CN115585062A - Air inlet channel of oscillating Ramp type vortex generator based on adjustable frequency - Google Patents
Air inlet channel of oscillating Ramp type vortex generator based on adjustable frequency Download PDFInfo
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- CN115585062A CN115585062A CN202211121238.0A CN202211121238A CN115585062A CN 115585062 A CN115585062 A CN 115585062A CN 202211121238 A CN202211121238 A CN 202211121238A CN 115585062 A CN115585062 A CN 115585062A
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- air inlet
- vortex generator
- inlet channel
- ramp type
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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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an air inlet channel of an oscillation Ramp type vortex generator based on adjustable frequency, which comprises: supersonic air inlet channels, cam disc assemblies and oscillating Ramp type vortex generators with adjustable frequency. The motor, the cam disc, the supporting plate and other components are designed into a cam disc assembly in a fused mode, and the vortex generator is driven by the cam disc to swing in a variable height and frequency mode, so that the vortex generator can oscillate. Because the materials and the configuration of the actuating mechanism have diversity, the actuating mechanism can be designed to generate the required vibration height or vibration frequency according to the specific working environment and the action effect, and the actuating mechanism is arranged on the air inlet passage flow control surface of an aircraft, so that the flow separation caused by the interference of a shock wave boundary layer can be effectively inhibited.
Description
Technical Field
The invention belongs to the technical field of supersonic air inlets, and particularly relates to an air inlet of an oscillating Ramp type vortex generator based on adjustable frequency.
Background
Shock/boundary layer interference is an important flow phenomenon in supersonic air inlets. The phenomenon easily causes boundary layer separation and obvious total pressure loss, and the separated air flow even possibly blocks the throat of the air inlet under certain conditions to induce that the air inlet is not started, thereby seriously threatening the flight safety. Therefore, the suppression of the shock wave/boundary layer interference phenomenon in the air inlet channel is always a problem to be considered in the design of the supersonic air inlet channel.
In order to suppress separation caused by shock wave/boundary layer interference in a supersonic air inlet, boundary layer bleed air and a miniature ramp type vortex generator are widely used at present. Boundary layer deflation is a common flow control method in an air inlet channel, and the method enhances the capability of resisting against inverse pressure gradient by removing low-energy fluid in the boundary layer, thereby achieving the purpose of inhibiting separation. However, the boundary layer air bleeding method inevitably needs to bleed off a part of the air intake trapped airflow while achieving the control effect, and in order to supplement the flow loss, the trapping area of the air intake must be designed to be larger. In addition, the problems of air bleeding resistance caused by air bleeding and thermal protection of the air bleeding path at high Mach numbers cannot be ignored.
The height of the miniature slope type vortex generator is only 10% -70% of the thickness of the boundary layer, so that the miniature slope type vortex generator can obtain a control effect, and simultaneously greatly reduces the additional resistance of a control part, and the miniature slope type vortex generator mainly has a structure of a sharp wedge, a triangle, a blade type, a wing type, a trapezoid, a blade cascade and the like. The main advantage of this is that, compared to other flow control techniques, no additional energy and mass supply is required, and the generated flow vortices can remain in the boundary layer for long distances and do not easily lift off the boundary layer. However, from the results of the existing research, the micro ramp type vortex generator can only effectively control shock wave/boundary layer interference under certain conditions, and the existence of the micro ramp type vortex generator on the surface of an air inlet duct can destroy the aerodynamic characteristics of the aircraft, thereby increasing the oil consumption of the aircraft and reducing the aerodynamic performance of the aircraft. Moreover, the flow field in a practical supersonic inlet is very complex, and the control capability of the fixed geometry vortex generator can not meet the practical control requirement of the inlet. Obviously, a new form of air inlet needs to be further developed by combining the flow characteristics of the air inlet, and a new control strategy and a control method are provided to realize better control of the incident shock wave/boundary layer interference in the air inlet.
