Investigation of Performance of Typical Inlet Stage of Multistage Axial-Flow Compressor
Description:
Memorandum presenting an investigation of a typical inlet stage of a multistage axial-flow compressor that was designed on the basis of an analysis of basic design variables. The stage, consisting of 19 rotor blades and 20 stator blades with 40 inlet guide vanes, had a hub-to-tip-radius ratio at the rotor inlet of 0.50 and a rotor-blade outside diameter of 14 inches. Results regarding the overall compressor performance, comparison of compressor performance with design, and rotor-row performance…
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Date:
July 18, 1949
Creator:
Burtt, Jack R.
Item Type:
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