Rotational flow distortion flow control device for S-shaped air inlet channel based on fluid oscillator

A technology of flow control and swirl distortion, applied in the direction of jet propulsion device, gas turbine device, turbine/propulsion device inlet, etc., can solve problems such as limited control range and inability to adjust excitation

Inactive Publication Date: 2021-07-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, although the above-mentioned control method can achieve better control effect under certain conditions, its control range is limited, and t

Method used

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  • Rotational flow distortion flow control device for S-shaped air inlet channel based on fluid oscillator
  • Rotational flow distortion flow control device for S-shaped air inlet channel based on fluid oscillator
  • Rotational flow distortion flow control device for S-shaped air inlet channel based on fluid oscillator

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Embodiment Construction

[0016] The invention proposes a flow control idea based on a figure-eight array fluid oscillator to control swirling flow distortion in an S-shaped inlet channel. see figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 As shown, the detailed implementation steps of this embodiment of the method design of the present invention are described below.

[0017] The fluid oscillators 3 are installed between the curved section 4 and the inlet stabilizing section 2, and are symmetrically distributed on the central plane of the inlet stabilizing section 2, and the distribution positions and installation numbers of the fluid oscillators are individually adjustable.

[0018] The oscillating jet 11 flows out from the outlet 9 of the fluid oscillator and interacts with the airflow from the inlet stable section 2. Due to the velocity difference between the jet and the inlet stable section 2, the flow is sheared to the vortex, and then the vortex develops to the curved section 4 and i...

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Abstract

The invention discloses a rotational flow distortion flow control device for an S-shaped air inlet channel based on a fluid oscillator. The rotational flow distortion flow control device is characterized in that the fluid oscillator is arranged in an inlet stabilizing section of the air inlet channel, and oscillation jet flow of an outlet of the fluid oscillator interacts with air flow of the inlet stabilizing section, so that vortex is induced to control flow separation and secondary rotational flow in the air inlet channel. Compared with an existing flow control device, the rotational flow distortion flow control device has the advantages of being simple in structure, free of movable parts, capable of achieving a good control effect by inputting small flow and the like, can increase the total pressure recovery coefficient of an outlet of the air inlet channel effectively, reduces the total pressure distortion index, and improves the outlet flow field quality.

Description

technical field [0001] The invention belongs to the field of flow separation control of an air intake port of an aero-engine, and designs an S-shaped inlet swirl distortion flow control device based on a fluid oscillator. Background technique [0002] The S-shaped inlet is an aerodynamic component that can effectively shield the engine blades and reduce the radar scattering area, thereby greatly improving the stealth performance of the aircraft, and the S-shaped inlet is easy to integrate with the fuselage. Man-machine, cruise missiles have been widely used. However, due to its unique structure, centrifugal force and strong reverse pressure gradient produce flow separation phenomenon in the large curvature bending section. Flow separation will lead to a decrease in the total pressure recovery coefficient of the inlet outlet section and an increase in the total pressure distortion index, which is not conducive to the stable operation of the engine. Moreover, under the joint...

Claims

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Application Information

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IPC IPC(8): F02C7/04F02C7/057
CPCF02C7/04F02C7/057
Inventor 黄河峡马志明林正康李灿民陈诚谭慧俊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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