18071722. GAS TURBINE ENGINE simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
- 1 GAS TURBINE ENGINE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINE - 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 Unanswered Questions
- 1.11 Original Abstract Submitted
GAS TURBINE ENGINE
Organization Name
Inventor(s)
Brandon Wayne Miller of Liberty Township OH (US)
Andrew Hudecki of Milford OH (US)
Steven Douglas Johnson of Milford OH (US)
Eric Barre of Cincinnati OH (US)
John Carl Glessner of Kings Mills OH (US)
Efren Souza Chavez of Queretaro (MX)
GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18071722 titled 'GAS TURBINE ENGINE
Simplified Explanation
The gas turbine engine described in the patent application includes a fan assembly, a turbomachine, a bypass passage, and a heat exchanger. The heat exchanger is in thermal communication with an airflow through the cooling passage, which extends between an inlet and an outlet.
- Fan assembly with a fan
- Turbomachine with compressor, combustion, and turbine sections
- Bypass passage over the turbomachine
- Heat exchanger with an annular cooling passage
- Inlet in airflow communication with the working gas flowpath
- Outlet in airflow communication with the bypass passage
Potential Applications
The technology described in this patent application could be applied in aircraft engines, power generation systems, and industrial gas turbines.
Problems Solved
This technology helps improve the efficiency and performance of gas turbine engines by enhancing cooling mechanisms and optimizing airflow within the engine.
Benefits
The benefits of this technology include increased efficiency, reduced emissions, improved reliability, and enhanced overall performance of gas turbine engines.
Potential Commercial Applications
Potential commercial applications of this technology include aerospace industry, power generation companies, and manufacturers of industrial gas turbines.
Possible Prior Art
One possible prior art for this technology could be the use of heat exchangers in gas turbine engines for cooling purposes. Another could be the optimization of airflow within gas turbine engines to improve efficiency.
Unanswered Questions
How does this technology compare to existing cooling systems in gas turbine engines?
The article does not provide a direct comparison with existing cooling systems in gas turbine engines, leaving the reader to wonder about the specific advantages of this innovation over current technologies.
What are the specific environmental impacts of implementing this technology in gas turbine engines?
The article does not address the environmental impacts of implementing this technology, such as potential reductions in emissions or energy consumption.
Original Abstract Submitted
A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
