Integrated Aircraft Power Converter for Motor and Thrust Reverser
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Solution Overview
Problem
Existing power conversion systems for aircraft turbofan engines are complex and heavy due to the need for converting electrical power between direct-current (DC) and alternating-current (AC) systems, which is required for both electric motor operation and thrust reverser actuation.
Innovation Solution
A power converter system that includes an electric-motor interface and a thrust-reverser interface, each with an inverting power stage having both DC and AC sides, along with a DC electrical connector and circuitry that couples the DC bus to both power stages, allowing for efficient bidirectional power conversion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If separate power converters are used for electric motor and thrust reverser actuator, then each component can be optimized independently, but the overall system weight and complexity increases
Solution Approach 1:
The patent combines separate power conversion systems for the electric motor and thrust reverser actuator into a single integrated power converter. This integration shares common components including the DC link, control electronics, and housing structure, thereby reducing total system weight while maintaining independent optimization capabilities for each load through separate AC output stages.
2Reliability
If complex AC/DC power conversion is used for both motor and actuator, then reliable power supply is ensured, but system complexity and weight increase
Solution Approach 1:
The integrated power converter employs a universal DC link and control architecture that serves both the electric motor and thrust reverser actuator. The single DC bus provides stable voltage regulation for both AC output stages, ensuring reliable power supply while reducing overall system complexity through shared infrastructure and centralized control.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The proposed power converter system reduces weight and complexity by integrating power conversion stages for both electric motors and thrust reversers within a single housing, enabling efficient AC/DC conversion and supporting both motoring and generating modes of operation.
Implementation Method 1
converting electrical power between the DC current of such a DC bus, and the alternating current required by and/or generated by an AC electric motor
Implementation Method 2
an electric motor configured to be mechanically coupled to a driveshaft of the fan engine
Implementation Method 3
an electric actuator of the fan engine for actuating a thrust reverser surface of the fan engine
Data Source
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AI summary
A power converter (300) for use with a fan engine (101) of an aircraft (100) comprises an electric-motor interface (309, 319) for electrical connection to an electric motor (102a, 103a) configured to be mechanically coupled to a driveshaft of the fan engine (101). It comprises an inverting electric-motor power stage (302, 312), having a DC side and an AC side, wherein the AC side of the electric-motor power stage is electrically coupled to the electric-motor interface (309, 319). It comprises a thrust-reverser interface (329a, 329b) for electrical connection to an electric actuator of the fan engine (101) for actuating a thrust reverser surface (106, 107) of the fan engine, and an inverting thrust-reverser power stage (322a, 322b), having a DC side and an AC side, wherein the AC side of the thrust-reverser power stage is electrically coupled to the thrust-reverser interface (329a, 329b). It comprises a DC electrical connector (308) comprising a positive voltage terminal and a negative voltage terminal for electrical connection to a DC bus (110) of the aircraft (100); and circuitry (303, 304) that electrically couples the positive and negative voltage terminals of the DC electrical connector (308) to the DC side of the electric-motor power stage (302, 312) and to the DC side of the thrust-reverser power stage (322a, 322b).