Method and unit for controlling a motor assembly

EP4493808A1Pending Publication Date: 2025-01-22SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
EP2023714799
Authority / Receiving Office
EP · EP
Patent Type
Applications
Current Assignee / Owner
Priority Date
2022-03-15
Filing Date
2023-03-14
Publication Date
2025-01-22

AI Technical Summary

Technical Problem

Gas turbine engines in aircraft face operational constraints that can lead to inefficiencies and overheating, particularly during acceleration and idling phases, due to the need to balance mechanical and electrical power demands, which existing methods struggle to manage effectively.

Method used

A method and control unit system that dynamically adjust the mechanical power draw by electric machines coupled to the gas turbine engine's shafts based on predetermined operating parameters such as temperature and fuel flow rates, allowing for adaptive power management to prevent overheating and maintain propulsive power without exceeding engine limits.

Benefits of technology

This approach enables efficient operation by preventing overheating and maintaining propulsive power during high-speed phases and idling, while optimizing fuel usage and electrical generation, thus enhancing the overall performance and reliability of the aircraft engine assembly.

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Abstract

The present invention relates to a method for controlling a motor assembly (100). The motor assembly (100) comprises a gas turbine engine (200) and at least one electric machine (300, 400) which is mechanically coupled to a rotating shaft (210, 220) of the gas turbine engine (200) so as to be rotated for generating electricity. In this control method, a mechanical power take-off setpoint by the electric machine (300, 400) is changed when an operating parameter of the gas turbine engine (200) reaches a predetermined limit. The invention also relates to a control unit (500) adapted to perform this method, a motor assembly (100) incorporating this control unit (100), the electric machine (300, 400) and the gas turbine engine (200), and a computer program for performing this method.
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