18337545. GAS TURBINE OPERATION simplified abstract (ROLLS-ROYCE plc)
Contents
GAS TURBINE OPERATION
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)
GAS TURBINE OPERATION - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337545 titled 'GAS TURBINE OPERATION
Simplified Explanation: The patent application describes a method for operating a gas turbine engine with a specific type of combustor to reduce emissions by using sustainable aviation fuel.
Key Features and Innovation:
- Gas turbine engine with a rich burn, quick quench, lean burn (RQL) combustor
- Reduction of particles/kg of nvPM in the exhaust by 10-70%
- Sustainable aviation fuel used instead of fossil-based hydrocarbon fuel
Potential Applications: The technology can be applied in the aviation industry to reduce emissions from gas turbine engines.
Problems Solved: This technology addresses the issue of high emissions from gas turbine engines, contributing to environmental pollution.
Benefits:
- Significant reduction in emissions
- Use of sustainable aviation fuel
- Improved environmental impact
Commercial Applications: The technology can be used in commercial aircraft to meet emission regulations and reduce the carbon footprint of air travel.
Questions about Gas Turbine Engine Emissions: 1. How does the use of sustainable aviation fuel impact emissions from gas turbine engines? 2. What are the potential long-term benefits of reducing emissions from gas turbine engines?
Original Abstract Submitted
There is provided a method of operating a gas turbine engine, the gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. The method comprises operating the gas turbine engine such that a reduction of 10-70% in an average of particles/kg of nvPM in the exhaust of the gas turbine engine when the engine is operating at 85% available thrust for given operating conditions and particles/kg of nvPM in the exhaust of the gas turbine engine when the engine is operating at 30% available thrust for the given operating conditions is obtained when a fuel provided to the combustor is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel.
