDFInfo
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- CN112377307A CN112377307A CN202011173522.3A CN202011173522A CN112377307A CN 112377307 A CN112377307 A CN 112377307A CN 202011173522 A CN202011173522 A CN 202011173522A CN 112377307 A CN112377307 A CN 112377307A
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application discloses a curved tube type vortex reducing system with a high-radius outlet, and relates to an aeroengine. The system comprises a chuck and a plurality of curved vortex reducing pipes. The scroll is subtracted to a plurality of pieces of bent formulas follow the circumference of chuck evenly arrange with the both sides compressor disk is coaxial, and every bent formula is subtracted the structure of scroll the same, and every bent formula is subtracted the installation radius of scroll the same, and every bent formula is subtracted the scroll and has bent formula and subtract the scroll entry and bent formula and subtract the scroll export, and each bent formula is subtracted the scroll entry and is met air current direction to reduce the air current and subtract the pressure loss that the scroll entry separation formed the vortex and led to the fact, and each bent formula is subtracted the scroll exit position and is despin, with the circumferential speed of restriction air current, has restrained the development of free vortex, has reduced the flow and has hindered. Therefore, the high-radius outlet curved pipe type vortex reducing system fully considers the aerodynamic characteristics, inhibits the development of free vortex in the radial inflow disc cavity, reduces the dissipation of airflow caused by turning, and reduces the pressure loss in the system.
Description
Technical Field
The application relates to the technical field of drag reduction of an air compressor air-entraining section of an aircraft engine secondary air system, in particular to a curved pipe type vortex reducing system for a high-radius outlet of an aircraft engine.
Background
Advanced aircraft engines seek higher thrust-weight ratio, higher thermal efficiency, longer service life and higher reliability, so that the pressure increase ratio of the gas compressor and the temperature before the turbine need to be continuously increased. The turbine front temperature of the aircraft engine is always increased, the temperature exceeds the heat resistance limit of the existing turbine material, and in addition, the higher temperature can cause the thermal creep of the turbine to be increased, so that the service life of the turbine is shortened. Therefore, the turbine front temperature must be cooled to a lower range.
Most of the cooling modes adopted at the current turbine are film cooling, and the required cooling gas is high-pressure gas usually extracted from a proper position of a compressor, and a turbine section is induced through a flow guide structure around a main flow passage of an engine, so that the cooling of turbine blades and a turbine disc is realized. The cooling gas is mainly introduced by a main flow of the high-pressure compressor. The induced airflow is pressurized by the compressor, so that the work of the turbine is consumed, but the induced airflow does not participate in combustion of the combustion chamber and expansion work in the turbine. Therefore, in order to reduce the work loss of the turbine and improve the cooling efficiency, the design of the bleed air flow path needs to take measures to solve the problems of pressure drop and temperature rise along the way.
At present, the existing aero-engine mostly adopts a mode of tapping at a drum barrel of an interstage of a compressor, and air is guided to an axial section along a radial direction through a disc cavity between two stages of discs of the compressor. In the radial intake rotating disk chamber, large and small vortices are formed in the disk chamber due to the large centrifugal force and coriolis force generated by the rotation, and these vortices cause a large pressure loss. One feasible solution is to design a reasonable vortex reducer structure to reduce the circumferential speed of fluid in the disc cavity, so as to achieve the aim of reducing the drag.
The straight pipe type vortex reducer widely applied at the present stage is that a straight pipe type vortex reducer is arranged in the radial air guide cavity to guide air flow. However, the straight-tube type vortex reducing tube can generate contraction and expansion of an airflow channel at an inlet and an outlet of the vortex reducing tube to cause viscous dissipation of airflow, and negative work is performed on the airflow.
Disclosure of Invention
It is an object of the present application to overcome the above problems or to at least partially solve or mitigate the above problems.
