Daniel J. Lahti - Cincinnati OH James L. Younghans - Cincinnati OH
Assignee:
General Electric Company - Cincinnati OH
International Classification:
B64D 2900
US Classification:
244130
Abstract:
An improved nacelle is provided for housing an aircraft engine and reducing aerodynamic drag during aircraft operation. In one embodiment, the nacelle houses a gas turbine engine and comprises a leading edge and a trailing edge, having a reference chord extending therebetween, and an outer surface which is continuous from the leading edge to the trailing edge. The outer surface includes a forward portion, an intermediate portion and an aft portion that has a profile defined by a varying thickness measured perpendicularly from the chord to the outer surface. The profile has a maximum thickness at the intersection of the forward and intermediate portions, which intersection is located greater than about 36% of the chord from the leading edge, and is effective for increasing laminar flow over the nacelle for reducing aerodynamic drag.
Curved Centerline Air Intake For A Gas Turbine Engine
William C. Ruehr - Cincinnati OH James L. Younghans - Cincinnati OH Edwin B. Smith - Mason OH
Assignee:
The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC
International Classification:
B64D 3302
US Classification:
137 151
Abstract:
An inlet for a gas turbine engine is disposed about a curved centerline for the purpose of accepting intake air that is flowing at an angle to engine centerline and progressively turning that intake airflow along a curved path into alignment with the engine. This curved inlet is intended for use in under-the-wing locations and similar regions where airflow direction is altered by aerodynamic characteristics of the airplane. By curving the inlet, aerodynamic loss and acoustic generation and emission are decreased.