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Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed (1952)

NASA Technical Reports Server (NTRS) · leaf 22

An illustration from Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed, 1952, leaf 22
-.4 -.3 -.2 -.1 0 -1 -2 Exit absolute tangential velocity parameter for take-off, (Vu/acr)5 Figure 5• - Comparison of required and limiting exit relative tangential velocity parameter (Wu/a£r)5 at cruise for various increaeed-diameter turbines.

NASA Technical Reports Server (NTRS)

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More pictures from Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed

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