Aircraft Emergency Power System Low Pressure Spool Generator
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Solution Overview
Problem
Aircrafts face power shortages during emergencies when all thrust-producing gas turbine engines and auxiliary power units fail, as existing emergency power systems often become overloaded and stall, failing to provide sufficient power for critical systems.
Innovation Solution
An emergency power system that includes multiple power sources such as emergency motor-generators connected to low-pressure spools, ram air turbines, flywheels, batteries, and fuel cells, with a controller to prioritize and manage power distribution to ensure critical loads are powered without overloading mechanical power sources.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the emergency power system is configured to power multiple hydraulic and/or electric loads during an emergency, then the power coverage is improved, but the emergency power system becomes overloaded and stalls
Solution Approach 1:
The patent segments the emergency power system into multiple independent emergency power sources (first emergency power source connected to high-pressure spool, second emergency power source connected to low-pressure spool). Each power source can independently supply power to different loads, preventing any single source from becoming overloaded while maintaining comprehensive power coverage across multiple hydraulic and electric loads.
2Device complexity
If a single emergency power source is used, then the system complexity is reduced, but the power capacity is insufficient to power all loads
Solution Approach 1:
The patent merges multiple emergency power sources (first and second emergency power sources) into a unified emergency power system. The first emergency power source is coupled to the high-pressure spool and the second emergency power source is coupled to the low-pressure spool, allowing their power capacities to combine and sufficiently power all hydraulic and electric loads during emergency conditions.
3Power
If the emergency power system is designed with multiple power sources, then the power capacity is improved, but the system complexity increases
Solution Approach 1:
The patent implements preliminary action through the controller that automatically monitors the operational status of gas turbine engines and pre-configures the emergency power system. When an emergency condition is detected, the controller automatically activates the appropriate emergency power source and configures load distribution, eliminating the need for complex manual intervention and reducing operational complexity despite having multiple power sources.
4Power
If the emergency power system is configured to provide full power to all loads, then the power availability is improved, but the mechanical power sources become overloaded and stall
Solution Approach 1:
The patent implements feedback control through the controller that continuously monitors the operational status of gas turbine engines and the performance of emergency power sources. The controller uses this feedback to dynamically adjust power distribution, ensuring that the emergency power sources operate within their capacity limits and do not cause the spools to slow down or stall, while still providing sufficient power to all necessary loads.
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 effectively provides power to essential electrical and hydraulic loads during emergencies by prioritizing energy distribution, preventing mechanical power source overload and ensuring continued operation of critical aircraft systems.
Implementation Method 1
An emergency power system for an aircraft that includes a mechanical power source, an emergency generator, and a controller. The mechanical power source can include a low pressure spool... the emergency generator... to provide emergency electrical power
Implementation Method 2
Some aircrafts are prepared for such emergencies by incorporating emergency power systems. These emergency power systems have one or more emergency power sources, such as a ram air turbine (RAT), to provide emergency power.
Implementation Method 3
An emergency power system that includes multiple power sources such as emergency motor-generators connected to low-pressure spools, ram air turbines, flywheels, batteries, and fuel cells
Implementation Method 4
An emergency power system that includes multiple power sources such as emergency motor-generators connected to low-pressure spools, ram air turbines, flywheels, batteries, and fuel cells
Implementation Method 5
An emergency power system that includes multiple power sources such as emergency motor-generators connected to low-pressure spools, ram air turbines, flywheels, batteries, and fuel cells
Data Source
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AI summary
An emergency power system (54) is useable on an aircraft having a gas turbine engine (10) with a low pressure spool (20) and a high pressure spool (28). The emergency power system (54) includes an emergency electrical generator (48) coupled to the low pressure spool (20) during an emergency for generating emergency electrical power and one or more additional electrical power sources (48A,66,70,72,74). A plurality of electrical loads (78,78A) are electrically connected to the emergency electrical generator (48) and the one or more additional electrical power sources (48A,66,70,72,74). Aircraft sensors (96A-96G) provide data regarding emergency electrical power availability and emergency electrical power demand. A controller (94) for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors (96A-96G). The controller (94) controls the emergency electrical generator (48) based upon the emergency electrical power demand and the emergency electrical power availability.