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A method of assembling a temperature sensing device for a gas turbine engine is provided. The method includes providing a temperature sensor and providing a housing configured to envelop the temperature sensor. The method further includes mounting the temperature sensor within the housing such that

A method of assembling a temperature sensing device for a gas turbine engine is provided. The method includes providing a temperature sensor and providing a housing configured to envelop the temperature sensor. The method further includes mounting the temperature sensor within the housing such that a portion of the temperature sensor is disposed outside of the housing and such that the housing is configured to receive a flow of cooling air.

대표청구항 ▼

1. A method of assembling a temperature sensing device for a gas turbine engine, said method comprising: providing a temperature sensor;providing a housing that directs cooling air from a forward region of the housing to an aft region of the housing;mounting the temperature sensor within the housing

1. A method of assembling a temperature sensing device for a gas turbine engine, said method comprising: providing a temperature sensor;providing a housing that directs cooling air from a forward region of the housing to an aft region of the housing;mounting the temperature sensor within the housing such that a tip of the temperature sensor is disposed outside of the housing;providing a cooling tube disposed forward of, and substantially parallel to, the temperature sensor within the housing and having a set of impingement apertures, wherein the cooling air is drawn into the cooling tube based at least in part on a pressure differential; andproviding a set of support ribs that are coupled to the cooling tube and the temperature sensor in a spaced-apart relationship defining a plurality of separate cooling regions, wherein the cooling air is directed, based at least in part on the pressure differential, longitudinally through the cooling tube and discharged through the set of impingement apertures to flow within the cooling regions. 2. The method in accordance with claim 1, further comprising thermally insulating the temperature sensor from the cooling air within the housing. 3. The method in accordance with claim 1, wherein the housing has an airfoil shape and the support ribs have a shape corresponding to the airfoil shape of housing. 4. The method in accordance with claim 1, wherein the cooling air is exhausted through a set of exit apertures in the housing. 5. A temperature sensing device for a gas turbine engine, said temperature sensing device comprising: a temperature sensor;a housing that envelops a first portion of said temperature sensor such that a second portion of said temperature sensor is disposed outside of said housing, wherein said housing is configured to receive cooling air;a cooling channel, having a set of impingement apertures, forward of and substantially parallel to the temperature sensor within the housing, wherein the cooling channel receives the cooling air based at least in part on a pressure differential; anda set of support ribs coupled to the cooling channel and the temperature sensor in a spaced-apart relationship that defines a plurality of separate cooling regions within the housing, wherein the cooling air is directed, based at least in part on the pressure differential, longitudinally through the cooling channel and discharged through the set of impingement apertures to flow within the cooling regions. 6. A device in accordance with claim 5, wherein said temperature sensor is configured to be thermally insulated from the cooling air within said housing. 7. A device in accordance with claim 5, wherein said device is configured to have a service temperature of between 2,300° F. and 2,800° F. 8. A device in accordance with claim 5, wherein said housing comprises a plurality of exit apertures for exhausting the cooling air from said housing. 9. The device in accordance with claim 5, wherein the housing has an airfoil shape that mitigates aerodynamic drag. 10. The device in accordance with claim 5, wherein the housing includes a set of exit apertures through which the cooling air is exhausted. 11. A gas turbine engine comprising: a combustion section with a combustion chamber; andthe temperature sensing device according to claim 5 extending into said combustion chamber. 12. A gas turbine engine in accordance with claim 11, wherein said temperature sensor is configured to be thermally insulated from the cooling air within said housing. 13. A gas turbine engine in accordance with claim 11, wherein said device is configured to have a service temperature of between 2,300° F. and 2,800° F. 14. A gas turbine engine in accordance with claim 11, wherein said housing comprises a plurality of exit apertures for exhausting the cooling air from said housing into said combustion chamber. 15. A gas turbine engine in accordance with claim 11, wherein said combustion section comprises a bypass flow path, said temperature sensing device configured to receive the cooling air from said bypass flow path.