Supersonic/hypersonic aerocraft engine overexpansion nozzle bypass type device

A hypersonic, aircraft technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problems of difficult implementation, large additional weight, complex mechanical structure, etc., to improve the thrust coefficient, improve non-design point performance, thrust performance improved effect

Inactive Publication Date: 2013-09-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to technical problems such as complex mechanical structure, large additional weight, and heat-proof sealing, it is difficult to realize

Method used

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  • Supersonic/hypersonic aerocraft engine overexpansion nozzle bypass type device
  • Supersonic/hypersonic aerocraft engine overexpansion nozzle bypass type device
  • Supersonic/hypersonic aerocraft engine overexpansion nozzle bypass type device

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Embodiment Construction

[0033] Below in conjunction with accompanying drawing and embodiment, the present invention is described in detail:

[0034] Such as image 3 , Figure 4 with Figure 5 As shown, the supersonic / hypersonic bypass type bleed air control device described in the present invention includes the constriction section and the expansion section of the over-expansion nozzle, and the bleed air bypass channel between the nozzle constriction section and the expansion section, bypass The bypass channel connects the constriction section and the expansion section of the nozzle, and the bypass channel includes an air inlet 1, a first channel 2, a first corner 3, a second channel 4, a second corner 5, a third channel 6, and an air outlet 7 . The air inlet 1 is arranged in the constriction section of the nozzle, and the design space of the air inlet 1 is preferably within the range of 0-50% of the front part of the nozzle inlet; the air outlet 7 is arranged in the expansion section of the noz...

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Abstract

The invention discloses a supersonic / hypersonic aerocraft engine overexpansion nozzle bypass type device. The device comprises a nozzle contracting segment, a nozzle expanding segment, an air-bleeding bypass and a control device for controlling the air-bleeding bypass to be opened and closed, the air-bleeding bypass is an internal flowing passage communicating the nozzle contracting segment and the nozzle expanding segment, and an internal flow field is established by the aid of natural pressure difference between an air inlet of the nozzle contracting segment and an air outlet of the nozzle expanding segment. When the aerocraft works in the transonic and over-expanding state, the bypass is opened, high-pressure air of the nozzle contracting segment is bled to the nozzle expanding segment to form secondary flow injecting effect, and thrust coefficient of the nozzle is increased; and when the aerocraft in the normal working state, the air-bleeding bypass passage is closed, and nozzle design point performances cannot be affected. The supersonic / hypersonic aerocraft engine overexpansion nozzle bypass type device is simple in structure, needs no extra air bleeding sources and is free of additional weight, and thrust performances of the nozzle are improved.

Description

technical field [0001] The invention relates to a flow path design in a nozzle of a supersonic / hypersonic aircraft. Background technique [0002] In order to meet the flight requirements across a large Mach number range, especially for combined cycle engines like TBCC / RBCC, the exhaust system is required to have good aerodynamic performance in a wide range, including thrust, lift, pitching moment, etc. The traditional axisymmetric nozzle has problems such as mechanical limitation and sealing of the expansion surface, which makes the nozzle unable to achieve high thrust performance under different flight conditions, which severely compresses the living space of supersonic / hypersonic aircraft. Therefore, it is an important research direction to expand its flight Mach number and improve its off-design point performance. [0003] Can refer to figure 1 with figure 2 It can be seen that figure 1 It shows that when the aircraft is in the transonic range (that is, around Mach n...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/38
Inventor 王明涛
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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