Porous hinge type air inlet pressure distortion element

An air intake pressure and hinged technology, applied in the field of aero-engines, can solve the problems of uncontrollable distortion map and inability to simulate the distortion of the flow field at the outlet of the aircraft inlet, so as to achieve the effect of improving flexibility and expanding the range of parameters

Inactive Publication Date: 2020-04-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Moving the plate can change the distortion state without interrupting the test. However, the achievable distortion map is uncontrollable and cannot simulate the real flow field distortion that may occur at the outlet of the aircraft inlet.

Method used

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  • Porous hinge type air inlet pressure distortion element
  • Porous hinge type air inlet pressure distortion element
  • Porous hinge type air inlet pressure distortion element

Examples

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Embodiment Construction

[0027] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0028] This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.

[0029] A porous hinge type intake pressure distortion element, comprising a porous hinge, an actuating rod and a support body;

[0030] The porous hinge includes a first adjusting plate and a second adjusting plate;

[0031] Both the first adjusting plate and the second adjusting plate are rectangular plates, each including first to fourth sides, wherein the first side and the third side are parallel to each other, and the second side and the fourth side are parallel to each other;

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PUM

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Abstract

The invention discloses a porous hinge type air inlet pressure distortion element which comprises a porous hinge, an actuating rod and a supporting body. The porous hinge comprises a first adjusting plate and a second adjusting plate; and the first adjusting plate and the second adjusting plate are each evenly provided with a plurality of through holes used for adjusting the turbulence degree of aflow field. The first edge of the first adjusting plate is hinged to the first edge of the second adjusting plate. The support body is streamlined, and one end of the support body is hinged to the third edge of the second adjusting plate; one end of the actuating rod is vertically hinged to the first side of the first adjusting plate; and the other end receives external force to adjust the angleof the first adjusting plate relative to the second adjusting plate. The porous hinge type air inlet pressure distortion element is used for simulating engine intake pressure distortion, can both realize change of the distortion state without interrupting the test, and can simulate the real flow field distortion atlas of the outlet of the aircraft intake passage; and the porous hinge type air inlet pressure distortion element is convenient to adjust and high in practicability.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a porous hinge type intake pressure distortion element. Background technique [0002] The research and development of high-performance aircraft must be the synthesis of the whole aircraft, engine and control system. The advancement of aircraft technology requires improved calculation and test methods to evaluate the matching of aircraft and engines. Computational fluid dynamics (CFD), analysis models, ground tests, flight tests and other methods must be used to obtain the necessary information for design evaluation at different stages of the aircraft development cycle and to make decisions. The ground test can provide the necessary information as early as possible to reduce the development cost and risk of the whole system, which plays a key role. [0003] In the matching evaluation process of the aircraft and the engine, the evaluation of the influence of intake distortio...

Claims

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Application Information

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IPC IPC(8): G01M15/02
CPCG01M15/02
Inventor 王英锋胡骏屠宝锋
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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