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Binary mixed pressure intake duct applied to supersonic solid ramjet

A technology of solid impingement engine and air inlet, which is applied in the direction of engine components, air inlet of turbine/propulsion device, combustion air/combustion-air treatment, etc. It can solve the problems not mentioned and achieve easy processing, expansion and stability Working range, the effect of reducing the starting Mach number

Inactive Publication Date: 2014-09-10
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, it did not mention the way of slotting, opening, and design of the suction chamber.

Method used

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  • Binary mixed pressure intake duct applied to supersonic solid ramjet
  • Binary mixed pressure intake duct applied to supersonic solid ramjet

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Embodiment

[0027] Supersonic solid impulse engine binary mixed pressure inlet, two wedges and three waves system. The starting Mach number is 2.5, and the design Mach number is 3.0. According to the inlet channel structure of the present invention, the positions and widths of the entrance 5 of the boundary layer auxiliary absorption channel and the entrance 6 of the boundary layer absorption chamber are determined through numerical simulation and engineering calculation. Among them, the inlet 5 of the boundary layer auxiliary suction channel is located at a horizontal distance of about 42 mm backward from the front edge lip of the outer cover 2, and the inlet 6 of the boundary layer suction chamber is located at a horizontal distance of about 81 mm backward from the front edge lip of the outer cover 2.

[0028] The above structure was subjected to wind tunnel test. The performance results are shown in the table below. Under the design Mach number 3.0, zero angle of attack and zero side...

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Abstract

A binary mixed pressure intake duct applied to supersonic solid ramjet comprises an upper part outer cover and a lower part containing a front body, a baffle plate and a back body. A ventilation channel is between the upper part and the lower part; and a section with equivalent height of the ventilation channel is a throat, which is arranged at the back of a leading edge of the outer cover; the baffle plate is clamped between the front body and the back body; a boundary layer auxiliary suction channel communicating with the ventilation channel of the binary mixed pressure intake duct is arranged between the front body and the baffle plate, and a communicating position is an inlet of the boundary layer auxiliary suction channel; a boundary layer suction cavity is between the baffle plate and the back body and communicates with the throat, and a communicating position is an inlet of the boundary layer suction cavity; the outlet of the boundary layer auxiliary suction channel enters into the boundary layer suction cavity; and the boundary layer suction cavity outlet is arranged between the front body and the back body. The invention has simple and convenient structure, does not occupy space in the intake duct, and can fully eliminate influences of the boundary layer on the intake duct and effectively improve the performance of the intake duct at a low suction flow.

Description

technical field [0001] The invention relates to a binary mixed-pressure intake port applied to a supersonic solid impulse engine, belonging to the design field of the supersonic solid impulse engine. Background technique [0002] The working performance of the inlet is directly related to the thrust of the solid impulse engine, which in turn affects the overall combat performance of the supersonic vehicle. With the increasingly clear requirements for supersonic aircraft missions in future wars, the demand for an inlet with good self-starting characteristics, high total pressure recovery coefficient and high flow coefficient in a wide range of Mach numbers is also increasingly prominent . [0003] When the Mach number reaches above 2.5, the boundary layer in the inlet has a greater impact on its performance, and the interference between the shock wave and the boundary layer becomes more and more serious. In order to obtain better performance, it is a consensus in the indust...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04
Inventor 杜绵银杨乐天
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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