THERMAL-STRUCTURAL DESIGN STUDY OF AN AIRFRAME-INTEGRATED SCRAMJET

摘要

The overall objectives of this study were to:(1) develop and evaluate a design concept for the cooled structures assembly for the Langley Scramjet engine;(2) develop concepts for engine subsystems in sufficient detail to show feasibility and estimate mass, volume, and operating requirements;and (3) establish design concepts for the aircraft/engine interface. Results of the study show that the objectives for the Scramjet engine can be met. A thermal protection system has been defined that makes it possible to attain a life of 100 hours and 1000 cycles, which is the specified goal. With stoichlometric combustion, the fuel provides an adequate heat sink for cooling the engine at Mach numbers up to 9 at the minimum fuel flow condition. The mechanical design is feasible for manufacture using conventional materials. For the cooled structures in a six-module engine, the mass per unit capture area is 1328 kg/m2 (259 lb/ft). The total mass of a six-module engine assembly including the fuel system is 1577 kg (3477 lb).