Kudin M. Numerical and Experimental Investigations the Features of the Flow Near the Aircraft Engine Rotor Blade Tips

Українська версія

Thesis for the degree of Candidate of Sciences (CSc)

State registration number

0499U001769

Thesis Registration Form

0499U001769.pdf

Applicant for

Specialization

  • 05.07.05 - Двигуни та енергоустановки літальних апаратів

25-06-1999

Specialized Academic Board

Д 64.062.03

Essay

The dissertation is devoted to creation of investigation technique of the aircraft engine rotor blades tip region flow using unsteady pressure at the casing. A fast-response static - pressure probe was used with a periodically sampling and averagi g data acquisition computer system to study the unsteady pressure fields at the casing of an axial-flow compressor stage. Periodically unsteady pressure data were used to predict the rotor operational conditions, circumferential radial clearance dist ibutions and existance of damages of some blades.

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