CN114576010A - Three-dimensional inward-rotation adjustable air inlet with two-stage compression characteristic and design method - Google Patents
Three-dimensional inward-rotation adjustable air inlet with two-stage compression characteristic and design method Download PDFInfo
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- CN114576010A CN114576010A CN202210154713.8A CN202210154713A CN114576010A CN 114576010 A CN114576010 A CN 114576010A CN 202210154713 A CN202210154713 A CN 202210154713A CN 114576010 A CN114576010 A CN 114576010A
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- 230000035939 shock Effects 0.000 claims description 41
- 238000007789 sealing Methods 0.000 claims description 7
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- 239000006185 dispersion Substances 0.000 claims description 6
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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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/10—Drag reduction
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Abstract
The invention discloses a three-dimensional inward-turning adjustable air inlet with two-stage compression characteristics and a design method thereof. The problem that the air inlet duct does not start under the low Mach number can be solved, the working Mach number range of the inward turning air inlet duct is widened, meanwhile, the compression efficiency of the air inlet duct under the high Mach number can be enhanced, the performance of the air inlet duct is improved, and the flow matching of the rotating air inlet duct/engine in a wide speed range can be realized.
Description
Technical Field
The invention relates to a wide-speed-range variable-geometry three-dimensional inward rotation air inlet applied to rocket-based combined power (RBCC), and belongs to the field of air inlet pneumatic design.
Background
The rocket-based combined power system (RBCC) combines a low-specific-impulse rocket engine and a high-specific-impulse air-breathing type ramjet engine, has the characteristics of wide Mach number range working, mature rocket technology, good economy and the like, is suitable for hypersonic flight, and is the combined power system firstly used on a hypersonic aircraft.
The hypersonic aircraft using the rocket-based combined cycle engine has the working modes as follows: the aircraft is accelerated to the working Mach number of the ramjet by the rocket engine, the rocket engine is closed, the ramjet starts to work, and the main flight phase is the work of the ramjet. The air inlet channel is used as a main windward part of the ramjet engine, the main function of the air inlet channel is to capture air flow and provide air flow with certain quality for the combustion chamber, and the performance of the air inlet channel influences whether the ramjet engine can work normally.
The common air inlet passage mainly comprises three typical air inlet passages of an axial symmetry type, a binary type and a side pressure type, and the main compression modes are shock wave compression. Since shock compression is the dominant mode, its compression efficiency is low. When the high-mach-number incoming flow is compressed to a certain mach number, multi-wave system compression is often adopted, so that the problem that a flow field in an air inlet channel has more shock waves and boundary layer interaction is caused, and the compression efficiency is further reduced. Since the last forty years, some scholars are separated from the traditional design idea of the hypersonic inlet, and a three-dimensional internal contraction inlet is provided.
The internal turn intake duct generally has a design point near the maximum flight mach number, which determines the intake duct size. At non-design points, a severe phenomenon, no start, occurs at low mach numbers with fixed geometry design inlets. To avoid this phenomenon, the intake duct often adopts a variable geometry design (changing the geometry profile) to improve the intake duct starting performance. But because the molded surface of the inward turning air inlet is a three-dimensional compression curved surface designed by adopting a streamline tracing method, the difficulty of a variable geometry scheme is increased. In order to realize wide-speed-range flight of hypersonic flight, the scheme design that the inward rotation three-dimensional compression characteristic is compatible with the variable geometry mode aerodynamics is significant.
Disclosure of Invention
The invention aims to provide a variable geometry inner rotation air inlet pneumatic design method with two-stage compression characteristics and an adjusting scheme based on high-flow capture characteristics and efficient three-dimensional compression characteristics of an inner rotation air inlet, so as to solve the problems of low-mach-number non-starting and wide-speed-range (Ma 2-8) air inlet/engine flow matching existing in a fixed geometry inner rotation air inlet and widen the working range of the inner rotation air inlet.
