Turbine engine exhaust temperature sensor

Abstract

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

Description

[0001] Cross-reference to related applications

[0002] This application claims priority to U.S. Provisional Patent Application No. 63 / 292,735, filed December 22, 2021, and U.S. Patent Application No. 17 / 837,102, filed June 10, 2022, which are incorporated herein by reference in their entirety. Technical Field

[0003] This disclosure relates generally to temperature sensors, and more particularly to exhaust temperature sensors in turbine engines. Background Technology

[0004] A turbine engine (and especially a gas turbine engine, also known as a combustion turbine engine) is a rotary engine that extracts energy from the combustion gas flow passing through the engine to multiple turbine blades. Gas turbine engines have been used for mobility and power generation on land and at sea, and are commonly used in aviation applications, such as for propulsion of aircraft.

[0005] During the operation of a gas turbine engine, fuel is burned to provide rotational energy and thrust through a set of turbines. To ensure or validate that the gas turbine engine is operating as expected, a temperature sensor probe may be included in the engine, where it is exposed to the exhaust gas. The temperature sensor measures the temperature of the exhaust stream and can provide signals or measurements to another system, such as the engine control system. For example, the temperature sensor output can be used to protect downstream engine components from temperatures that would exceed their design capabilities. Summary of the Invention

[0006] Technical Solution 1. A gas turbine engine, comprising:

[0007] A compressor section, a combustion section, and a turbine section arranged in series, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows; and

[0008] Exhaust temperature sensor, comprising:

[0009] A housing having an elongated 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 elongated probe portion comprises a material having a temperature capability between 50°C and 1280°C.

[0010] An exhaust flow path extends through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and the outlet; and

[0011] A temperature probe, which is located within the housing and thermally connected to the exhaust flow path.

[0012] Technical Solution 2. The gas turbine engine according to any of the foregoing technical solutions, wherein the temperature probe is directly exposed to the exhaust flow path.

[0013] Technical Solution 3. The gas turbine engine according to any of the foregoing technical solutions, wherein the material comprises at least one of ceramic matrix composite, refractory metal, platinum, gain-stabilized platinum, nickel-based superalloy, cobalt-based superalloy, ceramic or monolithic ceramic.

[0014] Technical Solution 4. The gas turbine engine according to any of the foregoing technical solutions, wherein the inlet is spaced apart from the outlet in the axial direction.

[0015] Technical Solution 5. A gas turbine engine according to any of the foregoing technical solutions, wherein the outer wall defines a chord between the leading edge and the trailing edge, wherein the outer wall is symmetrical about the chord.

[0016] Technical Solution 6. A gas turbine engine according to any of the foregoing technical solutions, wherein the exhaust temperature sensor further includes a sensor wire and a sleeve surrounding the sensor wire, wherein the sleeve is spaced from the outer wall of the housing to at least partially define the exhaust flow path through the interior.

[0017] Technical Solution 7. The gas turbine engine according to any of the foregoing technical solutions, wherein the sensor line comprises platinum.

[0018] Technical Solution 8. A gas turbine engine according to any of the foregoing technical solutions, wherein the axle comprises at least one of ceramic or ceramic matrix composite.

[0019] Technical Solution 9. The gas turbine engine according to any of the foregoing technical solutions, wherein the end of the temperature probe is positioned on the outside of the housing.

[0020] Technical Solution 10. A gas turbine engine according to any of the foregoing technical solutions, wherein the inlet includes a slot and the outlet includes a plurality of openings on the outer wall.

[0021] Technical Solution 11. A gas turbine engine according to any of the foregoing technical solutions, wherein the plurality of openings includes 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.

[0022] Technical Solution 12. The gas turbine engine according to any of the foregoing technical solutions, wherein the first set of openings and the second set of openings are located downstream of the leading edge.