Disclosure of Invention
In order to solve the problems, the invention provides an air inlet based on an oscillation Ramp type vortex generator with adjustable frequency, which can effectively solve the problems of unstable load on the wall surface of the air inlet, distortion of a speed profile, increase of turbulence degree and reduction of the performance of the air inlet caused by the interference of a shock wave boundary layer. According to different flight Mach numbers and flight attack angles of inlets of the air inlet channels, the frequency-adjustable oscillation Ramp type vortex generator can induce a high-strength oscillation flow direction vortex structure through high-frequency oscillation, a stronger momentum mixing effect in a boundary layer is induced, and the control of the interference of the strong shock wave boundary layer is realized.
In order to achieve the purpose, the air inlet channel of the oscillating Ramp type vortex generator based on the adjustable frequency adopts the following technical scheme:
an air inlet channel of an oscillation Ramp type vortex generator based on adjustable frequency comprises an air inlet channel outer compression surface, an air inlet channel lip cover, air inlet channel side walls positioned on two sides of the air inlet channel lip cover and an air inlet channel inner surface; the inlet lip cover, the side walls of the inlet on two sides of the inlet lip cover and the inner surface of the inlet inner channel enclose an inlet inner channel; a groove is formed in the inner surface of the channel in the air inlet channel, and a Ramp type vortex generator assembly and a cam assembly positioned on the inner side of the Ramp type vortex generator assembly are arranged in the groove; the Ramp type vortex generator assembly comprises a spring steel plate clamped on the surface of the groove and a plurality of vortex generators which are cut out from the spring steel plate and arranged side by side, and the vortex generators are in a state of being attached to the outer surface of the spring steel plate in a free state; a through hole penetrating through the spring steel plate is formed in the inner side position of the vortex generator; the cam assembly comprises a disk-shaped cam disc, a guide rod which is positioned at the inner side of each wing and is inserted into the opening, and a support plate which carries the guide rod and is acted by the cam disc; the vortex generator is supported by the guide rod to be opened outwards into the inner channel when the guide rod is matched with the concave part, and the vortex generator returns to a free state and is positioned in a state of being attached to the outer surface of the spring steel plate.
Furthermore, a ball bearing is installed between the supporting plate and the cam disc, and the supporting plate extends inwards to form limiting plates which are located on two sides of the ball bearing and used for installing the ball bearing.
Furthermore, two support frames extending inwards are installed on the inner side of the spring steel plate, the cam disc is installed between the two support frames, and a motor for driving the cam disc to rotate is further arranged on one support frame; the support frame is close to the partial hollow design of spring steel plate in order to provide the installation space who bears guide arm and backup pad.
Furthermore, the vortex generator is triangular, the sharp corner of the triangle is positioned at the rear end, and the opening formed by the vortex generator and the spring steel plate is back to the inlet of the air inlet channel.
Furthermore, a plurality of vortex generators are arranged and driven by the same supporting plate, and when the cam plate rotates, the vibration frequency and the vibration amplitude of each vortex generator are the same.
Furthermore, the air inlet channel is a binary supersonic speed air inlet channel, the internal contraction ratio of the air inlet channel is 1.65, and the working Mach number range is 0-4; two stages of compression inclined planes are adopted, the wedge angle of the two inclined planes is 8.5 degrees, and the compression angles of the two stages of lip covers are respectively 9 degrees and 11 degrees; the thickness of the boundary layer of the inlet cross section of the air inlet is 1/18 of the inlet height h of the air inlet.
Furthermore, a plurality of vortex generators are arranged at equal intervals along the direction perpendicular to the fluid flow, and the interval is s =7.5h v Wherein h is v Maximum opening of vortex generatorA height; the vortex generator is arranged 32h in front of the shock wave non-adhesive incidence position v At least one of (1) and (b); the vortex generator leading edges are located on the same line.
