CN108425708B - Combined vortex reducer structure - Google Patents
Combined vortex reducer structure Download PDFInfo
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- CN108425708B CN108425708B CN201810399023.2A CN201810399023A CN108425708B CN 108425708 B CN108425708 B CN 108425708B CN 201810399023 A CN201810399023 A CN 201810399023A CN 108425708 B CN108425708 B CN 108425708B
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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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
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a compound vortex reducer structure which comprises an upstream rotary wheel disc, a downstream rotary wheel disc, a drum hole ring, an upstream Duan Moguan vortex reducer, a middle section tubeless vortex reducer, a flow deflector and a rotary shaft. Drum holes are uniformly distributed on the circumference of the drum hole ring; the tubular vortex reducer structures are arranged at the upstream section and the middle section, the axis of the nozzle and the rotation tangent line of the wheel disc are reversely at a certain angle, the inlet is subjected to chamfering treatment, and the inlet is connected and fixed with the upstream wheel disc and the downstream wheel disc through the fixing grooves and the screws; the outlet section is provided with a deflector. The invention can improve the circulation capacity of the drum cylinder hole; the tubular vortex reducer structure reduces the inlet swirl ratio and simultaneously inhibits the development of the swirl ratio; the deflector with the guide vane is adopted to extract power from the rotating shaft, so that the air flow pressure is improved, and the pressure loss is reduced; meanwhile, due to the adoption of the nozzle type vortex reducer, the weight of the vortex reducer system can be effectively reduced, the installation method is simple and reliable, and the reliability and stability are improved.
Description
Technical Field
The invention relates to the technical field of design of air systems in aeroengines and gas turbines, in particular to a composite vortex reducer structure.
Background
With the development of aero-engine and gas turbine design technology and the continuous progress of demand, the temperature and thermal stress of hot end components are higher and higher, and higher requirements are put on the design technology of the air system in the aero-engine. At present, the internal cooling air is mainly led out from the compressor platform, flows through the drum cylinder hole and flows radially in the cavity of the co-rotating disc, is conveyed to the hot end part and other places through the inter-shaft channel to finish the functions of cooling and sealing, and then is converged into the main flow of fuel gas or discharged into the atmosphere.
The pressure and the temperature of the cooling air directly influence the action range and the performance of the cooling air, and the tangential velocity is larger and larger along with the reduction of the radius due to the conservation of angular momentum in the radial inflow process of the co-rotating disc cavity, so that the cooling air shows the characteristic of free vortex, and the cooling air has great pressure loss under the combined action of centrifugal force, golgi force and friction force, so that the quality of the cooling air is severely restricted. The pressure loss can be effectively reduced by installing the vortex breaker.
Currently, there are three main types of vortex reducers: baffle-type vortex reducer, tubeless vortex reducer and tubular vortex reducer. The existing tubular vortex reducer is of a high-radius cantilever supporting structure, the circular cross section guide pipe is uniformly distributed in the circumferential direction, the air flow from the drum hole is guided to a low-radius position from a high radius, the flow characteristic in the guide pipe is shown as a forced vortex, and the air flow does not pass through the development of free vortex, so that the pressure loss is reduced; the existing tubular vortex reducer adopts a low-radius supporting mode, air flows out of a drum hole and then enters a guide pipe after free vortex development of a certain distance, but when entering the guide pipe, the air flows have a certain angle with the section of an inlet, and larger pressure loss can be generated in the deflection process, in addition, the air flow flowing out of the low-radius guide pipe has larger speed, and the flow direction is deflected by 90 degrees after the air flows out of the low-radius guide pipe directly impact a rotating shaft, so that larger pressure loss can be generated in the process; the existing fin type vortex reducer is a plurality of partition plates crossing the disc space of the cavity of the co-rotating disc, the whole disc cavity is divided into equally-spaced non-communicated cavities, and the radial inflow process of air flow is restrained to be completed in the cavities; the existing tubeless vortex reducer adopts a blade grid type nozzle, so that a velocity component opposite to the rotation direction is generated when airflow flows out of the nozzle, the action of the Golgi force is reduced, and the pressure loss is reduced.
Through analysis of structural patents like vortex reducers, the applicant has found that the existing patents and techniques have at least the following problems:
the basic principle of the existing vortex reducer is to control the speed development of air flow in a cavity of a co-rotating disc, the speed characteristic is represented by a rotational ratio (the ratio of the tangential velocity component of air flow rotation to the circumferential velocity of a rotor), and different types of vortex reducers are different in the way of controlling the development of the rotational ratio. However, the vortex reducer structure with a single structure has the problem of poor matching of upstream and downstream flow characteristics, the rotational flow ratio of the air flow when entering the vortex reducer structure is not ideal, even becomes a constraint factor, and the air flow flowing out of the vortex reducer impacts a rotating shaft or a deflector to generate an air flow steering pressure loss which is not small; in addition, the vibration problem of the tubular vortex reducer, the weight increase problem of the fin vortex reducer, the pressure loss generated by flow separation caused by the sharp structure of the inlet and outlet structures of the vortex reducer and the bistable characteristic of the flow characteristic of the tubular vortex reducer severely restrict the application of the tubular vortex reducer in an air system in an engine.
Disclosure of Invention
The invention aims to solve the technical problem of providing a composite vortex breaker structure aiming at the defects related to the background technology.
The invention adopts the following technical scheme for solving the technical problems:
a compound vortex reducer structure comprises an upstream rotary wheel disc, a downstream rotary wheel disc, a drum hole ring, an upstream Duan Moguan vortex reducer, a middle section tubeless vortex reducer, a flow diverter and a rotary shaft;
the drum hole ring, the upstream Duan Moguan type vortex reducer, the middle section tubeless vortex reducer and the flow diverter are arranged between the upstream rotary wheel disc and the downstream rotary wheel disc from outside to inside, and the drum hole ring, the upstream Duan Moguan type vortex reducer, the middle section tubeless vortex reducer, the flow diverter, the upstream rotary wheel disc and the downstream rotary wheel disc are coaxial;
the two sides of the drum annular ring, the upstream Duan Moguan type vortex reducer and the middle section tubeless vortex reducer are fixedly connected with the inner wall surface of the upstream rotary wheel disc and the inner wall surface of the downstream rotary wheel disc respectively;
the back surface of the flow diverter is fixedly connected with the downstream rotary wheel disc, and the other surface of the flow diverter is fixedly connected with the rotary shaft through a flat key;
the rotating shaft is coaxial with the flow diverter, and a plurality of drum holes are uniformly formed in the circumference of the drum hole ring.
As a further optimization scheme of the composite vortex breaker structure, the shape of the drum hole in the drum hole ring is round or waist-round.
As a further optimization of the composite vortex breaker structure of the invention, the thickness of the drum hole ring is locally thinned near the drum hole.
As a further optimization scheme of the composite vortex reducer structure, the cross section of the nozzle in the upstream Duan Moguan vortex reducer and the nozzle in the intermediate section ductless vortex reducer is any one of a circular shape, a square shape, an elliptic shape and a blade grid shape.
As a further optimization scheme of the composite vortex reducer structure, the axes of the nozzles in the upstream Duan Moguan vortex reducer and the intermediate section ductless vortex reducer form a preset angle threshold with the tangential direction of the wheel disc, the direction is opposite to the rotation direction of the wheel disc, and the angle range is 15-90 degrees.
As a further optimization scheme of the composite vortex reducer structure, the number of the nozzles in the upstream Duan Moguan type vortex reducer and the nozzles in the intermediate section ductless type vortex reducer are the same and correspond to each other one by one, and the axes of the nozzles in the upstream Duan Moguan type vortex reducer and the nozzles of the corresponding intermediate section ductless type vortex reducer are overlapped.