In order to achieve the purpose, the invention adopts the following technical scheme:
a three-dimensional inward turning adjustable air inlet with two-stage compression characteristics comprises an inward turning air inlet capturing molded line, a fixed inward turning three-dimensional curved surface, a two-stage curved surface compression plate (surface), a reconstructed three-dimensional curved surface, a fixed distribution wedge, a flow adjusting flow passage and a main flow passage; fixed adversion three-dimensional curved surface is the local profile of adversion intake duct, and fixed adversion three-dimensional curved surface is tangent with second grade curved surface compression board exhibition to linking department, has the three-dimensional compression characteristic of partial adversion intake duct.
Furthermore, the secondary curved surface compression plate (surface) is a rotatable compression plate with equal width; when the second-stage curved surface compression plate rotates by an angle theta, the second-stage curved surface compression plate (surface) generates oblique shock waves, and the air inlet channel has three-dimensional compression characteristics of an inward-turning air inlet channel and two-stage shock wave compression characteristics at the same time; when the rotation angle of the second-level curved surface compression plate (surface) is in smooth transition with the fixed inward-rotation three-dimensional curved surface, the air inlet channel only has the three-dimensional compression characteristic.
Further, the molded lines are fixed to the inlet capture of the inward turning air inlet channel.
Furthermore, the fixed inward-turning three-dimensional curved surface is connected with the second-level curved surface compression plate (surface) through a pin. Similar to the connecting structure when the door rotates, in the unfolding direction, two lugs are protruded at two sides of the fixed compression surface, the middle of the fixed compression surface is sunken, two lugs are sunken at two sides of the rotary compression surface, the middle of the rotary compression surface is protruded, and the rotary pin penetrates through the lugs of the fixed compression surface and the protruded part of the rotary compression surface.
Furthermore, the two-stage curved surface compression plate (surface) rotates through a crank-slider mechanism. In practical conditions, the air inlet is installed on an airplane, and the problem of connection between a mechanism and the airplane body is not needed to be considered on the air inlet.
Furthermore, the reconstructed three-dimensional curved surface keeps the capture molded line of the front edge of the capture inlet of the inward-turning air inlet channel unchanged.
A design method of a three-dimensional inward turning adjustable air inlet with two-stage compression characteristics is characterized in that on the basis of an original inward turning air inlet, the characteristics of an inlet capture molded line of the inward turning air inlet and a part of a fixed inward turning three-dimensional curved surface are reserved.
Further, the design method of the two-stage curved surface compression plate (surface) comprises the following steps: when the Mach number is designed, a secondary curved surface compression surface is designed according to a second oblique shock wave sealing principle of a symmetrical surface of the air inlet channel, and the conventional binary shock wave sealing design principle of the air inlet channel is used for reference. And calculating a secondary compression angle through an oblique shock wave relational expression according to the Ma in front of the second-stage compression surface of the symmetric surface and the oblique shock wave angle, performing point dispersion on the molded line and the throat at the cut-off position of the fixed compression surface, and generating the secondary compression surface by adopting a B-spline curve.
Furthermore, the reconstruction of the three-dimensional curved surface is to compress the plate molded surface according to the fixed inward turning three-dimensional curved surface and the two-stage curved surface, reconstruct the inner molded surface of the air inlet on the basis of ensuring that the molded line of the captured inlet front edge of the inward turning air inlet is not changed, namely, perform curved surface sweep according to the captured inlet molded line, the molded line of the throat and the curved surface boundary generated by the B spline curve. The advantages are that: the front edge angle of the reconstructed three-dimensional curved surface is controlled, and the position of the lip reflected shock wave hitting the secondary curved surface compression plate is adjusted, so that the purpose of eliminating shoulder separation is achieved; secondly, the shape of the outlet of the three-dimensional curved surface can be controlled and reconstructed according to requirements to form throat shapes with different sizes.
