Patent ID: 7769503
Filing Date: 2010-08-03
Classification: F02C,F05D

Abstract:
1. In a computerized method of engine control of a turbojet engine of an aircraft during a descent of the aircraft, wherein a flight of the aircraft includes a plurality of time periods including a first time period being a portion of the flight commencing at takeoff and continuing until an initial cruising altitude is reached, a second time period being a portion of the flight during which the aircraft cruises at one or more cruising altitudes and continuing until an initial descent is commenced, a third time period having a duration and being during a portion of the flight commencing when the initial descent is commenced from a last cruising altitude of the one or more cruising altitudes and continuing until the aircraft reaches an altitude between approximately 9,000 and 11,000 feet, and a fourth time period being a portion of the flight for approaching a destination airport commencing when the aircraft descends from the altitude between approximately 9,000 and 11,000 feet and continuing until the aircraft lands, wherein engine pressure near the rear of the turbojet engine divided by engine pressure near the front of the turbojet engine determines an engine pressure ratio (EPR), and wherein the aircraft includes an engine-pressure-ratio-control computer system, an improvement comprising: