Aircraft engine power management for large generator loads
AssigneeHoneywell International Inc.
InventorSteve Ackerman
Life of this patent
Estimating the term…
Abstract
A method and system for managing increases in electrical loads in an aircraft engine has been developed. First, demand for an increased electrical load for an electrical generator of the aircraft engine is detected. Notification of the demand for the increased electrical load is transmitted to the aircraft engine full authority digital engine control system (FADEC). The FADEC calculates the necessary power management adjustments to maintain aircraft engine turbine temperature and adjustments to the compressor variable vane and surge bleed valve schedules. The FADEC then commands the adjustment in the aircraft engine power setting parameter, compressor variable vane position, and surge bleed valve position.
Claims19
A method for managing increases in electrical loads in an aircraft engine, comprising:
- detecting a demand for an increased electrical load for an electrical generator of the aircraft engine;
- transmitting notification of the demand for the increased electrical load to an aircraft engine full authority digital engine control system (FADEC);
- calculating any necessary adjustments to power management, compressor variable vanes, and surge bleed valve position of the aircraft engine in order to maintain a desired turbine temperature and avoid compressor surge;
- implementing necessary adjustments to the power management by referencing a fan speed schedule versus air temperature and altitude and making an engine fan speed adjustment for the increased electrical load by referencing a schedule of percentage delta of fan speed versus the generator load and altitude of the aircraft;
- and
- implementing necessary adjustments to the compressor variable vanes and surge bleed valve scheduling.
A system for managing increases in electrical loads in an aircraft engine, comprising:
- an electrical generator coupled to the aircraft engine and operable to generate electric power for electrical applications onboard the aircraft;
- an aircraft engine full authority digital engine control (FADEC);
- and
- an electrical power management system for the aircraft in operable communication with the electrical generator and the aircraft engine FADEC, the aircraft electrical power management system is configured to:
- (i) detect a demand for an increased electrical load for the electrical generator, and (ii) transmit notification of the demand for increased electrical load to the aircraft engine FADEC,
- wherein the aircraft engine FADEC is configured to:
- (1) determine necessary power management adjustments for the increase in electrical load to maintain aircraft engine turbine temperature, and (ii) implement necessary adjustments to the power management by referencing a fan speed schedule versus air temperature and altitude and making an engine fan speed adjustment for the increased electrical load by referencing a schedule of percentage delta of fan speed versus the generator load and altitude of the aircraft.
(canceled)
Dependencies are inferred from the claim text.