Further, the position of a lip reflection shock wave hitting a secondary curved surface compression plate is adjusted by controlling a reconstructed three-dimensional curved surface leading edge angle alpha, so that the purpose of eliminating shoulder separation is achieved, namely point dispersion is carried out according to an inward turning leading edge capture line and a throat rectangle, and a B spline curve is adopted to generate a three-dimensional curved surface; the lip shock wave falling point position is controlled by controlling the leading edge molded line angle, and the separation caused by shock wave boundary layer interference on the shoulder part is avoided when the design point is ensured.
Has the advantages that: the invention provides a variable geometry inward turning air inlet with an inward turning air inlet three-dimensional compression characteristic and a two-stage shock wave compression characteristic, which solves the problem that the air inlet cannot be started under low Mach number and widens the working Mach number range of the inward turning air inlet; meanwhile, the compression efficiency of the air inlet channel under high Mach number is enhanced, the performance of the air inlet channel is improved, and the flow matching of the rotating air inlet channel/engine in a wide speed range can be realized.
The method specifically comprises the following steps: (1) the adjustable internal-rotation air inlet has two-stage compression characteristics. When the second-stage curved surface compression plate rotates by an angle theta, the second-stage curved surface compression plate generates oblique shock waves, and the air inlet channel has three-dimensional compression characteristics of an inward-turning air inlet channel and compression characteristics of the second-stage shock waves; when the rotation angle of the second-level curved surface compression plate is in smooth transition with the fixed inward-turning three-dimensional curved surface, the air inlet channel only has three-dimensional compression characteristics. The advantages are that: when the high-Mach-number air inlet works, the air inlet has three-dimensional compression and two-stage shock wave compression characteristics, the air flow compression efficiency is further enhanced on the basis of an internal rotation air inlet, and the performance of the air inlet is improved; when the low-Mach-number compressor works, the air inlet channel only has three-dimensional compression characteristics, the curved surface inside the air inlet channel is smooth in transition, the area shrinkage of the channel in the air inlet channel and the three-dimensional compression characteristics of the inner-rotation air inlet channel are guaranteed, and the reduction of compression efficiency caused by the fact that supersonic airflow of the inner channel is accelerated and expanded due to the rotation of the two-stage curved-surface compression plate is avoided.
(2) The second-level curved surface compression plate can rotate. The starting of the inward-rotating air inlet and the flow of the air inlet are adjusted by controlling the rotation angle theta of the second-stage curved surface compression plate.
Drawings
FIG. 1 is a rectangular inlet initial inward turning inlet mold half profile and inward turning adjustable inlet with two stage compression feature
Comparing the profiles of the front half mold of the throat; FIG. 1(a) is a left side view, FIG. 1(b) is an isometric view, FIG. 1(c) is a front view, and FIG. 1(d) is a top view;
FIG. 2 is a rectangular inlet internal turn tunable inlet with two-stage compression features;
FIG. 3 is a design point state rectangular inlet internal turn tunable inlet;
FIG. 4 is a non-design point state rectangular inlet internal turning adjustable intake duct;
FIG. 5 is a comparison of the profile of a circular capture inlet original internal turn inlet (dashed line) and a three-dimensional internal turn adjustable inlet throat front half with two-stage compression features;
FIG. 6 is a circular inlet internal turn variable intake with two-stage compression features;
in the figure: 1-inward turning inlet capturing profile, 2-original streamline tracing inward turning inlet profile (dotted line), 3-fixed inward turning three-dimensional curved surface, 4-design point symmetrical plane secondary oblique shock wave seal, 5-secondary curved surface compression plate (surface), 6-reconstructed three-dimensional curved surface, 7-fixed inward turning three-dimensional curved surface tangent with secondary compression and expansion direction, 8-fixed splitter wedge, 9-crank slider mechanism, 10-discharge channel, 11-punching channel, 12-three-dimensional inward turning compression supersonic airflow, and 13-supersonic airflow after secondary oblique shock wave compression.
