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Holographic Visualization of Compressor Blade Wake Interaction.
Final technical rept. 19 Mar 73-19 Jan 74,
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
Pagination or Media Count:
Successful holographic studies were made of unsteady aerodynamic effects within the stator passage of a single-stage test compressor operating at tip speeds between 1400 and 1600 feet per second. A shock wave associated with the rotor trailing edge was observed to reflect from the stator vanes, producing a characteristic downstream array of shock segments. This array possesses a helical structure which will excite propagating acoustic modes of duct, and will affect the interpretation of instrument readings and of downstream noise phenomena. A systematic variation of density gradients was observed within the stator passages, consistent with a wake transport theory previously developed by Kerrebrock and Mikolajczak. Both point-source and diffuse-background holograms were employed, the latter in the form of double exposures which yielded shearing differential interferograms.
APPROVED FOR PUBLIC RELEASE