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Hypersonic axisymmetric air inlet channel lip and design method thereof

A design method and intake port technology, applied to the intake port of the turbine/propulsion device, combustion air/combustion-air treatment, engine components, etc., can solve the problem of increasing the weight and complexity of the system and the total pressure loss of the intake port Large size, complex processing of the intake port, etc., to improve the starting performance, ensure the compression performance, and benefit the overall design

Active Publication Date: 2018-08-17
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The vortex generator is a small wing with a small aspect ratio installed vertically on the surface of the inlet at a certain installation angle. The boundary layer flow field in the gradient can continue to attach to the surface of the inlet precursor without separation after gaining additional energy. This flow control technology brings the complexity of inlet processing, and the suction device and control circuit also increase System weight and complexity
Passive flow control technology will bring the disadvantages of large total pressure loss in the inlet port and serious airflow distortion

Method used

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  • Hypersonic axisymmetric air inlet channel lip and design method thereof
  • Hypersonic axisymmetric air inlet channel lip and design method thereof
  • Hypersonic axisymmetric air inlet channel lip and design method thereof

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Embodiment 1

[0032] attached figure 1 , attached figure 2 , attached image 3 , attached Figure 4 , attached Figure 5A kind of hyper / supersonic axisymmetric inlet lip is shown, and described inlet is arranged on the engine of aircraft, and the front end of described inlet is provided with serrated lip, and described serrated lip includes several A piece of V-shaped sawtooth unit, the side walls of the V-shaped sawtooth unit are connected end to end to form a serrated lip, the center of the serrated lip is the axis of rotation, and the V-shaped sawtooth units are arranged in a circular array with the axis of rotation as the array axis.

[0033] A super / supersonic axisymmetric inlet lip and its design method. The design parameters of the serrated lip are: V-shaped serrated units N=15, central angle θ=24°, sweep angle λ=60°, The radius of the circle where the flat lip of the unit is located is 300mm, and the elongation length of the V-shaped sawtooth unit is calculated by taking the av...

Embodiment 2

[0037] as attached figure 1 , attached figure 2 , attached image 3 , attached Figure 4 , attached Figure 6 The shown a hyper / supersonic axisymmetric inlet lip is different from Embodiment 1 in that:

[0038] A super / supersonic axisymmetric inlet lip and its design method, the design parameters of the serrated lip are: the designed sawtooth parameters are: V-shaped sawtooth units N=10, central angle θ=36°, backswept Angle λ=60°, the sawtooth forward distance is calculated by taking the average value of the given range

[0039] Taking the relative deviation ε as 1%, here is a method to determine the lip translation length x through experiment and Lagrange interpolation calculation:

[0040] First translate the elongation length a of the V-shaped sawtooth unit by x 11 =2mm,x 12 =3mm,x 13 =5mm, the corresponding relative deviation data ε is obtained through experiments 11 , ε 12 , ε 13 , it is found that the relative deviation data do not satisfy |ε 1j |≤ε, defin...

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Abstract

The invention relates to a design method of an air inlet channel lip of a hypersonic flight vehicle, and belongs to the technical field of hypersonic air inlet channel application. According to the design method, an air inlet channel is arranged on an engine of the flight vehicle, and the front end of the air inlet channel is a sawtooth-shaped lip; and the sawtooth-shaped lip comprises a pluralityof lip blades, the side walls of the lip blades are connected in an end-to-end mode to form the closed sawtooth-shaped lip, the center of the sawtooth-shaped lip is taken as a revolving axis line, and the lip blades are arranged in an array mode by taking the revolving axis as an array axis. According to the design method of the air inlet channel lip of the hypersonic flight vehicle, a moving mechanism is not introduced, so that the weight and the complexity of the system are prevented from being increased, and the problems of connection, sealing, cooling, control and the like are prevented from occurring; the machining and manufacturing process is simple, the starting performance of the axisymmetric air inlet channel can be improved, meanwhile, the compression performance of the axisymmetric air inlet channel is not influenced, and the capture flow is reduced, so that the working efficiency of the air inlet channel is guaranteed, and the starting performance of the air inlet channelis improved.

Description

technical field [0001] The invention belongs to the technical field of application of hypersonic air inlets, and in particular relates to a hypersonic / supersonic axisymmetric air inlet lip and a design method thereof. Background technique [0002] Hypersonic aircraft is currently the frontier of national defense development. As a weapon that can achieve rapid strikes, it responds quickly to combat commands, survives on the battlefield, and has great destructive power. Therefore, the research and development of hypersonic aircraft has huge military, Economic value, so as to consolidate and enhance the country's national defense strength and comprehensive national strength. Hypersonic aircraft fly in the atmosphere, usually using a scramjet engine as power, the hypersonic inlet is one of the important components of the scramjet engine, its main function is to capture the incoming flow and decelerate and pressurize the airflow to ensure combustion The organization of the chamb...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/04
CPCF02C7/04
Inventor 王翼赵星宇范晓樯徐尚成陆雷闫郭伟
Owner NAT UNIV OF DEFENSE TECH
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