The application provides a bent pipe formula of high radius export subtracts vortex system arranges the radial drainage segment department at the compressor of aeroengine secondary air system, the compressor includes the drum barrel that the outer fringe department vertical extension that corresponds the compressor dish of arranging and follows the compressor dish of both sides in both sides forms, and the compressor dish and the drum barrel of both sides form inside dish chamber, drum barrel department is equipped with a plurality of drum holes, and each drum hole is used for introducing the air current, and each drum hole configuration becomes to promote the circulation ability of air current in drum hole department, the bent pipe formula subtracts vortex system includes:
the chuck is connected between the compressor disks on the two sides and is coaxially arranged with the compressor disks on the two sides; and
the curved vortex reducing pipes are uniformly arranged along the circumferential direction of the chuck and are coaxial with the compressor disks on the two sides, the structure of each curved vortex reducing pipe is the same, the installation radius of each curved vortex reducing pipe is the same, each curved vortex reducing pipe is provided with a curved vortex reducing pipe inlet and a curved vortex reducing pipe outlet, the inlet of each curved vortex reducing pipe faces the direction of the airflow so as to reduce the pressure loss caused by the separation of the airflow at the inlet of the vortex reducing pipe to form vortex, and the outlet of each curved vortex reducing pipe is reversely rotated so as to limit the circumferential speed of the airflow;
in the running state of the gas compressor, the curved vortex reducing pipes and the gas compressor disks on the two sides rotate coaxially, at the same speed and in the same direction, and airflow flows through the drum holes to enter a disk cavity of the gas compressor and then flows into an axial channel of the gas compressor through the curved vortex reducing pipes.
Optionally, the axis curve of each curved vortex reducing tube is generated by a spline curve.
Optionally, the spline curve is a bezier spline curve or a B-spline curve.
Optionally, the curved vortex reducing pipe inlet plane and a circumferential tangent line where the curved vortex reducing pipe inlet central point is located form an included angle α, and the curved vortex reducing pipe outlet plane and a circumferential tangent line where the curved vortex reducing pipe outlet central point is located form an included angle β.
Optionally, the included angle α is 5 ° to 45 °, and the included angle β is 5 ° to 45 °.
Optionally, each compressor disk has an outer radius RbThe inner radius of each compressor disk is RaThe center radius of the inlet of the curved vortex reducing pipe is R1The center radius of the outlet of the curved vortex reducing pipe is R2Wherein R is1Is 0.7Rb～0.9Rb，R2Is 0.5Rb～0.55Rb。
Optionally, the radius of the outlet center of the curved vortex reducing pipe is located at the middle position of the disc cavity, and the inlet center of the curved vortex reducing pipe and the outlet center of the curved vortex reducing pipe are located on the same radius line.
Optionally, each drum aperture is an oblong aperture.
The utility model provides a bent pipe formula of high radius export subtracts vortex system, subtract the scroll including a plurality of curved formulas, it follows the circumference of chuck evenly arrange and with both sides compressor disk is coaxial, and every curved formula subtracts the structure of scroll the same, and every curved formula subtracts the installation radius of scroll the same, and every curved formula subtracts the scroll has curved formula and subtracts the scroll entry and the export of curved formula, and every curved formula subtracts the scroll entry and is met air current direction to reduce the air current and separating the loss of pressure that forms the vortex and cause subtracting the scroll entry, and every curved formula subtracts scroll exit position derotation, with the circumferential speed of restriction air current, has restrained the development of free vortex, has reduced the flow and has hindered. Therefore, the high-radius outlet curved pipe type vortex reducing system fully considers the aerodynamic characteristics, inhibits the development of free vortex in the radial inflow disc cavity, reduces the dissipation of airflow caused by turning, and reduces the pressure loss in the system.
Further, the present application improves the circulation capacity at the drum aperture for the air flow by using oblong drum apertures.
Furthermore, the central radius of the outlet of the curved vortex reducing pipe is positioned in the middle of the disc cavity, the outlet of the vortex reducing pipe is properly increased, the negative work of the vortex reducing device on the air flow is reduced, the viscous dissipation loss at the turning part of the radial channel is not obviously increased, and the problems of vibration, collision and the like are favorably reduced.
The above and other objects, advantages and features of the present application will become more apparent to those skilled in the art from the following detailed description of specific embodiments thereof, taken in conjunction with the accompanying drawings.
