Measuring unsteady pressure on rotating compressor bladesThe capability for accurate measurement of unsteady pressure on the surface of compressor and fan blades during engine operation was established. Tests were run on miniature semiconductor strain gage pressure transducers mounted in several arrangements. Both surface mountings and recessed flush mountings were tested. Test parameters included mounting arrangement, blade material, temperature, local strain in the blade, acceleration normal to the transducer diaphragm, centripetal acceleration, and pressure. Test results showed no failures of transducers or mountings and indicated an uncertainty of unsteady pressure measurement of approximately + or - 6%, plus 0.1 kPa for a typical application.
Document ID
19800028460
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Englund, D. R. (NASA Lewis Research Center Cleveland, Ohio, United States)
Grant, H. P. (NASA Lewis Research Center Cleveland, OH, United States)
Lanati, G. A. (United Technologies Corp. Pratt and Whitney Aircraft Group, East Hartford, Conn., United States)