Gas Generator Power Unit for Aircraft Engine Failure
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Solution Overview
Problem
In aircraft engine failure scenarios, existing power regulation systems are insufficient to maintain acceptable flight conditions and non-propulsive energy requirements, particularly due to limitations in power generation and the need for APU restart, which adds workload and delays recovery.
Innovation Solution
A continuous, engine-class main power unit (GPP) is introduced to manage non-propulsive power generation, providing additional power through a gas generator architecture suitable for all flight phases, with emergency regimes to instantly address power demands and relieve operational engines, allowing increased altitude operation and efficient energy distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If APU is used to assist power generation in flight, then electrical power supply is improved, but restart time and operational complexity increase
Solution Approach 1:
The GPP is pre-positioned and pre-configured on the aircraft, ready for immediate deployment upon engine failure. Unlike APU which requires restart procedures, the GPP is already in place and can be activated instantly through control system signals, eliminating the 90-second restart delay
Solution Approach 2:
The invention extracts the power generation function from the traditional APU concept and implements it through a dedicated GPP unit specifically designed for flight-phase operation. The GPP is separated from ground-only power systems and integrated as a flight-critical component with direct aircraft bus connections
2Power
If APU is restarted during flight, then power generation capacity is improved, but pilot workload and monitoring requirements increase
Solution Approach 1:
The GPP system incorporates automatic self-monitoring and self-regulation capabilities through integrated control systems that continuously track operational parameters, power output, and system health. The control system automatically manages load distribution between GPP and remaining operational engines without requiring pilot intervention or monitoring
Solution Approach 2:
The system implements continuous feedback loops where control systems monitor GPP performance, power consumption patterns, and aircraft system demands. This feedback enables automatic adjustment of power output and load management, eliminating the need for pilot monitoring and manual adjustments
3Force
If engine(s) compensate for failure in OEI mode, then propulsion is maintained, but non-propulsive power generation becomes insufficient
Solution Approach 1:
The power generation system is segmented into distinct functional components: operational engines dedicated to propulsion, and the GPP unit dedicated to non-propulsive power generation. This segmentation allows each component to optimize its function without compromising the other, ensuring sufficient power for both propulsion and auxiliary systems in OEI mode
Solution Approach 2:
The GPP acts as an intermediary power source between the operational engines and the aircraft's non-propulsive power consumers. It mediates the power distribution by absorbing the load of auxiliary systems, thereby relieving the operational engines from excessive power demands and allowing them to maintain optimal propulsion performance
4Temperature
If APU provides electrical power only at high altitude, then pneumatic power is maintained, but energy distribution efficiency decreases
Solution Approach 1:
The GPP is designed as a universal power generation system capable of providing both pneumatic and electrical power across all flight phases and altitude ranges. Unlike APU which is optimized for ground operation with limited flight capability, the GPP delivers multi-functional power generation that adapts to varying altitude and power demand conditions, maintaining energy distribution efficiency throughout the flight envelope
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 GPP system ensures immediate and sustained power supply to maintain flight conditions, reduces pilot workload, and extends operational altitude by managing non-propulsive power effectively, even in single-engine failure scenarios, while optimizing energy use and facilitating preventive maintenance.
Implementation Method 1
A GPP comprises a gas generator
Implementation Method 2
After combustion, the hot compressed gases are expanded in the turbine which mechanically drives the compressor
Data Source
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AI summary
With a view to optimizing the resources needed to continue the flight upon the loss of at least one main engine, the invention seeks to unburden the propulsion system that has remained operative of all or some of the non-propulsive energy tappings through a continuously-operating additional generation of non-propulsive power. More specifically the method involves, using the power production unit GPP, constantly in operation during flight and taking over some (PGA) of the nominal total non-propulsive power (PTA) of the aircraft, to supply, almost instantaneously, increased non-propulsive powers (PSU, PMU, PIU) according to at least three respective emergency settings (RS, RM, RI) upon said engine failure. The GPP control and monitoring function assesses the time elapsed for each emergency setting (RS, RM, RI), and informs the data processing unit of this time with an alarm being emitted if the operating times (Xmax, Ymax, Zmax) allocated to each emergency setting (RS, RM, RI) are exceeded, and the emergency function adjusts the aircraft's non-propulsive power tappings between the main engines and the unit GPP either automatically or on the orders of the pilot.