18452958. COMBUSTOR FUEL NOZZLE ASSEMBLY simplified abstract (General Electric Company)
Contents
COMBUSTOR FUEL NOZZLE ASSEMBLY
Organization Name
Inventor(s)
Nayan Vinod Patel of Liberty Township OH (US)
Michael A. Benjamin of Cincinnati OH (US)
COMBUSTOR FUEL NOZZLE ASSEMBLY - A simplified explanation of the abstract
This abstract first appeared for US patent application 18452958 titled 'COMBUSTOR FUEL NOZZLE ASSEMBLY
Simplified Explanation:
This patent application describes a turbine engine with a compressor section, a combustion section, and a turbine section arranged in series. The combustion section includes a combustor with a combustion chamber, a fuel supply connected to the chamber, and a fuel nozzle assembly with air and fuel passages.
Key Features and Innovation:
- Turbine engine with compressor, combustion, and turbine sections in series
- Combustor with combustion chamber and fuel supply
- Fuel nozzle assembly with air and fuel passages
Potential Applications: The technology can be used in aircraft engines, power generation systems, and other industrial applications requiring efficient combustion processes.
Problems Solved: This technology addresses the need for improved fuel combustion efficiency and performance in turbine engines.
Benefits:
- Enhanced fuel combustion efficiency
- Improved overall performance of turbine engines
- Potential for reduced emissions
Commercial Applications: Potential commercial applications include aircraft propulsion systems, power plants, and marine propulsion systems.
Prior Art: Readers can explore prior patents related to turbine engine combustion systems and fuel injection technologies to understand the existing knowledge in this field.
Frequently Updated Research: Researchers may find updated studies on fuel combustion technologies, turbine engine efficiency, and combustion chamber design relevant to this technology.
Questions about Turbine Engine Combustion Systems: 1. What are the key components of a turbine engine combustion system? 2. How does the design of fuel nozzles impact combustion efficiency in turbine engines?
Original Abstract Submitted
A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
