Accession Number : ADA515419


Title :   Aero-Mechanical Coupling in a High-Speed Compressor


Descriptive Note : Final technical rept. 1 Jan 2007-30 Nov 2009


Corporate Author : NOTRE DAME UNIV IN DEPT OF AEROSPACE AND MECHANICAL ENGINEERING


Personal Author(s) : Morris, Scott C ; Corke, Thomas C


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a515419.pdf


Report Date : Feb 2010


Pagination or Media Count : 97


Abstract : This report describes the results of several studies which sought to improve the understanding of coupling between the fluid and structures which are common in modern, high-speed axial compressors. There were two major areas of focus. The first was the development of measurement technique specifically for the study of these phenomena, termed Blade Image Velocimetry (BIV). The technique can measure fluid and structural velocity fields simultaneously and a demonstration of the utility of these measurements is provided for a flat plate undergoing flutter. The theory of the technique is presented with an empirically validated analysis of measurement error. The results of the application of BIV to a high-speed axial compressor are also presented. The second area of focus was the investigation of an isolated compressor blade in a high Mach number flow. The steady vibration amplitude, aerodynamic damping and impulse response were investigated. A complex interdependence was observed for these quantities for variations in flow conditions and blade structural properties.


Descriptors :   *AXIAL FLOW COMPRESSORS , *COMPRESSOR BLADES , MEASUREMENT , VIBRATION , VALIDATION , DEMONSTRATIONS , FLUTTER SIMULATORS , THEORY , DAMPING , FLUIDS , FLAT PLATE MODELS , STEADY STATE , VELOCITY , STRUCTURAL PROPERTIES


Subject Categories : Hydraulic and Pneumatic Equipment
      Test Facilities, Equipment and Methods


Distribution Statement : APPROVED FOR PUBLIC RELEASE