Intermittent Combustion Aircraft Propulsion With Variable-Speed Rotors
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Solution Overview
Problem
There is a need for more cost-effective and fuel-efficient propulsion system configurations for aircraft, particularly business jets, which operate at high altitudes and fast speeds.
Innovation Solution
A propulsion system for aircraft utilizing an intermittent combustion engine with a remote powerplant configuration, including a turbo-compounded or turbocharged intermittent combustion engine housed within the aircraft fuselage, coupled to ducted or open rotors through variable speed transmissions and drivetrains, which facilitate rotation of propulsor rotors at varying speeds and directions, optimizing thrust and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If small gas turbine engines are used for high altitude and fast speed flight, then aircraft propulsion capability is improved, but manufacturing and servicing costs increase
Solution Approach 1:
The patent applies this principle by using a reciprocating engine with piston cylinders that can be more easily manufactured and serviced compared to gas turbine engines. The simpler mechanical components allow for lower manufacturing costs and easier maintenance, directly addressing the cost issue while maintaining propulsion capability for high-speed flight
2Speed
If small gas turbine engines are used for high altitude flight, then aircraft propulsion capability is improved, but fuel efficiency deteriorates
Solution Approach 1:
The patent employs parameter changes by utilizing a reciprocating engine with variable valve timing and compression ratios that can be optimized for different flight conditions. The engine can adjust its operating parameters to maintain fuel efficiency across a range of altitudes and speeds, unlike fixed-parameter gas turbine engines
3Adaptability or versatility
If variable speed transmissions are used to facilitate rotation of propulsor rotors at varying speeds, then adaptability is improved, but device complexity increases
Solution Approach 1:
The patent applies dynamics by using variable speed transmissions that allow the propulsor rotors to rotate at different speeds independent of the engine crankshaft speed. This enables the system to adapt thrust output to varying flight conditions while managing complexity through controlled variability rather than complete system redesign
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 system reduces manufacturing and servicing costs, enhances fuel efficiency, and allows for adjustable thrust without significant changes in powerplant rotational speed, improving aircraft performance at high altitudes and speeds.
Implementation Method 1
Aircraft propulsion systems may include an intermittent combustion engine (ICE)
Implementation Method 2
The aircraft powerplant may be configured as a turbo-compounded intermittent combustion engine
Data Source
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AI summary
An aircraft system is provided that includes a first propulsor rotor (42A), a first transmission (106A), a second propulsor rotor (42B), a second transmission (106B) and an intermittent combustion engine (68). The first propulsor rotor (42A) is rotatable about a first propulsor axis (48A). The first transmission (106A) is coupled to the first propulsor rotor (42A). The second propulsor rotor (44) is rotatable about a second propulsor axis (48B). The second transmission (106B) is coupled to the second propulsor rotor (44). The intermittent combustion engine (68) is configured to drive rotation of the first propulsor rotor (42) through the first transmission (106A). The intermittent combustion engine (68) is configured to drive rotation of the second propulsor rotor (44) through the second transmission (106B).