Drawings
Some specific embodiments of the present application will be described in detail hereinafter by way of illustration and not limitation with reference to the accompanying drawings. The same reference numbers in the drawings identify the same or similar elements or components. Those skilled in the art will appreciate that the drawings are not necessarily drawn to scale. In the drawings:
FIG. 1 is a schematic perspective view of a high radius outlet curved tube vortex reduction system according to one embodiment of the present application;
FIG. 2 is a schematic front view of the high radius outlet curved tube vortex reduction system of FIG. 1;
FIG. 3 is a schematic top view of the curved tube vortex reduction system of the high radius outlet of FIG. 1;
FIG. 4 is a schematic partial enlarged view at A of the high radius outlet curved tube vortex reduction system shown in FIG. 2;
FIG. 5 is a graph comparing the total pressure drop coefficient for the curved tube type vortex reducing system with the straight tube type vortex reducer for the high radius outlet shown in FIG. 1 under several typical conditions.
The symbols in the drawings represent the following meanings:
1 a compressor disk of a preceding stage,
2 a compressor disk of the rear stage,
3, a drum, 31 a drum hole,
4, a clamping disc is arranged on the upper surface of the cylinder,
5 curved vortex reducing pipes, 51 curved vortex reducing pipe inlets and 52 curved vortex reducing pipe outlets.
Detailed Description
The inventors have found that the pressure loss in the disc chamber is mainly composed of three parts: the free vortex generated by the gas flowing out of the drum hole when the disc cavity flows from a high radius to a low radius hinders the radial flow of the gas flow; the pressure loss of the airflow generated inside the vortex reducing pipe; the airflow has high speed when flowing out from the vortex reducing pipe orifice with low radius, and the flow direction is turned from the radial direction to the axial direction after impacting the rotating shaft, so that great pressure loss is generated. The present application was developed based on this.
FIG. 1 is a schematic perspective view of a high radius outlet curved tube vortex reduction system according to one embodiment of the present application. FIG. 2 is a schematic front view of the high radius outlet curved tube vortex reduction system of FIG. 1. FIG. 3 is a schematic top view of the curved tube vortex reduction system of the high radius outlet of FIG. 1. FIG. 4 is a schematic partial enlarged view at A of the high radius outlet curved tube vortex reduction system shown in FIG. 2.
As shown in fig. 1-4, the present application provides a high radius outlet curved tube type vortex reducing system disposed at a radial flow induction section of a compressor of an aircraft engine secondary air system. The compressor comprises compressor disks which are correspondingly arranged on two sides of the compressor and a drum barrel 3 which is vertically extended along the outer edges of the compressor disks on the two sides. The compressor disks are a front stage compressor disk 1 and a rear stage compressor disk 2. The compressor disks on both sides form an internal disk chamber with the drum 3. The drum 3 is provided with a plurality of drum holes 31 which are uniformly arranged on the drum 3 along the circumferential direction. The number of the drum holes 31 is N, which is a natural number greater than 1. Each drum aperture 31 is for introducing a gas stream. Each drum aperture 31 is configured to enhance the air flow communication at the drum aperture 31. The curved tube vortex reduction system may generally include: a chuck 4 and a plurality of curved vortex reducing pipes 5. The chuck 4 is connected between the compressor disks on the two sides and is coaxially installed with the compressor disks on the two sides. The plurality of curved vortex reducing pipes 5 are uniformly arranged along the 360-degree circumference of the chuck 4 and are fixed on the chuck 4. The plurality of curved vortex reducing pipes 5 can rotate coaxially, in the same direction and at the same speed with the compressor disks on the two sides. The number of the curved vortex reducing pipes 5 is n, and n is a natural number larger than 1. Each of the curved vortex reducing tubes 5 has the same structure, i.e. the same geometry. The mounting radius of each curved vortex reducing pipe 5 is the same. Each curved vortex reducing pipe 5 is provided with a curved vortex reducing pipe inlet 51 and a curved vortex reducing pipe outlet 52, each curved vortex reducing pipe inlet 51 faces to the direction of the airflow to reduce pressure loss caused by vortex formed by separation of the airflow at the vortex reducing pipe inlet, and each curved vortex reducing pipe outlet 52 is reversely rotated to limit the circumferential speed of the airflow, inhibit the development of free vortex and reduce flow obstruction. In the operation state of the gas compressor, the curved vortex reducing pipes 50 rotate coaxially, at the same speed and in the same direction with the gas compressor discs on the two sides, airflow flows through the drum holes 31 and enters disc cavities of the gas compressor, and flows into an axial channel of the gas compressor through the curved vortex reducing pipes 50.
More specifically, as shown in fig. 1, the axis curve of each curved vortex reduction pipe 5 is generated by a spline curve. In this embodiment, the spline curve is a bezier spline curve or a B spline curve, and in other embodiments, other spline curves may be used.
