Aircraft Turbine Engine Reactivation Timing for Standby Exit
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Solution Overview
Problem
Existing methods for exiting a standby mode in aircraft turbine engines do not provide adaptive management tailored to specific flight conditions, potentially causing damage and safety risks due to inconsistent reactivation durations.
Innovation Solution
A method for managing the exit from standby mode in aircraft turbine engines, involving normal, accelerated, and rapid reactivation steps tailored to different conditions, with durations ranging from 1 to 15 seconds, using an electric assist machine and fuel flow rate laws to balance engine power and maintain flight safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a conventional restart or rapid restart is used to exit standby mode, then the engine can be reactivated quickly, but the engine may suffer damage due to insufficient thermal stabilization
Solution Approach 1:
The patent implements dynamic reactivation management by adjusting the reactivation duration based on real-time engine parameters and flight conditions. The system transitions from static fixed-duration restart procedures to dynamic adaptive restart procedures that modify parameters such as fuel flow rate, air intake, and reactivation duration according to the engine's thermal state and operational requirements, thereby resolving the contradiction between fast reactivation and engine protection
Solution Approach 2:
The patent changes physical parameters including fuel flow rate, air intake volume, and reactivation duration based on engine temperature and flight conditions. By dynamically adjusting these parameters, the system optimizes the balance between reactivation speed and engine component protection, avoiding both insufficient stabilization and excessive damage
2Reliability
If a long reactivation duration is used, then the engine is better protected from damage, but the aircraft loses time and productivity
Solution Approach 1:
The system dynamically determines reactivation duration based on real-time conditions rather than using fixed conservative timelines. By continuously monitoring engine parameters and flight context, the system adjusts the reactivation duration to the minimum necessary time for safe operation, thereby maximizing flight productivity while maintaining engine protection
Solution Approach 2:
The engine management system autonomously monitors its own thermal state and automatically determines the appropriate reactivation duration without requiring conservative external constraints. The system uses self-diagnosis of engine temperature and operational state to optimize reactivation timing, eliminating the need for overly cautious fixed-duration protocols
3Loss of energy
If the engine is kept in standby mode for extended periods, then fuel consumption is reduced, but the engine may require more aggressive reactivation procedures
Solution Approach 1:
The patent implements continuous feedback monitoring of engine parameters during standby mode and reactivation. The system tracks thermal state, rotational speed, and other critical parameters to determine the optimal reactivation strategy. This feedback mechanism allows the system to adapt reactivation procedures based on the actual engine state, preventing both unnecessary fuel consumption and reactivation damage
Solution Approach 2:
The system performs preliminary thermal stabilization and parameter adjustment during the transition from standby to operational mode. By preparing the engine in advance with gradual heating and controlled parameter changes before full power activation, the system reduces the need for aggressive reactivation procedures while maintaining fuel efficiency during standby periods
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
Maximizes benefits by minimizing turbine engine damage while ensuring safe and efficient reactivation based on specific conditions, optimizing reactivation times to match operational needs.
Implementation Method 1
comprises a step of assisting the second turbine engine by an electric machine of the aircraft
Implementation Method 2
implementing a fuel flow rate law making a reactivation time of between 1 and 3 minutes possible
Data Source
AI summary
This method for managing the exiting of a specific-consumption mode of an aircraft comprises a step of identifying a need to reactivate a turbine engine in the nominal mode of said turbine engine, and a step of: —normal reactivation of the turbine engine in the nominal mode for the turbine engine for a first duration when a first condition is met; —accelerated reactivation of the turbine engine in the nominal mode for the turbine engine for a second duration when a second condition is met; —rapid reactivation of the turbine engine in the nominal mode of the turbine engine for a third duration when a third condition is met, the first duration being longer than the second duration, and the second duration being longer than the third duration.