NASA Lewis Research Center, 21000 Brookpark Road, Cleveland, Ohio 44135

B -- FLANGE VIBRATION TESTING DUE 042895 POC Margaret Proctor, Project Manager, (216) 433-7526, MS SPT-D2 Glen M. Williams, Contracting Officer (216) 433-2885. NASA Lewis Research Center is seeking sources to provide vibrational testing at cryogenic temperatures of flanges used in rocket engine systems. Up to four flange designs will be tested under vehicle transportation load and flight load conditions. Testing to failure (a leak occurs) is needed to compare the margins of safety of each flange design. Vibrational loads needed range from 0 to 10 g's in amplitude and up to 2000 Hz in frequency. A minimum of 80 psig internal pressure must be maintained during testing. Some techniques must be used to determine if the flange is leaking, possibly a mass spectrometer. Although the actual operating fluid used with these flanges is liquid hydrogen (60 R), testing in nitrogen at a maximum temperature of 180 R is acceptable. The flange joint connects two sections of 5-inch diameter ducting that is approximately six feet long when assembled. Approximately 15 channels of accelerometer, strain gage, and thermocouple data will need to be recorded as well as any leakage. Test data in digital and/or magnetic tape format and a test report summarizing the results for each flange tested are deliverables. All test results are needed by September 1, 1995. See Numbered Note(s): 25. (0068)

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