Abstract
Abstract.The authors describe briefly a series of jet tests, utilizing gas produced from the combustion of diesel fuel oil, as a means for comparing the resistance of a number of high temperature alloys to hot gas impingement. The deficiencies of this method for simulating conditions in a gas turbine are discussed.The main part of the paper is concerned with comparative tests of a number of high temperature alloys when tested in the form of blades in a Type B turbo‐supercharger. The test rotor contained 142 blades representing 12 different alloys. Both wrought and precision cast blades were included. Tests were made at eight temperatures ranging from approximately 1200° to 1500° F., test runs at each temperature being of 50 to 150 hours duration except in the case of the 1500° F. test run which is being continued for 1000 hours.After several of the test runs, measurements were made to determine the amount of permanent extension in the blades and disc. The extension of the blades and disc accompanying progressively higher testing temperatures is shown graphically. A procedure for correlating the metal temperature of the blades with that of the combustion gas in the nozzle chamber of the supercharger is described.
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