喷管与机后体一体化设计初探

Preliminary Investigated of Integrated Design for Nozzle and Aircraft Afterbody

航空燃气涡轮发动机尾喷管在装机时发生了诸如气动、燃烧、冷却和结构等一系列问题。为此,进行了气动热力分析和结构可行性分析;借助喷管与机后体一体化设计技术,进行了新的流路设计、内流和外流冷却系统设计,改进了快卸环设计和多项结构设计,并进行了试验验证,最终取得了良好的装机效果,获得了使用部门的好评。

A series of questions occurred such as aerodynamic, combustion, cooling and structure when the aero -gas turbine nozzle was installed, so aerothermodynamics and structure feasibility analyses were conducted. The new flowpath design, internal flow and outflow cooling systems designs were conducted by the means of integration design for the nozzle and aircraft afierbody , and the designs of quick - release ring and multiple structures were improved. The experimental verification was conducted and good effect of installation was obtained as well as the services given some favorable comment.