More specifically, as shown in FIG. 4, the vortex reducing pipe is partially enlarged to more clearly illustrate and describe its structural and dimensional features. The plane of the curved type vortex reducing pipe inlet 51 and the circumferential tangent line of the central point of the curved type vortex reducing pipe inlet 51 form an included angle alpha, and the plane of the curved type vortex reducing pipe outlet 52 and the circumferential tangent line of the central point of the curved type vortex reducing pipe outlet 52 form an included angle beta. Further, the included angle alpha is 5-45 degrees, and the included angle beta is 5-45 degrees. For example, when α is 10 °, β is 5 °. When α is 10 °, β is 20 °. Specifically, the method is determined by calculation according to the actual power consumption of the engine.
More specifically, as shown in fig. 4, each compressor disk has an outer radius RbEach compressor disk having an inner radius of Ra. Further, RaAbout 0.39Rb. The center radius of the curved vortex reducing pipe inlet 51 is R1The center radius of the curved vortex reducing pipe outlet 52 is R2Wherein R is1Is 0.7Rb～0.9Rb，R2Is 0.5Rb～0.55Rb。
In the process of implementing the application, the inventor finds that the straight-tube type vortex reducing tube in the prior art also has the problems of obvious vibration, complex installation and the like.
In order to solve the above problem, further, as shown in fig. 4, the center radius of the curved vortex reducing pipe outlet 52 is located at the middle position of the disk cavity, and the center of the curved vortex reducing pipe inlet 51 and the center of the curved vortex reducing pipe outlet 52 are located on the same radius line. The curved vortex reducing pipe outlet 52 has a higher installation radius, so that the negative work of the vortex reducer on the airflow is reduced, the viscous dissipation loss at the turning part of the radial channel is not obviously increased, and the problems of vibration, collision and the like are favorably reduced.
Optionally, each drum aperture 31 is an oblong aperture. By using oblong drum holes, the circulation capacity at the drum holes 31 of the air flow is improved.
The curved pipe type vortex reducing system with the high-radius outlet provided by the application provides a sectional vortex reducing measure by considering the pressure loss in the air entraining process of the air compressor. By using oblong drum holes, the circulation capacity at the drum holes 31 of the air flow is improved; the direction of the inlet 51 of the curved vortex reducing pipe faces the direction of the airflow, so that the pressure loss caused by the vortex formed by the separation of the airflow at the inlet of the vortex reducing pipe is reduced; the proper increase in radius of the curved vortex reducer outlet 52 reduces the negative work that the vortex reducer does on the air flow, while the increase in viscous dissipation losses that occurs at the turn of the radial passage is insignificant. The total pressure loss of the air stream of the entire radial bleed air system is thus reduced.
As shown in fig. 5, the total pressure coefficient conditions of the radial flow guiding disc cavity inlet and outlet of the curved vortex reducing pipe 5 for installing the conventional straight pipe type vortex reducer and the high-radius outlet of the present application under a plurality of typical aircraft engine working conditions are compared through numerical simulation. As can be seen from fig. 5, under these typical conditions, the total pressure coefficient of the inlet and outlet of the radial flow-guiding disc cavity of the curved vortex reducing pipe 5 provided with the high-radius outlet is significantly smaller, and a better drag reduction effect is achieved.
It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which this application belongs.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the present application.
Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. In the description of the present application, "a plurality" means two or more unless specifically defined otherwise.
