Nacelle inlet for an aircraft gas turbine engine
AssigneeGeneral Electric Company
InventorsNorbert O. Stockman, David E. Yates, Timothy S. Crum
Life of this patent
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Abstract
A nacelle inlet for channeling airflow to a gas turbine engine having a longitudinal centerline axis includes an annular forward nacelle having a leading edge defining an inlet face for receiving the freestream airflow. A diffuser is disposed in flow communication with the inlet face, with the diffuser being defined about a droop axis inclined relative to the engine centerline axis. The forward nacelle includes a crown and a keel defining therebetween a scarf axis, with the keel extending axially forwardly of the crown so that the scarf axis forms an acute scarf angle greater than zero relative to a reference line perpendicular to the droop axis.
Claims13
A scroop nacelle inlet for channeling freestream airflow to a gas turbine engine having a longitudinal centerline axis comprising:
- an annular forward nacelle having a leading edge defining an inlet face for receiving said airflow and a diffuser disposed in flow communication with said inlet face, said diffuser being defined about a droop axis inclined relative to said engine centerline axis;
- and
- said forward nacelle having a radially upper crown including a portion of said leading edge and a radially lower keel including a portion of said leading edge, said keel leading edge portion and said crown leading edge portion defining therebetween a scarf axis, said keel leading edge portion extending axially forward of said crown leading edge portion so that said scarf axis forms an acute scarf angle greater than zero relative to a reference line perpendicular to said droop axis.
Dependencies are inferred from the claim text.