[0023] Technical Solution 13. An exhaust temperature sensor, comprising:

[0024] A housing having an elongated probe portion comprising at least one of ceramic, monolithic ceramic, or ceramic matrix composite and defining an axial direction, wherein the elongated probe portion has an outer wall defining an interior and defining an airfoil section extending from a leading edge to a trailing edge;

[0025] An exhaust flow path extends through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and the outlet; and

[0026] A temperature probe, which is located within the housing and thermally connected to the exhaust flow path.

[0027] Technical Solution 14. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the temperature probe is directly exposed to the exhaust flow path.

[0028] Technical Solution 15. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the inlet is spaced apart from the outlet in the axial direction.

[0029] Technical Solution 16. The exhaust temperature sensor according to any of the foregoing technical solutions, wherein the end of the temperature probe is positioned on the outside of the housing.

[0030] Technical Solution 17. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the outer wall defines a chord between the leading edge and the trailing edge, wherein the outer wall is symmetrical about the chord.

[0031] Technical Solution 18. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the inlet includes a groove and the outlet includes a plurality of openings on the outer wall.

[0032] Technical Solution 19. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the plurality of openings includes 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.

[0033] Technical Solution 20. An exhaust temperature sensor according to any of the foregoing technical solutions, wherein the first set of openings and the second set of openings are located downstream of the leading edge. Attached Figure Description

[0034] The complete and enabling disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, in which:

[0035] Figure 1 These are cross-sectional views of a gas turbine engine based on the various aspects described in this article.

[0036] Figure 2 It is based on the various aspects described in this article that include an exhaust gas temperature (EGT) sensor. Figure 1 A partial cross-sectional view of the combustion section of a gas turbine engine.

[0037] Figure 3 It is based on the various aspects described in this article. Figure 2 Front perspective view of the EGT sensor.

[0038] Figure 4 It is based on the various aspects described in this article. Figure 2 Rear perspective view of the EGT sensor.

[0039] Figure 5 yes Figure 4 A cross-sectional view of the EGT sensor along line VV.

[0040] Figure 6 yes Figure 4 A cross-sectional view of the EGT sensor along line VI-VI. Detailed Implementation

[0041] The embodiments described in this disclosure pertain to temperature sensors and probe assemblies. For illustrative purposes, an exemplary environment in which a temperature sensor may be used will be described in the form of a turbine engine. In a non-limiting example, such a turbine engine may be in the form of a gas turbine engine, a turboprop engine, a turboshaft engine, a turbofan engine, or an open rotor engine. However, it will be understood that aspects of the disclosure described herein are not so limited and may have general applicability. For example, this disclosure may be applicable to temperature sensors used in other engines or vehicles and may provide benefits in industrial, commercial, and residential applications.

[0042] Exhaust gas temperature (EGT) sensors typically include a housing that surrounds a thermocouple element and is configured to extend or protrude into the combustion gas stream for measuring the temperature within the stream. As fluid movement passes through the sensor housing, the EGT sensor immersed in the combustion gas stream experiences drag, aerodynamic blockage, or other flow disturbances in the combustion gas downstream of the EGT sensor. Such fluid movement can cause component wear on the EGT sensor and fluid vortices, shedding, turbulence, or other flow disturbances in the combustion gas downstream of the EGT sensor. These flow disturbances can remain in the stream and encounter downstream engine components in the high-pressure turbine, negatively impacting engine performance. Due to its immersion in the combustion gas stream, the immersed EGT sensor also experiences aerodynamic drag, generating strain and stress within the housing. These stresses can cause creep, plastic deformation, crack initiation, or crack propagation within the EGT housing.

[0043] Additionally, EGT sensors are exposed to hot combustion gases, which in some examples can range from 500℉ to 2500℉ (260°C to 1370°C) or even higher. Such sensors may be necessary to protect components from the thermal environment during repeated use while allowing accurate measurement of the combustion gas flow. Positioning the EGT sensor as close to the burner as possible provides for more accurate combustion gas temperature measurements; however, temperatures within or directly adjacent to the burner can exceed what the sensor material can withstand.

