Scramjet including integrated inlet and combustor

Details Scramjet including integrated inlet and combustor Scramjet including integrated inlet and combustor

F - Mech Eng,Light,Heat,Weapons

02

K

60/63

F02K 7/14 (2006.01) F02K 7/10 (2006.01)

Patent

CA 2034434

ABSTRACT A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scramjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween, Means for injecting fuel into the inlet- combustor at the step are provided for mixing fuel with supersonic airflow generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel injecting means is effective for injecting fuel to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in aconventional scramjet engine.

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