Two-dimensional, unilateral oblique shock diffuser as the air inlet for a gas turbine jet engine for the propulsion of heavy-duty aircraft

摘要

A two-dimensional, unidirectional oblique air impact diffuser is used as an air inlet for a gas turbine jet engine for aircraft. The air inlet includes an upper rigid air inlet ramp and an air inlet bottom spaced below the ramp. An air scoop lip is pivotally attached to the air inlet bottom so that it can be pivoted from a standard setting point downwardly away from the air inlet ramp and also from the standard setting point toward the ramp. The pivotal displacement of the air scoop lip is a function of the aircraft angle of attack and the flight Mach number. The angular displacement of the air scoop lip from the standard setting point increases downwardly as the aircraft angle of attack increases and decreases as the Mach number increases.