18337568. GAS TURBINE ENGINE HEAT EXCHANGE simplified abstract (ROLLS-ROYCE plc)
Contents
GAS TURBINE ENGINE HEAT EXCHANGE
Organization Name
Inventor(s)
Craig W. Bemment of Derby (GB)
Alastair G. Hobday of Derby (GB)
Benjamin J. Keeler of Chesterfield (GB)
Christopher P. Madden of Derby (GB)
GAS TURBINE ENGINE HEAT EXCHANGE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337568 titled 'GAS TURBINE ENGINE HEAT EXCHANGE
The patent application describes a method of operating a gas turbine engine with a fuel management system that includes fuel-oil heat exchangers, a fuel pump, and a recirculation valve.
- The fuel management system includes two fuel-oil heat exchangers for transferring heat between oil and fuel.
- A fuel pump is located between the heat exchangers to deliver fuel to the combustor.
- A recirculation valve downstream of the primary heat exchanger allows a controlled amount of fuel to be returned to the inlet.
- The method involves selecting fuels to ensure a minimum calorific value of 43.5 MJ/kg for the fuel provided to the engine.
Potential Applications: - Gas turbine engines in various industries such as aviation, power generation, and marine propulsion.
Problems Solved: - Efficient heat transfer between oil and fuel. - Controlled fuel recirculation for optimal combustion.
Benefits: - Improved fuel efficiency. - Enhanced engine performance. - Reduced emissions.
Commercial Applications: Title: "Enhanced Fuel Management System for Gas Turbine Engines" This technology can be applied in industries such as aviation, power generation plants, and marine vessels to improve fuel efficiency and reduce emissions, leading to cost savings and environmental benefits.
Questions about the technology: 1. How does the fuel management system contribute to the overall efficiency of the gas turbine engine? 2. What are the potential cost savings associated with implementing this technology in gas turbine engines?
Original Abstract Submitted
A method of operating a gas turbine engine including: a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor, wherein the fuel management system includes two fuel-oil heat exchangers through which oil and fuel flow, which are arranged to transfer heat between the oil and fuel and include primary and secondary fuel-oil heat exchangers; a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the heat exchangers; and a recirculation valve located downstream of the primary heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary heat exchanger to be returned to the inlet. The method includes selecting one or more fuels such that the calorific value of the fuel provided to the gas turbine engine is at least 43.5 MJ/kg.
