Materials Research for the Hypersonic Air Breathing Engine

Abstract

The temperatures which will typically be encountered by various parts of a hypersonic air breathing engine at different Mach numbers are indicated in FIG. 1. A limited gain can be expected from the employment of cooling systems but in general the need for materials possessing heat resisting properties which are markedly superior to those conventionally used, such as the Nimonic range, is apparent at approximately Mach 4. Combustor flame stabilizing equipment for example must survive as an item of structure at temperatures around 1,300 deg. C. for Mach 4 and 1,500 deg. C. for Mach 5. Intake leading edges and ducts containing intake air are two further areas requiring the use of new high temperature metals once Mach 5 has been significantly exceeded. The combustor gas temperatures shown in FIG. 1, even allowing for limited cooling, require the use of a material capable of operating with a hot face temperature of 2,000 deg. C. or above. In this instance the material might be used as a non‐structural lining designed to lean on the cooler load‐carrying structure. In each of these instances the material is subjected to the effects of a high velocity oxidizing atmosphere.