Publication Date:
2019-07-12
Description:
Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors.
Keywords:
Aircraft Design, Testing and Performance
Type:
NACA-RM-SE58E26
Format:
application/pdf
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