Influence of a Gap for Film Cooling on Transient Flow Characteristics of Rocket Engine Nozzles

التفاصيل البيبلوغرافية
العنوان: Influence of a Gap for Film Cooling on Transient Flow Characteristics of Rocket Engine Nozzles
المؤلفون: Masahiro Takahashi, Masanori Tsuboi, Yasuhide Watanabe, Mamoru Takahashi, Hiroshi Tamura, Takeo Tomita
المصدر: 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
بيانات النشر: American Institute of Aeronautics and Astronautics, 2002.
سنة النشر: 2002
مصطلحات موضوعية: Engineering, business.industry, Computation, Nozzle, Flow (psychology), Rotational symmetry, Electronic engineering, Point (geometry), Rocket engine, Mechanics, business, Discharge coefficient, Joint (geology)
الوصف: Axisymmetric computation was applied to the transient flow in a sub-scaled LE-7A nozzle with three different configurations of a joint section between its upper nozzle and nozzle extension sections, such as a backward facing step for film-cooling, to investigate the influences of the flow disturbances produced by such nozzle surface shapes on the transient flow characteristics and to examine the possible cause of side-loads observed in the experiments. Rapid movement of the separation point occurred when it passed through the joint section. One of reasons for the occurrence of a highly asymmetrical flow causing large side-load is considered to be that the location of the separation point becomes very sensitive to the flow condition when the separation point passes through the joint section.
DOI: 10.2514/6.2002-4147
URL الوصول: https://explore.openaire.eu/search/publication?articleId=doi_________::6727780ae1a0bfd0047e300e11355fc2
https://doi.org/10.2514/6.2002-4147
رقم الانضمام: edsair.doi...........6727780ae1a0bfd0047e300e11355fc2
قاعدة البيانات: OpenAIRE