The aim of this investigation was to perform a parametric computational study of the blockerless engine thrust reverser system concept. Early experimental investigations had revealed that injection flow rates of the order of 3% of the fan flow were needed to divert the entire fan flow out through the cascade opening. For a high bypass ratio engine, this amount was too much to be bled from the compressor. This study performs a more detailed evaluation of the concept and covers cases that could not be tested during the experimental investigation due to the limitations of experimental facility. A numerical model simulating the experimental setup was constructed, and effects of various design parameters such as injection location, injection angle, injection thickness, cascade opening, and operational parameters such as fan flow and injection flow rates were studied using trajectory-based analysis. The results suggest that the injection location and injection angle have a profound effect on the performance, and injection flow rates of less than 1.5% could easily divert the entire fan flow through the cascade opening by optimizing parameters of interest.
Optimization of Blockerless Engine Thrust Reverser
Journal of propulsion and power ; 33 , 1
2017
Article (Journal)
English
Optimization of Blockerless Engine Thrust Reverser
Online Contents | 2016
|Aircraft engine thrust reverser
Emerald Group Publishing | 1998
Optimization of Blockerless Engine Thrust Reverser
AIAA | 2016
|