TURBINE ENGINE EXHAUST GAS TEMPERATURE SENSOR

Abstract

A gas turbine engine may include a compressor section, a combustion section, and a turbine section in a series flow arrangement. At least one of the combustion section and the turbine section may have an exhaust gas passage. The turbine engine may also include an exhaust gas temperature sensor with a housing containing an elongated probe portion. The elongated probe portion may have an outer wall enclosing an interior. A temperature probe may be provided inside the housing. Figure for the abbreviation: Fig 3

Description

Title of the invention: TURBINE ENGINE EXHAUST GAS TEMPERATURE SENSOR Technical field

[0001] The disclosure relates, generally, to temperature sensors and, more particularly, to exhaust gas temperature sensors in turbine engines.

[0002] Turbine engines, and in particular gas turbine engines, also called combustion turbine engines, are rotary engines that extract energy from a flow of burned gases passing through the engine over a multitude of turbine blades. Gas turbine engines have been used for land and water locomotion and for power generation, and are commonly used for aeronautical applications, such as for aircraft propulsion.

[0003] During operation of gas turbine engines, fuel is burned to provide rotational power and thrust via a set of turbines. To ensure or validate that the gas turbine engine is operating as designed, a temperature sensor probe may be included in the engine in which it is exposed to the exhaust gases. The temperature sensor may measure the temperature of the exhaust gas stream and may provide a signal or measurement value to another system, such as an engine control system. The temperature sensor output may be used, for example, to protect downstream engine components from temperatures exceeding their design capacity. Brief description of the drawings

[0004] A complete and sufficient description of the present disclosure, including the best mode for carrying it out, intended for those skilled in the art, is presented in the specification with reference to the appended figures in which:

[0005] [Fig-1] is a cross-sectional view of a gas turbine engine according to various aspects described herein;

[0006] [Fig.2] is a partial cross-sectional view of a combustion section of the gas turbine engine of [Fig.l] with an exhaust gas temperature (EGT) sensor according to various aspects described herein;

[0007] [Fig.3] is a front perspective view of the EGT sensor of [Fig.2] according to various aspects described herein;

[0008] [Fig.4] is a rear perspective view of the EGT sensor of [Fig.2] according to various aspects described herein;

[0009] [Fig.5] is a cross-sectional view of the EGT sensor of [Fig.4] along line VV;

[0010] [Fig.6] is a cross-sectional view of the EGT sensor of [Fig.4] along line VI-VI; DETAILED DESCRIPTION

[0011] The described embodiments of the present disclosure relate to a temperature sensor and probe assembly. For purposes of illustration, an exemplary environment in which the temperature sensor may be used will be described as a turbine engine. Such a turbine engine may be in the form of a gas turbine engine, a turboprop, a turboshaft, a turbofan, or an open rotor engine in non-limiting examples. It should be understood, however, that aspects of the disclosure described herein are not limited thereby and may have general applicability. For example, the disclosure may have applicability for a temperature sensor in other engines or vehicles, and may be used to provide benefits in industrial, commercial, and residential applications.

[0012] Exhaust gas temperature (EGT) sensors generally include a housing surrounding a thermocouple element and configured to extend or protrude into a combustion gas flow for measuring temperatures in the flow. EGT sensors immersed within the combustion gas flow produce drag, aerodynamic blockage, or other flow disturbances in the combustion gas downstream of the EGT sensor due to fluid movement at the sensor housing. Such fluid movement can generate component wear on the EGT sensor as well as fluid swirls, delamination, turbulent flow, or other flow disturbances in the combustion gas downstream of the EGT sensor.Such flow disturbances can persist in the flow and reach downstream engine components in the high-pressure turbine, which can adversely affect engine performance. The submerged EGT sensor also experiences aerodynamic drag due to its immersion in the combustion gas flow, which generates stresses and tensions within the housing, which stresses can produce finning, plastic deformation, crack initiation, or crack propagation within the EGT sensor housing.

[0013] Additionally, EGT sensors are exposed to hot combustion gases, which may be in the range of 500°F to 2500°F (260°C to 1370°C) or higher in some examples. Such sensors may be necessary to protect components for allow for accurate flue gas flow measurement while withstanding the hot environment for repetitive use. Positioning an EGT sensor as close to the combustion chamber as possible can promote more accurate flue gas temperature measurements; however, temperatures within or immediately adjacent to the combustion chamber may be higher than the sensor materials can tolerate.

[0014] Aspects of the disclosure provide an improved aerodynamic EGT sensor capable of operating within the high temperature turbine engine combustion chamber environment with reduced effects on downstream fluid flows, increased component life, and reduced stress on parts. Turbine engines with the improved EGT sensor described herein may have improved engine performance and higher engine efficiency compared to engines using traditional EGT sensors.

[0015] As used herein, the term "set" or a "set" of elements can be any number of elements, including a single element. Further, as used herein, the term "upstream" refers to a direction that is opposite the direction of fluid flow, and the term "downstream" refers to a direction that is the same as the direction of fluid flow. The term "in front" or "ahead" means in front of something and "in back" or "behind" means behind something. For example, when used for fluid flow, the term in front / ahead can mean upstream and the term in back / behind can mean downstream.

[0016] Additionally, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the general context of a turbine engine, radial refers to a direction along a radius extending between a central longitudinal axis of the engine and an outer circumference of the engine.

[0017] Additionally, as used herein, the term "control device" or "control module" may include a component configured or adapted to provide an instruction, command, operation, or any form of communication for operable components to effect operation thereof. A control module may include any known processor, microcontroller, or logic device, including, but not limited to: field-programmable gate arrays (FPGAs), an application-specific integrated circuit (ASIC), a full-authority digital control system (FADEC), a proportional (P) controller, a proportional-integral (PI) controller, a proportional-derivative (PD) controller, a proportional-integral-derivative (PID) controller, a hardware-accelerated logic control (e.g., for encoding, decoding, transcoding, etc.), combinations thereof, and similar elements.

[0018] Non-limiting examples of a control module may be configured or adapted to implement, operate, or otherwise execute program code to achieve operational or functional results, including performing various methods, features, processing tasks, calculations, comparisons, detections or measurements of values, or the like to enable or accomplish technical operations or operations described herein. The operational or functional results may be based on one or more inputs, stored data values, detected or measured values, true or false indications, or the like. Although "program code" is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., having the technical effect of performing particular tasks or implementing particular abstract data types.

[0019] In another non-limiting example, a control module may also include a data storage component accessible by the processor, including transient, volatile, non-transient, or non-volatile memory. Other non-limiting examples of the memory may include random access memory (RAM), read only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as disks, DVDs, CD-ROMs, flash disks, universal serial bus (USB) disks, and the like, or any suitable combination of memory types. In one example, program code may be stored within the memory in a machine-readable format accessible by the processor.Additionally, the memory may store various data, various types of data, various sensed or measured data values, various inputs, various generated or processed data, or various similar elements accessible by the processor to provide an instruction, command, or operation to achieve a functional or operational result, as described herein.

[0020] Additionally, as used herein, elements that are "electrically connected," "electrically coupled," or "in signal communication" may include an electrical transmission or an electrical signal that is sent, received, or communicated by such connected or coupled elements. Further, such electrical couplings or links may include a wired or wireless link or any combination of the foregoing.

[0021] Similarly, as used herein, although sensors may be described as detecting or measuring a respective value, the detection or measurement may include determining a value indicative of or relative to the respective value, instead of directly detecting or measuring the value itself. The detected or measured values ​​may further be provided to additional components. For example, the value may be provided to a control module or processor as defined above, and the control module or processor may perform processing on the value to determine a representative value or an electrical characteristic representative of said value.

[0022] All directional references (e.g., radial, axial, upper, lower, up, down, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, front, rear) are used only for identification purposes to facilitate the reader's understanding of the disclosure, and are not intended as a limitation, particularly with respect to the position, orientation, or use of the related elements. Connection references (e.g., attachment, coupling, link, and junction) are to be interpreted broadly and may include intermediate members between elements and relative movement between elements, unless otherwise indicated.As such, linking references do not necessarily imply that two elements are directly connected and in a fixed relationship with each other. The exemplary drawings are for illustration purposes only and the dimensions, positions, order and relative sizes reflected in the accompanying drawings may vary.

