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Two-stage beveled supersonic speed air inlet lip

A supersonic, oblique cutting technique applied to turbine/propulsion air intakes, combustion air/combustion-air handling, engine components, etc., to reduce buildup, improve flow, and reduce drag

Inactive Publication Date: 2010-08-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, there is no new concept research on the design of supersonic inlet lip

Method used

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  • Two-stage beveled supersonic speed air inlet lip
  • Two-stage beveled supersonic speed air inlet lip
  • Two-stage beveled supersonic speed air inlet lip

Examples

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Embodiment Construction

[0025] The invention will be described more fully hereinafter with reference to the accompanying drawings, each of which shows an example of the application of the invention. The angle parameters marked in the figure are only for this application example. It should not be construed that the invention is limited to the application examples described here, but the invention can be embodied in many different forms.

[0026] figure 1 A schematic diagram of the entrance wave system and lip position of a supersonic inlet without a partition using two-stage chamfered lips is shown. The supersonic incoming flow 1 produces a conical shock wave 3 under the action of the bulge compression surface 2, which forms a normal shock wave 4 before the entrance, and the inner surface 5 of the lip is consistent with the surface inclination angle of the bulge compression surface 2 at the entrance position. The sweep angle of the first-stage chamfered lip 6 is consistent with the angle of the norm...

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Abstract

The invention provides a two-stage beveled supersonic speed air inlet lip, relates to the two-stage beveled supersonic speed air inlet lip and belongs to the technical field of supersonic speed air inlet passages. In the two-stage beveled supersonic speed air inlet lip, an air inlet passage bump is arranged on the outer side of a machine body; an air inlet passage bump compression surface on the outer side of the air inlet passage bump is relatively provided with an air inlet passage; an outer lip, an inner lip and a lip front edge line are formed at one end, near the air inlet passage bump, of the air inlet passage; supersonic speed incoming flow produces a conical shock wave under the action of the air inlet passage bump compression surface; a positive shock wave is formed in front of an inlet; a first-stage beveled lip is formed on the positive shock wave; a second-stage beveled lip is formed on a position, near the machine body, of the first-stage beveled lip; and the outer lip and the inner lip adopt a quarter transcendental elliptic equation. The two-stage beveled supersonic speed air inlet lip fulfills the aims of realizing application to an isolation passage-free supersonic speed air inlet passage or other forms of supersonic speed air inlet passages, enhancing boundary layer removing effect of the isolation passage-free supersonic speed air inlet passage, enhancing total pressure recovery coefficient of the air inlet passage, reducing outlet flow distortion of the air inlet passage and fixing geometrical and lip two-stage beveling.

Description

technical field [0001] The invention relates to a two-stage chamfered supersonic air intake lip, which belongs to the technical field of supersonic air intakes. Background technique [0002] Supersonic flight refers to flight with a Mach number greater than 1. Air intakes are a critical component of air-breathing engine-powered vehicles that fly in the atmosphere, including airplanes and missiles. The main function of the intake port is to provide the downstream with high-energy airflow that meets the quality requirements of the engine flow field with as little flow loss as possible. From a technical point of view, the design requirements of the inlet mainly include the following points: ① under the design state, the flow capture capability is strong, providing as much flow as possible for the propulsion system; ② the total pressure recovery coefficient (efficiency) of the inlet outlet is high, The distortion of the outlet airflow is small; ③The structure is as simple as p...

Claims

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Application Information

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IPC IPC(8): F02C7/04
Inventor 李博梁德旺
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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