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CN-122009500-A - Plane embedded type air inlet channel with flow controller and aircraft

CN122009500ACN 122009500 ACN122009500 ACN 122009500ACN-122009500-A

Abstract

The invention provides a plane embedded type air inlet channel with a flow controller, which comprises a dovetail groove-shaped flow controller based on two-stage expansion angles considered by resistance reduction and air movement, a second part inclined plane forming an angle with the plane of an aircraft body and a bulge in front of the inlet channel inlet. The dovetail-shaped flow controller generates vortex on the side wall surface, so that the low-energy boundary layer on the surface of the machine body is discharged to two sides, the flow field quality at the inlet of the air inlet channel is improved, the bulge in front of the inlet of the air inlet channel reduces the flow field distortion of the outlet of the air inlet channel, and the second part inclined plane forming an angle with the plane of the machine body increases the air flow capturing capacity of the inlet of the air inlet channel. The invention arranges the inlet surface on the second part inclined plane forming an angle with the plane of the machine body, thereby being convenient for integrating the dovetail-shaped flow controller and the bulge, ensuring the effective loading space in the interior as far as possible, improving the total pressure recovery coefficient of the air inlet channel, reducing the flow field distortion and improving the overall performance of the aircraft.

Inventors

  • LI BO

Assignees

  • 南京航空航天大学

Dates

Publication Date
20260512
Application Date
20260303

Claims (10)

  1. 1. The plane embedded type air inlet with the flow controller is characterized by comprising an outer shell surface which is a part of an aircraft body, a plane embedded type air inlet (4) which is positioned on the outer shell surface, and an air inlet inner pipeline (42) which extends from the plane embedded type air inlet to the inside of the outer shell surface, wherein the outer shell surface is inwards recessed to form a dovetail groove-shaped flow controller (2), the front end of the dovetail groove-shaped flow controller (2) is a tip and positioned in front of the plane embedded type air inlet (4), the width of the rear end of the dovetail groove-shaped flow controller (2) is the same as the width of the outer shell surface, and the intersections of the rear end of the dovetail groove-shaped flow controller (2) and two side edges of the outer shell surface are respectively positioned at two sides of the plane embedded type air inlet (4), the dovetail groove-shaped flow controller (2) is of a symmetrical structure, and the central axis of the dovetail groove-shaped flow controller (2) and the central axis of the air inlet (4) and the central axis of the outer shell surface are positioned in the same plane; The front end of the plane embedded type air inlet channel inlet (4) is provided with a bulge (5), the bulge (5) is positioned in the groove range of the dovetail-shaped flow controller (2), the rear end of the bulge (5) is connected with the air inlet channel inlet (4), and the bulge (5) gradually inclines inwards from the most protruding point to form a transition guide surface between the bulge and the plane embedded type air inlet channel inlet (4); The outer shell surface forms two part inclined planes in the range of the dovetail groove-shaped flow controller (2), the plane embedded air inlet (4) and the bulge (5), the first part inclined plane (21) gradually and inwards extends from front to back from the front end of the dovetail groove-shaped flow controller (2), the second part inclined plane (3) gradually and inwards extends from back to front of the plane embedded air inlet (4), the plane embedded air inlet (4) is all located in the range of the second part inclined plane (3), and the first part inclined plane (21) and the second part inclined plane (3) are tangential through a transitional arc curved surface (23).
  2. 2. The planar embedded air inlet with a flow controller according to claim 1, wherein the angles between the two side wall surfaces (22) of the dovetail-shaped flow controller (2) and the axial direction of the machine body are the expansion angles of the dovetail grooves, and the two expansion steps are carried out from the head to the back.
  3. 3. The planar embedded air inlet with flow controller according to claim 1, wherein a transitional air inlet lip (41) is arranged between two sides of the planar embedded air inlet (4) and the second part inclined plane (3), and the molded surface of the air inlet lip (41) is tangential to the second part inclined plane (3).
  4. 4. A planar embedded air inlet with flow controller according to claim 3, characterized in that the maximum height of the bulge (5) is about half the maximum depth of the dovetail-shaped flow controller (2), and the maximum width of the bulge (5) is substantially equal to the width of the inlet lips (41) on both sides.
  5. 5. The planar embedded air inlet with flow controller according to claim 1, wherein the planar embedded air inlet (4) and the dovetail flow controller (2) are not molded to exceed the surface of the aircraft fuselage, and the air inlet is not visible from the front of the aircraft fuselage.
  6. 6. The planar embedded air inlet with flow controller as set forth in claim 4, wherein the front end of said bulge (5) is pointed and the bulge (5) gradually slopes outwardly from the front end to the most convex point and inwardly from the most convex point.
  7. 7. The planar embedded air inlet with a flow controller according to claim 6, wherein the bulges (5) are of a bilateral symmetry.
  8. 8. The planar embedded air inlet with flow controller as set forth in claim 2, wherein the expansion half angle of the dovetail groove is 20.5 ° at the first stage and 30 ° at the second stage.
  9. 9. The planar embedded air inlet with a flow controller as set forth in claim 8, wherein the first part inclined plane (21) forms an angle of 11.5 degrees with the plane of the machine body, and the maximum depth of the groove formed by the dovetail-shaped flow controller (2) is 0.7-1.0 times the thickness of the local boundary layer.
  10. 10. An aircraft characterized by a planar embedded inlet with flow controllers according to any one of claims 1 to 9, the outer skin having the same width as the aircraft fuselage.