[0023] [Fig. 1] is a cross-sectional diagram of a gas turbine engine 10 for an aircraft. The engine 10 includes, in a downstream series flow relationship, a fan section 12 including a fan 14, a compressor section 15 including a low pressure (LP) booster or compressor 16 and a high pressure (HP) compressor 18, a combustor section 20, and a turbine section 21 including an HP turbine 22 and an LP turbine 24. An HP shaft or spool 26 drivingly connects the HP turbine 22 to the HP compressor 18 and an LP shaft or spool 28 drivingly connects the LP turbine 24 to the LP compressor 16 and the fan 14. The HP turbine 22 includes an HP turbine rotor 30 having turbine blades 32 mounted to a periphery of the HP turbine rotor 30.

[0024] The gas turbine engine 10 may further include an exhaust gas temperature (EGT) sensor 35, illustrated in the diagram. In the example of [Fig. 1], the EGT sensor 35 is configured as an exhaust gas temperature sensor and positioned within the combustion section 20 although this is not necessarily the case. The EGT sensor 35 may also be positioned upstream or downstream of the combustion section 20. In some examples, multiple EGT sensors 35 may be arranged around the engine 10, for example, spaced around a circumference of the engine 10.

[0025] The gas turbine engine 10 may operate such that rotation of the fan 14 draws air into the HP compressor 18. The HP compressor 18 compresses the air and delivers compressed air to the combustion section 20. In the combustion section 20, the compressed air may be mixed with a fuel, and the air / fuel mixture is ignited, expanding and generating high-temperature combustion exhaust gases 34 (not shown in [Fig. 1 ]). The combustion exhaust gases 34 flow downstream, past the EGT sensor 35 and through the HP and LP turbines 22, 24, generating the mechanical force to drive the respective HP and LP spools 26, 28. Finally, the exhaust gases 34 may be expelled from the rear of the engine 10.

[0026] [Fig. 2] illustrates the EGT sensor 35 of [Fig. 1]. In some examples, the EGT sensor 35 may be in signal communication or communicatively coupled with other components of the engine 10. Such signal communication is illustrated by the dotted line. In the illustrated example, the EGT sensor 35 is illustrated as being communicatively coupled to a second EGT sensor 35B similar to the EGT sensor 35, as well as to a control module 36. The EGT sensor 35 may be in signal communication with any suitable component inside or outside the engine 10. In some examples, the control module 36 may be configured to receive a detected or measured temperature, or a value representative or indicative thereof, from the EGT sensor 35. The control module 36 may also perform additional or separate functionality based on the detected or measured temperature.In some examples, the control module 36 may sum, average, or merge temperatures or values ​​received from or provided by multiple sets of temperature sensing probes, including the EGT sensors 35, 35B.

[0027] An exhaust gas passage 44 is illustrated and may be at least partially defined by an engine wall 46 in the turbine engine 10. It is to be understood that the engine wall 46 is illustrated in a schematic view, and the engine wall 46 may have any suitable thickness, geometric profile, or similar element, including hollow portions, solid portions, or coupled wall segments, in some non-limiting examples. The engine wall 46 may include an inner engine wall, an outer engine wall, a combustor liner, a high-pressure turbine housing, a low-pressure turbine housing, or similar elements, in some non-limiting examples.

[0028] The EGT sensor 35 may include a housing 40 forming a first portion 41 and an elongated probe portion 42. In some examples, the elongated probe portion 42 may form an element housing providing structural support for a thermocouple element. In the non-limiting example shown, the first portion 41 may be disposed externally or outside of an exhaust gas passageway 44, while the elongated probe portion 42 may be disposed within or directly exposed to the exhaust gas passageway 44. The EGT sensor 35 may have any suitable configuration. In some non-limiting examples, at least one of the EGT sensor 35, the first portion 41, and the elongated probe portion 42 may be supported by, coupled to, or secured to the engine wall 46. Additionally, although a single continuous engine wall 46 is illustrated, the engine wall 46 may include multiple independent or discrete walls in some examples.

[0029] The elongated probe portion 42 of the housing 40 may define an axial direction 48 as shown. The elongated probe portion 42 may extend into the exhaust gas passage 44. The combustion exhaust gas 34 may flow through the exhaust gas passage 44 and reach the elongated probe portion 42.

