The Unsteady Response of an Axial Flow Turbo-Machinery Rotor to Inlet Flow Distortions.
Abstract
Distorted inlet flow is a very realistic and prevalent problem in jet aircraft engines, and the consequences of subjecting the rotating blades of an axial flow fan or compressor to an inlet distortion are excessive radiated noise, blade vibration, and performance degradation. Therefore, it is important for the turbomachinery designer to be concerned with designs which minimize the unsteady response of turbomachines to such spatial inlet distortions. The study discussed in this report is a combination of experimental and analytical efforts which are directed toward obtaining information relating the influence of distortion characteristics and rotor design and operating variables such as solidity, stagger angle, rotor-stator spacing, and blade loading to the unsteady rotor response. The approach taken to measure the response of the rotor was to make detailed circumferential surveys of the time-mean flow field upstream and downstream of the rotor using five-hole prism type probes. This enabled the total pressure, static pressure, and the three components of velocity to be determined. These data were then Fourier analyzed to provide a method of quantifying the size of the distortion, thus permitting the attenuation of the distortion to be evaluated. A portion of the data obtained in this study was analyzed to determine the total pressure losses associated with a distorted inflow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 12, 1978
- Accession Number
- ADA084446
Entities
People
- L. C. Barr
Organizations
- Pennsylvania State University