Patent ID: 7690595
Filing Date: 2010-04-06
Classification: B64D,Y10T

Abstract:
1. A system for manipulating airflow for a high speed aircraft engine, comprising: a non-axi-symmetric, mixed compression inlet for a bulk airflow stream having a forward supersonic diffuser that receives a bulk airflow stream and transitions rearwardly through a minimum area throat region into a subsonic diffuser to provide subsonic airflow to a high speed aircraft engine; a scoop having a small air intake located inside the supersonic diffuser of the mixed compression inlet and positioned in a region prone to generate low pressure airflow as a component of the bulk airflow stream, the scoop capturing and removing the low pressure airflow from the bulk airflow stream; wherein the air intake of the scoop is located in the throat region rearwardly of where the supersonic diffuser first completely surrounds and confines the bulk airflow stream; and wherein the mixed compression inlet comprises a geometry that includes at least one corner defined by an upper wall and a lower wall that are joined at the corner, and the scoop is located in the corner and is defined by the side wall, which joins the upper and lower walls at a point laterally inboard from the corner relative to the bulk airflow stream.