As a further optimization scheme of the composite vortex reducer structure, a first fixing groove and a second fixing groove for fixing an upstream Duan Moguan vortex reducer and a middle-section tubeless vortex reducer are respectively formed in the inner wall surface of the upstream rotary wheel disc, and a third fixing groove and a fourth fixing groove for fixing the upstream Duan Moguan vortex reducer and the middle-section tubeless vortex reducer are correspondingly formed in the inner wall surface of the downstream rotary wheel disc;
two sides of the upstream Duan Moguan vortex reducer are respectively arranged in the first fixed groove and the third fixed groove;
two sides of the middle section tubeless vortex reducer are respectively arranged in the second fixed groove and the fourth fixed groove;
and the two sides of the upstream Duan Moguan vortex reducer and the middle section tubeless vortex reducer are respectively fixedly connected with the upstream rotary wheel disc and the downstream rotary wheel disc.
As a further optimization scheme of the composite vortex breaker structure, the structural profile of the flow diverter is arc-shaped.
As a further optimization scheme of the composite vortex breaker structure, the structural profile of the flow diverter is provided with guide vanes which are uniformly distributed in the circumferential direction.
As a further optimization scheme of the composite vortex breaker structure, the molded surface of the guide vane is any one of a linear guide vane, a spiral guide vane, a hyperbolic guide vane and a logarithmic guide vane.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
the composite vortex reducer structure provided by the invention is based on the theory of delaying the development of the swirl ratio, and simultaneously gives consideration to the pressure loss in the whole bleed air process of the air compressor, thereby providing a sectional vortex reducing measure. By using a kidney-shaped drum hole, the circulation capacity of the air flow at the drum and the circumferential uniformity of the speed of the outlet of the drum hole can be greatly improved, and the locally thinned drum hole structure can limit the increase of the reflux area and the swirl ratio generated when the air flow passes through the drum hole on the premise of not losing structural rigidity, so that the pressure loss at the stage is reduced; the tubular vortex reducer is selectively arranged at the upstream section, airflow generates a tangential velocity component opposite to the rotation direction when passing through the nozzle, the swirl ratio of the airflow is reduced, so that the development of the swirl ratio is restrained, the pressure loss in the process of flowing through the nozzle can be reduced to the greatest extent when a planar blade grid type nozzle is adopted, the extra pressure loss caused by the tubular vortex reducer is reduced, and when a conventional circular or elliptic nozzle is adopted, the pressure loss caused by flow separation of the airflow in the process of entering the tubular vortex reducer can be reduced by introducing an inlet rounding structure; through the development of a certain distance, the swirl ratio in the disc cavity is raised, and the raised swirl ratio can be reduced again through the development of the swirl ratio further restrained by the tubeless vortex reducer arranged in the middle section, so that the pressure loss of the part is reduced, the speed distribution of the outlet airflow is improved, and the pressure loss in the process of deflecting the airflow to the axial direction is reduced; the flow deflector arranged through the outlet section can enable the air flow flowing out of the guide pipe to be gradually changed from radial direction to axial direction, and the guide vane is introduced to further extract power from the rotating shaft, so that the air flow is acted, the air flow pressure is further improved, and the circumferential speed of the air flow is improved.
Through the segmentation vortex reduction measure, furthest reduces the pressure loss of cooling air in the air compressor bleed air in-process, and in addition, each section vortex reduction ware structure passes through the bolt and is connected with upstream and downstream carousel, simple structure, and tubular vortex reduction ware adopts the double fixed mode of upper end screw thread lower extreme holding ring can effectively weaken the vibrations in the working process, improves job stabilization nature and reliability. In addition, the invention has the characteristics of wide application range, good drag reduction effect, convenient installation and stable structure.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a schematic illustration of the mating structure of an upstream rotary wheel disc and drum grommet of the present invention;
FIG. 4 is a schematic view of a flow diverter according to the present invention;
FIGS. 5a and 5b are schematic cross-sectional views of a partially reduced thickness waisted annular ring according to the present invention, with the thickness of the annular ring being partially constant;
fig. 6a, 6b, 6c, and 6d are schematic diagrams of a linear type guide vane, a spiral type guide vane, a hyperbolic type guide vane, and a logarithmic type guide vane, respectively, according to the present invention.
