A controllable air intake channel and method based on a leak slit switch

An air intake and flow leakage technology, which is applied to the air intake of turbine/propulsion device, jet propulsion device, gas turbine device, etc. The effect of widening the working range, reducing the starting Mach number and simplifying the structure

Active Publication Date: 2022-05-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a controllable intake port based on the switch of the leak slit to solve the problem of non-starting at low Mach number and the mismatching problem of the intake port / engine flow in the fixed geometry intake port in a wide speed range

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  • A controllable air intake channel and method based on a leak slit switch
  • A controllable air intake channel and method based on a leak slit switch
  • A controllable air intake channel and method based on a leak slit switch

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Embodiment Construction

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

[0022] Aiming at the problems of starting and flow matching existing in a fixed-geometry intake port, the present invention proposes a controllable intake port and a method based on a bleed slot switch.

[0023] like figure 1 As shown in the figure, a controllable air intake based on a bleed slot switch of the present invention includes an intake duct center body 1, and a fairing 4 is arranged on the air intake central body 1, and the fairing 4 is provided with multiple discharge flow slots. , the discharge seam includes the internal pressure section discharge seam 2 and the expansion section discharge seam 5, the internal pressure section discharge seam 2 is opened in the inner pressure section of the fairing 4, and the expansion section discharge seam 5 is opened in the expansion of the fairing 4 The internal pressure section discharge slit 2 and the expansion secti...

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Abstract

The invention discloses a controllable air intake channel and a method based on a switch of a leakage slit. The air intake channel includes a center body of the air intake channel. There are multiple drainage slots, and the opening area of ​​the drainage slots is controllable. The present invention directly discharges the airflow out of the intake passage by opening the flow slit in the fairing of the intake passage, without special consideration of the flow path of the airflow, simplifies the structure, improves the starting performance of the intake passage, and reduces the start-up Mach of the intake passage Number, widen the working range of the inlet; adjust the flow of the inlet to meet the engine flow requirements under different flight conditions; this inlet and design ideas can be applied to binary, axisymmetric and internal rotation and other types road.

Description

technical field [0001] The invention relates to a controllable air intake channel and a method based on a leakage slit switch, and belongs to the field of aerodynamic design of the air intake channel. Background technique [0002] At present, supersonic and hypersonic aircraft have become the focus of attention of various military powers. As one of the key components of the air-breathing propulsion system, the air inlet has an important influence on the aerodynamic performance of the air-breathing propulsion system and even the whole aircraft. In order to realize the wide speed range flight from ground takeoff to supersonic speed and even hypersonic speed, the design of the air inlet is extremely critical. Its design requires that the air intake should not only work stably in a wide range, but also have high performance under the design state. The design of the intake port is usually based on the high flight Mach number as the design point, but at the non-design point, the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04F02C7/045F02C7/057F02K7/14
CPCF02C7/04F02C7/045F02C7/057F02K7/14
Inventor 袁化成刘甫州王鑫周珂玉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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