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, in general, 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 burnt gases passing through the engine over a multitude of turbine blades. Gas turbine engines have been used for land and water transportation and for power generation, and they are commonly used for aeronautical applications, such as aircraft propulsion.

[0003] During the operation of gas turbine engines, fuel is burned to provide rotational energy and thrust via a set of turbines. To ensure or validate that the gas turbine engine is operating as intended, a temperature sensor probe can be included in the engine, where it is exposed to the exhaust gases. The temperature sensor can measure the temperature of the exhaust gas stream and can provide a signal or measurement value to another system, such as an engine control system. The temperature sensor output can 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 this disclosure, including the best embodiment thereof, intended for those skilled in the art, is presented in the memorandum with reference to the accompanying 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.1] 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 the VV line;

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

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

[0012] Exhaust gas temperature (EGT) sensors generally comprise a housing surrounding a thermocouple element and configured to extend or protrude into a combustion gas flow for measuring temperatures within the flow. EGT sensors immersed within the combustion gas flow produce resistance, aerodynamic blockage, or other flow disturbances in the combustion gases downstream of the EGT sensor due to fluid movement at the sensor housing. Such fluid movements can generate component wear on the EGT sensor as well as fluid vortices, separation, turbulent flow, or other flow disturbances in the combustion gases downstream of the EGT sensor.Such flow disturbances can persist in the flow and reach downstream engine components in the high-pressure turbine, potentially impairing engine performance. The immersed EGT sensor also experiences aerodynamic drag due to its immersion in the combustion gas flow, generating stresses and strains within the housing. These strains can lead to fining, plastic deformation, crack initiation, or crack propagation within the EGT sensor housing.

[0013] Furthermore, EGT sensors are exposed to hot combustion gases, which can be in the range of 500 °F to 2500 °F (260 °C to 1370 °C) or even higher in some examples. Such sensors may be necessary to protect components for To enable accurate measurement of flue gas flow while withstanding hot environments for repeated use. Positioning an EGT sensor as close as possible to the combustion chamber can promote more accurate flue gas temperature measurements; however, temperatures inside or immediately adjacent to the combustion chamber may exceed the sensor materials' tolerance.

[0014] Aspects of the disclosure propose 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 "assembly" or an "assembly" of elements can be any number of elements, including a single element. Furthermore, 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 identical to the direction of fluid flow. The term "front" or "in front" means in front of something, and "back" or "behind" means behind something. For example, when used for fluid flow, the term front / in front can mean upstream, and the term back / behind can mean downstream.

[0016] Furthermore, 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] Furthermore, 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 components that can be used to perform their operation. A control module may include any known processor, microcontroller, or logic device, including, but not limited to: user-programmable pre-broadcast arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital control systems (FADECs), proportional (P) control devices, proportional-integral (PI) control devices, proportional-derivative (PD) control devices, proportional-integral-derivative (PID) control devices, and a device 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 the performance of various processes, functionalities, processing tasks, calculations, comparisons, detections, or measurements of values, or similar elements, 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 similar elements. 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 specific tasks or implementing specific types of abstract data.

[0019] In another non-limiting example, a control module may also include a processor-accessible data storage component, including transient, volatile, non-transient, or non-volatile memory. Other 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 disks, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, and the like, or any suitable combination of memory types. In one example, program code may be stored within memory in a machine-readable format accessible by the processor.Furthermore, memory can store various data, various types of data, various values ​​of detected or measured data, various inputs, various generated or processed data, or various similar items accessible by the processor to provide an instruction, command, or operation to achieve a functional or operational result, as described herein.

[0020] Furthermore, as used herein, elements that are "electrically linked," "electrically coupled," or "in signal communication" may include electrical transmission or an electrical signal that is sent, received, or communicated by such linked or coupled elements. In addition, such electrical couplings or links may include a wired or wireless link or any combination thereof.

[0021] Similarly, as used herein, although sensors may be described as detecting or measuring a respective value, the detection or measurement This may include determining an indicative value 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, superior, inferior, up, down, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, front, rear) are used solely for identification purposes to aid the reader's understanding of the disclosure and do not constitute a limitation, particularly with respect to the position, orientation, or use of related elements. Connecting references (e.g., fastening, coupling, linking, and joining) are to be interpreted broadly and may include intermediate components between elements and relative motion between elements, unless otherwise specified.As such, connecting references do not necessarily mean that two elements are directly linked and in a fixed relationship with each other. The example drawings are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying drawings may vary.

[0023] Figure 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) amplifier or compressor 16 and a high-pressure (HP) compressor 18, a combustion section 20, and a turbine section 21 including an HP turbine 22 and an LP turbine 24. An HP shaft or reel 26 drives the HP turbine 22 to the HP compressor 18, and an LP shaft or reel 28 drives 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 on one 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 inside 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 35 sensors can be arranged around the motor 10, for example, spaced around a circumference of the motor 10.