[0044] This disclosure provides an improved aerodynamic EGT sensor capable of operating in a high-temperature turbine engine combustor environment, wherein the impact on downstream fluid flow is reduced, component life is increased, and component stress is reduced. Turbine engines having the improved EGT sensor described herein can exhibit improved engine performance and higher engine efficiency compared to engines using conventional EGT sensors.

[0045] As used herein, the term "group" or a "set" of elements can refer to any number of elements, including only one. Additionally, as used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, and the term "downstream" refers to a direction in the same direction as the fluid flow. The terms "before" or "in front" mean in front of something, and "after" or "behind" means behind something. For example, when used in relation to fluid flow, "before" / "in front" can mean upstream, and "after" / "behind" can mean downstream.

[0046] 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 the direction of a ray extending between the engine's central longitudinal axis and its outer perimeter.

[0047] Additionally, as used herein, a “controller” or “controller module” may include a component configured or adapted to provide instructions, control, operation, or any form of communication to an operable component to achieve its operation. A controller module may include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), and combinations thereof.

[0048] Non-limiting examples of controller modules may be configured or adapted to run, operate, or otherwise execute program code to achieve operational or functional results, including performing various methods, functions, processing tasks, calculations, comparisons, sensing or measurement of values, etc., to enable or accomplish the technical operations or actions described herein. Operational or functional results may be based on one or more inputs, stored data values, sensed or measured values, true or false indications, etc. Although described as "program code," non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a particular task or implementing a particular abstract data type.

[0049] In another non-limiting example, the controller module may also include a processor-accessible data storage component, including memory, whether transient, volatile, or non-transient or non-volatile. Further non-limiting examples of 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 discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc.), or any suitable combination of these types of memory. In one example, program code may be stored in memory in a processor-accessible machine-readable format. Additionally, memory may store various types of data, sensed or measured data values, inputs, generated or processed data, etc., accessible to the processor when instructions, control, or operations are provided to achieve functional or operational results (as described herein).

[0050] Additionally, as used herein, the elements “electrical connection,” “electrical coupling,” or “signal communication” can include the transmission or signaling of electrical connections or couplings to or from such connections or couplings. Furthermore, such electrical connections or couplings can include wired or wireless connections, or combinations thereof.

[0051] Furthermore, as used herein, although a sensor may be described as “sensing” or “measuring” a corresponding value, sensing or measuring may include determining a value that indicates or is related to the corresponding value, rather than directly sensing or measuring the value itself. The sensed or measured value may be further provided to additional components. For example, the value may be provided to a controller module or processor as defined above, and the controller module or processor may perform processing on the value to determine a value that represents or represents an electrical characteristic of the value.

[0052] All directional references (e.g., radial, axial, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, front, rear) are used for identification purposes only to aid the reader's understanding of this disclosure and do not impose limitations (particularly regarding their location, orientation, or use). Connection references (e.g., attachment, joint, connection, and link) are to be interpreted broadly and may include intermediate components between a group of elements and relative movement between elements, unless otherwise indicated. Thus, a connection reference does not necessarily mean that two elements are directly connected and fixed to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the figures attached herein may vary.

[0053] Figure 1This is a schematic cross-sectional view of a gas turbine engine 10 for an aircraft. The engine 10 includes a fan section 12, a compressor section 15, a combustion section 20, and a turbine section 21 arranged in a downstream series relationship. The fan section 12 includes a fan 14. The compressor section 15 includes a supercharger or low-pressure (LP) compressor 16 and a high-pressure (HP) compressor 18. The turbine section 21 includes an HP turbine 22 and an LP turbine 24. An HP shaft or spool 26 drivesably connects the HP turbine 22 to the HP compressor 18, and an LP shaft or spool 28 drivesly connects the LP turbine 24 to the LP compressor 16 and the fan 14. The HP turbine 22 includes an HP turbine rotor 30, which has turbine blades 32 mounted on its periphery.