[0030] Referring to [Fig. 3], the elongated probe portion 42 of the EGT sensor 35 is illustrated in greater detail. An axial direction 48 may be defined along the elongated probe portion 42. The elongated probe portion 42 may include an outer wall 50 defining an interior 52. In some examples, the outer wall 50 may have an aerodynamically elongated geometric profile. For example, the outer wall 50 may define an airfoil cross-section extending between a leading edge 54 and a trailing edge 56, although this is not necessarily the case. The outer wall 50 may have any suitable geometry, including circular, oval, symmetrical, asymmetrical, or irregular, in non-limiting examples.

[0031] It is contemplated that portions of the housing 40, including the elongated probe portion 42, may include a material having a high temperature capability. As used herein, a "temperature capability" of a material refers to the highest operating temperature contemplated for use of that material, wherein subjecting the material to temperatures higher than its temperature capability may result in effects such as oxidation, fatigue, plastic deformation, or melting of the material. In some examples, the elongated probe portion 42 may have a temperature capability between -56.7°C and 1287.8°C, including between 50°C and 1280°C.In some examples, the elongated probe portion 42 may be fabricated from ceramic matrix composite (CMC), refractory metal, platinum, gain-stabilized platinum, nickel-based superalloy, cobalt-based superalloy, ceramic, monolithic ceramic, combinations of the foregoing, and the like.

[0032] The outer wall 50 may include at least one inlet 58 and at least one outlet 60. The interior 52 of the outer wall 50 may be in fluid communication with the inlet 58 and the outlet 60. In the example shown, the inlet 58 is provided at the leading edge 54, although any position of the inlet 58 may be used. The outlet 60 may be positioned downstream of the leading edge 54. In some examples, multiple inlets 58 or multiple outlets 60 may be provided. In some examples, the inlet 58 may be spaced from the outlet 60 in the axial direction 48. In some examples, the inlet 58 and the outlet 60 may be aligned with each other in the axial direction 48. Any number of inlets 58 and outlets 60 may be provided. Inlet 58 and outlet 60 can also have any suitable geometric profile.In the illustrated example, the inlet 58 is shaped like a slot 59 while the outlet 60 has a generally circular profile, although this is not necessarily the case. In addition, the outlet 60 may have a plurality of openings on the outer wall 50. In some examples, the outlet 60 may include a first set of openings 62 on a first side 64 of the outer wall 50 and a second set of openings 66 on a second side 68 of the outer wall 50 (visible in [Fig. 4]). Each of the first set of openings 62 and the second set of openings 66 may be downstream of the leading edge 54.

[0033] A temperature probe 70 may be provided within the housing 40. The temperature probe 70 may extend in the axial direction 48 through the elongated probe portion 42. In the example shown, the temperature probe 70 includes a distal end 72 that is positioned outside the housing 40, although this is not necessarily the case. In some examples, the distal end 72 of the temperature probe 70 may be positioned completely within the interior 52 of the housing 40. The inlet 58 and outlet 60 may allow combustion gas to reach the temperature probe 70 for measurement.

[0034] [Fig. 4] illustrates a rear perspective view of the elongated probe portion 42. In this view, the second side 68 of the outer wall 50 is visible with the second set of openings 66. Although the illustration shows outlets 60 on opposite sides of the elongated probe portion 42, any positioning for the outlets 60 may be used.

[0035] Referring to [Fig. 5], a cross-sectional view of the elongated probe portion 42 is illustrated along the line VV. The outer wall 50 may also define a chord line 74 between the leading edge 54 and the trailing edge 56. In some examples, the outer wall 50 may be symmetrical about the chord line 74.

[0036] The temperature probe 70 may further include a sensor wire 80 configured to sense or detect a temperature of the combustion exhaust gases 34. In In some examples, a sheath 82 may be provided surrounding the sensor wire 80. The sheath 82 may be spaced from the outer wall 50 of the housing 40.

