Aircraft Propulsion Fuel Cell Air Supply Without A Dedicated Compressor
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Solution Overview
Problem
Gas turbine engines with integrated fuel cell systems face a significant weight penalty and power requirement due to the need for a dedicated compressor, limiting their inclusion in certain aircraft due to suboptimal power output/weight performance.
Innovation Solution
The aircraft propulsion system configures the gas turbine engine to provide compressed air to the fuel cell system, allowing for the elimination of a dedicated compressor in the fuel cell system, and utilizes a condenser to convert water vapor from the fuel cell output into liquid water for combustor cooling, reducing NOx emissions and increasing turbine efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a dedicated compressor is included in the fuel cell system, then sufficient compressed air input is provided for electrical power production, but significant weight penalty and power input requirements occur
Solution Approach 1:
The gas turbine engine's compressor is designed to serve dual functions: providing compressed air for the gas turbine combustion process and simultaneously supplying compressed air to the fuel cell system. This multi-functionality eliminates the need for a dedicated fuel cell compressor, reducing overall system weight and component count while ensuring sufficient compressed air supply for electrical power generation at various altitudes
Solution Approach 2:
The patent merges the air compression function into a single integrated system by combining the gas turbine compressor and fuel cell air supply system. The compressor of the gas turbine engine is directly coupled to provide compressed air to both the combustor and the fuel cell air input, consolidating what would traditionally be separate compression systems into one unified component
2Power
If a dedicated compressor is included in the fuel cell system, then compressed air supply is ensured, but device complexity and power input requirements increase
Solution Approach 1:
The gas turbine compressor performs multiple functions simultaneously: compressing air for the gas turbine cycle and supplying compressed air to the fuel cell system. This eliminates the need for a separate fuel cell compressor, reducing device complexity and the number of moving parts while ensuring adequate compressed air supply for electrical power production
Solution Approach 2:
The patent combines the air compression function into a single integrated system where the gas turbine engine's compressor serves both the gas turbine combustor and the fuel cell system. This merging of functions reduces system complexity by eliminating redundant components and simplifying the overall architecture
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
This configuration reduces NOx emissions, lowers turbine entry temperature, and allows for increased fuel consumption rates while extending turbine lifetime, enhancing overall propulsion system performance without the need for a separate compressor.
Implementation Method 1
a condenser coupled to the output port and arranged to condense water vapour in the gaseous output to produce liquid water
Implementation Method 2
provide at least a portion of the liquid water to a combustor of the gas turbine engine to effect cooling of the combustor during operation
Implementation Method 3
a humidifier arranged to receive at least a portion of the liquid water produced by the condenser and to humidify the air from the compressor prior to input thereof to the air input of the PEM fuel cell system
Implementation Method 4
a fuel cell system which produces gaseous output comprising water vapour at an output port thereof during operation
Data Source
AI summary
An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.