CN-116337256-B - Turbine engine exhaust gas temperature sensor

Abstract

The gas turbine engine may include a compressor section, a combustion section, and a turbine section arranged in a serial flow. At least one of the combustion section or the turbine section may have an exhaust passage. The turbine engine may also include an exhaust gas temperature sensor having a housing with an elongated probe portion. The elongate probe portion may have an outer wall defining an interior. The temperature probe may be disposed within the housing.

Inventors

• J.P. Parsons

Assignees

• 和谐工业有限责任公司

Dates

Publication Date

20260508

Application Date

20221010

Priority Date

20220610

Claims (20)

1. 1. A gas turbine engine, comprising: A compressor section, a combustion section, and a turbine section arranged in a series flow, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows, and An exhaust gas temperature sensor, comprising: A housing having an elongate probe portion defining an axial direction and having an outer wall defining an interior and defining an airfoil section extending from a leading edge to a trailing edge, wherein the elongate probe portion comprises a material having a temperature capability between 50 ℃ and 1280 ℃, and wherein the outer wall defines a chord line extending from the leading edge to the trailing edge, and wherein a first length extends along the chord line between the leading edge and the interior; An exhaust flow path passing through an interior of the elongate probe section and extending between an inlet in the outer wall at the leading edge and an outlet in the outer wall downstream of the leading edge, wherein the interior of the elongate probe section is in fluid communication with the inlet and the outlet, wherein a portion of the exhaust flow path extends along the first length from the inlet to the interior, and A temperature probe within the housing and thermally coupled to the exhaust flow path.
2. 2. The gas turbine engine of claim 1, wherein the temperature probe is directly exposed to the exhaust flow path.
3. 3. The gas turbine engine of claim 1, wherein the material comprises at least one of a ceramic matrix composite, a refractory metal, platinum, gain-stabilized platinum, a nickel-based superalloy, a cobalt-based superalloy, a ceramic, or a monolithic ceramic.
4. 4. The gas turbine engine of claim 1, wherein the inlet is spaced from the outlet in the axial direction.
5. 5. The gas turbine engine of claim 1, wherein the outer wall is symmetrical about the chord line.
6. 6. The gas turbine engine of claim 1, wherein the exhaust gas temperature sensor further comprises a sensor wire and a sleeve surrounding the sensor wire, wherein the sleeve is spaced from an outer wall of the housing to at least partially define the exhaust gas flow path through the interior.
7. 7. The gas turbine engine of claim 6, wherein the sensor wire comprises platinum.
8. 8. The gas turbine engine of claim 7, wherein the sleeve comprises at least one of a ceramic or a ceramic matrix composite.
9. 9. The gas turbine engine of claim 1, wherein an end of the temperature probe is positioned outside of the housing.
10. 10. The gas turbine engine of any of claims 1-9, wherein the inlet comprises a slot and the outlet comprises a plurality of openings on the outer wall.
11. 11. The gas turbine engine of claim 10, wherein the plurality of openings comprises a first set of openings on a first side of the outer wall and a second set of openings on a second side of the outer wall.
12. 12. The gas turbine engine of claim 11, wherein the first set of openings and the second set of openings are positioned downstream of the leading edge.
13. 13. An exhaust gas temperature sensor, comprising: A housing having an elongate probe portion comprising at least one of ceramic, monolithic ceramic, or ceramic matrix composite and defining an axial direction, wherein the elongate probe portion has an outer wall defining an interior and defining an airfoil section extending from a leading edge to a trailing edge, and wherein the outer wall defines a chord line extending from the leading edge to the trailing edge, and wherein a first length extends along the chord line between the leading edge and the interior; An exhaust flow path passing through an interior of the elongate probe section and extending between an inlet in the outer wall at the leading edge and an outlet in the outer wall downstream of the leading edge, wherein the interior of the elongate probe section is in fluid communication with the inlet and the outlet, wherein a portion of the exhaust flow path extends along the first length from the inlet to the interior, and A temperature probe within the housing and thermally coupled to the exhaust flow path.
14. 14. The exhaust gas temperature sensor of claim 13, wherein the temperature probe is directly exposed to the exhaust gas flow path.
15. 15. The exhaust gas temperature sensor of claim 13, wherein the inlet is spaced from the outlet in the axial direction.
16. 16. The exhaust gas temperature sensor of claim 13, wherein an end of the temperature probe is positioned outside of the housing.
17. 17. The exhaust gas temperature sensor of claim 13, wherein the outer wall is symmetrical about the chord line.
18. 18. The exhaust gas temperature sensor of any of claims 13-17, wherein the inlet comprises a slot and the outlet comprises a plurality of openings on the outer wall.
19. 19. The exhaust gas temperature sensor of claim 18, wherein the plurality of openings comprises a first set of openings on a first side of the outer wall and a second set of openings on a second side of the outer wall.
20. 20. The exhaust gas temperature sensor of claim 19, wherein the first set of openings and the second set of openings are positioned downstream of the leading edge.

