Analysis particularly emphasizes cost of design compromises in operation of engine over range of altitudes and powers; for geared-in turbines, compressor losses were sometimes large and altitude range was restricted; by use of auxiliary propeller, these losses could be reduced.
Performance of composite engine consisting of reciprocating spark-ignition engine, blowdown turbine, and steady-flow turbine
Nat Advisory Committee Aeronautics -- Tech Note
1947
56 pages
Article (Journal)
English
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