Has the beneficial effects that: the invention provides an air inlet channel of an oscillation Ramp type vortex generator based on adjustable frequency, which can realize the change of vibration height and vibration frequency under the driving of an actuating mechanism, thereby inducing higher-intensity flow direction vortex with controllable frequency, realizing stronger momentum mixing effect, breaking through the limitation that the traditional fixed geometry vortex generator can only act on specific working conditions, greatly expanding the action range of the vortex generator and effectively solving some adverse effects generated by boundary layer separation caused by shock wave/boundary layer interference in the air inlet channel. Because the materials and the configuration of the actuating mechanism have diversity, the actuating mechanism can be designed to generate the required vibration height or vibration frequency according to the specific working environment and the action effect, so that the flow separation problem of the air inlet channel under different working conditions can be effectively solved, the back pressure resistance of the air inlet channel is improved while the flow field quality of the air inlet channel is improved, and the performance of the whole air inlet channel is improved.
Drawings
Fig. 1 is a three-dimensional diagram of an air inlet channel of an oscillating Ramp type vortex generator based on frequency modulation.
Fig. 2 is a cross-sectional view of an inlet of the adjustable frequency oscillating Ramp type vortex generator of the present invention in an initial position.
Fig. 3 is a cross-sectional view of the inlet of the frequency-adjustable oscillating Ramp type vortex generator of the present invention at the highest position.
Fig. 4 is a front view of an actuating mechanism in an intake passage of an oscillating Ramp type vortex generator based on frequency modulation according to the present invention.
Fig. 5 is a front view of the actuating mechanism in the air inlet channel of the oscillating Ramp type vortex generator based on frequency modulation of the invention.
Fig. 6 is a right side view of the actuating mechanism in the air inlet channel of the oscillating Ramp type vortex generator based on frequency modulation of the invention.
Fig. 7 is a structure diagram of a vortex generator of an air inlet channel of an oscillating Ramp type vortex generator based on frequency modulation according to the present invention.
Detailed Description
The invention discloses an air inlet channel of an oscillating Ramp type vortex generator based on adjustable frequency, and the technical scheme provided by the invention is explained in detail in the following by combining with the attached drawings.
Referring to fig. 1 to 7, the present invention provides an air intake duct based on an oscillating Ramp type vortex generator with adjustable frequency, which includes a cam plate assembly and a flow control member vortex generator.
The air inlet comprises an oscillating Ramp type vortex generator assembly, an air inlet outer compression surface 2, an air inlet lip cover 3, an air inlet inner channel surface and air inlet side walls 5 positioned on two sides of the air inlet lip cover; the inlet channel lip cover 3 is positioned outside the surface of the inner channel, and the lip cover 3, the inlet channel side wall 5 and the surface of the inner channel form an inlet channel inner channel 4; the frequency-adjustable oscillation Ramp type vortex generator 1 is placed on the inner channel surface 4 of the air inlet channel, and when the performance of the air inlet channel is influenced by separation to a small extent, the vortex generator 1 is embedded into the inner channel lower surface 4 to keep the wall surface flat; when the performance of the air inlet channel is greatly influenced by separation, the vortex generator 1 can oscillate up and down through controllable frequency; the spring steel plate 14 is embedded in the lower surface of the air inlet duct inner passage.
The cam disc assembly comprises a front driving part and a rear driving part, wherein the front driving part comprises a motor 7, a transmission shaft 8, a key groove 9, a cam disc 13, a support frame 10 and a guide column 10.1, and the rear driving part comprises a guide rod 11.1, a support plate 11.2, a limiting plate 11.3 and a ball bearing 12.
As shown in fig. 1, 5 and 7, the flow control member includes a triangular vortex generator 1, the triangular vortex generator 1 is a V-shaped vortex generator 1 formed by cutting a spring steel plate 14, a tip of the vortex generator 1 is separated from the spring steel plate 14, and a wider end of the vortex generator 1 is not separated from the spring steel plate 14 and is bent to form a vortex generator oscillation shaft 6 structure. Since the vortex generator 1 is formed by cutting the spring steel plate 14, it has an initial elastic force, and when the vortex generator 1 is in an unstressed free state, the vortex generator 1 is attached to the outer surface of the spring steel plate 14, as shown in position 1.2 in fig. 7. The spring steel plate 14 is connected with the surface of the channel in the air inlet channel through a flat head screw. The thickness of the spring steel plate 14 is larger than that of the vortex generator 1, the width of the spring steel plate 14 does not exceed the width of the surface of the channel in the air inlet channel, and the flow direction position of the spring steel plate 14 and the position of the vortex generator 1 are determined by the incident position of the lip cover.
