18337699. CONTROL OF FUEL TEMPERATURE simplified abstract (ROLLS-ROYCE plc)
CONTROL OF FUEL TEMPERATURE
Organization Name
Inventor(s)
Christopher P. Madden of Derby (GB)
Craig W. Bemment of Derby (GB)
Benjamin J. Keeler of Chesterfield (GB)
CONTROL OF FUEL TEMPERATURE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337699 titled 'CONTROL OF FUEL TEMPERATURE
The abstract describes a method of operating a gas turbine engine with a lean burn staged combustion system, including a fuel-oil heat exchanger to transfer heat between oil and fuel before combustion in the combustor.
- Heat is transferred from the oil to the fuel to raise the fuel temperature to at least 135°C on entry to the combustor at cruise conditions.
- The method aims to improve the efficiency and performance of the gas turbine engine by preheating the fuel before combustion.
- The innovation helps optimize the combustion process and reduce emissions in the gas turbine engine.
- By transferring heat from the oil to the fuel, the method enhances the overall thermal efficiency of the engine.
- The use of a fuel-oil heat exchanger in the gas turbine engine is a novel approach to improving combustion efficiency.
Potential Applications: - Aerospace industry for aircraft gas turbine engines - Power generation plants using gas turbines - Marine propulsion systems utilizing gas turbine engines
Problems Solved: - Enhanced combustion efficiency - Reduced emissions - Improved overall performance of gas turbine engines
Benefits: - Increased fuel efficiency - Lower emissions - Improved engine performance and reliability
Commercial Applications: - Aircraft manufacturers - Power generation companies - Marine industry for ship propulsion systems
Questions about the technology: 1. How does the fuel-oil heat exchanger impact the overall efficiency of the gas turbine engine? 2. What are the specific advantages of preheating the fuel before combustion in the combustor?
Frequently Updated Research: - Ongoing studies on optimizing fuel combustion in gas turbine engines - Research on improving thermal efficiency in aerospace propulsion systems
Original Abstract Submitted
A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine for an aircraft.
