Hybrid-Electric Engine Noise Control via Rotational Force Ratio
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Solution Overview
Problem
Aircraft gas turbine engines generate significant noise during takeoff and landing, posing challenges for noise regulation compliance without compromising propulsion capabilities.
Innovation Solution
A hybrid-electric gas turbine engine system that adjusts the rotational force ratio between electric and thermal forces as altitude increases, maintaining a constant total rotational force while reducing noise, and optionally adjusts propeller blade pitch to control noise emission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If gas turbine engine power is reduced during takeoff and landing operations, then aircraft noise is reduced, but propulsive capability is compromised
Solution Approach 1:
The patent combines a gas turbine engine with an electric motor to create a hybrid-electric propulsion system. The electric motor assists the gas turbine engine during takeoff and landing operations, enabling noise reduction by lowering gas turbine power output while maintaining sufficient total propulsive capability through the electric motor's contribution.
Solution Approach 2:
The system dynamically adjusts the operational parameters of the gas turbine engine, specifically reducing its power output during noise-sensitive flight phases (takeoff and landing). This parameter change is compensated by increasing electric motor output, thereby reducing overall noise emission while preserving required propulsive performance.
2Object-affected harmful factors
If electric motor assists gas turbine engine during takeoff, then noise is reduced, but device complexity increases
Solution Approach 1:
The electric motor serves multiple functions: it assists the gas turbine engine during takeoff and landing to reduce noise, provides backup propulsion capability, and can operate independently in certain flight conditions. This multi-functionality justifies the added system complexity by delivering multiple benefits from a single component addition.
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
Effectively reduces aircraft noise during takeoff and landing while maintaining sufficient propulsion capabilities, adhering to noise regulations and ensuring operational safety and performance.
Implementation Method 1
an electric motor configured to apply an electric rotational force to the shaft
Implementation Method 2
a turbine configured to apply a thermal rotational force to the shaft
Data Source
Figure 1
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Figure 4
AI summary
A method (500) for controlling noise emitted by a hybrid-electric gas turbine engine for an aircraft during a takeoff flight condition includes applying a first total rotational force to a shaft that includes a first electric rotational force applied by the electric motor and a first thermal rotational force applied by the turbine. The first total rotational force has a first rotational force ratio of the first electric rotational force to the first thermal rotational force. The method further includes controlling the noise emitted by the gas turbine engine by reducing the first rotational force ratio from an initial rotational force ratio as an altitude of the aircraft increases while maintaining the first total rotational force substantially constant.