In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
The above description is only for the preferred embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides a bent pipe formula of high radius export subtracts vortex system arranges radial drainage segment department at the compressor of aeroengine secondary air system, the compressor includes compressor dish (1, 2) that correspond the arrangement in both sides and along drum barrel (3) that the outer fringe department of both sides compressor dish extends perpendicularly and forms, and the compressor dish of both sides forms inside dish chamber with the drum barrel, drum barrel department is equipped with a plurality of drum holes (31), and each drum hole is used for introducing the air current, its characterized in that, each drum hole configuration becomes can promote the circulation ability of air current at drum barrel hole department, bent pipe formula subtracts vortex system includes:
the clamping disc (4) is connected between the compressor discs on the two sides and is coaxially mounted with the compressor discs on the two sides; and
the curved vortex reducing pipes (50) are uniformly arranged along the circumferential direction of the chuck and are coaxial with the compressor disks on the two sides, the structure of each curved vortex reducing pipe is the same, the installation radius of each curved vortex reducing pipe is the same, each curved vortex reducing pipe is provided with a curved vortex reducing pipe inlet (51) and a curved vortex reducing pipe outlet (52), the inlet of each curved vortex reducing pipe faces the direction of the airflow so as to reduce the pressure loss caused by the vortex formed by the separation of the airflow at the inlet of the vortex reducing pipe, and the outlet of each curved vortex reducing pipe is reversely rotated so as to limit the circumferential speed of the airflow;
in the running state of the gas compressor, the curved vortex reducing pipes and the gas compressor disks on the two sides rotate coaxially, at the same speed and in the same direction, and airflow flows through the drum holes to enter a disk cavity of the gas compressor and then flows into an axial channel of the gas compressor through the curved vortex reducing pipes.
2. The high radius outlet curved tube vortex reduction system of claim 1, wherein the axis curve of each curved vortex reduction tube is generated by a spline curve.
3. The high radius outlet curved pipe vortex reduction system of claim 2, wherein said spline curve is a bezier spline curve or a B-spline curve.
4. The high radius outlet curved tube vortex reducing system of claim 1, wherein said curved vortex reducing tube inlet plane and a circumferential tangent of said curved vortex reducing tube inlet center point form an included angle α, and said curved vortex reducing tube outlet plane and a circumferential tangent of said curved vortex reducing tube outlet center point form an included angle β.
5. The high radius outlet curved tube vortex reducing system of claim 4, wherein said included angle α is 5 ° to 45 °, and said included angle β is 5 ° to 45 °.
6. The high radius outlet curved tube vortex reduction system of claim 1, wherein the outer radius of each compressor disk is RbThe inner radius of each compressor disk is RaThe center radius of the inlet of the curved vortex reducing pipe is R1The center radius of the outlet of the curved vortex reducing pipe is R2Wherein R is1Is 0.7Rb～0.9Rb，R2Is 0.5Rb～0.55Rb。
7. The high radius outlet curved tube vortex reduction system of claim 1, wherein the curved vortex reduction tube outlet center radius is located at a disc cavity mid-position and the curved vortex reduction tube inlet center is located on the same radius line as the curved vortex reduction tube outlet center.
8. The high radius outlet curved tube vortex reduction system of any one of claims 1-7, wherein: each drum aperture is an oblong hole.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011173522.3A CN112377307A (en) | 2020-10-28 | 2020-10-28 | Curved tube type vortex reducing system with high-radius outlet |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011173522.3A CN112377307A (en) | 2020-10-28 | 2020-10-28 | Curved tube type vortex reducing system with high-radius outlet |
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Cited By (5)
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| CN114810664A (en) * | 2022-04-26 | 2022-07-29 | 北京航空航天大学 | Variable-pipe-diameter vortex reducer for gas compressor and vortex reducing system thereof |
| CN114837816A (en) * | 2022-05-31 | 2022-08-02 | 北京航空航天大学 | Guide plate type vortex reducer with variable angle |
| CN114838000A (en) * | 2022-06-01 | 2022-08-02 | 北京航空航天大学 | Variable-length tubular type vortex reducer system of aero-engine compressor |
| CN114838008A (en) * | 2022-05-20 | 2022-08-02 | 北京航空航天大学 | Variable-angle reverse rotation nozzle vortex reduction system for radial inner flow disc cavity of gas compressor |
| CN114961893A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine vortex reducer air entraining device and aeroengine |
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| CN114961893A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine vortex reducer air entraining device and aeroengine |
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| CN114838008B (en) * | 2022-05-20 | 2023-01-20 | 北京航空航天大学 | Variable-angle reverse rotation nozzle vortex reduction system for radial inner flow disc cavity of gas compressor |
| CN114837816A (en) * | 2022-05-31 | 2022-08-02 | 北京航空航天大学 | Guide plate type vortex reducer with variable angle |
| CN114837816B (en) * | 2022-05-31 | 2024-05-28 | 北京航空航天大学 | Variable angle's deflector formula vortex breaker |
| CN114838000A (en) * | 2022-06-01 | 2022-08-02 | 北京航空航天大学 | Variable-length tubular type vortex reducer system of aero-engine compressor |
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