[0054] The gas turbine engine 10 may also include an exhaust gas temperature (EGT) sensor 35, shown in schematic outline. Figure 1 In the example, the EGT sensor 35 is configured as an exhaust temperature sensor and located within the combustion zone 20, but this is not necessary. The EGT sensor 35 may also be located upstream or downstream of the combustion zone 20. In some examples, multiple EGT sensors 35 may be arranged around the engine 10, for example, spaced around the periphery of the engine 10.

[0055] The gas turbine engine 10 is operable such that the rotation of the fan 14 draws air into the HP compressor 18. The HP compressor 18 compresses the air and delivers the compressed air to the combustion chamber 20. In the combustion chamber 20, the compressed air can be mixed with fuel, and the air / fuel mixture ignites, expands, and produces high-temperature combustion exhaust 34 (not in the combustion chamber). Figure 1 (As shown in the diagram). The combustion exhaust 34 flows downstream, passing through the EGT sensor 35 and the HP turbine 22 and LP turbine 24, generating mechanical force to drive the corresponding HP shaft 26 and LP shaft 28. Finally, the exhaust 34 can be discharged from the rear of the engine 10.

[0056] Figure 2 Show Figure 1The EGT sensor 35. In some examples, the EGT sensor 35 may be in signal communication or communicatively coupled to other components of the engine 10. Such signal communication is shown in dashed lines. In the illustrated example, the EGT sensor 35 is shown communicatively coupled to a second EGT sensor 35B similar to the EGT sensor 35 and a controller 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 controller module 36 may be configured to receive, represent, or indicate the sensed or measured temperature from the EGT sensor 35. The controller module 36 may also perform additional or separate functions based on the sensed or measured temperature. In some examples, the controller module 36 may sum, average, or combine the temperatures or values ​​received from or provided by multiple temperature sensing probe assemblies (including the EGT sensors 35, 35B).

[0057] Exhaust passage 44 is shown and may be at least partially defined by engine wall 46 in turbine engine 10. It should be understood that engine wall 46 is shown schematically, and in some non-limiting examples, engine wall 46 may have any suitable thickness, geometry, etc., including hollow portions, solid portions, or joined wall segments. In non-limiting examples, engine wall 46 may include an inner engine wall, an outer engine wall, a combustor bushing, a high-pressure turbine housing, a low-pressure turbine housing, etc.

[0058] EGT sensor 35 may include a housing 40 forming a first portion 41 and an extended probe portion 42. In some examples, the extended probe portion 42 may be formed as an element housing providing structural support for a thermocouple element. In the illustrated non-limiting example, the first portion 41 may be disposed outside or external to the exhaust passage 44, while the extended probe portion 42 may be disposed within or directly exposed to the exhaust passage 44. EGT sensor 35 may have any suitable configuration. In some non-limiting examples, at least one of EGT sensor 35, first portion 41, or extended probe portion 42 may be supported by, coupled to, or fixed to engine wall 46. Furthermore, although a single continuous engine wall 46 is shown, in some examples, engine wall 46 may include multiple separate or independent walls.

[0059] The extended probe portion 42 of the housing 40 can define an axial direction 48 (as shown). The extended probe portion 42 can extend into the exhaust passage 44. Combustion exhaust 34 can flow through the exhaust passage 44 and encounter the extended probe portion 42.

[0060] Go to Figure 3The extended probe portion 42 of the EGT sensor 35 is shown in further detail. An axial direction 48 may be defined along the extended probe portion 42. The extended probe portion 42 may include an outer wall 50 that defines an interior 52. In some examples, the outer wall 50 may have an aerodynamic elongation geometry. For example, the outer wall 50 may define an airfoil section extending between a leading edge 54 and a trailing edge 56, but this is not necessary. In non-limiting examples, the outer wall 50 may have any suitable geometry, including circular, elliptical, symmetrical, asymmetrical, or irregular.

