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This question requires you to demonstrate your knowledge and understanding of gas turbine engines. The heavy-lift CH-47F Chinook helicopter is powered by two Lycoming T55 turboshaft engines. This two spool engine uses a separate compressorturbine and power-turbine. a. Draw a process diagram for this engine showing your stage notation and mechanical linkages; [3 marks] b. Each engine produces 3,629 kW brake shaft power when hovering at sea-level. Given the engine performance data in Table Q4, determine; I. The engine brake specific fuel consumption (in kg/kW.h). [3 marks] II. the power-turbine entry temperature [5 marks] III. the compressor-turbine entry pressure [6 marks] iv) The compressor pressure ratio [8 marks] Q4a) There were no numerical answer to this question Q4b i) BSFC = 0.38 kg/kW.h = 0.1054 mg/kW.s = 1.054x10-4 kg/kW.s Q4b ii) Tt6 = 1088 K Q4b iii) Pt3 = 897 kPa Q4b iv) PR = 9.32
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