HYBRID AIRCRAFT PROPULSION SYSTEM
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Applicant
Rolls-Royce plc
Representative
Rolls-Royce plc
Application number
EP19171413A1
Kind
A1
Document number
3569498
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HYBRID AIRCRAFT PROPULSION SYSTEM

3569498 - EP19171413A1 - EPO

Application Apr 26, 2019 - Publication Nov 20, 2019

David Scothern

Abstract

A hybrid aircraft propulsion system. The sytem comprises a gas turbine engine (5) comprising a compressor (11), a combustor (12), one or more turbines (13), a shaft (14) coupled to one of the turbines (13), and a bypass fan (10) mechanically driven by the shaft (14). The system further comprises an electrical generator (15) mechanically coupled to the shaft (14), and an auxiliary propulsor (6) mechanically coupled to an electric motor (16) and electrically coupled to the electric generator (15). At maximum power, the gas turbine engine (5) is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.

Description

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