Detailed Description
The invention is further explained below with reference to the drawings.
The invention mainly aims at the problems of starting and wide speed range air inlet/engine flow matching existing in a fixed geometry internal rotation air inlet, and provides a three-dimensional internal rotation adjustable air inlet with two-stage compression characteristics and a design method thereof, so that the working range of the internal rotation air inlet is widened. The internal adjustable air inlet designed according to the design method is not limited to rectangular, round and other inlet capture shapes, the figure only shows schematic diagrams of the internal adjustable air inlet of the rectangular and round capture inlets, and the internal adjustable air inlet of the rectangular capture inlet is specifically explained.
FIG. 1 is a comparison of the profiles of the front half of the throat of an original inward turning inlet with a rectangular inlet and an inward turning adjustable inlet with a two-stage compression feature. The design method of the internal rotation adjustable air inlet with the two-stage compression characteristic comprises the following steps: on the basis of an original inward-turning air inlet, the characteristics and parts of an inlet capture molded line of the inward-turning air inlet are reserved (for a rectangular capture inward-turning air inlet, a part of a compression surface molded surface (curved surface) is reserved, namely, the curved surface is cut off from a secondary compression plate) to fix an inward-turning three-dimensional curved surface; the design method of the two-stage curved surface compression surface comprises the following steps: when the Mach number is designed, a second-level curved surface compression surface is designed according to a second oblique shock wave sealing principle of a symmetrical surface of an air inlet channel (according to Ma and an oblique shock wave angle (oblique shock wave sealing) in front of the second-level compression surface of the symmetrical surface, the second-level compression angle can be calculated through an oblique shock wave relational expression, then, point dispersion is carried out on a molded line and a throat at the cut-off position of the fixed compression surface, a B-spline curve is adopted to generate the second-level compression surface), the width is equal, and the design principle of the conventional binary air inlet channel shock wave sealing is used for reference. The fixed inward-turning three-dimensional curved surface is tangent to the span-wise connection position of the compression surface of the second-level curved surface.
The reconstructed three-dimensional curved surface is obtained by compressing the plate molded surface according to the fixed inward turning three-dimensional curved surface and the two-stage curved surface, reconstructing the inner molded surface of the air inlet (performing point dispersion according to the inward turning front edge capturing molded line and the throat rectangle, and generating the three-dimensional curved surface by adopting a B spline curve) on the basis of ensuring that the front edge molded line of the capturing inlet of the inward turning air inlet is not changed: and performing curved surface sweep according to the inlet capture molded line, the throat molded line and a curved surface boundary generated by the B spline curve. And the position of the lip reflected shock wave hitting the secondary curved surface compression plate is adjusted by controlling the reconstructed three-dimensional curved surface leading edge angle alpha, so that the purpose of eliminating shoulder separation is achieved (the position of a lip shock wave falling point is controlled by controlling the leading edge molded line angle, and the separation caused by shock wave boundary layer interference is avoided at the shoulder at the design point). The inlet throat is rectangular.
Fig. 2 shows a rectangular inward-turning adjustable air inlet channel with two-stage compression characteristics, which is designed by the design method of the present invention, and the air inlet channel has a design point Ma of 6 and a working range Ma of 2-8, and is composed of a fixed inward-turning three-dimensional curved surface, a two-stage curved surface compression plate (surface), a reconstructed three-dimensional curved surface, a fixed flow distribution wedge, a flow discharge channel, and a stamping channel. The adjustable mode of the inward-turning air inlet channel adopts a rotary two-stage curved surface compression plate. The starting of the inward-rotating air inlet channel and the flow of the stamping channel are adjusted by controlling the rotation angle theta of the second-level curved surface compression plate.