[0061] It is envisioned that a portion of the housing 40, including the elongated probe portion 42, may comprise a material with high-temperature capability. As used herein, a material's "temperature capability" will refer to the highest operating temperature envisioned for use with that material, where subjecting the material to temperatures exceeding its temperature capability could result in effects such as oxidation, fatigue, plastic deformation, or melting. In some examples, the elongated probe portion 42 may have a temperature capability between -56.7°C and 1287.8°C (inclusive between 50°C and 1280°C). In some examples, the elongated probe portion 42 may be made of ceramic matrix composites (CMC), refractory metals, platinum, gain-stabilized platinum, nickel-based superalloys, cobalt-based superalloys, ceramics, monolithic ceramics, combinations thereof, etc.

[0062] 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 located at the leading edge 54, but any inlet 58 location may be used. The outlet 60 may be located 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 apart 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. The inlets 58 and the outlets 60 may also have any suitable geometric profile. In the example shown, the inlet 58 is in the form of a groove 59, while the outlet 60 has a generally circular profile, but this is not necessary. Additionally, the outlet 60 may include multiple 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. Figure 4 (See below). Each of the first set of openings 62 and the second set of openings 66 is downstream of the leading edge 54.

[0063] Temperature probe 70 may be disposed within housing 40. Temperature probe 70 may extend in the axial direction 48 through elongated probe portion 42. In the illustrated example, temperature probe 70 includes a distal end 72 positioned outside housing 40, but this is not necessary. In some examples, the distal end 72 of temperature probe 70 may be entirely positioned within interior 52 of housing 40. Inlet 58 and outlet 60 provide access for combustion gases to reach temperature probe 70 for measurement.

[0064] Figure 4 A rear perspective view of the elongated probe portion 42 is shown. In this figure, a second set of openings 66 is visible on the second side 68 of the outer wall 50. Although shown as an outlet 60 on the opposite side of the elongated probe portion 42, any positioning of the outlet 60 is possible.

[0065] Now refer to Figure 5 A cross-sectional view of the elongated probe portion 42 is shown along line VV. The outer wall 50 may also define a chord 74 between the leading edge 54 and the trailing edge 56. In some examples, the outer wall 50 may be symmetrical about the chord 74.

[0066] The temperature probe 70 may also include a sensor line 80 configured to sense or detect the temperature of the combustion exhaust gas 34. In some examples, a sleeve 82 may be provided to wrap around the sensor line 80. The sleeve 82 may be spaced apart from the outer wall 50 of the housing 40.

[0067] Temperature probe 70 (including either or both of sensor line 80 or sleeve 82) may comprise a material capable of operating at high temperatures. In some examples, sensor line 80 or sleeve 82 may have a temperature capability between -56.7°C and 1287.8°C (inclusive between 50°C and 1280°C). In some examples, sensor line 80 or sleeve 82 may comprise at least one of refractory metals, platinum, ceramics, monolithic ceramics, and ceramic matrix composites.

[0068] The exhaust flow path 86 can extend through the interior 52 of the extended probe portion 42 (which extends between the inlet 58 and at least one outlet 60). In the illustrated example, the combustion exhaust 34 is shown flowing along the exhaust flow path 86 from the inlet 58 to the outlet 60 and encountering the temperature probe 70. In some examples, the exhaust flow path 86 may be at least partially defined between the sleeve 82 and the outer wall 50. In this way, the temperature probe 70 may be thermally coupled to the exhaust flow path 86. In some examples, the temperature probe 70 may be directly exposed to the exhaust flow path 86. In some examples, the distal end 72 may extend outside the housing 40 and encounter the combustion exhaust 34, wherein the temperature probe 70 may be thermally coupled to the exhaust flow path 86 outside the housing 40. Additionally, the exhaust flow path 86 may be divided downstream of the inlet 58 between a first set of openings 62 and a second set of openings 66.

[0069] Figure 6 A cross-sectional view of the extended probe portion 42 along line VI-VI is shown. During operation, combustion exhaust 34 enters the housing 40 through inlet 58, flows through temperature probe 70 between temperature probe 70 and outer wall 50, and exits the housing 40 through at least one outlet 60. In the example shown, inlet 58 is spaced from outlet 60 in the axial direction 48, but this is not necessary. Furthermore, in the example shown, temperature probe 70 is spaced from outer wall 50 at a constant interval or gap along the entire extended probe portion 42. It will be understood that in some non-limiting examples, portions of temperature probe 70 may be abutted or coupled to outer wall 50 without interval, or a variable interval may be formed between temperature probe 70 and outer wall 50.

