High-performance rectangular dual-channel external parallel-connection TBCC air inlet way and design method

A dual-channel, high-performance technology, used in computing, mechanical equipment, jet propulsion, etc., can solve problems such as poor starting performance in low-speed channels, and achieve the effects of widening the stable working range, improving starting performance, and simplifying the structure.

Active Publication Date: 2018-01-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It can widen the working Mach number range of the intake port and so

Method used

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  • High-performance rectangular dual-channel external parallel-connection TBCC air inlet way and design method
  • High-performance rectangular dual-channel external parallel-connection TBCC air inlet way and design method
  • High-performance rectangular dual-channel external parallel-connection TBCC air inlet way and design method

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Example Embodiment

[0021] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0022] see figure 1 and figure 2 As shown, the present invention discloses a specific embodiment of a high-performance rectangular dual-channel external parallel TBCC inlet, including a high-speed channel 13 extending from front to rear, a low-speed channel 13 located inside the high-speed channel and extending from front to rear side by side with the high-speed channel Passage 14, primary compression surface 1, passage divider 5 between the high-speed passage and the low-speed passage, rotating lip cover 3 hinged at the front end of the passage divider 5 and extending forward; the outer wall of the high-speed passage 13 is the high-speed passage lip Cover 6, the inner wall surface of the low-velocity channel 14 includes a movable contraction section 8 hinged at the rear end of the primary compression surface 1, a movable throat section 10 hinged at the rea...

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Abstract

The invention discloses a high-performance rectangular double-channel outer parallel TBCC inlet. In terms of design, on the basis of the traditional two-stage external compression hypersonic inlet, the present invention designs the two-stage compression surface as a rotating lip cover, and adds a low-speed channel on this basis to realize the external parallel structure, and the low-speed The lower wall of the channel is designed as a variable structure, so that the shrinkage ratio in the low-speed channel can be adjusted, thereby improving the problem of poor starting performance in the low-speed channel. The two-stage compression surface of the high-speed channel and the lip cover of the low-speed channel are combined into one, and act as a mode conversion valve, which simplifies the structure of the intake port and enhances reliability. At the same time, the present invention also provides a specific embodiment of the rotating lip cover. The rotating lip cover is controlled by a servo motor in the form of a sliding thin plate introduced into the side wall of the passage, so that the movement of the rotating lip cover can be controlled. While satisfying the mode conversion, The flow control of the low-speed channel can also be realized by cooperating with the variable throat.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a high-performance rectangular dual-channel outer parallel TBCC inlet. Background technique [0002] With the advent of supersonic / hypersonic strike weapons, hypersonic vehicle technology has become the focus of research in various countries. The core technology of a hypersonic vehicle is the engine, that is, the high-performance propulsion technology. For the wide Mach number operating range required by hypersonic vehicles, it is difficult for general forms of aero-engines to meet the requirements, so combined engines emerged as the times require. Among them, the turbine-base-combine-cycle (Turbine-Base-Combine-Cycle) engine combines the aviation turbine with the aviation turbine, sub-combustion / scramjet engine to realize variable cycle work, so that the engine can work well under different working conditions Characteristics have become the focus of combined dynamics research at...

Claims

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Application Information

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IPC IPC(8): F02C7/042G06F17/50
Inventor 孙姝张宇超谭慧俊刘亚洲黄河峡张悦
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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