[0037] The temperature probe 70, including one or both of the sensor wire 80 and the sheath 82, may include a material with a high temperature capability. In some examples, the sensor wire 80 or the sheath 82 may have a temperature capability between -56.7°C and 1287.8°C, including between 50°C and 1280°C. In some examples, the sensor wire 80 or the sheath 82 may include at least one of a refractory metal, platinum, a ceramic, a monolithic ceramic, and a ceramic matrix composite.

[0038] An exhaust gas flow path 86 may pass through the interior 52 of the elongated probe portion 42 extending between the inlet 58 and the at least one outlet 60. In the illustrated example, combustion exhaust gases 34 are shown flowing along the exhaust gas flow path 86 from the inlet 58 to the outlets 60 and reaching the temperature probe 70. The exhaust gas flow path 86 may be at least partially defined between the jacket 82 and the outer wall 50 in some examples. In this manner, the temperature probe 70 may be thermally coupled to the exhaust gas flow path 86. In some examples, the temperature probe 70 may be directly exposed to the exhaust gas flow path 86.In some examples, the distal end 72 may extend outside the housing 40 and reach the combustion exhaust gases 34, wherein the temperature probe 70 may be thermally coupled to the exhaust gas flow path 86 outside the housing 40. Additionally, the exhaust gas flow path 86 may split between the first set of openings 62 and the second set of openings 66 downstream of the inlet 58.

[0039] [Fig. 6] illustrates a cross-sectional view of the elongated probe portion 42 along the line VLVI. In operation, combustion exhaust gases 34 may enter the housing 40 through the inlet 58, flow past the temperature probe 70 between the temperature probe 70 and the outer wall 50, and exit the housing 40 through the at least one outlet 60. In the example shown, the inlet 58 is spaced in the axial direction 48 from the outlet 60, although this is not necessarily the case. Furthermore, in the example shown, the temperature probe 70 is spaced from the outer wall 50 with a constant spacing distance or air gap along the entire elongated probe portion 42.It should be understood that portions of the temperature probe 70 may abut or be coupled to the outer wall 50 without any spacing, or that a variable spacing may be formed between the temperature probe 70 and the outer wall 50, in certain non-limiting examples.

[0040] The aspects described above provide multiple advantages to an improved EGT sensor. The elongated geometric profile of the sensor housing can significantly reduce aerodynamic stresses on the disclosed EGT sensor and reduce an air penetration coefficient for the EGT sensor. In some non-limiting examples, a component stress reduction of between 400% and 750% has been measured for the disclosed EGT sensor with an elongated housing compared to a traditional EGT sensor. In other non-limiting examples, an air penetration coefficient for the disclosed EGT sensor is between 0.15 and 0.6, instead of between 0.3 and 1.2 for a traditional EGT sensor. In other non-limiting examples, a tensile force reduction of 100% has been measured for the disclosed EGT sensor compared to a traditional EGT sensor.Such a reduction in aerodynamic stress can also reduce additional heating of the EGT sensor due to fluid flow impingement, which can reduce component wear, increase part life, and improve sensor accuracy.

[0041] In addition, reducing the aerodynamic resistance of the sensor housing may reduce a pressure drop in the combustion gas flow. Such a reduction in pressure drop may increase the efficiency of the turbine engine during operation, since the disclosed EGT sensor housing results in minimal disturbance to the combustion gas flow while maintaining temperature sensing or detection performance.

[0042] Further, the elongated or contoured sensor housing may have an increased centroidal moment of inertia relative to conventional EGT sensor housings. In one non-limiting example, the centroidal moment of inertia for the disclosed EGT sensor was increased by over 850% relative to a conventional EGT sensor. It should be appreciated that such an increase in the moment of inertia of the EGT sensor may result in a considerable reduction in stresses in the EGT sensor during operation.

[0043] Additionally, the use of high temperature capable materials in the improved EGT sensor may enhance resistance to the hot environment within or directly adjacent to the combustion chamber. Enhancing heat tolerance or resistance through one or both of the elongated housing and the high temperature capable materials may also allow positioning of the disclosed EGT sensor closer to the combustion chamber than traditional EGT sensors. Closer sensor positioning may further improve gas temperature measurement accuracy. In some examples, the disclosed EGT sensor may be coupled to the combustion chamber liner for direct temperature measurement within the combustion chamber. In some examples, the disclosed EGT sensor may be positioned directly adjacent to or downstream of the combustion chamber.

