Development of a boundary layer control device for tip clearence experiments in an axial compressor
Shreeve, Raymond P.
MetadataShow full item record
A boundary layer control device was designed to change significantly the case-wall boundary layer thickness entering a large-scale, multistage axial compressor. The device was intended to double the boundary layer thickness in order to evaluate the influence of the inlet boundary layer in controlled tip clearance experiments being conducted on the compressor. The boundary layer characteristics expected to be produced by the control device were predicted empirically and experimental verification was required. Kiel, cobra, and impact probes were used in the experiments and pressures were recorded manually using water manometers. The geometry of the boundary layer control device, an annular array of spires, was derived from shapes developed for simulating the atmospheric boundary layer in large rectangular section wind tunnels. A significantly thicker boundary layer was measured in the compressor than was intended. However, the results were interpreted and recommendations were made for geometry changes necessary to achieve the intended control for the tip clearance investigation. Keywords: Axial flow compressor blades; Boundary layer spires; Boundary layer control; Theses. (EDC)
Showing items related by title, author, creator and subject.
Winner, Crawford Douglas (Troy, New York; Rensselaer Polytechnic Institute, 1951-05);The limit imposed on the operating range of a radial flow compressor by surging or pulsations in the reduced flow region has long been a source of concern to design engineers who would like to use this otherwise simple, ...
Peacock, R. E. (Monterey, California. Naval Postgraduate School, 1981-11); NPS-67-81-016A review is presented of experiments examining the effects of blade tip gaps encountered in turbomachines and the methods by which the synthesised data are currently used in turbomachinery design and performance analysis. ...
Villescas, Ivan J. (Monterey, California. Naval Postgraduate School, 2005-09);Investigating the effect of steam ingestion into an aircraft jet engine is necessary to improve understanding of stall and surge in transonic axial compressors. Specifically, to understand the "pop stall" phenomenon ...