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A sliding variant adjustable caret intake

A kind of air inlet and variant technology, which is applied to the combustion of the air inlet of the power plant, the power plant on the aircraft, the arrangement/installation of the power plant, etc., and can solve the complex shape of the air intake parts, the separation of the airflow, and the strong reflection signal and other issues to achieve the effect of improving the performance of high Mach number

Active Publication Date: 2017-11-21
CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The shape of this inlet part is extremely complex, and the section of the inlet changes from a parallelogram to a special-shaped shape close to a bottleneck within a short distance after fixing the compression swash plate, which is prone to airflow separation and strong reflection signals

Method used

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  • A sliding variant adjustable caret intake
  • A sliding variant adjustable caret intake
  • A sliding variant adjustable caret intake

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specific Embodiment approach

[0029] (1) As attached figure 1 As shown, the air inlet section is a parallelogram with a double chamfered lip 1;

[0030] (2) As attached figure 2 As shown, an upper sidewall fixed compression swash plate 2 and an inner wall fixed compression swash plate 3 are arranged behind the lip 1, and attachment surfaces are provided on the upper side wall fixed compression swash plate 2 and the inner side wall fixed compression swash plate 3 Layer desorption opening area 4;

[0031] (3) As attached image 3 As shown, after the compression swash plate 2 is fixed on the upper side wall, there is hinged a sliding variable adjustable compression swash plate 6 driven by the compression swash plate driving piston rod 7, which moves with the sliding variant through the expansion swash plate follower hinge 5 Expansion inclined plate 8 is connected;

[0032] (4) As attached image 3 As shown, the flexible honeycomb sealing structure 9 keeps the seal between the adjustable compression swas...

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Abstract

The invention relates to a sliding variant adjustable CARET intake duct, wherein the shape of a cross section of the intake duct is a parallelogram, a lip of the intake duct is in a typical dual-beveling shape, and first-grade fixed compression sloping plates are arranged on the upper side wall and inner side wall of an inlet so as to form a CARET wing-shaped wave rider compression surface; a first-grade adjustable compression sloping plate and a first-grade follow-up expansion sloping plate which are composed of parallel sliding mechanisms are arranged at the rear of the fixed compression sloping plate of the upper side wall, the compression sloping plate is connected with the expansion sloping plate through a flexible structure, and pressure equalizing holes are formed in the expansion sloping plate; and boundary layer absorption holes are formed in the fixed compression sloping plates of the intake duct, and a bleed valve is arranged on a side wall. According to the scheme, by virtue of parallel slide of the compression sloping plate in a lowering process, the compression sloping plate does not intervene with the side wall structure of the parallelogram, and no gap exists. When an aircraft flies at a subsonic speed or a low supersonic speed, the adjustable compression sloping plate slides to retract, and the incoming flow is compressed by the fixed compression sloping plates, thereby improving high-Mach-number total pressure recovery. The scheme has the advantages of realizing full-envelope high total pressure recovery and keeping low target characteristics of internal pipelines.

Description

technical field [0001] This patent relates to the design of an air intake duct and belongs to the technical field of aircraft design. Background technique [0002] The role of the supersonic aircraft inlet is to decelerate and compress the supersonic incoming flow to the subsonic airflow required for engine operation, while maintaining the high energy of the incoming flow as much as possible, that is, requiring high total pressure recovery. [0003] In order to improve the recovery of supersonic total pressure, a compression swash plate or a compression cone is designed to change the inlet shock wave from the normal shock wave of the pitot tube inlet to an oblique shock wave, reducing the shock wave intensity and energy loss. The inlet with fixed compression surface is used in supersonic aircraft such as F-104. In order to expand the Mach number adaptation range of the supersonic inlet and expect to have high performance in the entire envelope, an adjustable inlet with a ro...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D33/02
CPCB64D33/02B64D2033/0226B64D2033/0273
Inventor 张文宇史文卿杨庭李玉建尚仁操袁泽建
Owner CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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