The bottom surface of the vortex generator 1 is connected with a rear driving part guide rod 7.1, a cam disc 13 rotates to drive a support plate 11.2 and the guide rod 11.1 to move up and down, and then the guide rod 11.1 pushes the vortex generator 1 to move up and down around a vortex generator oscillation shaft 6. Specifically, the cam plate 13 is provided with a plurality of cam portions uniformly arranged on the outer edge, and a concave portion is arranged between two adjacent cam portions. The cam disc 13 rotates to drive the guide rod 11.1 to protrude outwards according to the corresponding frequency. When the guide rod 11.1 is engaged with the cam portion to protrude outward, the vortex generator 1 is abutted by the guide rod 11.1 to open outward into the inner passage 4 (as shown in position 1.1 in fig. 7, which is the maximum outward opening position of the vortex generator 1), and when the guide rod 11.1 is engaged with the recessed portion, the vortex generator 1 returns to the free state, i.e., returns to the state of being engaged with the outer surface of the spring steel plate 14 (as shown in position 1.2 in fig. 7).
The air inlet channel is a binary supersonic speed air inlet channel, the internal contraction ratio of the air inlet channel is 1.65, and the working Mach number range is 0-4; the two-stage compression inclined plane 2 is adopted, the wedge angle of the two inclined planes is 8.5 degrees, and the compression angles of the two-stage lip covers are respectively 9 degrees and 11 degrees; the thickness of the boundary layer of the inlet section of the air inlet channel is 1/18 of the inlet height h of the air inlet channel;
as shown in fig. 1, 5 and 7, the rotation speed of the motor 7 of the front driving part of the cam plate structure is adjustable; the transmission shaft 8 and the cam disc 13 are limited through a key groove 9; two ends of the transmission shaft 8 are fixed on the support frame 10, the guide post 10.1 on the support frame 10 penetrates through the support plate 11.2, the support plate 11.2 is maintained to move along the direction of the guide post 10.1, and the support plate 11.2 is prevented from being transversely clamped due to external load; the windward side of the support frame 10 should be sharpened.
As shown in fig. 1, 5 and 7, one end of the guide rod 11.1 of the rear driving part is connected to the vortex generator 1, and the other end is connected to the support plate 11.2 and driven by the rotating cam disc 13 to vibrate up and down; the ball bearing 12 additionally arranged between the cam disc 13 and the support plate 11.2 is a standard component produced according to the national standard GB/T272-1993, so that the transmission process of the cam disc 13 is ensured to be smoothly carried out; the limiting plate 11.3 has a limiting effect and prevents the rolling bearing 12 from moving transversely.
As shown in fig. 1 to 5, a higher vibration frequency is obtained by increasing the number of the convex portions on the cam disc 13, the cam disc 13 rotates one turn, which is equivalent to six round trips of the support plate 11.2 through six cams, and the vortex generator 1 swings up and down six times, which is six times higher than the frequency obtained by using the conventional cam, and the whole process of the mechanism motion is natural, and no dead point or inertia force is generated, so that the mechanism has better stability. The cam disc 13 is driven by the motor 7, the rotating speed of the motor 7 is adjustable, and the frequency of the up-and-down reciprocating oscillation of the vortex generator 1 around the oscillation shaft 6 of the vortex generator is controlled by controlling the rotating speed of the cam disc 13.
Referring to fig. 5 and 7, the vortex generators 1 are equally spaced in a direction perpendicular to the fluid flow, and the spacing is s =7.5h v (wherein h is v The maximum height at which the vortex generator can oscillate); the vortex generators are arranged 32h in front of the shock wave non-adhesive incidence position v At least one of (1) and (b); the front edges of the vortex generators are positioned on the same straight line to form a vortex generator row vertical to the incoming flow; the arranged vortex generators 1 are driven by the same supporting plate 11.2, and the vibration frequency and the vibration amplitude of each vortex generator 1 are the same.
