Improved propulsion device for multi-engine hybrid aircraft

By designing propulsion components with gas generators and free turbines in dual-engine aircraft and leveraging the transmission of electricity between high and low power motors, the problems of engine start redundancy and power consumption optimization in standby mode are solved, achieving efficient engine performance optimization and power supply.

CN119677943APending Publication Date: 2025-03-21SAFRAN HELICOPTER ENGINES
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Patent Information

Application Number
CN202380059280.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Priority Date
2022-07-27
Filing Date
2023-06-22
Publication Date
2025-03-21

AI Technical Summary

Technical Problem

The prior art is difficult to provide redundancy for starting the engine in standby mode in dual-engine or multi-engine aircraft and limits optimization of engine power consumption.

Method used

A propulsion assembly is designed, including at least one first engine and a second engine, each of which has a gas generator and a free turbine. The main rotor is coupled to the free turbine of the engine, the engine is equipped with a first motor and a second motor, the first motor may be coupled to the gas generator or the free turbine during the starting stage and generate electrical energy from the free turbine after the starting stage.

Benefits of technology

With this architecture, power can be provided while limiting the impact of engine efficiency, and unit consumption can be optimized in SEO mode, improving the engine's starting reliability in standby mode, and reducing equipment quality.

✦ Generated by Eureka AI based on patent content.
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Abstract

A propulsion assembly (100) for a hybrid aircraft, comprising: first and second engines (1, 2), each having a gas generator (12, 22) and a free turbine (11, 21); a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric motor (30, 40) and a second electric motor (32, 42) lower in power than the first electric motor, one of the electric motors being coupled to the gas generator (12, 22) to rotate the gas generator during a start-up phase and to the free turbine (11, 21) after the start-up phase to generate electrical energy, the other of the electric motors is coupled only to the gas generator (12, 22), and at least one of the first or second electric motors of the first and / or second engines (1, 2) can transmit electrical energy to the other.
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