In the figure, 1-upstream rotary wheel disc, 11-first fixed groove, 12-second fixed groove, 2-upstream Duan Moguan type vortex reducer, 3-middle section ductless vortex reducer, 4-bias deflector, 41-linear guide vane, 42-spiral guide vane, 43-hyperbolic guide vane, 44-logarithmic curve type guide vane, 5-rotary shaft, 6-drum annular, 61-drum annular with locally unchanged thickness, 62-drum annular with locally thinned waist circular drum annular, 7-downstream rotary wheel disc.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the components are exaggerated for clarity.
As shown in fig. 1, the invention discloses a composite vortex reducer structure, which comprises an upstream rotary wheel disc 1, a downstream rotary wheel disc 7, a drum hole ring 6, an upstream Duan Moguan vortex reducer 2, a middle section ductless vortex reducer 3, a flow deflector 4 and a rotary shaft 5; the drum hole ring 6, the upstream Duan Moguan type vortex reducer 2, the middle section tubeless vortex reducer 3 and the flow diverter 4 are arranged between the upstream rotary wheel disc 1 and the downstream rotary wheel disc 7 from outside to inside, and the drum hole ring 6, the upstream Duan Moguan type vortex reducer 2, the middle section tubeless vortex reducer 3, the flow diverter 4, the upstream rotary wheel disc 1 and the downstream rotary wheel disc 7 are coaxial; the two sides of the drum annular ring 6, the upstream Duan Moguan type vortex reducer 2 and the middle section tubeless vortex reducer 3 are respectively fixedly connected with the inner wall surface of the upstream rotary wheel disc 1 and the inner wall surface of the downstream rotary wheel disc 7; the back surface of the flow diverter 4 is fixedly connected with the downstream rotary wheel disc 7, and the other surface is fixedly connected with the rotary shaft 5 through a flat key; the rotating shaft 5 and the flow deflector 4 are coaxial, and a plurality of drum holes are uniformly formed in the circumference of the drum hole ring 6.
The drum hole ring 6 can be designed to be of an integral structure with the upstream rotary wheel disc 1, is connected with the downstream rotary wheel disc 7 through bolts, and is provided with a plurality of straight-through comb teeth sealing rings on two sides of the drum hole, so that air flow can smoothly enter the drum hole instead of leaking from a gap between the root of a static blade above the drum hole and the rotary wheel disc. The upstream Duan Moguan vortex reducer 2 is circumferentially and uniformly provided with nozzles with despin angles, the inlets of the nozzles are rounded, the pressure loss when the air flow enters the nozzles is reduced, the outlets are not rounded, and the range of the outlet backflow area is reduced. The nozzle cross-sectional shape is elliptical to provide high uniformity and uniformity of the outlet airflow in the circumferential direction. The middle section ductless vortex reducer 3 is fixed with the upstream rotary wheel disc 1 and the downstream rotary wheel disc 7 respectively through screws. Nozzles with a chamfer are uniformly distributed in the circumferential direction, the inlet of the nozzle is rounded, and the outlet of the nozzle is kept sharp. The deflector 4 is connected with the rotating shaft 5 through a flat key and a locating pin, and is fixed with the downstream rotating wheel disc 7 through screws. The profile of the deflector 4 is arc-shaped, and the surface of the deflector is provided with linear guide vanes 41 uniformly distributed in the circumferential direction.
In the embodiment of fig. 2, the number of kidney-shaped holes in the kidney-shaped drum grommet 61 is the same as the number of despin nozzles in the upstream Duan Moguan type vortex breaker 2 and the intermediate ductless vortex breaker 3, and the kidney-shaped hole outlets are in the same circumferential position as the upstream Duan Moguan type vortex breaker 2 nozzle inlets; the air flow direction of the outlet of the nozzle of the upstream Duan Moguan vortex reducer 2 is in the same extension line with the inlet of the nozzle of the middle section ductless vortex reducer 3. Circumferentially distributed linear guide vanes 41 are radially arranged.