Description

Plane embedded type air inlet channel with flow controller and aircraft Technical Field The invention relates to the field of aircraft air inlet channel design, in particular to an subsonic plane embedded air inlet channel, and simultaneously relates to an aircraft with the air inlet channel. Background Subsonic aircraft are the most common and widely used type of aircrafts in air suction type aircrafts, and an air inlet of a power system of the subsonic aircraft is generally in the forms of a pitot type air inlet, an S-bend air inlet, a buried air inlet and the like. The pitot type air inlet is generally positioned at the head of an aircraft or a nacelle, occupies a large amount of internal space of the aircraft body, and has a limited application range. The S-bend air inlet generally lifts the inlet of the air inlet off the surface of the fuselage by providing a specialized boundary layer partition and baffle to avoid ingestion of low energy air flow into the boundary layer of the fuselage surface. Obviously, this increases aerodynamic drag of the aircraft, as the boundary layer barrier increases the frontal area of the aircraft, and increases weight and structural complexity. The embedded air inlet does not have a part protruding out of the surface of the aircraft body, so that the inlet of the air inlet cannot be seen from the front, and windward resistance cannot be increased, and therefore, the embedded air inlet has good electromagnetic stealth performance and low resistance, and the subsonic air inlet is mostly a plane embedded air inlet. For the plane embedded air inlet, the aircraft body in front of the inlet is flat, so that the boundary layer on the surface of the aircraft body is easier to accumulate, and the quality of a flow field in front of the inlet of the plane embedded air inlet is poor. If the length of the aircraft body is longer, the influence of the boundary layer is more serious, if certain flow control measures are not adopted, a large number of boundary layers sucked into the air inlet channel can cause the consequences of reduction of the total pressure recovery coefficient of the outlet of the air inlet channel and increase of the flow field distortion index, and even if the flow field distortion of the outlet of the air inlet channel exceeds the maximum allowable distortion value of the engine in a part of flight state, the engine cannot be matched normally. Therefore, the design of the air inlet is particularly important for the long plane embedded air inlet of the aircraft body, and a new technical scheme is needed to solve the problems. Disclosure of Invention In order to solve the problems, the invention provides a plane embedded type air inlet channel with a flow controller. The invention can improve the total pressure recovery coefficient of the air inlet channel, reduce the flow field distortion of the outlet of the air inlet channel and keep the aerodynamic resistance of the aircraft low. The invention also provides an aircraft with the plane embedded air inlet channel. In order to achieve the above purpose, the planar embedded air inlet with the flow controller provided by the invention can adopt the following technical scheme: A planar embedded air inlet with a flow controller comprises an outer shell surface which is a part of an aircraft body, a planar embedded air inlet arranged on the outer shell surface, and an air inlet inner pipeline extending from the planar embedded air inlet to the inner part of the outer shell surface; the front end of the dovetail groove-shaped flow controller is a tip and is positioned in front of the plane embedded type air inlet, the width of the rear end of the dovetail groove-shaped flow controller is the same as that of the outer shell surface, the intersections of the rear end of the dovetail groove-shaped flow controller and the two side edges of the outer shell surface are respectively positioned at the two sides of the plane embedded type air inlet, the dovetail groove-shaped flow controller is of a symmetrical structure, the central axis of the dovetail groove-shaped flow controller, the central axis of the air inlet and the central axis of the outer shell surface are positioned on the same plane, the front end of the plane embedded type air inlet is provided with a bulge, the bulge is positioned in the groove range of the dovetail groove-shaped flow controller, the rear end of the bulge is connected with the air inlet, the bulge is gradually inclined inwards from the most protruding point to form a transitional guide surface between the plane embedded type air inlet, the outer shell surface forms two part inclined planes in the range of the dovetail groove-shaped flow controller, the plane embedded type air inlet and the bulge, the first part inclined plane gradually inclines inwards from the front end of the dovetail groove-shaped flow controller, the second part inclined plane gradually inclines inwards from the front end of