Gas turbine engine with axial flow fan with twin stream impeller and variable area bypass nozzle
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United States of America Patent
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Mar 27, 2018
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app pub date -
May 17, 2017
filing date -
Feb 11, 2017
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Abstract
A gas turbine engine for a small aircraft such as a UAV having a bypass flow with a variable area bypass nozzle located at an outlet of the bypass channel, the nozzle having one position with a maximum flow area and a second position with a minimal flow area. The compressor is a twin stream compressor with an inner flow path for compressed air to the combustor and an outer flow path for the bypass channel. A fan stage can be used in front of the compressor.
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