18337491. GAS TURBINE ENGINE simplified abstract (ROLLS-ROYCE plc)

GAS TURBINE ENGINE

Organization Name

ROLLS-ROYCE plc

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)

Andrea Minelli of Derby (GB)

Andrew T. Smith of Derby (GB)

Peter Swann of Derby (GB)

Martin K. Yates of Derby (GB)

GAS TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18337491 titled 'GAS TURBINE ENGINE

The abstract describes a method of operating a gas turbine engine with a heat exchange system to raise fuel temperature to at least 135°C on entry to the combustor at cruise conditions.

• Engine core components include a turbine, compressor, combustor, core shaft, fan, fan shaft, gearbox, primary oil loop system, and heat exchange system.
• The heat exchange system includes an air-oil heat exchanger and a fuel-oil heat exchanger arranged in parallel on different branches of the system.
• A modulation valve allows for varying the oil flow sent via each branch to control the temperature.
• The method involves controlling the heat exchange system to increase fuel temperature for optimal combustion efficiency.

Potential Applications: - Aerospace industry for aircraft propulsion systems - Power generation for gas turbine power plants

Problems Solved: - Improved fuel combustion efficiency - Enhanced engine performance and reliability

Benefits: - Increased fuel efficiency - Reduced emissions - Extended engine lifespan

Commercial Applications: - Aircraft engines - Power generation systems for industrial applications

Questions about the technology: 1. How does the heat exchange system impact fuel combustion efficiency? 2. What are the potential cost savings associated with this method of operating a gas turbine engine?

Original Abstract Submitted

A method of operating a gas turbine engine including an engine core including: a turbine, compressor, combustor, core shaft; fan; fan shaft; gearbox that receives input from the core shaft and outputs drive to the fan via the fan shaft; primary oil loop system that supplies oil to the gearbox; and heat exchange system, which includes an air-oil heat exchanger through which oil in the primary oil loop system flows; and a fuel-oil heat exchanger through which the oil and fuel flow so heat is transferred therebetween, wherein the system branches so oil flows along each branch and the exchangers are arranged in parallel on different branches of the system; and a modulation valve that allows the oil sent via each branch to be varied. The method includes controlling the heat exchange system to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.