[0025] The gas turbine engine 10 can operate such that the rotation of the blower 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 can be mixed with 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, passing through the EGT sensor 35 and through the HP and LP turbines 22, 24, generating the mechanical force to drive the respective HP and LP coils 26, 28. Finally, the exhaust gases 34 can be expelled from the rear of the engine 10.

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

[0027] An exhaust gas passage 44 is illustrated and can be at least partially defined by an engine wall 46 in the turbine engine 10. It should be understood that the engine wall 46 is illustrated in a schematic view, and the engine wall 46 can have any suitable thickness, any suitable geometric profile, or any similar feature, including hollow parts, solid parts, or coupled wall segments, in some non-limiting examples. The engine wall 46 can include an inner engine wall, an outer engine wall, a combustion chamber lining, a high-pressure turbine housing, a low-pressure turbine housing, or similar features, in some non-limiting examples.

[0028] The EGT sensor 35 may include a housing 40 forming a first part 41 and an elongated probe part 42. In some examples, the elongated probe part 42 can form a housing for an element providing structural support for a thermocouple element. In the non-limiting example shown, the first portion 41 can be disposed outside or outside an exhaust gas passage 44, while the elongated probe portion 42 can be disposed inside or directly exposed to the exhaust gas passage 44. The EGT sensor 35 can 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 can be supported by, coupled to, or attached to the engine wall 46. Furthermore, although only a single continuous engine wall 46 is shown, the engine wall 46 can include multiple independent or discrete walls in some examples.

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

[0030] With reference to [Fig. 3], the elongated probe portion 42 of the EGT sensor 35 is illustrated in more detail. An axial direction 48 can be defined along the elongated probe portion 42. The elongated probe portion 42 may include an outer wall 50 delimiting an inner portion 52. In some examples, the outer wall 50 may have an aerodynamically elongated geometric profile. For example, the outer wall 50 may define a cross-section of an aerodynamic profile 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, but not limited to, circular, oval, symmetrical, asymmetrical, or irregular.

[0031] It is envisaged that parts of the housing 40, including the elongated probe portion 42, may include a material having a high temperature capacity. As used herein, the "temperature capacity" of a material refers to the highest envisaged operating temperature for the use of that material, at which subjecting the material to temperatures higher than its temperature capacity may produce effects such as oxidation, fatigue, plastic deformation, or melting of the material. In some examples, the elongated probe portion 42 may have a temperature capacity 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 made of ceramic matrix composite (CMC), refractory metal, platinum, gain-stabilized platinum, nickel-based superalloy, cobalt-based superalloy, ceramic, monolithic ceramic, combinations of the above, and similar materials.

[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 fluidic 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 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. The inlet 58 and the outlet 60 can also have any suitable geometric profile.In the illustrated example, the inlet 58 has the shape of a slot 59, while the outlet 60 generally has a circular profile, although this is not necessarily the case. Furthermore, 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 inside 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 inside the interior 52 of the housing 40. The inlet 58 and outlet 60 may allow the 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 represents outlets 60 on opposite sides of the elongated probe portion 42, any positioning for the outlets 60 can be used.

[0035] With reference to [Fig. 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 line 74 between the leading edge 54 and the trailing edge 56. In some examples, the outer wall 50 may be symmetrical with respect to the chord line 74.

[0036] The temperature probe 70 may further include a sensor wire 80 configured to detect or sense 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 capacity. In some examples, the sensor wire 80 or the sheath 82 may have a temperature capacity 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 can pass through the interior 52 of the elongated probe portion 42 extending between the inlet 58 and at least one outlet 60. In the illustrated example, the 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 can be at least partially defined between the sheath 82 and the outer wall 50 in some examples. In this way, the temperature probe 70 can be thermally coupled to the exhaust gas flow path 86. In some examples, the temperature probe 70 can be directly exposed to the exhaust gas flow path 86.In some examples, the distal end 72 can extend outside the housing 40 and reach the combustion exhaust gases 34, in which the temperature probe 70 can be thermally coupled to the exhaust gas flow path 86 outside the housing 40. In addition, the exhaust gas flow path 86 can split between the first set of openings 62 and the second set of openings 66 downstream of the inlet 58.

[0039] Figure 6 illustrates a cross-sectional view of the elongated probe portion 42 along the VLVI line. During operation, the combustion exhaust gases 34 can 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 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 a constant air gap along the entire length of the elongated probe portion 42.It is important to understand that parts of the temperature probe 70 may come into contact with 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 confer 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 lower its drag coefficient. 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, the drag 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 still other non-limiting examples, a 100% reduction in traction force 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 encroachment, which can reduce component wear, increase part life, and improve sensor accuracy.

[0041] Furthermore, reducing the aerodynamic drag of the sensor housing can minimize pressure drop in the combustion gas flow. Such a reduction in pressure drop can increase the efficiency of the operating turbine engine, since the disclosed EGT sensor housing causes minimal disturbance to the combustion gas flow while maintaining temperature detection or sensing performance.

