CN109367796B - Embedded air inlet boundary layer control device based on fluid oscillator - Google Patents
Embedded air inlet boundary layer control device based on fluid oscillator Download PDFInfo
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- CN109367796B CN109367796B CN201811083924.7A CN201811083924A CN109367796B CN 109367796 B CN109367796 B CN 109367796B CN 201811083924 A CN201811083924 A CN 201811083924A CN 109367796 B CN109367796 B CN 109367796B
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- oscillator
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- seam
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
Abstract
The invention provides an embedded air inlet boundary layer control device based on a fluid oscillator, wherein a plurality of oscillators are arranged in an aircraft body (1), and low-energy flow of the boundary layer is blown off and sucked through the oscillators. Compared with the traditional single blowing or sucking of low energy flow of the boundary layer, the invention can obviously improve the total pressure recovery coefficient of the embedded air inlet channel, effectively reduce the distortion index and has good engineering application value.
Description
Technical Field
The invention belongs to the field of aerodynamic design of aircrafts, and relates to a boundary layer control device, in particular to an embedded type air inlet boundary layer control device based on a fluid oscillator.
Background
The submerged air intake is a special air intake that integrates an inlet with an aircraft without any protruding parts. The embedded air inlet channel not only can effectively reduce the windward resistance and the radar scattering area of the aircraft due to small windward area, but also can reduce the size of the aircraft body due to the integration of the embedded air inlet channel and the aircraft body, and is favorable for installation, transportation and multi-platform emission. As a result, submerged air intakes are receiving increasing attention and applications.
However, just as the inlet of the submerged inlet is placed entirely within the low energy flow of the fuselage/missile body boundary layer, it relies solely on the pressure gradient perpendicular to the incoming flow direction of the forward lip and the swirl induced by the lateral edges. Therefore, the embedded air inlet can suck a large amount of low-energy flow, and the total pressure recovery coefficient of the outlet of the air inlet is low and the distortion is overlarge.
Patent CN102249004 and patent CN101994570 propose a solution of boundary layer both-side blowing method and boundary layer bleed air based on vortex generators to improve the performance of the submerged intake duct, and patent ZL201318007259.5 proposes a boundary layer trailing edge notch blowing method based on vortex generators to improve the performance of the submerged intake duct. The invention provides a boundary layer control idea based on a fluidic oscillator to improve the performance of an embedded air inlet channel.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the problems of low total pressure recovery coefficient and large outlet flow field distortion of the current embedded air inlet channel, the invention provides a boundary layer control idea based on a fluid oscillator, which is different from a vortex generator and boundary layer deflation, so as to improve the performance of the embedded air inlet channel.
The technical scheme of the invention is as follows: a plurality of oscillators are installed in an aircraft body 1, and low-energy flow of a boundary layer is blown off and sucked through the oscillators.
The utility model provides an bury formula intake duct boundary layer controlling means based on fluid oscillator, the oscillator is installed in intake duct 7 the place ahead to 7 central division planes symmetric distributions in the intake duct import, distribution position, logarithm are all adjustable alone.
The utility model provides an bury formula intake duct boundary layer controlling means based on fluid oscillator, the oscillator includes that first oscillator goes out gas seam 2, second oscillator play gas seam 3, high-pressure chamber 4, oscillator entry 5, oscillator feedback chamber 6, first oscillator goes out gas seam 2, second oscillator play gas seam 3 and is located aircraft organism 1 surface, and high-speed air current passes through oscillator entry 5 and moves in oscillator feedback chamber 6 in high-pressure chamber 4, goes out gas seam 2 or the second oscillator through first oscillator and gives vent to anger seam 3 and flows out, gives vent to anger seam 2 and produces the efflux when first oscillator, and second oscillator goes out gas seam 3 and can take place to produce the refluence simultaneously to reduce the boundary layer low energy flow that gets into the aircraft organism 1 surface of intake duct 7.
In the embedded type air inlet boundary layer control device based on the fluid oscillator, a certain angle theta is formed between the oscillator inlet 5, the first oscillator air outlet seam 2 and the second oscillator air outlet seam 3 and the central separation surface of the air inlet 7; the included angle alpha between the inlet 5 of the oscillator and the cross section of the aircraft body 1 is formed; the first oscillator air outlet gap 2 and the second oscillator air outlet gap 3 respectively form certain angles beta 1 and beta 2 with the cross section of the aircraft body 1; the angles theta, alpha, beta 1 and beta 2 are independently adjustable and are changed between 0 degree and 90 degrees.
The invention has the advantages that:
according to the embedded type air inlet boundary layer control device based on the fluid oscillator, the fluid oscillator is arranged in the aircraft body, and the two air outlet seams of the oscillator blow off and suck the boundary layer on the surface of the front body of the inlet of the air inlet. Compared with the traditional single blowing or sucking of low energy flow of the boundary layer, the invention can obviously improve the total pressure recovery coefficient of the embedded air inlet channel, effectively reduce the distortion index and has good engineering application value.
Description of the drawings:
FIG. 1 is a top plan view of the layout of the present invention;
wherein: 1, an aircraft body 2, a first oscillator air outlet gap 3, a second oscillator air outlet gap 7 and an air inlet;
FIG. 2 is a side view of the layout of the present invention;
wherein: an inlet 8 of an air inlet channel of an aircraft body 7 is embedded in the air inlet channel;
FIG. 3 is a front view of the present invention;
wherein: 4 high pressure chamber 5 oscillator inlet 6 oscillator feedback chamber.