Description

Turbine engine exhaust gas temperature sensor Cross Reference to Related Applications This application claims priority from U.S. provisional patent application Ser. No. 63/292,735 filed on month 22 of 2021 and U.S. patent application Ser. No. 17/837,102 filed on month 10 of 2022, which are incorporated herein by reference in their entireties. Technical Field The present disclosure relates generally to temperature sensors, and more particularly to exhaust gas temperature sensors in turbine engines. Background Turbine engines (and in particular gas turbine engines, also referred to as combustion turbine engines) are rotary engines that extract energy from a flow of combustion gas through the engine onto a plurality of turbine blades. Gas turbine engines have been used for land and marine movement and power generation, and are commonly used for aeronautical applications, such as for propulsion of aircraft. During operation of a gas turbine engine, fuel is combusted to provide rotational energy and thrust through a set of turbines. To ensure or confirm (validate) that the gas turbine engine is operating as desired, a temperature sensor probe may be included in the engine, where it is exposed to the exhaust gas. The temperature sensor may measure the temperature of the exhaust stream and may provide a signal or measurement to another system, such as an engine control system. For example, the temperature sensor output may be used to protect downstream engine components from temperatures that may exceed their design capabilities (capability). Disclosure of Invention Claim 1. A gas turbine engine comprising: A compressor section, a combustion section, and a turbine section arranged in a series flow, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows, and An exhaust gas temperature sensor, comprising: A housing having an elongate probe portion defining an axial direction and having an outer wall defining an interior and defining an airfoil section extending from a leading edge to a trailing edge, wherein the elongate probe portion comprises a material having a temperature capability between 50 ℃ and 1280 ℃; An exhaust flow path passing through an interior of the elongate probe section and extending between an inlet in the outer wall at the leading edge and an outlet in the outer wall downstream of the leading edge, wherein the interior of the elongate probe section is in fluid communication with the inlet and the outlet, and A temperature probe within the housing and thermally coupled to the exhaust flow path. Claim 2 the gas turbine engine of any preceding claim, wherein the temperature probe is directly exposed to the exhaust flow path. Claim 3 the gas turbine engine of any preceding claim, wherein the material comprises at least one of a ceramic matrix composite, refractory metal, platinum, gain-stabilized platinum, nickel-base superalloy, cobalt-base superalloy, ceramic, or monolithic ceramic. Claim 4, the gas turbine engine of any preceding claim, wherein the inlet is spaced from the outlet in the axial direction. Claim 5 the gas turbine engine of any preceding claim, wherein the outer wall defines a chord line between the leading edge and the trailing edge, wherein the outer wall is symmetrical about the chord line. Claim 6 the gas turbine engine of any preceding claim, wherein the exhaust gas temperature sensor further comprises a sensor wire and a sleeve surrounding the sensor wire, wherein the sleeve is spaced from an outer wall of the housing to at least partially define the exhaust gas flow path through the interior. Claim 7. The gas turbine engine of any of the preceding claims, wherein the sensor wire comprises platinum. Claim 8 the gas turbine engine of any preceding claim, wherein the sleeve comprises at least one of a ceramic or a ceramic matrix composite. Claim 9 the gas turbine engine of any preceding claim, wherein an end of the temperature probe is positioned outside of the housing. Technical solution the gas turbine engine of any preceding technical solution, wherein the inlet includes a slot and the outlet includes a plurality of openings in the outer wall. Claim 11 the gas turbine engine of any preceding claim, wherein the plurality of openings comprises a first set of openings on a first side of the outer wall and a second set of openings on a second side of the outer wall. Claim 12 the gas turbine engine of any preceding claim, wherein the first set of openings and the second set of openings are positioned downstream of the leading edge. Technical solution 13. An exhaust gas temperature sensor includes: A housing having an elongate probe portion comprising at least one of a ceramic, monolithic ceramic, or ceramic matrix composite and defining an axial direction, wherein the elongate probe portion has an outer wall defining an interior and defining an airfoil section extending from a leading edge to a trailing ed