Fuel Cell Assembly Thermal Control Inside a Gas Turbine Engine
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Solution Overview
Problem
Existing gas turbine engines face inefficiencies and thermal management challenges when integrating fuel cell assemblies, particularly due to thermal transients and material compatibility issues with varying inlet air temperatures during different flight stages.
Innovation Solution
The integration of a fuel cell assembly within the gas turbine engine, utilizing a housing to maintain a stable operating temperature range for the fuel cell stack through an air processing unit that controls airflow temperature and includes a fuel cell sensor and controller to manage thermal transients, along with a fuel processing unit to optimize hydrogen-rich fuel streams.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a fuel cell assembly is integrated into a gas turbine engine without temperature control, then power generation capability is improved, but thermal stress and material compatibility issues worsen due to varying inlet air temperatures during different flight stages
Solution Approach 1:
An air processing unit is introduced as an intermediary component between the engine inlet and the fuel cell assembly. This unit conditions the inlet air by controlling its temperature before it reaches the fuel cell stack, thereby protecting the fuel cell materials from thermal stress while maintaining power generation capability during various flight stages
Solution Approach 2:
The system dynamically changes the temperature parameter of the inlet air based on operating conditions. During ground operations or cold weather flight, the air processing unit heats the inlet air to prevent excessive thermal stress on fuel cell materials, while allowing cooler air during conditions that require thermal management
2Device complexity
If the fuel cell assembly operates without temperature management, then system complexity is reduced, but operational stability deteriorates due to thermal transients during different flight stages
Solution Approach 1:
The air processing unit utilizes engine bleed air as a heat source to warm the inlet air for the fuel cell assembly during cold conditions. This self-service approach uses readily available engine resources to maintain fuel cell operational stability without requiring external power sources or complex thermal management systems
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 enhances the operational stability and efficiency of the fuel cell assembly by maintaining consistent temperature conditions, reducing thermal stress, and optimizing power generation, thereby improving overall system performance and reliability.
Implementation Method 1
a fuel cell assembly operable therewith
Implementation Method 2
an air processing unit that controls airflow temperature
Data Source
AI summary
A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell, an inlet line in fluid communication with an inlet of the fuel cell, and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell, wherein the inlet line is positioned to be in thermal communication with the output products during operation of the gas turbine engine.