The rotor wake/vortex flowfield generated in a scale model simulator of General Electric's counter-rotating unducted fan (UDF) engine was investigated using three-dimensional hot-wire anemometry. The purpose was to obtain a set of benchmark experimental aerodynamic data defining the rotor wake and vortex structure, particularly in the tip region, and to relate this observed flow structure to its acoustic signature. The tests were conducted in a large, freejet anechoic chamber. Measurements of the three components of velocity were made at axial stations upstream and downstream of each rotor for conditions that simulate takeoff, cutback, and approach power. Two different forward blade designs were evaluated. The tip vortices, the axial velocity defect in the vortex core, and differences in the interaction of the wakes and vorticies generated by the forward and aft rotor are used to explain differences in noise generated by the two different rotor designs. Part 1 presents the three-dimensional flowfield measurements. Part 2 (aeroacoustic prediction and analysis), which will be presented later, will give an acoustic prediction using the measured data.
Rotor-rotor interaction for counter-rotating fans, part 1: Three-dimensional flowfield measurements
Rotor-Rotor Interaktion für Gegenstromfantriebwerke. 1. Teil: Messung des dreidimensionalen Strömungsfeldes
AIAA Journal ; 32 , 11 ; 2224-2233
1994
10 Seiten, 13 Bilder, 13 Quellen
Aufsatz (Zeitschrift)
Englisch
Rotor-Rotor Interaction for Counter-Rotating Fans, Part 1: Three-Dimensional Flowfield Measurements
Online Contents | 1994
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