18337531. AIRCRAFT FUEL SYSTEM simplified abstract (ROLLS-ROYCE plc)
Contents
AIRCRAFT FUEL SYSTEM
Organization Name
Inventor(s)
Christopher P. Madden of Derby (GB)
David M. Beaven of Nottingham (GB)
Craig W. Bemment of Derby (GB)
Benjamin J. Keeler of Chesterfield (GB)
AIRCRAFT FUEL SYSTEM - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337531 titled 'AIRCRAFT FUEL SYSTEM
The abstract describes a method of operating a gas turbine engine with a unique fuel system that includes a fuel pump, fuel distributing valve, and fuel-oil heat exchanger to optimize fuel delivery and viscosity.
- Fuel system includes a fuel pump, fuel distributing valve, and fuel-oil heat exchanger.
- Fuel distributing valve biases fuel flow to different nozzles, ensuring optimal fuel distribution.
- Fuel-oil heat exchanger transfers heat from oil to fuel, reducing fuel viscosity to 0.58 mm/s or lower before entering the combustor.
- Engine designed for aircraft applications.
Potential Applications: - Aircraft engines - Power generation systems - Industrial gas turbines
Problems Solved: - Optimized fuel delivery for improved engine performance - Reduced fuel viscosity for enhanced combustion efficiency
Benefits: - Increased fuel efficiency - Enhanced engine reliability - Lower maintenance costs
Commercial Applications: Title: "Optimized Fuel System for Gas Turbine Engines" This technology can be used in commercial aircraft, power plants, and industrial applications, offering improved performance and efficiency.
Questions about the technology: 1. How does the fuel-oil heat exchanger impact fuel viscosity in the engine? The fuel-oil heat exchanger transfers heat from oil to fuel, reducing viscosity to improve combustion efficiency.
2. What are the potential cost savings associated with this optimized fuel system? The optimized fuel system can lead to lower maintenance costs and increased fuel efficiency, resulting in overall cost savings for operators.
Original Abstract Submitted
Provided is a method of operating a gas turbine engine. The engine includes a combustor having a plurality of fuel spray nozzles and a fuel system arranged to provide fuel to the combustor. The system includes: fuel pump; fuel distributing valve downstream of the pump arranged to distribute fuel to the plurality of nozzles and bias fuel flow to the nozzles such that a first subset of the plurality of nozzles receives more fuel than a second subset of the plurality of nozzles; and fuel-oil heat exchanger. The method includes providing a fuel to the combustor and transferring heat from oil to the fuel in the fuel-oil heat exchanger before the fuel enters the combustor so as to lower a viscosity of the fuel to 0.58 mm/s or lower on entry to the combustor at cruise conditions. Also provided is a gas turbine engine for an aircraft.