The method specifically comprises the following steps: when the air inlet channel works at a high Mach number (Ma is more than or equal to 4), the rotation angle theta of the second-stage curved surface compression plate is 0 degrees, supersonic incoming flow is subjected to inward three-dimensional compression and two-stage oblique shock wave compression, the air inlet channel has the three-dimensional compression characteristic of the inward air inlet channel and the two-stage shock wave compression characteristic, and the compression efficiency is high; when the low-Mach-number air inlet is not started (Ma is 2-4), the rotation angle theta of the two-stage curved surface compression plate is increased, the area of the throat is enlarged, the drainage channel is opened, part of air flow is discharged from the drainage channel, and the air inlet is started. At the moment, the second-stage curved surface compression plate generates oblique shock waves, but the area of the inner channel along the way cannot be expanded basically to accelerate airflow, and the air inlet channel still has three-dimensional compression characteristics of an inward turning air inlet channel and two-stage shock wave compression characteristics; and when the rotation angle of the second-level curved surface compression plate is in smooth transition with the fixed inward-turning three-dimensional curved surface, the air inlet channel only has the three-dimensional compression characteristic.
Fig. 3 and fig. 4 show schematic diagrams of the operating states of the adjustable rectangular inlet inward-turning air inlet when Ma is 6 and Ma is 2, the design point Ma of the air inlet is 6, and the two-stage oblique shock wave sealing is performed. Ma is 6, the rotation angle theta of the secondary rotating plate is 0 degrees, and supersonic incoming flow is subjected to inward rotation three-dimensional compression and secondary oblique shock wave compression; and Ma is equal to 2, the rotation angle theta of the secondary rotating plate is equal to 6 degrees, and the secondary curved surface compression plate is in smooth transition with the fixed inward-rotating three-dimensional curved surface.
Figure 5 is a comparison of the profile of the original inward turning inlet (dashed line) of the circular capture inlet and the front half of the three-dimensional inward turning adjustable inlet throat with two-stage compression features. Except that the three-dimensional curved surface is not required to be reconstructed, the specific design thought, characteristics and variable geometry adjusting mode are the same as those of a rectangular capture inlet.
FIG. 6 shows a circular internal turn variable inlet with two-stage compression characteristics designed using the design method of the present invention.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A three-dimensional inward turning adjustable air inlet with two-stage compression characteristics comprises an inward turning air inlet capturing molded line, a fixed inward turning three-dimensional curved surface, a two-stage curved surface compression plate, a reconstructed three-dimensional curved surface, a fixed distribution wedge, a flow regulation flow channel and a main flow channel; the three-dimensional curved surface of fixed adversion is the local profile of adversion intake duct, and fixed adversion three-dimensional curved surface is tangent with the exhibition of second grade curved surface compression board to the junction, has the three-dimensional compression characteristic of partial adversion intake duct.
2. The three-dimensional internal-rotation adjustable air inlet channel with two-stage compression characteristic as claimed in claim 1, wherein the two-stage curved compression plate is a constant-width rotatable compression plate; when the second-stage curved surface compression plate rotates by an angle theta, the second-stage curved surface compression plate generates oblique shock waves, and the air inlet channel has three-dimensional compression characteristics of an inward-turning air inlet channel and compression characteristics of the second-stage shock waves; when the rotation angle of the second-level curved surface compression plate is in smooth transition with the fixed inward-turning three-dimensional curved surface, the air inlet channel only has three-dimensional compression characteristics.
3. The three-dimensional internal-turn variable intake duct of claim 1, wherein the internal-turn intake duct inlet capture profile is fixed.
4. The three-dimensional internal-turning adjustable intake duct with two-stage compression characteristic of claim 1, wherein the fixed internal-turning three-dimensional curved surface is connected with the two-stage curved compression plate through a pin.
5. The three-dimensional internal-rotation adjustable intake duct with two-stage compression characteristic according to claim 2, wherein the two-stage curved compression plate is rotated by a slider-crank mechanism.
6. The three-dimensional internal-turning adjustable intake duct with two-stage compression characteristic according to claim 1, wherein the reconstructed three-dimensional curved surface keeps the capture inlet leading edge capture profile of the internal-turning intake duct unchanged.
