STAGED COMBUSTOR

Organization Name

ROLLS-ROYCE plc

Inventor(s)

Christopher P. Madden of Derby (GB)

David M. Beaven of Nottingham (GB)

Craig W. Bemment of Derby (GB)

Paul W. Ferra of Derby (GB)

Barani P. Gunasekaran of Derby (GB)

Benjamin J. Keeler of Chesterfield (GB)

Peter Swann of Derby (GB)

Martin K. Yates of Derby (GB)

STAGED COMBUSTOR - A simplified explanation of the abstract

This abstract first appeared for US patent application 18337615 titled 'STAGED COMBUSTOR

Simplified Explanation: The patent application describes a method for operating a gas turbine engine with a staged combustor that biases fuel flow to specific nozzles during a re-light procedure.

The method involves providing fuel with a calorific value of at least 43.5 MJ/kg to the combustor.
The fuel spray nozzles are arranged in a way that directs fuel flow to a subset of nozzles near ignitors for efficient re-lighting.
This innovation aims to improve the re-lighting process of gas turbine engines, enhancing their overall performance and reliability.

Key Features and Innovation:

Biasing fuel flow to specific nozzles during a re-light procedure
Providing fuel with a high calorific value for efficient combustion
Arrangement of fuel spray nozzles near ignitors for improved re-lighting process

Potential Applications: This technology can be applied in various gas turbine engines used in power generation, aviation, and industrial applications.

Problems Solved:

Enhances re-lighting procedures in gas turbine engines
Improves overall performance and reliability of the engine

Benefits:

Increased efficiency in re-lighting procedures
Enhanced performance and reliability of gas turbine engines

Commercial Applications: Potential commercial applications include power generation plants, aircraft propulsion systems, and industrial gas turbines.

Questions about Gas Turbine Engine Re-lighting Method: 1. How does the method of biasing fuel flow improve the re-lighting process of gas turbine engines? 2. What are the potential benefits of using fuel with a calorific value of at least 43.5 MJ/kg in the combustor?

Original Abstract Submitted

There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor comprising an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises providing fuel to the combustor having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine.