Investigation of the Stall Hammershock at the Engine Inlet

Abstract

The peak static pressures measured at the inlet to the engine during stall are presented for a turbojet and two turbofan engines. It is shown for one turbofan and the turbojet that the static pressure ratio across the hammershock does not exceed significantly the normal shock pressure ratio necessary to stop the flow. The second turbofan engine did not follow this rule. Possible reasons for the departure are discussed. For the two turbofan engines the influence of the stall method on the hammershock intensity has been investigated. Data related to the spatial distribution of pressure in the hammershock are also presented. Nomenclature a = speed of sound Cp = specific heat at constant pressure M = Mach number P - total pressure P = static pressure T = static temperature t = time