[0044] To the extent not already described, the various features and structures of the various embodiments may be used in combination with each other as needed.

[0045] Further aspects of the disclosure are provided by the subject matter of the following clauses:

[0046] A gas turbine engine, comprising a compressor section, a combustion section, and a turbine section in a series flow arrangement, with at least one of the combustion section and the turbine section having an exhaust gas passage through which combustion exhaust gases flow; and an exhaust gas temperature sensor comprising a housing with an elongate probe portion defining an axial direction and having an outer wall defining an interior and defining an airfoil cross-section extending from a leading edge to a trailing edge, with the elongate probe portion comprising a material with a temperature capability between 50°C and 1280°C;an exhaust gas flow path through the interior of the elongated probe portion 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, with the interior of the elongated probe portion in fluid communication with the inlet and the outlet; and a temperature probe within the housing and thermally coupled to the exhaust gas flow path.;

[0047] The gas turbine engine according to any one of the preceding clauses, wherein the temperature sensor is directly exposed to the exhaust gas flow path.

[0048] The gas turbine engine according to any one of the preceding clauses, wherein the material comprises at least one of a ceramic matrix composite, a refractory metal, a platinum, a gain-stabilized platinum, a nickel-based superalloy, a cobalt-based superalloy, a ceramic, and a monolithic ceramic.

[0049] The gas turbine engine according to any one of the preceding clauses, wherein the inlet comprises a slot.

[0050] The gas turbine engine according to any one of the preceding clauses, wherein the outlet comprises a plurality of openings on the outer wall.

[0051] The gas turbine engine of any preceding clause, wherein the plurality of openings comprises a first set of openings on a first side of the outer wall.

[0052] The gas turbine engine of any preceding clause, wherein the plurality of openings comprises a second set of openings on a second side of the outer wall.

[0053] The gas turbine engine according to any one of the preceding clauses, wherein the first set of openings and the second set of openings are positioned downstream of the leading edge.

[0054] The gas turbine engine of any preceding clause, wherein the exhaust gas flow path splits between the first set of openings and the second set of openings downstream of the inlet.

[0055] The gas turbine engine according to any one of the preceding clauses, wherein the inlet is spaced from the outlet in the axial direction.

[0056] The gas turbine engine of any preceding clause, wherein the outer wall defines a chord line between the leading edge and the trailing edge, with the outer wall being symmetrical about the chord line.

[0057] The gas turbine engine of any preceding clause, wherein the exhaust gas temperature sensor further comprises a sensor wire and a sheath surrounding the sensor wire.

[0058] The gas turbine engine of any preceding clause, wherein the duct is spaced from the outer wall of the housing to at least partially define the exhaust gas flow path through the interior.

[0059] The gas turbine engine according to any one of the preceding clauses, wherein at least one of the sensor wire and the sheath comprises a material with a temperature capability between 50°C and 1280°C.

[0060] The gas turbine engine according to any one of the preceding clauses, wherein at least one of the sensor wire and the sheath comprises at least one of a ceramic matrix composite, a refractory metal, a platinum, a gain-stabilized platinum, a nickel-based superalloy, a cobalt-based superalloy, a ceramic, and a monolithic ceramic.

[0061] The gas turbine engine according to any one of the preceding clauses, wherein the sensor wire comprises platinum.

[0062] The gas turbine engine according to any one of the preceding clauses, wherein the cladding comprises at least one of a ceramic and a ceramic matrix composite.

[0063] The gas turbine engine according to any one of the preceding clauses, wherein one end of the temperature probe is positioned outside the housing.

[0064] The gas turbine engine of any preceding clause, wherein the exhaust gas temperature sensor is coupled to a combustor liner of the combustor.

[0065] The gas turbine engine according to any one of the preceding clauses, wherein the exhaust gas temperature sensor is positioned directly adjacent to the combustion chamber.

[0066] An exhaust gas temperature sensor, comprising a housing with an elongated probe portion comprising at least one of a ceramic, a monolithic ceramic, and a ceramic matrix composite and defining an axial direction, with the elongated probe portion having an outer wall defining an interior and defining an airfoil cross-section extending from a leading edge to a trailing edge, an exhaust gas flow path through the interior of the elongated probe portion 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, with the interior of the elongated probe portion in fluid communication with the inlet and the outlet, and a temperature probe within the housing and thermally coupled to the exhaust gas flow path.

