Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity
Description:
Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.
Date:
May 25, 1954
Creator:
Rossbach, Richard J.; Schramm, Wilson B. & Hubbartt, James E.
Item Type:
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Partner:
UNT Libraries Government Documents Department