A design method of circular rotating annular supersonic flow channel for non-uniform inflow and flow channel

By constructing the central body and outer wall profile using the CST modeling method and B-spline curves, a circular to annular supersonic flow channel was designed, which solved the problem of transforming non-uniform inflow into uniform flow and improved the flow uniformity and the accuracy of the flow channel design.

CN117349979BActive Publication Date: 2026-05-29NAT UNIV OF DEFENSE TECH
View PDF 2 Cites 0 Cited by

Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
NAT UNIV OF DEFENSE TECH
Filing Date
2023-10-05
Publication Date
2026-05-29

AI Technical Summary

Technical Problem

Existing technologies cannot effectively transform non-uniform circular inlet flow into uniform annular outlet flow, especially in supersonic equipment. The design methods cannot precisely control the aerodynamic profile of the flow channel, resulting in poor flow characteristics.

Method used

The CST modeling method and B-spline curves were used to construct the central body and outer wall profiles. By fitting the central body profile, controlling eccentricity and controlling the flow cross section, a circular to annular supersonic flow channel was designed, including a conical central body and outer wall. The flow cross section area change and eccentricity adjustment were controlled to generate an optimized flow channel structure.

Benefits of technology

It realizes the transformation from non-uniform inflow to uniform flow, improves flow uniformity, reduces flow losses, simplifies the design process, and enhances the structural simplicity and adjustability of the flow channel.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN117349979B_ABST
    Figure CN117349979B_ABST
Patent Text Reader

Abstract

The application relates to a circular rotating ring-shaped supersonic flow channel design method and flow channel for a non-uniform incoming flow, and the design method comprises the following steps: acquiring a flow channel inlet shape and an inlet size parameter of a supersonic flow channel, and acquiring a flow channel outlet shape and an outlet size parameter of the supersonic flow channel; determining a basic configuration of the supersonic flow channel based on the flow channel inlet shape and the flow channel outlet shape, wherein the supersonic flow channel comprises a center body with an overall conical structure and an outer wall for surrounding the center body; fitting a center body profile of the center body along a flow direction of the supersonic flow channel; acquiring a flow direction cross-section control scheme for controlling the flow direction cross-section area change of the supersonic flow channel; fitting an outer wall profile of the outer wall based on the flow direction cross-section control scheme and the center body profile; acquiring an eccentricity control scheme of the center body profile; and performing eccentricity adjustment on the center body profile based on the eccentricity control scheme to generate the supersonic flow channel.
Need to check novelty before this filing date? Find Prior Art