AERODYNAMIC INTERFERENCE EFFECTS ON NORMAL ANDnAXIAL FORCE COEFFICIENTS OF SEVERAL ENGINE-STRUT-BODY CONFIGURATIONS AT MACH NUMBERS OF .1:8 AND 2.0

摘要

An air-cooled internal-strut-supported "blade was investigated in a modified production turbojet engine to determine the cooling effective¬ness of this type of blade design and the cooling-air pressure loss through the blade under engine operating conditions. This blade con-sisted of a finned internal load-carrying member or strut integral with the blade mounting base and an attached shell that forms the airfoil shape and insulates the strut from the direct effects of the hot gas stream. The greater part of the investigation was conducted over a range of engine speeds from 4000 to 11,500 rpm and a range of coolant-to-gas weight-flow ratios per blade from approximately 0.02 to 0.10. The experimental results Of this investigation are presented and com¬pared with' the results from an analytical investigation of a similar internal-strut-supported blade and with the results of experimental investigations of shell-supported blades.