[0070] The aspects described above provide for an improved EGT sensor with several benefits. The elongated geometry of the sensor housing significantly reduces aerodynamic stress on the disclosed EGT sensor and also reduces the drag coefficient of the EGT sensor. In some non-limiting examples, a reduction in component stress of between 400% and 750% was measured with respect to the disclosed EGT sensor having an elongated housing compared to a conventional EGT sensor. In other non-limiting examples, the drag coefficient of the disclosed EGT sensor is between 0.15 and 0.6 (compared to the drag coefficient of conventional EGT sensors between 0.3 and 1.2). In still other non-limiting examples, a 100% reduction in drag load was measured with respect to the disclosed EGT sensor compared to a conventional EGT sensor. Such a reduction in aerodynamic stress also reduces additional heating of the EGT sensor due to fluid flow impact, which can reduce component wear, increase part life, and improve sensor accuracy.

[0071] Furthermore, the reduction in aerodynamic drag of the sensor housing reduces the pressure drop in the combustion airflow. This reduction in pressure drop can increase the efficiency of the turbine engine during operation, as the disclosed EGT sensor housing provides minimal disturbance to the combustion airflow while maintaining temperature sensing or detection performance.

[0072] Furthermore, an elongated or streamlined sensor housing can have an increased moment of inertia compared to a conventional EGT sensor housing. In a non-limiting example, the moment of inertia of the disclosed EGT sensor is increased by more than 850% compared to a conventional EGT sensor. It should be understood that such an increase in the moment of inertia of the EGT sensor can provide for significantly reducing stress in the EGT sensor during operation.

[0073] Furthermore, the use of high-temperature-capable materials in the improved EGT sensor provides additional robustness against the thermal environment within or directly adjacent to the burner. Improved thermal resistance or robustness from either or both of the elongated housing or the high-temperature-capable materials also allows for closer positioning of the disclosed EGT sensor to the combustion chamber compared to conventional EGT sensors. Closer sensor positioning further improves the accuracy of gas temperature measurements. In some examples, the disclosed EGT sensor can be coupled to the burner bushing for direct temperature measurement within the combustion chamber. In some examples, the disclosed EGT sensor can be positioned directly adjacent to the burner or downstream of the burner.

[0074] Within the scope not described herein, various features and structures of different embodiments may be used in combination with each other as desired. A feature not shown in all embodiments is not intended to be construed as incapable, but is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as desired to form new embodiments, whether or not the new embodiments are explicitly described. Combinations or permutations of features described herein are covered by this disclosure.

[0075] This written description uses examples to disclose aspects of this disclosure, including the best mode, and also enables any person skilled in the art to implement aspects of this disclosure, including making and using any apparatus or system and performing any combination of methods. The patentable scope of this disclosure is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0076] Further aspects of this disclosure are provided by the subject matter of the following terms:

[0077] A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in series, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows; and an exhaust temperature sensor including a housing having an extended 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 extended probe portion comprises a material having a temperature capability between 50°C and 1280°C; an exhaust flow path extending through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and outlet; and a temperature probe located within the housing and thermally coupled to the exhaust flow path.

[0078] Any of the foregoing provisions for a gas turbine engine in which the temperature probe is directly exposed to the exhaust flow path.

[0079] The gas turbine engine of any of the foregoing provisions, wherein the material includes at least one of ceramic matrix composites, refractory metals, platinum, gain-stabilized platinum, nickel-based superalloys, cobalt-based superalloys, ceramics, or monolithic ceramics.

[0080] Any gas turbine engine as described in the foregoing clauses, wherein the inlet includes a slot.