In the present embodiment, the half apex angle AP of the vortex generator 1 is 24 °, and the slope chord length c =7.2h v The bottom is an isosceles triangle; the thickness of the vortex generator 1 (i.e. the thickness of the V-shape cut by the spring steel plate) can be changed; the initial position of the vortex generator is within a recess in the spring steel plate 14; the front edge of the vortex generator is vertical to the incoming flow direction, the tail edge swings up and down around the oscillation shaft 6 of the vortex generator, and the swinging direction is vertical to the spring steel plate 14; the number of the vortex generators 1 is determined by the width of the lower surface 4 of the inner channel; maximum oscillation height h of vortex generator 1 v The value is 10% -70% of the thickness of the local boundary layer.
The oscillation height and frequency of the frequency-adjustable oscillation Ramp type vortex generator 1 can be adjusted according to the actual control requirement of the air inlet channel.
The invention has many ways to implement the technical scheme, and the above description is only one of the embodiments of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (7)
1. An air inlet channel of an oscillating Ramp type vortex generator based on adjustable frequency is characterized in that:
comprises an external compression surface (2) of the air inlet, an air inlet lip cover (3), air inlet side walls (5) positioned at two sides of the air inlet lip cover and an internal surface of an internal channel of the air inlet; an air inlet channel inner channel (4) is defined by the air inlet channel lip cover (3), the air inlet channel side walls (5) positioned at two sides of the air inlet channel lip cover and the inner surface of the air inlet channel inner channel;
a groove is formed in the inner surface of the channel in the air inlet channel, and a Ramp type vortex generator assembly and a cam assembly positioned on the inner side of the Ramp type vortex generator assembly are arranged in the groove;
the Ramp type vortex generator assembly comprises a spring steel plate (14) clamped on the surface of the groove and a plurality of vortex generators (1) which are cut out from the spring steel plate (14) and arranged side by side, wherein the vortex generators (1) are in a state of being attached to the outer surface of the spring steel plate (14) in a free state; a through hole penetrating through the spring steel plate (14) is formed in the inner side of the vortex generator (1); the cam assembly comprises a disk-shaped cam disk (13), a guide rod (11.1) which is located inside each vane and is inserted into the opening, and a support plate (11.2) which carries the guide rod (11.1) and is acted on by the cam disk (13); the cam disc (13) is provided with a plurality of cam parts uniformly arranged on the outer edge, a concave part is arranged between every two adjacent cam parts, the cam disc (13) rotates to drive the guide rod (11.1) to protrude outwards according to corresponding frequency, when the guide rod (11.1) is matched with the cam parts to protrude outwards, the vortex generator (1) is abutted by the guide rod (11.1) to open outwards into the inner channel, and when the guide rod (11.1) is matched with the concave part, the vortex generator (1) returns to a free state, namely, returns to a state of being attached to the outer surface of the spring steel plate (14).
2. The air inlet channel based on the oscillating Ramp type vortex generator with adjustable frequency according to claim 1, characterized in that: install ball bearing (12) between backup pad (11.2) and cam disc (13), backup pad (11.2) inwards extends and is located ball bearing (12) both sides and is used for installing limiting plate (11.3) of ball bearing (12).
3. The air inlet channel based on the oscillating Ramp type vortex generator with adjustable frequency according to claim 2, characterized in that: two support frames (10) extending inwards are arranged on the inner side of the spring steel plate (14), the cam disc (13) is arranged between the two support frames (10), and a motor for driving the cam disc (13) to rotate is further arranged on one support frame (10); the support frame (10) is partially designed to be hollow close to the spring steel plate (14) so as to provide an installation space for the bearing guide rod (11.1) and the support plate (11.2).
4. The air inlet channel based on the adjustable-frequency oscillating Ramp type vortex generator as claimed in claim 3, characterized in that: vortex generator (1) is triangle-shaped, and triangle-shaped's closed angle is located the rear end, and the opening that vortex generator (1) and spring steel plate (14) formed back to the intake duct import.
