Shape Changing Airfoil

TITLE AND SUBTITLE:
Shape Changing Airfoil

AUTHOR(S):
Eric A. Ott

REPORT DATE:
October 2005

FUNDING NUMBERS:
WBS-22-714-92-50
NAS3-01135
Work element 3.2, Task order 23

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
General Electric Aircraft Engines
One Neumann Way
Cincinnati, Ohio 45215-1915

PERFORMING ORGANIZATION REPORT NUMBER:
E-15289

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Final Contractor Report-July 2, 2003-May 30, 2004

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA CR-2005-213971

SUPPLEMENTARY NOTES:
Project Manager, Clayton L. Meyers, Aeronautics Division, NASA Glenn Research Center, organization code PRV, 216-433-3882.

ABSTRACT:
Scoping of shape changing airfoil concepts including both aerodynamic analysis and materials-related technology assessment effort was performed. Three general categories of potential components were considered--fan blades, booster and compressor blades, and stator airfoils. Based on perceived contributions to improving engine efficiency, the fan blade was chosen as the primary application for a more detailed assessment. A high-level aerodynamic assessment using a GE90-90B Block 4 engine cycle and fan blade geometry indicates that blade camber changes of approximately ±4° would be sufficient to result in fan efficiency improvements nearing 1 percent. Constraints related to flight safety and failed mode operation suggest that use of the baseline blade shape with actuation to the optimum cruise condition during a portion of the cycle would be likely required. Application of these conditions to the QAT fan blade and engine cycle was estimated to result in an overall fan efficiency gain of 0.4 percent.

SUBJECT TERMS:
Propulsion systems (aircraft)

NUMBER OF PAGES:
50

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