Abstract
The General Electric CF6-50 engine nacelle was originally equipped with both fan nozzle and core nozzle thrust reversers. Many airline operators later deactivated the core reverser. Elimination of the core reverser enabled design changes to be made to help improve performance. A reduction in core nozzle length of approximately 2 ft was possible. This concept, defined as the short core exhaust nozzle, was evaluated in engine ground tests, including performance, acoustic, and endurance tests under the NASA Lewis Engine Component Improvement Program. The test results verified the performance predictions from scale model tests. The short core exhaust nozzle provides an internal cruise SFC reduction of 0.9% without an increase in engine noise. The nozzle hardware successfully completed 1000 flight cycles of endurance testing with no signs of distress.
Published Version
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