The specific implementation mode is as follows:
the invention discloses an embedded air inlet boundary layer control device based on a fluid oscillator.
As shown in fig. 1 to 3, the boundary layer control device is installed in front of the inlet 7 of the air intake, and is symmetrically distributed with the central partition plane of the inlet 7 of the air intake, and the distribution position and the logarithm are both independently adjustable.
An embedded air inlet boundary layer control device based on a fluid oscillator comprises a first oscillator air outlet seam 2, a second oscillator air outlet seam 3, a high-pressure cavity 4, an oscillator inlet 5 and an oscillator feedback cavity 6. The central separation surface of the oscillator inlet 5, the first oscillator air outlet gap 2, the second oscillator air outlet gap 3 and the air inlet channel inlet 7 forms a certain angle theta, the included angle alpha between the oscillator inlet 5 and the cross section of the aircraft body 1 is formed, and the first oscillator air outlet gap 2 and the second oscillator air outlet gap 3 respectively form certain angles beta 1 and beta 2 with the cross section of the aircraft body 1. The angles theta, alpha, beta 1 and beta 2 are independently adjustable and are changed between 0 degree and 90 degrees.
The first oscillator air outlet gap 2 and the second oscillator air outlet gap 3 are located on the surface of the aircraft body 1, and high-speed airflow in the high-pressure cavity 4 moves in the oscillator feedback cavity 6 through the oscillator inlet 5 and flows out through the first oscillator air outlet gap 2 or the second oscillator air outlet gap 3. When the first oscillator air outlet seam 2 generates jet flow, the second oscillator air outlet seam 3 simultaneously generates backflow to generate suction, so that the boundary layer low-energy flow of the surface of the aircraft body 1 entering the air inlet channel inlet 7 is reduced.
Claims (2)
1. An embedded air inlet boundary layer control device based on a fluid oscillator is characterized in that a plurality of oscillators are installed in an aircraft body (1), and boundary layer low-energy flow is blown off and sucked through the oscillators;
the oscillator is arranged in front of the inlet (7) of the air inlet and symmetrically distributed on the central separation plane of the inlet (7) of the air inlet, and the distribution position and the logarithm are both independently adjustable;
the oscillator includes that first oscillator goes out gas seam (2), second oscillator play gas seam (3), high-pressure chamber (4), oscillator entry (5), oscillator feedback chamber (6), first oscillator goes out gas seam (2), second oscillator play gas seam (3) and is located aircraft organism (1) surface, and high-speed air current passes through oscillator entry (5) and moves in oscillator feedback chamber (6) in high-pressure cavity (4), goes out gas seam (2) or second oscillator play gas seam (3) through first oscillator and flows, and gas seam (2) produce the efflux when first oscillator, and the second oscillator goes out gas seam (3) can take place the refluence simultaneously and produce the suction to reduce the boundary layer low-energy flow that gets into aircraft organism (1) surface of intake duct import (7).
2. The device for controlling the boundary layer of the embedded air inlet based on the fluidic oscillator as recited in claim 1, wherein the oscillator inlet (5), the first oscillator air outlet slit (2), and the second oscillator air outlet slit (3) all form a certain angle θ with the central separation plane of the air inlet (7); the included angle alpha between the inlet (5) of the oscillator and the cross section of the aircraft body (1); the first oscillator air outlet seam (2) and the second oscillator air outlet seam (3) respectively form certain angles beta 1 and beta 2 with the cross section of the aircraft body (1); the angles theta, alpha, beta 1 and beta 2 are independently adjustable and are changed between 0 degree and 90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811083924.7A CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811083924.7A CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
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| CN109367796A CN109367796A (en) | 2019-02-22 |
| CN109367796B true CN109367796B (en) | 2022-03-15 |
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| CN201811083924.7A Active CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1950255A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Boundary layer suction arrangement |
| CN101956996A (en) * | 2009-07-08 | 2011-01-26 | 通用电气公司 | The adjustable fluid flow system |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102249004A (en) * | 2011-05-23 | 2011-11-23 | 南京航空航天大学 | Aircraft using submerged intake |
| CN103616155A (en) * | 2013-11-29 | 2014-03-05 | 中国人民解放军国防科学技术大学 | Flow control device of supersonic flow field |
| CN106809377A (en) * | 2015-12-01 | 2017-06-09 | 波音公司 | A kind of aerodynamic simplified fluidic oscillator for controlling aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020134891A1 (en) * | 2001-02-09 | 2002-09-26 | Guillot Stephen A. | Ejector pump flow control |
| US7967258B2 (en) * | 2005-10-06 | 2011-06-28 | Lockheed Martin Corporation | Dual bimorph synthetic pulsator |
-
2018
- 2018-09-17 CN CN201811083924.7A patent/CN109367796B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1950255A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Boundary layer suction arrangement |
| CN101956996A (en) * | 2009-07-08 | 2011-01-26 | 通用电气公司 | The adjustable fluid flow system |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102249004A (en) * | 2011-05-23 | 2011-11-23 | 南京航空航天大学 | Aircraft using submerged intake |
| CN103616155A (en) * | 2013-11-29 | 2014-03-05 | 中国人民解放军国防科学技术大学 | Flow control device of supersonic flow field |
| CN106809377A (en) * | 2015-12-01 | 2017-06-09 | 波音公司 | A kind of aerodynamic simplified fluidic oscillator for controlling aircraft |
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| CN109367796A (en) | 2019-02-22 |
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