一种低阻低损的超燃冲压发动机燃烧室型面设计方法
By optimizing the combustion chamber profile design of the scramjet engine and combining the arc-shaped expansion injection section with the flame stabilizer, the problems of high flow resistance and weak back pressure resistance in the existing technology have been solved, achieving low resistance and low loss performance over a wide Mach number range.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NAT UNIV OF DEFENSE TECH
- Filing Date
- 2023-10-10
- Publication Date
- 2026-07-17
AI Technical Summary
Existing scramjet engine combustion chambers exhibit high flow resistance and total pressure loss at high Mach numbers, and weak resistance to back pressure at low Mach numbers and high equivalence ratios. Current design methods are not applicable to a wide range of design cruise Mach number conditions.
A low-drag, low-loss scramjet engine combustion chamber profile was designed. By combining the arc-shaped expansion injection section with the flame stabilizer, a double-arc nozzle-type combustion-exhaust channel is formed. An igniter is installed in the downstream wall cavity. The geometry of the injection section and the flame stabilizer is optimized to match the flow parameters and achieve a streamlined transition.
It can effectively reduce flow resistance and total pressure loss under both high and low Mach number conditions, and improve the ability to resist back pressure. It is suitable for cruise conditions at Mach 4-7, and takes into account both combustion efficiency and thrust performance.
Smart Images
Figure CN117272545B_ABST