17946499. GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
- 1 GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Original Abstract Submitted
GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY
Organization Name
Inventor(s)
Paul Hadley Vitt of Liberty Township OH (US)
Matteo Renato Usseglio of Turin (IT)
Brian Lewis Devendorf of Georgetown MA (US)
GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY - A simplified explanation of the abstract
This abstract first appeared for US patent application 17946499 titled 'GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY
Simplified Explanation
The aircraft engine described in the patent application includes a unique configuration with a compressor section, a turbine section with counter-rotating turbine blades, fluid supply lines, a fuel cell assembly, and a heat exchanger. The fuel cell assembly is connected to the turbine section to provide output products, while the heat exchanger receives exhaust gases from the turbine and is connected to the fluid supply lines.
- Compressor section with a compressor
- Turbine section with counter-rotating turbine blades
- Fluid supply lines
- Fuel cell assembly connected to the turbine section
- Heat exchanger connected to the fluid supply lines and receiving exhaust gases from the turbine
Potential Applications
The technology described in this patent application could be applied in aircraft engines, power generation systems, and other industrial applications where efficient energy conversion is required.
Problems Solved
This technology addresses the need for improved energy efficiency and reduced emissions in aircraft engines and other power generation systems. By integrating a fuel cell assembly and a heat exchanger into the engine design, the system can produce power more efficiently and with lower environmental impact.
Benefits
The benefits of this technology include increased energy efficiency, reduced emissions, and potentially lower operating costs for aircraft and other systems utilizing this engine design. By optimizing the energy conversion process and utilizing alternative fuel sources, the engine can provide a more sustainable power solution.
Potential Commercial Applications
The technology described in this patent application could have commercial applications in the aerospace industry, power generation sector, and other industries requiring high-performance and environmentally friendly energy solutions. A SEO optimized title for this section could be "Commercial Applications of Innovative Aircraft Engine Technology".
Possible Prior Art
One possible prior art for this technology could be existing aircraft engine designs that incorporate fuel cell technology or heat exchangers for energy conversion. Research into similar engine configurations and alternative power sources may also be relevant as prior art in this field.
Unanswered Questions
How does this technology compare to traditional aircraft engine designs in terms of performance and efficiency?
This article does not provide a direct comparison between the innovative engine design described and traditional aircraft engines. Further research or testing would be needed to determine the performance and efficiency differences between the two types of engines.
What are the potential challenges or limitations of implementing this technology in practical applications?
The article does not address any potential challenges or limitations that may arise when implementing this technology in real-world applications. Factors such as cost, scalability, and compatibility with existing systems could impact the feasibility of adopting this engine design. Further analysis would be needed to assess these aspects.
Original Abstract Submitted
An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.
