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CN-121993292-A - Inward rotation type air inlet channel overflow port

CN121993292ACN 121993292 ACN121993292 ACN 121993292ACN-121993292-A

Abstract

The invention discloses an inner rotation type air inlet channel overflow port, which comprises a rounding section and two straight front edge sections, wherein the two straight front edge sections are respectively connected with two ends of the rounding section in a smooth tangent way, two smooth bulges are arranged on parts of the rounding section, one bulge is positioned at the downstream of a tangent point of the rounding section and the straight front edge section, the other bulge is positioned at the downstream of a tangent point of the rounding section and the other straight front edge section, and the highest points of the bulges are positioned at the upstream of the maximum heat flow peak position of the wall surface of the rounding section, so that the wall surface between the tangent point and the highest point of the bulges is lifted, compression waves are intersected with a shock wave of a straight front edge section on one side in advance, expansion waves entering the wall surface of the rounding section are matched earlier, and the maximum heat flow peak downstream of the highest point of the bulges can be further weakened, namely the heat flow peak of the wall surface of the rounding section is reduced.

Inventors

  • LI WANG
  • LI ZHUFEI

Assignees

  • 中国科学技术大学

Dates

Publication Date
20260508
Application Date
20260205

Claims (9)

  1. 1. The inner rotation type air inlet channel overflow port comprises a rounding section (1) and two straight front edge sections (2), wherein the two straight front edge sections (2) are respectively and smoothly tangent to two ends of the rounding section (1), and the inner rotation type air inlet channel overflow port is characterized in that two smooth bulges (11) are arranged on parts of the rounding section (1), one bulge (11) is positioned at the downstream of the tangent point of the rounding section (1) and the straight front edge sections (2), the other bulge (11) is positioned at the downstream of the tangent point of the rounding section (1) and the other straight front edge sections (2), and the highest points of the bulges (11) are all positioned at the upstream of the maximum heat flow peak position of the wall surface of the rounding section (1).
  2. 2. An inner turn inlet overflow as claimed in claim 1, characterized in that two of said protrusions (11) are symmetrically distributed about the middle part of said rounded section (1).
  3. 3. The inner rotation type inlet overflow according to claim 2, characterized in that the starting portion of the protrusion (11) and the rounded section (1) coincide with the tangent point of the respective straight leading edge section (2) and are smoothly tangent to the respective straight leading edge section (2), and the ending portion is smoothly tangent to the respective portion of the rounded section (1), the passivation radius of the protrusion (11) and the passivation radius r of the straight leading edge section (2) remaining the same.
  4. 4. A inner turn inlet overflow as claimed in claim 3, wherein the projections (11) comprise simple harmonic wave-shaped projections.
  5. 5. The inner rotation type air inlet overflow port according to claim 4, characterized in that the protrusion (11) is a cosine wave-shaped protrusion.
  6. 6. The inner rotation type air inlet overflow port according to claim 5, characterized in that a point on the center line of the cosine wave-shaped bulge is located at a distance R P from the center line of the rounding section (1), and varies along the circumferential direction of the rounding section (1) according to the following formula: ; ; Wherein, the R is the radius of the center line of the rounding section (1), beta is the half-expansion angle of the straight front edge section (2), h is the height of the cosine waveform bulge, For the circumferential angle of the highest point position of the cosine wave-shaped bulge, Is the circumferential angle of the cosine wave-shaped bulge end point position.
  7. 7. The inner rotation type inlet overflow port according to claim 6, characterized in that the half-divergence angle β of the straight leading edge section (2) satisfies 12 ° < β < 65 °.
  8. 8. The inner turn inlet overflow port of claim 6, wherein the height h of the cosine wave shaped protrusion satisfies 0 < h < 0.1R.
  9. 9. The inner turn inlet overflow of claim 6, wherein the cosine wave shaped bulge has a circumferential angle at the highest point position And circumferential angle of start and end positions The method meets the following conditions: 。

Description

Inward rotation type air inlet channel overflow port Technical Field The invention relates to the technical field of hypersonic aircrafts, in particular to an inner rotating type air inlet channel overflow port. Background The air intake duct acts as an important component of the scramjet engine, whose performance directly affects the efficiency of the overall propulsion system. In recent years, the inner rotary type air inlet channel gradually becomes a research hot spot due to the advantages of high compression efficiency, strong flow capturing performance and the like. The overflow port of the inner rotating type air inlet channel is generally arranged in a V-shaped structure so as to improve the starting capability of the air inlet channel under the condition of low Mach number inflow. The overflow port of the V-shaped structure is usually required to be passivated, so that the aerodynamic heat protection performance is improved. In hypersonic flight, leading edge desizing shock waves intersect at the lip to form a series of complex shock wave interference, which causes severe aerodynamic/thermal loads and seriously threatens flight safety. For the V-shaped overflow port, the shock wave interference type can be converted into regular reflection on the same side by increasing the radius of the rounding at the root of the V-shape, and the wall surface heat flow can be obviously reduced. However, even if the disturbance type has been changed to the same-side regular reflection, since the air flow is continuously compressed when reaching the rounded section, and the compression degree is enhanced with the increase of the Mach number, a significant heat flow peak is still formed, and the flight safety is seriously threatened. Disclosure of Invention In view of this, the invention provides an inner rotation type air inlet overflow port, which is helpful for reducing the heat flow peak value of the wall surface of the rounding section. In order to achieve the above purpose, the present invention provides the following technical solutions: The inner rotation type air inlet channel overflow port comprises a rounding section and two straight front edge sections, wherein the two straight front edge sections are respectively connected with two ends of the rounding section in a smooth tangent mode, two smooth bulges are arranged on parts of the rounding section, one bulge is positioned at the downstream of the tangent point of the rounding section and the straight front edge section, the other bulge is positioned at the downstream of the tangent point of the rounding section and the other straight front edge section, and the highest points of the bulges are all positioned at the upstream of the maximum heat flow peak position of the wall surface of the rounding section without the bulge overflow port. Preferably, two of said protrusions are symmetrically distributed about the middle portion of said rounded section. Preferably, the start portion of the protrusion and the rounded segment coincide with the tangent point of the respective straight leading edge segment and are smoothly tangent to the respective straight leading edge segment, and the end portion of the protrusion and the passivation radius r of the straight leading edge segment remain consistent. Preferably, the protrusions comprise simple harmonic wave shaped protrusions. Preferably, the protrusions are cosine wave protrusions. Preferably, a distance between a point on the central line of the cosine wave-shaped bulge and the center line of the rounding segment is R P, and the distance varies along the circumferential direction of the rounding segment according to the following formula: ; ; Wherein, the R is the radius of the center line of the rounding section, beta is the half-expansion angle of the straight front edge section, h is the height of the cosine waveform bulge,For the circumferential angle of the highest point position of the cosine wave-shaped bulge,Is the circumferential angle of the cosine wave-shaped bulge end point position. Preferably, the half divergence angle beta of the straight leading edge segment satisfies 12 deg. < beta < 65 deg.. Preferably, the height h of the cosine wave-shaped protrusion satisfies 0 < h < 0.1R. Preferably, the circumferential angle of the highest point position of the cosine wave-shaped bulgeAnd circumferential angle of start and end positionsThe method meets the following conditions: 。 According to the technical scheme, the inner rotation type air inlet channel overflow port is provided with the two smooth bulges at the part of the rounding section, one bulge is positioned at the downstream of the tangent point of the rounding section and the straight front edge section at one side, the other bulge is positioned at the downstream of the tangent point of the rounding section and the straight front edge section at the other side and is positioned at the upstream of the maximum heat flow peak position of the