CFD analysis of the impingement cooling effect of the coolant jet caused by the T56 1st stage disc metering hole

Abstract

This investigation examines the results of the CFD analysis of the effect of coolant impingement on the back of a disc (or wheel) as part of the secondary cooling circuit of the T56-A-15LFE turboprop engine. As part of the collaborative study involving Rolls-Royce, CSIR and NRC of Canada performed a conjugate heat transfer analysis using techniques developed through experience with other South African Air Force (SAAF) engines [1], boundary conditions and geometrical detail supplied by Rolls-Royce [2] and the commercial CFD code Star-CD. The results of the analysis indicate that the effect, although clearly visible on used parts (Figure 1), is localized and confined to the metal surface. This, coupled with the isolation of the impingement zone (far from the critical stress locations) meant that the impingement effect was not considered in the calculation of aerothermal boundary conditions for the life assessment study of these components