5. The air inlet channel based on the adjustable-frequency oscillating Ramp type vortex generator as claimed in claim 4, wherein: the plurality of vortex generators (1) are driven by the same supporting plate (11.2), and when the cam disc (13) rotates, the vibration frequency and the vibration amplitude of each vortex generator (1) are the same.
6. The air inlet channel based on the adjustable-frequency oscillating Ramp type vortex generator as claimed in claim 5, wherein: the air inlet channel is a binary supersonic speed air inlet channel, the internal contraction ratio of the air inlet channel is 1.65, and the working Mach number range is 0-4; two-stage compression inclined planes (2) are adopted, the wedge angle of the two inclined planes is 8.5 degrees, and the compression angles of the two-stage lip covers are respectively 9 degrees and 11 degrees; the thickness of the boundary layer of the inlet cross section of the air inlet is 1/18 of the inlet height h of the air inlet.
7. The air inlet channel based on the oscillating Ramp type vortex generator with adjustable frequency according to claim 1, characterized in that: the vortex generators (1) are arranged at equal intervals along the direction perpendicular to the fluid flow, and the interval is s =7.5h v Wherein h is v Is the maximum height at which the vortex generator (1) is open; the vortex generator (1) is arranged 32h in front of the shock wave non-adhesive incidence position v At least one of (1) and (b); the front edges of the vortex generators (1) are positioned on the same straight line.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211121238.0A CN115585062B (en) | 2022-09-15 | 2022-09-15 | Air inlet channel based on oscillation type Ramp type vortex generator capable of adjusting frequency |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211121238.0A CN115585062B (en) | 2022-09-15 | 2022-09-15 | Air inlet channel based on oscillation type Ramp type vortex generator capable of adjusting frequency |
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| Publication Number | Publication Date |
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| CN115585062A true CN115585062A (en) | 2023-01-10 |
| CN115585062B CN115585062B (en) | 2023-06-20 |
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| CN202211121238.0A Active CN115585062B (en) | 2022-09-15 | 2022-09-15 | Air inlet channel based on oscillation type Ramp type vortex generator capable of adjusting frequency |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116659807A (en) * | 2023-07-27 | 2023-08-29 | 南京理工大学 | High super air inlet channel shock wave/boundary layer interference and wall plate fluid-solid coupling experimental device |
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| GB747705A (en) * | 1953-02-06 | 1956-04-11 | Rene Leduc | Improvements in and relating to aero-thermodynamic ducts adapted to operate at supersonic speeds |
| GB2070139A (en) * | 1980-02-26 | 1981-09-03 | Gen Electric | Inlet Cowl for Supersonic Aircraft Engine |
| EP2071155A2 (en) * | 2007-12-14 | 2009-06-17 | United Technologies Corporation | Nacelle assembly with turbulators |
| US20120325325A1 (en) * | 2011-06-23 | 2012-12-27 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN115030817A (en) * | 2022-04-14 | 2022-09-09 | 中国航天空气动力技术研究院 | Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine |
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2022
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB747705A (en) * | 1953-02-06 | 1956-04-11 | Rene Leduc | Improvements in and relating to aero-thermodynamic ducts adapted to operate at supersonic speeds |
| GB2070139A (en) * | 1980-02-26 | 1981-09-03 | Gen Electric | Inlet Cowl for Supersonic Aircraft Engine |
| EP2071155A2 (en) * | 2007-12-14 | 2009-06-17 | United Technologies Corporation | Nacelle assembly with turbulators |
| US20120325325A1 (en) * | 2011-06-23 | 2012-12-27 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN115030817A (en) * | 2022-04-14 | 2022-09-09 | 中国航天空气动力技术研究院 | Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116659807A (en) * | 2023-07-27 | 2023-08-29 | 南京理工大学 | High super air inlet channel shock wave/boundary layer interference and wall plate fluid-solid coupling experimental device |
| CN116659807B (en) * | 2023-07-27 | 2023-10-03 | 南京理工大学 | High super air inlet channel shock wave/boundary layer interference and wall plate fluid-solid coupling experimental device |
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| CN115585062B (en) | 2023-06-20 |
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