In fig. 3, a first fixing groove 11 and a second fixing groove 12 for fixing an upstream Duan Moguan type vortex breaker 2 and a middle-stage tubeless vortex breaker 3 are respectively arranged on the inner wall surface of an upstream rotary wheel disc 1, and a third fixing groove and a fourth fixing groove for fixing the upstream Duan Moguan type vortex breaker 2 and the middle-stage tubeless vortex breaker 3 are correspondingly arranged on the inner wall surface of a downstream rotary wheel disc 7; the two sides of the upstream Duan Moguan vortex reducer 2 are respectively arranged in the first fixed groove 11 and the third fixed groove; two sides of the middle section tubeless vortex reducer 3 are respectively arranged in the second fixed groove 12 and the fourth fixed groove; and both sides of the upstream Duan Moguan vortex reducer 2 and the middle section tubeless vortex reducer 3 are respectively fixedly connected with the upstream rotary wheel disc 1 and the downstream rotary wheel disc 7. The first to fourth fixing grooves are used for fixing the upstream Duan Moguan vortex reducer 2 and the middle non-tubular section vortex reducer 3, so that the vortex reducer is prevented from being separated under the action of centrifugal force, and the stability of the structure of the composite vortex reducer is improved.
Fig. 4 is a schematic view of a deflector with deflector employed in the embodiment of fig. 1-3. Fig. 5a is a schematic view of a waisted-shaped grommet 61 with a locally reduced thickness of the grommet, and fig. 5b is a partial schematic view of a waisted-shaped grommet 62 with a locally constant thickness of the grommet.
Fig. 6 a-6 d are schematic diagrams of four embodiments of the deflector profile with deflector according to the present invention. In the step 6a, the guide plates are linear, and the channels between the two guide plates are contracted channels, so that the air flow can be guided and accelerated, and the axial outlet air flow velocity field is improved. FIG. 6b shows a spiral profile deflector, which has smoother profile and better deflector effect; FIG. 6c is a hyperbolic profile baffle with better acceleration of the airflow as it flows therein, extracting power from the shaft, acting on the airflow, increasing its pressure; FIG. 6d shows an exponential profile deflector that can effectively adjust the direction of the reverse airflow under high flow conditions.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (10)
1. The composite vortex reducer structure is characterized by comprising an upstream rotary wheel disc (1), a downstream rotary wheel disc (7), a drum annular ring (6), an upstream Duan Moguan type vortex reducer (2), a middle section ductless vortex reducer (3), a flow deflector (4) and a rotary shaft (5);
the drum hole ring (6), the upstream Duan Moguan type vortex reducer (2), the middle section tubeless type vortex reducer (3) and the flow diverter (4) are arranged between the upstream rotary wheel disc (1) and the downstream rotary wheel disc (7) from outside to inside, and the drum hole ring (6), the upstream Duan Moguan type vortex reducer (2), the middle section tubeless type vortex reducer (3), the flow diverter (4), the upstream rotary wheel disc (1) and the downstream rotary wheel disc (7) are coaxial;
the two sides of the drum annular ring (6), the upstream Duan Moguan type vortex reducer (2) and the middle section tubeless type vortex reducer (3) are respectively fixedly connected with the inner wall surface of the upstream rotary wheel disc (1) and the inner wall surface of the downstream rotary wheel disc (7);
the back surface of the flow deflector (4) is fixedly connected with the downstream rotary wheel disc (7), and the other surface of the flow deflector is fixedly connected with the rotary shaft (5) through a flat key;
the rotating shaft (5) is coaxial with the flow deflector (4), and a plurality of drum holes are uniformly formed in the circumference of the drum hole ring (6).
2. A composite vortex breaker structure according to claim 1, characterized in that the shape of the drum holes in the drum hole ring (6) is circular or kidney-shaped.
3. A composite vortex breaker structure according to claim 2, characterized in that the thickness of the drum hole ring (6) is locally thinned in the vicinity of its drum hole.
4. The composite vortex breaker structure according to claim 1, wherein the cross-sectional shape of the nozzle in the upstream Duan Moguan vortex breaker (2) and the intermediate section ductless vortex breaker (3) is any one of circular, square, elliptical, and cascade.
5. The composite vortex breaker structure according to claim 1, wherein the axes of the nozzles in the upstream Duan Moguan vortex breaker (2) and the intermediate ductless vortex breaker (3) form a preset angle threshold with the tangential direction of the wheel disc, and the direction is opposite to the rotation direction of the wheel disc, and the angle range is 15-90 °.
