Year: 2024
Type: article
Abstract: In general, there are many cooling methods of Liquid Rocket Engine such as Ablation Cooling Method, Penetration Cooling Method, Regenerative Cooling Method, Film Cooling Method, and Heat Insulating Coating Method(TBC).It will be designed and manufactured using one or more methods.Since film cooling has a direct impact on combustion efficiency, cold flow tests are essential to verify the design flow rate.Numerous cold flow tests to verify the design flow rate increases the testing costs and the manufacturing period.In this paper, we optimized the test procedure and proposed a Film Cooling Model to estimate the design flow rate with a minimal number of cold flow tests.Additionally, when the flow rate prediction model was applied to the combustion test results, the difference in flow rate was confirmed to be within 1%. 초 록액체로켓엔진의 냉각 방식에는 삭마냉각 방식, 침투냉각, 복사냉각, 재생냉각 방식, 막냉각 방식과 TBC와 같 은 열 차폐 방식이 있으며,
Authors: Wonju Jea, Dong hyuk Kang, Sang Hun Han, Jonggyu Kim, Hong Jip Kim
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W4406411446