[0067] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein the temperature probe is directly exposed to the exhaust gas flow path.

[0068] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein the inlet comprises a slot and the outlet comprises a plurality of openings on the outer wall.

[0069] The exhaust gas temperature sensor according to any one of the preceding clauses, 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.

[0070] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein the first set of apertures and the second set of apertures are positioned downstream of the leading edge.

[0071] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein the inlet is spaced from the outlet in the axial direction.

[0072] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein one end of the temperature probe is positioned outside the housing.

[0073] The exhaust gas temperature sensor according to any one of the preceding clauses, wherein the outer wall defines a chord line between the edge leading and trailing edge, with the outer wall being symmetrical about the chord line.

[0074] A gas turbine engine, comprising a compressor section, a combustion section, and a turbine section in a series flow arrangement, with at least one of the combustion section and the turbine section having an exhaust gas passage through which combustion exhaust gases flow; and an exhaust gas temperature sensor comprising a housing with an elongate probe portion defining an axial direction and having an outer wall defining an interior and defining an airfoil cross-section extending from a leading edge to a trailing edge, with the elongate probe portion comprising at least one of a ceramic, a monolithic ceramic, and a ceramic matrix composite;an exhaust gas flow path through the interior of the elongated probe portion 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, with the interior of the elongated probe portion in fluid communication with the inlet and the outlet; and a temperature probe within the housing and thermally coupled to the exhaust gas flow path.;

[0075] An exhaust gas temperature sensor, comprising a housing with an elongate probe portion defining an axial direction and having an outer wall defining an interior and defining an airfoil cross-section extending from a leading edge to a trailing edge, with the elongate probe portion comprising a material with a temperature capability between 50°C and 1280°C; an exhaust gas flow path through the interior of the elongate probe portion 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, with the interior of the elongate probe portion in fluid communication with the inlet and the outlet, and a temperature probe within the housing and thermally coupled to the exhaust gas flow path.

Claims

Claims

1. An exhaust gas temperature sensor, comprising: a housing (40) with an elongated probe portion defining an axial direction and having an outer wall (50) defining an interior (52) and defining an airfoil cross-section extending from a leading edge to a trailing edge, with the elongated probe portion comprising a material with a temperature capability between 50°C and 1280°C; an exhaust gas flow path (86) through the interior of the elongated probe portion 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, with the interior of the elongated probe portion in fluid communication with the inlet and the outlet; and a temperature probe (70) within the housing and thermally coupled to the exhaust gas flow path.

2. An exhaust gas temperature sensor according to claim 1, wherein the temperature probe (70) is directly exposed to the exhaust gas flow path (86).

3. An exhaust gas temperature sensor according to claim 1, wherein the inlet (58) comprises a slot (59) and the outlet comprises a plurality of openings on the outer wall (50).

4. The exhaust gas temperature sensor of claim 3, 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.

5. The exhaust gas temperature sensor of claim 4, wherein the first set of apertures and the second set of apertures are positioned downstream of the leading edge.

6. An exhaust gas temperature sensor according to claim 1, wherein the inlet is spaced from the outlet in the axial direction.

7. An exhaust gas temperature sensor according to claim 1, wherein one end of the temperature probe (70) is positioned outside the housing.

8. An exhaust gas temperature sensor according to any preceding claim, wherein the material comprises at least one of a ceramic matrix composite, a refractory metal, a platinum, a gain-stabilized platinum, a nickel-based superalloy, a cobalt-based superalloy, a ceramic, or a monolithic ceramic.

9. An exhaust gas temperature sensor according to any preceding claim, wherein the outer wall (50) defines a chord line between the leading edge and the trailing edge, with the outer wall being symmetrical about the chord line.

10. An exhaust gas temperature sensor according to any preceding claim, further comprises a sensor wire (80) and a sheath (82) surrounding the sensor wire, with the sheath spaced from the exterior wall of the housing to at least partially define the exhaust gas flow path through the interior.

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