18337497. HEAT TRANSFER simplified abstract (ROLLS-ROYCE plc)
Contents
HEAT TRANSFER
Organization Name
Inventor(s)
Craig W. Bemment of Derby (GB)
Alastair G. Hobday of Derby (GB)
Benjamin J. Keeler of Chesterfield (GB)
HEAT TRANSFER - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337497 titled 'HEAT TRANSFER
Simplified Explanation: The patent application describes a method of operating a gas turbine engine using fuel with specific lubricity characteristics to improve engine performance.
- The method involves operating a gas turbine engine with a specific lubricity range of fuel.
- The engine core includes a turbine, compressor, and combustor connected by a core shaft.
- A fan located upstream of the engine core is driven by a gearbox connected to the core shaft.
- A heat exchange system transfers heat to the fuel using fuel-oil heat exchangers.
- The fuel pump, located downstream of the heat exchanger, delivers fuel to the combustor.
Key Features and Innovation:
- Operating a gas turbine engine with fuel of specific lubricity improves engine performance.
- Integration of fuel-oil heat exchangers in the engine system enhances fuel efficiency.
- Placement of the fuel pump downstream of the heat exchanger optimizes fuel delivery to the combustor.
Potential Applications: The technology can be applied in various gas turbine engines across different industries, including aviation, power generation, and marine propulsion.
Problems Solved: The method addresses issues related to fuel efficiency, engine performance, and maintenance in gas turbine engines.
Benefits:
- Improved engine efficiency and performance.
- Enhanced fuel combustion and delivery.
- Reduced maintenance and operational costs.
Commercial Applications: The technology can be utilized in commercial aircraft, power plants, and marine vessels to enhance fuel efficiency and overall engine performance.
Prior Art: Readers can explore prior patents related to gas turbine engine fuel systems, lubricity requirements, and heat exchange technologies to understand the background of this innovation.
Frequently Updated Research: Stay updated on advancements in fuel technology, heat exchange systems, and gas turbine engine efficiency to further enhance the application of this method.
Questions about Gas Turbine Engine Fuel Lubricity: 1. How does the specific lubricity range of fuel impact gas turbine engine performance? 2. What are the potential implications of using fuel with different lubricity characteristics on engine maintenance and longevity?
Original Abstract Submitted
A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
