Hybrid Electric Engine Braking for Aircraft Taxi Thrust Control
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Solution Overview
Problem
Gas turbine engines are inefficient at low power settings, leading to excess fuel consumption and brake wear during taxi and landing operations due to excess thrust.
Innovation Solution
A hybrid electric propulsion system with a low-spool generator and high-spool electric motor, controlled by a controller, transfers power between spools to manage thrust and reduce brake wear by using energy storage during braking conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the gas turbine engine operates at idle thrust setting, then the aircraft can maintain basic propulsion for ground operations, but fuel consumption increases and brake wear deteriorates due to excess thrust
Solution Approach 1:
The patent replaces the traditional mechanical brake system with an electric motor system to control aircraft deceleration during ground operations. The electric motor can operate in regenerative braking mode to capture kinetic energy and in motor mode to provide precise thrust control, eliminating the need for mechanical brakes and reducing both fuel consumption and brake wear.
Solution Approach 2:
The system dynamically adjusts the operating parameters of the gas turbine engine by using the electric motor to supplement or reduce thrust as needed. This allows the engine to operate at more efficient power settings while the electric motor makes up the difference, thereby reducing overall fuel consumption during taxi and ground operations.
2Productivity
If the gas turbine engine operates at idle thrust setting, then the aircraft can maintain basic propulsion for ground operations, but brake wear increases due to repeated taxi and landing cycles
Solution Approach 1:
The patent replaces the traditional mechanical brake system with an electric motor system to control aircraft deceleration during ground operations. The electric motor can operate in regenerative braking mode to capture kinetic energy and in motor mode to provide precise thrust control, eliminating the need for mechanical brakes and reducing both fuel consumption and brake wear.
Solution Approach 2:
The system uses the electric motor to provide self-service braking functionality, where the motor itself performs the deceleration task that would otherwise require separate mechanical brake components. This integrates the braking function into the propulsion system, reducing wear on dedicated brake components.
3Reliability
If the low-spool generator extracts energy from the low spool during braking, then brake wear is reduced, but the rotational speed of the low spool must be reduced which may affect engine operation
Solution Approach 1:
The controller acts as an intermediary that coordinates between the low-spool generator energy extraction and the high-spool electric motor power delivery. It manages the transition of power flow to ensure that as the low spool speed decreases during regenerative braking, the high spool and its associated accessories receive adequate power to maintain proper engine operation.
Solution Approach 2:
The patent replaces the traditional mechanical brake system with an electric motor system to control aircraft deceleration during ground operations. The electric motor can operate in regenerative braking mode to capture kinetic energy and in motor mode to provide precise thrust control, eliminating the need for mechanical brakes and reducing both fuel consumption and brake wear.
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
Reduces brake wear and fuel consumption by optimizing power distribution between spools, maintaining engine combustion, and stabilizing engine operation during braking.
Implementation Method 1
a low-spool generator operably coupled to the low spool
Implementation Method 2
a high-spool electric motor operably coupled to the high spool
Implementation Method 3
a controller configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to an energy storage system
Implementation Method 4
transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine
Data Source
AI summary
An engine system of an aircraft includes an energy storage system, a gas turbine engine, and a controller. The gas turbine engine includes a low spool, a high spool, a low-spool generator operably coupled to the low spool, and a high-spool electric motor operably coupled to the high spool. The controller is configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to the energy storage system based on the storage capacity state of the energy storage system, and transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine while a rotational speed of the low spool is reduced responsive to the low-spool generator extracting energy from the low spool.