Abstract
A numerical model is developed to quantitative evaluation of the thermal and structural characteristics of the regenerative cooled scramjet engine. The three-dimensional internal CFD platform for scramjet and the computational program of domestic aviation kerosene properties are incorporated together to develop three dimensional thermal evaluation code. Then the thermal evaluation results from the code can be introduced into the thermal-stress finite element program to complete quantitative structural analysis of engine structure. The results show the temperature and heat flux distribution of the scramjet structure is very uneven. Local plasticity occurs in some areas. The results of this paper can be an valuable reference for the test and design of regenerative cooled scramjet.
Highlights
The sustained operating conditions of scramjet engines demand designs that include active cooling by the fuel and the use of lightweight materials that withstand extreme heat fluxes under oxidizing conditions
The thermal evaluation results from the code can be introduced into the thermal-stress finite element program to complete quantitative structural analysis of engine structure
The wall of scramjet can consist of four layers: a coating, liner, the channel, and the closeout, which can be made of different materials
Summary
The sustained operating conditions of scramjet engines demand designs that include active cooling by the fuel and the use of lightweight materials that withstand extreme heat fluxes under oxidizing conditions. Since the mass flow rate and the heat sink capacity of the cooling liquid hydrocarbon fuel have significant limitation, the cooling channels design is very important. Pratt & Whitney Space Propulsion has developed prediction tools to achieve quantitative evaluation of the thermal and structural characteristics of the scramjet engine.The scheme that different heat flux areas require different cooling channels was adopted. Three-dimensional internal CFD platform for scramjet and the computational program of domestic aviation kerosene properties are incorporated together to develop three dimensional thermal evaluation code. The thermal evaluation results from the code can be introduced into the thermal-stress finite element program to complete quantitative structural analysis of engine structure
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