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US 10,935,431 B2Granted
Sensor arrangement for measuring gas turbine combustor temperatures
AssigneeRaytheon Technologies Corporation
InventorStephen K. Kramer
Life of this patent
Estimating the term…
Abstract
A sensor system for use in a gas turbine engine. The sensor system includes a reflective surface configured to reflect optical features corresponding to combustion in a combustion chamber that exit the combustion chamber via at least one opening therein. The sensor system further includes an optical sensor configured to receive the reflected optical features from the reflective surface.
Claims18
A sensor system for use in a gas turbine engine, comprising:
- a reflective surface configured to reflect optical features corresponding to combustion in a combustion chamber that exit the combustion chamber via at least one opening therein;
- a fuel nozzle having a fuel nozzle stem;
- and
- an optical sensor coupled to the fuel nozzle stem, located outside of the combustion chamber, and configured to receive the reflected optical features from the reflective surface.
1 more element
A sensor system for use in a gas turbine engine, comprising:
- a combustor component in communication with a combustion chamber of the gas turbine engine;
- a liner and shell assembly;
- a diffuser case defining an inner shroud and an outer shroud between the diffuser case and the liner and shell assembly;
- a reflective surface configured to reflect optical features corresponding to combustion in the combustion chamber towards the combustor component, the optical features being reflected through at least one of the inner shroud or the outer shroud;
- and
- an optical sensor coupled to the combustor component and configured to receive the reflected optical features.
3 more elements
A combustor component for use in a gas turbine engine, comprising:
- a first section configured to be mounted to a diffuser case of the gas turbine engine;
- a third section configured to be in communication with a combustion chamber of the gas turbine engine;
- a second section extending between the first section and the third section;
- and
- a sensor located on the second section and configured to detect an optical property of combustion that occurs within the combustion chamber during operation of the gas turbine engine.
2 more elements
Dependencies are inferred from the claim text.