[0081] Any gas turbine engine as described in the foregoing, wherein the outlet includes multiple openings on the outer wall.

[0082] Any gas turbine engine as described in the foregoing, wherein the plurality of openings includes a first set of openings on a first side of the outer wall.

[0083] Any gas turbine engine as described in the foregoing clauses, wherein the plurality of openings includes a second set of openings on a second side of the outer wall.

[0084] Any gas turbine engine as described in the foregoing clauses, wherein the first set of openings and the second set of openings are located downstream of the leading edge.

[0085] Any gas turbine engine as described in the foregoing clauses, wherein the exhaust flow path is distributed downstream of the inlet between a first set of openings and a second set of openings.

[0086] Any gas turbine engine as described in the foregoing, wherein the inlet is spaced apart from the outlet in the axial direction.

[0087] Any gas turbine engine of the foregoing provisions, wherein the outer wall defines a chord between the leading edge and the trailing edge, wherein the outer wall is symmetrical about the chord.

[0088] Any gas turbine engine as described in the foregoing clauses, wherein the exhaust temperature sensor also includes a sensor wire and a sleeve surrounding the sensor wire.

[0089] Any gas turbine engine of the foregoing provisions, wherein the sleeve is spaced from the outer wall of the housing to at least partially define the exhaust flow path through the interior.

[0090] Any gas turbine engine in the foregoing provisions, wherein at least one of the sensor wires or sleeves comprises a material capable of operating at temperatures between 50°C and 1280°C.

[0091] Any gas turbine engine in any of the foregoing provisions, wherein at least one of the sensor lines or sleeves comprises at least one of a ceramic matrix composite, a refractory metal, platinum, gain-stabilized platinum, a nickel-based superalloy, a cobalt-based superalloy, ceramic, or monolithic ceramic.

[0092] Any gas turbine engine as described in the foregoing clauses, wherein the sensor line includes platinum.

[0093] Any gas turbine engine as described in the foregoing clauses, wherein the housing comprises at least one of ceramic or ceramic matrix composite.

[0094] Any gas turbine engine as described in the foregoing clauses, wherein the end of the temperature probe is positioned on the outside of the housing.

[0095] Any gas turbine engine as described in the foregoing clauses, wherein the exhaust temperature sensor is connected to the burner bushing of the burner.

[0096] Any of the foregoing provisions for a gas turbine engine in which the exhaust temperature sensor is located directly adjacent to the combustor.

[0097] An exhaust temperature sensor includes a housing having an extended probe portion comprising at least one of ceramic, monolithic ceramic, or ceramic matrix composite and defining an axial direction, wherein the extended probe portion has an outer wall defining an interior and defining an airfoil cross-section extending from a leading edge to a trailing edge; an exhaust flow path extending through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and outlet; and a temperature probe residing within the housing and thermally coupled to the exhaust flow path.

[0098] Any exhaust temperature sensor mentioned in the foregoing clauses, wherein the temperature probe is directly exposed to the exhaust flow path.

[0099] The exhaust temperature sensor of any of the foregoing provisions, wherein the inlet comprises a groove and the outlet comprises a plurality of openings on the outer wall.

[0100] The exhaust temperature sensor of any of the foregoing provisions, wherein the plurality of openings includes 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.

[0101] The exhaust temperature sensor of any of the foregoing provisions, wherein the first set of openings and the second set of openings are located downstream of the leading edge.

[0102] The exhaust temperature sensor of any of the foregoing provisions, wherein the inlet is spaced from the outlet in the axial direction.

[0103] The exhaust temperature sensor of any of the foregoing provisions, wherein the end of the temperature probe is positioned on the outside of the housing.

[0104] The exhaust temperature sensor of any of the foregoing provisions, wherein the outer wall defines a chord between the leading and trailing edges, wherein the outer wall is symmetrical about the chord.

[0105] A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in series, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows; and an exhaust temperature sensor including a housing having an extended 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 extended probe portion comprises at least one of ceramic, monolithic ceramic, or a ceramic matrix composite; an exhaust flow path extending through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and outlet; and a temperature probe located within the housing and thermally coupled to the exhaust flow path.

