一种适用于大热流推力室的异型冷却通道设计方法
By establishing a mapping relationship between the thrust chamber wall and the computational domain, an adaptive mesh is generated, and the number and shape of cooling channels are optimized. This solves the problem of efficient cooling of the thrust chamber of a reusable rocket engine, achieving a reduction in the temperature of the thrust chamber wall and an improvement in cooling efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF ASTRONAUTICAL SYST ENG
- Filing Date
- 2023-11-20
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies struggle to achieve efficient cooling in the thrust chamber of reusable rocket engines, leading to excessively high wall temperatures and even burn-out problems.
An irregular cooling channel design method is adopted. By establishing a mapping relationship between the thrust chamber wall and the computational domain, an adaptive mesh is generated to optimize the number, shape and hydraulic diameter of the cooling channels. Combined with the objective function and constraints, the cooling effect is optimized.
It effectively reduces the temperature of the thrust chamber wall, improves cooling efficiency, avoids overheating of the wall, optimizes the cooling channel form and hydraulic diameter, and achieves better cooling effect.
Smart Images
Figure CN117610155B_ABST