7. A design method of a three-dimensional inward turning adjustable air inlet with two-stage compression characteristics is characterized in that on the basis of an original inward turning air inlet, the characteristics of an inlet capture molded line of the inward turning air inlet and a part of a fixed inward turning three-dimensional curved surface are reserved.
8. The design method of the three-dimensional adjustable inward turning inlet duct with the two-stage compression characteristic as claimed in claim 7, wherein the design method of the two-stage curved compression plate is as follows: when the Mach number is designed, designing a second-level curved surface compression surface according to a second oblique shock wave sealing principle of an air inlet channel symmetric surface: and calculating a secondary compression angle through an oblique shock wave relational expression according to the Ma in front of the second-stage compression surface of the symmetric surface and the oblique shock wave angle, performing point dispersion on the molded line and the throat at the cut-off position of the fixed compression surface, and generating the secondary compression surface by adopting a B-spline curve.
9. The method as claimed in claim 7, wherein the step of reconstructing the three-dimensional curved surface is to reconstruct the inner profile of the intake duct according to the fixed inward-turning three-dimensional curved surface and the two-stage curved surface compression plate profile on the basis of ensuring that the profile of the captured inlet leading edge of the inward-turning intake duct is not changed, that is, the curved surface sweep is performed according to the captured inlet profile and the throat profile and the curved surface boundary generated by the B-spline curve.
10. The design method of the three-dimensional internal rotation adjustable intake duct with the two-stage compression characteristic according to claim 7, wherein the position of the lip reflection shock wave hitting the second-stage curved surface compression plate is adjusted by controlling the reconstructed three-dimensional curved surface leading edge angle a, so as to achieve the purpose of eliminating shoulder separation, that is, point dispersion is performed according to an internal rotation leading edge capture line and a throat rectangle, and a B-spline curve is used to generate the three-dimensional curved surface; the lip shock wave falling point position is controlled by controlling the leading edge molded line angle, and the separation caused by shock wave boundary layer interference on the shoulder part is avoided when the design point is ensured.
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| CN202210154713.8A CN114576010A (en) | 2022-02-21 | 2022-02-21 | Three-dimensional inward-rotation adjustable air inlet with two-stage compression characteristic and design method |
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| CN202210154713.8A CN114576010A (en) | 2022-02-21 | 2022-02-21 | Three-dimensional inward-rotation adjustable air inlet with two-stage compression characteristic and design method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5167117A (en) * | 1989-12-20 | 1992-12-01 | Mtu Motoren Und Turbinen-Union Muenchen Gmbh | Method and apparatus for cooling an airplane engine |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN108590860A (en) * | 2018-05-09 | 2018-09-28 | 南京航空航天大学 | The assembly power variable geometry inlet and its design method of single-degree-of-freedom control |
| CN109209645A (en) * | 2018-11-06 | 2019-01-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of three-dimension curved surface compression change geometry inlet structure preparation method |
| CN111255569A (en) * | 2020-01-13 | 2020-06-09 | 南京航空航天大学 | Mode conversion and variable geometry combined adjusting internal parallel type air inlet and control method |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
-
2022
- 2022-02-21 CN CN202210154713.8A patent/CN114576010A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5167117A (en) * | 1989-12-20 | 1992-12-01 | Mtu Motoren Und Turbinen-Union Muenchen Gmbh | Method and apparatus for cooling an airplane engine |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN108590860A (en) * | 2018-05-09 | 2018-09-28 | 南京航空航天大学 | The assembly power variable geometry inlet and its design method of single-degree-of-freedom control |
| CN109209645A (en) * | 2018-11-06 | 2019-01-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of three-dimension curved surface compression change geometry inlet structure preparation method |
| CN111255569A (en) * | 2020-01-13 | 2020-06-09 | 南京航空航天大学 | Mode conversion and variable geometry combined adjusting internal parallel type air inlet and control method |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
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