[0106] An exhaust temperature sensor includes a housing having an extended 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 extended probe portion comprises a material having a temperature capability between 50°C and 1280°C; an exhaust flow path extending through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and outlet; and a temperature probe residing within the housing and thermally coupled to the exhaust flow path.

Claims

1. A gas turbine engine, comprising: A compressor section, a combustion section and a turbine section arranged in series, wherein at least one of the combustion section or the turbine section has an exhaust passage through which combustion exhaust flows; as well as Exhaust temperature sensor, comprising: A housing having an elongated 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 elongated probe portion comprises a material having a temperature capability between 50°C and 1280°C, and wherein the outer wall defines a chord extending from the leading edge to the trailing edge, and wherein a first length extends along the chord between the leading edge and the interior; An exhaust flow path extends through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and the outlet, and wherein a portion of the exhaust flow path extends along the first length from the inlet to the interior; and A temperature probe, which is located within the housing and thermally connected to the exhaust flow path.

2. The gas turbine engine according to claim 1, wherein, The temperature probe is directly exposed to the exhaust flow path.

3. The gas turbine engine according to claim 1, wherein, The material includes at least one of ceramic matrix composites, refractory metals, platinum, gain-stabilized platinum, nickel-based superalloys, cobalt-based superalloys, ceramics, or monolithic ceramics.

4. The gas turbine engine according to claim 1, wherein, The inlet is spaced apart from the outlet in the axial direction.

5. The gas turbine engine according to claim 1, wherein, The outer wall is symmetrical about the chord.

6. The gas turbine engine according to claim 1, wherein, The exhaust temperature sensor also includes a sensor wire and a sleeve wrapped around the sensor wire, wherein the sleeve is spaced from the outer wall of the housing to at least partially define the exhaust flow path through the interior.

7. The gas turbine engine according to claim 6, wherein, The sensor line comprises platinum.

8. The gas turbine engine according to claim 7, wherein, The set includes at least one of ceramic or ceramic matrix composite.

9. The gas turbine engine according to claim 1, wherein, The end of the temperature probe is positioned on the outside of the housing.

10. The gas turbine engine according to any one of claims 1-9, wherein, The inlet includes a groove, and the outlet includes a plurality of openings on the outer wall.

11. The gas turbine engine according to claim 10, wherein, The plurality of openings includes 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. The gas turbine engine according to claim 11, wherein, The first set of openings and the second set of openings are located downstream of the leading edge.

13. An exhaust temperature sensor, comprising: A housing having an elongated probe portion comprising at least one of ceramic, monolithic ceramic, or ceramic matrix composite and defining an axial direction, wherein the elongated 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 extending from the leading edge to the trailing edge, and wherein a first length extends along the chord between the leading edge and the interior; An exhaust flow path extends through the interior of the extended probe portion and 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 extended probe portion is in fluid communication with the inlet and the outlet, and wherein a portion of the exhaust flow path extends along the first length from the inlet to the interior; as well as A temperature probe, which is located within the housing and thermally connected to the exhaust flow path.

14. The exhaust temperature sensor according to claim 13, wherein, The temperature probe is directly exposed to the exhaust flow path.

15. The exhaust temperature sensor according to claim 13, wherein, The inlet is spaced apart from the outlet in the axial direction.

16. The exhaust temperature sensor according to claim 13, wherein, The end of the temperature probe is positioned on the outside of the housing.

17. The exhaust temperature sensor according to claim 13, wherein, The outer wall is symmetrical about the chord.

18. The exhaust temperature sensor according to any one of claims 13-17, wherein, The inlet includes a groove, and the outlet includes a plurality of openings on the outer wall.

19. The exhaust temperature sensor according to claim 18, wherein, The plurality of openings includes 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. The exhaust temperature sensor according to claim 19, wherein, The first set of openings and the second set of openings are located downstream of the leading edge.

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