6. The composite vortex breaker structure according to claim 5, wherein the number of the nozzles in the upstream Duan Moguan type vortex breaker (2) and the middle section ductless type vortex breaker (3) is the same and corresponds to one another, and the axes of the nozzles in the upstream Duan Moguan type vortex breaker (2) and the nozzles of the corresponding middle section ductless type vortex breaker (3) coincide.
7. The composite vortex breaker structure according to claim 1, wherein the inner wall surface of the upstream rotary wheel disc (1) is provided with a first fixing groove (11) and a second fixing groove for fixing the upstream Duan Moguan vortex breaker (2) and the middle-section ductless vortex breaker (3), and the inner wall surface of the downstream rotary wheel disc (7) is correspondingly provided with a third fixing groove and a fourth fixing groove for fixing the upstream Duan Moguan vortex breaker (2) and the middle-section ductless vortex breaker (3);
two sides of the upstream Duan Moguan vortex reducer (2) are respectively arranged in the first fixed groove and the third fixed groove;
two sides of the middle section tubeless vortex reducer (3) are respectively arranged in the second fixing groove and the fourth fixing groove;
and the two sides of the upstream Duan Moguan type vortex reducer (2) and the middle section tubeless type vortex reducer (3) are respectively fixedly connected with the upstream rotary wheel disc (1) and the downstream rotary wheel disc (7).
8. The composite vortex breaker structure according to claim 1, characterized in that the structural profile of the flow diverter (4) is circular arc-shaped.
9. The composite vortex breaker structure according to claim 8, wherein the structural profile of the deflector (4) is provided with circumferentially uniform flow deflectors.
10. The composite vortex breaker structure according to claim 9, wherein the profile of the guide vane is any one of a linear guide vane (41), a spiral guide vane (42), a hyperbolic guide vane (43) and a logarithmic guide vane (44).
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| CN201810399023.2A CN108425708B (en) | 2018-04-28 | 2018-04-28 | Combined vortex reducer structure |
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| CN201810399023.2A CN108425708B (en) | 2018-04-28 | 2018-04-28 | Combined vortex reducer structure |
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| CN108425708B true CN108425708B (en) | 2023-08-01 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110005525A (en) * | 2019-03-01 | 2019-07-12 | 南京航空航天大学 | It is a kind of to go the compressor of whirl spraying mouth to subtract vortex structure with cascade-type |
| CN110081027A (en) * | 2019-04-29 | 2019-08-02 | 南京航空航天大学 | It is a kind of to subtract whirlpool device bleed air system for the finned of compressor |
| CN110469540B (en) * | 2019-07-24 | 2020-10-20 | 南京航空航天大学 | Combined type vortex reducer structure and counter-rotating compressor system adopting same |
| CN112648077A (en) * | 2020-12-17 | 2021-04-13 | 北京航空航天大学 | Novel nozzle fin combined type vortex reducing system |
| 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 |
| CN115017838B (en) * | 2022-05-23 | 2024-09-20 | 南京航空航天大学 | Simulation method, system and storage medium for radial bleed air vortex reducer of axial-flow compressor |
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| CN203614465U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Baffle mode eddy device of gas compressor and gas compressor |
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| CN208236466U (en) * | 2018-04-28 | 2018-12-14 | 南京航空航天大学 | A kind of combined type subtracts whirlpool device structure |
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| JP4091874B2 (en) * | 2003-05-21 | 2008-05-28 | 本田技研工業株式会社 | Secondary air supply device for gas turbine engine |
| US8453463B2 (en) * | 2009-05-27 | 2013-06-04 | Pratt & Whitney Canada Corp. | Anti-vortex device for a gas turbine engine compressor |
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| CN105392963A (en) * | 2013-07-17 | 2016-03-09 | 西门子股份公司 | Rotor for a thermal turbomachine |
| CN203614465U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Baffle mode eddy device of gas compressor and gas compressor |
| CN208236466U (en) * | 2018-04-28 | 2018-12-14 | 南京航空航天大学 | A kind of combined type subtracts whirlpool device structure |
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