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US 11,635,750 B2Granted
System and method for removably inserting a sensor assembly into a compressor casing
AssigneeGeneral Electric Company
InventorsKurt Kramer Schleif, Andrew David Ellis, Robert David Jones, Stephen Paul Wassynger
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Abstract
A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.
Claims16
A measurement system for a gas turbine engine, comprising:
- a sensor assembly;
- and
- a plurality of sensors coupled to the sensor assembly, wherein, from outside a casing of the gas turbine engine, the sensor assembly is configured to be removably inserted into and removed from a space defined by both an inner surface of a casing wall of the casing and a circumferential track disposed within the casing wall, via a single port coupled to the space, without having to disassemble the casing, wherein the circumferential track extends along the casing wall in direct contact with the casing wall, and wherein the circumferential track encloses the plurality of sensors within the space when the sensor assembly is inserted into the space.
A turbine system comprising:
- a gas turbine engine, comprising:
- a compressor comprising a compressor casing wall having an inner surface;
- a combustor downstream of the compressor;
- a turbine downstream of the combustor;
- a circumferential track disposed within the compressor casing wall, wherein the circumferential track extends along the compressor casing wall in direct contact with the compressor casing wall;
- and
- a circumferential cavity defined by both the inner surface of the compressor casing wall and the circumferential track, wherein the circumferential cavity extends about at least a portion of the inner surface of the compressor casing wall in a circumferential direction relative to a longitudinal axis of the gas turbine engine;
- and
- a measurement system, comprising:
- a sensor assembly;
- and
- a plurality of sensors coupled to the sensor assembly, wherein the sensor assembly is configured to be removably inserted within and removed from the circumferential cavity from outside the compressor casing wall, via a single port coupled to the circumferential cavity, without having to disassemble a compressor casing, wherein the circumferential track encloses the plurality of sensors within the circumferential cavity when the sensor assembly is inserted into the circumferential cavity.
9 more elements
A method, comprising:
- inserting a sensor assembly having a plurality of sensors into a cavity defined by both an inner surface of a compressor casing wall of a compressor casing of a compressor of a gas turbine engine and a circumferential track disposed within the casing wall without having to disassemble the compressor casing, wherein the compressor casing includes a single port coupled to the cavity through which the sensor assembly is inserted from outside the compressor casing, wherein the circumferential track extends along the compressor casing wall in direct contact with the compressor casing wall, and wherein the circumferential track encloses the plurality of sensors within the cavity;
- and
- acquiring, via the plurality of sensors, baseline data during an operation of the gas turbine for validating the operation of the gas turbine engine independent of a control system for the gas turbine engine, wherein the operation of the gas turbine engine utilizes combustion in a combustor of the gas turbine engine to drive the compressor;
- and
- removing the sensor assembly from the cavity, via the single port, from outside the compressor casing without having to disassemble the compressor casing.
2 more elements
Dependencies are inferred from the claim text.