Abstract
The ramjet engine performs faster than a Turbojet Engine at higher Mach numbers, but the engine can’t start with the own power itself. The starting thrust must be attained by additional thrust producing devices like solid rocket boosters. The more reasonable solution to overcome the starting problem is the integration of ramjet engine with turbojet engine, which leads to the Turboramjet. This work describes some challenges in the design of an inlet for turbo-ramjet. Since it is a critical component, its design has important effects on the overall performance of the engine. Here this work deals with a design of a turbo ramjet inlet and an analysis for its optimization. Our aim is to reduce total pressure loss and entropy rise. A design of turbo-ramjet intake is made with CATIA as well as a complete engine for better understanding. Gambit is used to mesh the geometry while ANSYS 14 is used to perform the analysis for design optimization.
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