18211622. AIRCRAFT FUELLING simplified abstract (ROLLS-ROYCE plc)
Contents
AIRCRAFT FUELLING
Organization Name
Inventor(s)
Christopher P. Madden of Derby (GB)
Craig W. Bemment of Derby (GB)
AIRCRAFT FUELLING - A simplified explanation of the abstract
This abstract first appeared for US patent application 18211622 titled 'AIRCRAFT FUELLING
The abstract describes a method of operating a gas turbine engine with a combustor that includes a combustion chamber and multiple fuel spray nozzles. The engine operates with a first subset of fuel spray nozzles receiving more fuel than a second subset, with a specific ratio between the two subsets.
- The gas turbine engine includes a combustor with a unique fuel injection system.
- The method involves supplying more fuel to a specific subset of fuel spray nozzles.
- The ratio of fuel spray nozzles in the first subset to the second subset falls within a specific range.
- Fuel is provided to fuel-oil heat exchangers in the engine.
- The innovation is designed for use in gas turbine engines for aircraft.
Potential Applications: - Aircraft propulsion systems - Power generation in aviation - Industrial gas turbine engines
Problems Solved: - Efficient fuel distribution in a combustor - Optimal performance of gas turbine engines - Enhanced fuel combustion control
Benefits: - Improved fuel efficiency - Enhanced engine performance - Reduced emissions
Commercial Applications: Title: Fuel Injection System for Gas Turbine Engines This technology can be utilized in commercial aircraft engines, power generation plants, and industrial gas turbine applications. The innovation offers improved fuel efficiency and performance, making it attractive for companies seeking to enhance their operations.
Questions about the technology: 1. How does the unique fuel injection system improve the efficiency of gas turbine engines? - The specific fuel distribution to different subsets of fuel spray nozzles optimizes combustion, leading to increased efficiency and performance. 2. What are the potential cost savings associated with using this method of fuel injection in gas turbine engines? - By improving fuel efficiency and combustion control, companies can potentially save on fuel costs and maintenance expenses in the long run.
Original Abstract Submitted
A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes: providing fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.
