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A supersonic aircraft inlet with adjustable throat area and its adjustment method

An air inlet, supersonic technology, applied in the direction of machines/engines, jet propulsion devices, gas turbine devices, etc., can solve the problems of large aircraft resistance, large total pressure loss coefficient of the air inlet, and reduced engine thrust. Flexible configuration, simple and convenient adjustment process, and the effect of shortening the length

Inactive Publication Date: 2019-02-26
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, if the inlet does not start, the total pressure loss coefficient of the inlet will be larger, and the thrust of the engine will decrease; at the same time, the overflow will make the aircraft resistance greater

Method used

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  • A supersonic aircraft inlet with adjustable throat area and its adjustment method
  • A supersonic aircraft inlet with adjustable throat area and its adjustment method
  • A supersonic aircraft inlet with adjustable throat area and its adjustment method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] Such as Figure 1-6 As shown, a supersonic aircraft air intake with adjustable throat area, the air intake includes a lip 1, a throat 2 and an expansion section 3, the part of the air intake located at the front end of the lip 1 is a multi-section wedge surface, The air inlet forms a constricted section between the lip 1 and the throat 2. In the air inlet, the throat 2 has the smallest cross-sectional area. A displacement mechanism (not shown in the figure) is arranged in the air inlet. Vanes 4 are arranged in the air inlet through the displacement mechanism, and the displacement mechanism can control the blades 4 to move back and forth and rotate in the air inlet.

[0022] Further, the blades 4 are arranged on the side walls on both sides of the air inlet through a displacement mechanism.

[0023] Further, the blade 4 is a supersonic airfoil or a supersonic airfoil.

[0024] Further, a fin 5 is provided on the upper part of the lip 1 of the air inlet, and one end of t...

Embodiment 2

[0035] Such as Figure 7-12 As shown, the difference between Embodiment 2 and Embodiment 1 is that the blades 4 are at least 2 pieces, and the blades 4 are set to 3 pieces here, specifically the upper blade, the middle blade and the lower blade, and the 3 blades 4 and the wing The combination of slices 5 makes the adjustment process more precise and effective.

[0036] A method for adjusting the air inlet of a supersonic aircraft with an adjustable throat area. In the take-off state, the blades 4 in the air inlet are all in the expansion section 3 of the air inlet, and the fins 5 on the upper part of the lip 1 rotate downwards to reduce the air intake. The opening area of ​​the small lip 1; when the starting Mach number of the air inlet is reached and lower than the design Mach number of the aircraft, the fins 5 are gradually adjusted to rotate upwards until reset. After the fins 5 are reset, the upper blades of the expansion section 3 are sequentially , the middle blade and ...

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Abstract

The invention relates to the field of supersonic propulsion and discloses a supersonic aircraft air inlet channel with an adjustable throat area and an adjusting method. The air inlet channel comprises a lip, a throat and an expansion section, a displacement mechanism is arranged in the air inlet channel, blades are arranged in the air inlet channel through the displacement mechanism, and the displacement mechanism can control the blades to move forwards and backwards and rotate in the air inlet channel. According to the supersonic aircraft air inlet channel and the adjusting method, large-scale and continuous adjustment of the throat area ratio can be realized, so that the air inlet channel always works in a low-loss state, and the adjusting process is simple and convenient.

Description

technical field [0001] The invention relates to the field of supersonic propulsion, in particular to an air inlet of a supersonic aircraft with an adjustable throat area and an adjustment method, which is suitable for supersonic flight with a Mach number above 1.5. Background technique [0002] For an air-breathing supersonic vehicle, the total pressure recovery coefficient at the inlet outlet is closely related to the thrust and fuel consumption of the engine. In order to increase engine thrust and reduce fuel consumption, the intake port is required to have a higher total pressure recovery coefficient. [0003] At present, there are three types of air inlets for ultrasonic flight, internal pressure type, external pressure type and mixed pressure type. The internal pressure inlet can achieve isentropic compression, and the total pressure recovery coefficient is the highest, but there are serious starting problems, so it has not been used in engineering practice; the extern...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/042F02C7/057
CPCF02C7/042F02C7/057
Inventor 邱名郝颜范召林江雄陈逖王子维
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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