Proposed aircraft configurations for the mid-to-late 1980's require thrust reverser designs which provide 4-8 % higher effectivity and are compatible with the streamlined nacelle envelopes proposed for these applications. In order to investigate these thrust reverser systems, a comprehensive data base is needed to refine pertinent design parameters. A parametric test program was conducted in the SLS thrust stand at Rohr Industries, Inc. to investigate various reverser cascade design changes. These tests were conducted on a two-dimensional, 35 % scale simulation of a 9.8 deg pie-shaped sector of the CF6 fan duct with the reverser in the full-deployed position. The program investigated the effect of blade profile, blade spacing and blade skew angle on reverser effectivity and flow coefficient; cascade entrance and exit flow streamline orientation; cascade exit total pressure profile; and internal pressure loading in the full-deployed position. All tests were conducted at static conditions and nozzle pressure ratio variations from 1.3 to 1.7. In addition to these parametric tests, a scale model of representative production CF6 cascade boxes were tested so that predictions could be made from model results for comparison with full-scale engine tests. These comparisons give credence to the design and prediction techniques established from the model tests. The CF6 model test predictions and full-scale results will be discussed in this paper.
Performance investigation of a fan thrust reverser for a high by-pass turbofan engine
Untersuchung der Leistung einer Blaeserschubumkehrvorrichtung fuer ein Mantelstromtriebwerk
AIAA-Papers ; 1-9
1984
9 Seiten, 23 Bilder, 3 Tabellen, 1 Quelle
Conference paper
English
New thrust reverser varies exhaust nozzle size - To optimize turbofan engine performance
Online Contents | 1995
Aircraft engine thrust reverser
Emerald Group Publishing | 1998