Abstract
A new thermal protection design method for hypersonic vehicle's leading edge is pro-posed,which can effectively reduce temperature of the leading edge without additional cooling mea-sures.This method reduces the leading-edge's temperature by the multi-scale collaborative design of the macroscopic thermal optimization and the mesoscopic woven structures of Three-dimensional Orthogonal Woven Ceramic Matrix Composites(TOCMC).The macroscopic thermal optimization is achieved by designing different mesoscopic woven structures in different regions to create com-bined heat transfer channels to dredge the heat.The combined heat transfer channel is macroscop-ically represented by the anisotropic thermal conductivity of TOCMC.The thermal optimization multiple linear regression model is established to optimize the heat transport channel,which pre-dicts Theoretical Optimal Thermal Conductivity Configuration(TOTCC)in different regions to achieve the lowest leading-edge temperature.The function-oriented mesostructure design method is invented to design the corresponding mesostructure of TOCMC according to the TOTCC,which consists of universal thermal conductivity prediction formulas for TOCMC.These universal formu-las are firstly derived based on the thermal resistance network method,which is verified by exper-iments with an error of 6.25％.The results show that the collaborative design method can effectively reduce the leading edge temperature by about 12.8％without adding cooling measures.
基金项目
Science Center for Gas Turbine Project,China(P2022-B-Ⅱ-025-001)
国家科技重大专项(Y2019-I-0018-0017)
NETL
NSTL
万方数据