Gas turbine engine temperature measurement system
AssigneeROLLS-ROYCE plc
InventorGuy Stevenson
Life of this patent
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Abstract
A temperature measurement system for a gas turbine engine, the gas turbine engine including, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section. The temperature measurement system includes one or more optical thermometers, each optical thermometer configured to measure the temperature of a component washed by the working gas of the engine, the or each component being in the combustor section or the turbine section at a first position along the axis of the engine.
Claims16
A temperature measurement system for a gas turbine engine, the gas turbine engine comprising, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section;
- the temperature measurement system comprising one or more optical thermometers, each optical thermometer being configured to measure a temperature of a component washed by a working gas of the gas turbine engine, the or each component being in the combustor section or the turbine section at a first position along an axis of the gas turbine engine, wherein
- the turbine section comprises a circumferential row of nozzle guide vanes at an entrance into the turbine section from the combustor section;
- the or each optical thermometer is configured to measure a temperature of a respective nozzle guide vane;
- and
- each of the optical thermometers is radially outward of the respective nozzle guide vane relative to the axis of the gas turbine engine.
Dependencies are inferred from the claim text.