| 摘要 |
PROBLEM TO BE SOLVED: To provide an effusion cooling rocket combustor minimizing deterioration in performance by distributing and supplying the optimum amount of a coolant according to the heat load distribution of a combustion chamber by a simple method, and providing improved durability, a simplified structure, a reduced weight, and a reduced cost. SOLUTION: A permeation flow flux q<SB>cool</SB>of the coolant specified as K<SB>liner</SB>×ΔP/t is set to conform with the heat load distribution of the combustion chamber by changing the thickness of a liner by using a C/C composite material simultaneously having permeability, excellent heat resistance and excellent high temperature strength as a material for a combustion chamber liner 22 and a nozzle liner 32 or by utilizing impregnation/coating of silica glass or anisotropy of transmissivity of the C/C composite material. COPYRIGHT: (C)2008,JPO&INPIT
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