18211809. AIRCRAFT COMBUSTION SYSTEMS simplified abstract (ROLLS-ROYCE plc)
Contents
- 1 AIRCRAFT COMBUSTION SYSTEMS
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 AIRCRAFT COMBUSTION SYSTEMS - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Commercial Applications
- 1.9 Questions about Gas Turbine Engine Technology
- 1.10 Original Abstract Submitted
AIRCRAFT COMBUSTION SYSTEMS
Organization Name
Inventor(s)
Christopher P. Madden of Derby (GB)
Craig W. Bemment of Derby (GB)
AIRCRAFT COMBUSTION SYSTEMS - A simplified explanation of the abstract
This abstract first appeared for US patent application 18211809 titled 'AIRCRAFT COMBUSTION SYSTEMS
Simplified Explanation
The patent application describes a method for operating a gas turbine engine with a combustor that has two subsets of fuel spray nozzles, where one subset receives more fuel than the other. The method involves supplying fuel with a high calorific value to the nozzles.
- The method involves operating a gas turbine engine with a combustor having two subsets of fuel spray nozzles.
- One subset of nozzles receives more fuel than the other.
- The fuel supplied to the nozzles has a high calorific value of at least 43.5 MJ/kg.
- The ratio of the number of nozzles in the subsets falls within the range of 1:2 to 1:5.
- This method can be applied to gas turbine engines used in aircraft.
Potential Applications
The technology can be applied in various gas turbine engines, particularly those used in aircraft, to optimize fuel injection and combustion processes.
Problems Solved
1. Efficient fuel injection in gas turbine engines. 2. Optimization of combustion processes. 3. Enhanced performance and fuel efficiency in aircraft engines.
Benefits
1. Improved fuel efficiency. 2. Enhanced engine performance. 3. Reduced emissions. 4. Cost-effective operation of gas turbine engines.
Commercial Applications
The technology can be utilized in the aerospace industry for the development of more efficient and environmentally friendly aircraft engines. It can also find applications in power generation and other industries that use gas turbine engines.
Questions about Gas Turbine Engine Technology
How does the method of supplying fuel to different subsets of fuel spray nozzles improve engine performance?
The method allows for more precise control over the fuel-air mixture in the combustion chamber, leading to optimized combustion processes and improved engine efficiency.
What are the potential challenges in implementing this technology in existing gas turbine engines?
One potential challenge could be the need for modifications to the fuel injection system to accommodate the two subsets of fuel spray nozzles and ensure proper fuel distribution.
Original Abstract Submitted
A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have 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 a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ/kg. A gas turbine engine can be for an aircraft.
