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.

Abstract: A method and apparatus are disclosed for limiting ingestion of debris into the inlet of a gas turbine engine. The invention includes providing first means in communication with a source of fluid under pressure for introducing at least one jet of fluid at a point aft of the leading edge of a nacelle associated with the engine inlet. The first means are adapted to discharge the fluid jet away from the leading edge and in the aft direction to establish a low pressure region aft of the leading edge and in sufficient proximity to a second vortex formation region so as to draw airflows from the second region into the low pressure region and away from the engine inlet.