Gas Turbine Engine Start Sequence to Cut Battery Draw
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Solution Overview
Problem
Existing gas turbine systems consume significant battery power when starting and stopping engines on the ground, which reduces available power during flight, and are limited by the need for ground power units for starting and stopping.
Innovation Solution
A gas turbine system with a controller that selectively uses battery power for starting and stopping specific engines, switching to generator power after steady states are reached, and employs temperature-based motoring to reduce battery consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If battery power is used to start and stop all gas turbine engines on the ground, then engine starting and stopping can be performed, but battery electricity consumption increases significantly
Solution Approach 1:
The patent divides the gas turbine engines into a first engine and a second engine, and segments the starting process into two stages: first starting the first engine using battery power, then using the first engine's generator to power the second engine's starter. This segmentation reduces battery consumption while maintaining the ability to start multiple engines.
Solution Approach 2:
The patent performs preliminary action by starting the first engine before the second engine, and using the first engine's generator to provide power for the second engine's starting. This preliminary setup allows the system to reduce battery dependency for subsequent engine starting operations.
2Ease of operation
If battery power is used for engine starting and stopping, then ground operations can be performed, but available battery power during flight is reduced
Solution Approach 1:
The patent segments the power supply responsibility: battery power is used only for the first engine's starting, while the second engine's starting is powered by the first engine's generator. This segmentation preserves battery power for flight operations while enabling ground starting operations.
Solution Approach 2:
The first engine, once started, serves itself by generating power that is then used to start the second engine. This self-service mechanism reduces the need for continuous battery power consumption during ground operations, preserving battery capacity for flight.
3Use of energy by moving object
If ground power units are used for engine starting and stopping, then battery consumption is reduced, but system complexity and ground infrastructure requirements increase
Solution Approach 1:
The patent implements a self-service system where the first engine's generator provides power for the second engine's starting. This eliminates the need for external ground power units, reducing infrastructure complexity while achieving low battery consumption.
Solution Approach 2:
The first engine serves multiple functions: it generates power for its own operation and also provides electrical power to start the second engine. This multi-functionality eliminates the need for separate ground power units, reducing system complexity.
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 battery power consumption during engine starting and stopping, allowing for sufficient power during flight and eliminating the need for ground power units, thereby miniaturizing batteries and reducing aircraft weight.
Implementation Method 1
a battery that stores electricity generated by the generators
Implementation Method 2
generators that are respectively connected to rotary shafts of the plurality of gas turbine engines
Data Source
AI summary
Provided is a gas turbine system in which electricity consumption of a battery when starting or stopping a gas turbine engine is reduced and sufficient battery power during flight can be secured. The present invention includes a plurality of gas turbine engines 21, 22, and 23, generators 41, 42, and 43, a battery 5, and a controller 7. The controller 7 decides at least one main starting gas turbine engine 21 from the plurality of gas turbine engines before the plurality of gas turbine engines are started, starts the main starting gas turbine engine 21 using electricity from the battery 5, and starts the secondary starting gas turbine engines 22 and 23 of the plurality of gas turbine engines other than the main starting gas turbine engine 21 using electricity from the generator 41 connected to the main starting gas turbine engine 21 after the main starting gas turbine engine 21 reaches a steady state.