[0042] Furthermore, the elongated or profiled sensor housing can have an increased centroidal moment of inertia compared to traditional EGT sensor housings. In a non-limiting example, the centroidal moment of inertia for the disclosed EGT sensor was increased by more than 850% compared to a traditional EGT sensor. It should be noted that such an increase in the EGT sensor's moment of inertia can lead to a considerable reduction in stresses within the EGT sensor during operation.

[0043] Furthermore, the use of high-temperature-capacity materials in the improved EGT sensor can enhance resistance to the hot environment inside or directly adjacent to the combustion chamber. Increased heat tolerance or resistance through either the elongated housing or the use of high-temperature-capacity materials can also allow the disclosed EGT sensor to be positioned closer to the combustion chamber than conventional EGT sensors. Closer sensor positioning can further improve gas temperature measurement accuracy. In some examples, the disclosed EGT sensor can be coupled to the combustion chamber lining for direct temperature measurement inside the combustion chamber. In some examples, the disclosed EGT sensor may be positioned directly adjacent to or downstream of the combustion chamber.

[0044] Insofar as this has not already been described, the different characteristics and structures of the various embodiments can be used in combination with each other as required.

[0045] Other aspects of 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 elongated probe portion defining an axial direction and having an outer wall delimiting an interior and defining an aerodynamic profile cross-section extending from a leading edge to a trailing edge, with the elongated probe portion comprising a material having a temperature capacity 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 fluidic communication with the inlet and outlet; and a temperature probe inside the housing and thermally coupled to the exhaust gas flow path.

[0047] The gas turbine engine according to any one of the preceding clauses, in which the temperature probe 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 includes a slot.

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

[0051] The gas turbine engine 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.

[0052] The gas turbine engine according to any one of the preceding clauses, 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, in which the first set of openings and the second set of openings are positioned downstream of the leading edge.

[0054] The gas turbine engine according to any one of the preceding clauses, in which 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, in which the inlet is spaced from the outlet in the axial direction.

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

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

[0058] The gas turbine engine according to any one of the preceding clauses, wherein the duct is spaced from the outer wall of the housing to define at least partially 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 capacity 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, in which the sheath 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, in which one end of the temperature probe is positioned outside the housing.

[0064] The gas turbine engine according to any one of the preceding clauses, wherein the exhaust gas temperature sensor is coupled to a combustion chamber lining of the combustion chamber.

[0065] The gas turbine engine according to any one of the preceding clauses, in which 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 delimiting an interior and defining a cross-section of an aerodynamic profile 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 fluidic communication with the inlet and outlet, and a temperature probe inside 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, in which the first set of openings and the second set of openings 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 edge and trailing edge, with the outer wall being symmetrical with respect to 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 elongated probe portion defining an axial direction and having an outer wall delimiting an interior and defining an aerodynamic profile cross-section extending from a leading edge to a trailing edge, with the elongated 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 fluidic communication with the inlet and outlet; and a temperature probe inside the housing and thermally coupled to the exhaust gas flow path.

[0075] An exhaust gas temperature sensor, comprising a housing with an elongated probe portion defining an axial direction and having an outer wall delimiting an interior and defining a cross-section of an aerodynamic profile extending from a leading edge to a trailing edge, with the elongated probe portion comprising a material with a temperature capacity 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 fluidic communication with the inlet and outlet, and a temperature probe inside the housing and thermally coupled to the exhaust gas flow path.

Claims

Demands

1. Exhaust gas temperature sensor, comprising: a housing (40) with an elongated probe portion defining an axial direction and having an outer wall (50) delimiting an interior (52) and defining a cross-section of an aerodynamic profile extending from a leading edge to a trailing edge, with the elongated probe portion comprising a material with a temperature capacity 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 fluidic communication with the inlet and outlet;and a temperature probe (70) inside the housing and thermally coupled to the exhaust gas flow path, characterized in that the temperature probe (70) extends in the axial direction (48) through the elongated probe portion (42) and is directly exposed to the exhaust gas inlet in the elongated probe portion (42).

2. 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).

3. Exhaust gas temperature sensor according to claim 2, 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.

4. Exhaust gas temperature sensor according to claim 3, wherein the first set of openings and the second set of openings are positioned downstream of the leading edge.

5. Exhaust gas temperature sensor according to claim 1, wherein the inlet is spaced from the outlet in the axial direction.

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

7. Exhaust gas temperature sensor according to any one of the preceding claims, 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.

8. Exhaust gas temperature sensor according to any one of the preceding claims, wherein the outer wall (50) defines a chord line between the leading edge and the trailing edge, with the outer wall being symmetrical with respect to the chord line.

9. Exhaust gas temperature sensor according to any one of the preceding claims, further includes a sensor wire (80) and a sheath (82) surrounding the sensor wire, with the sheath spaced from the outer wall of the housing to define at least partially the exhaust gas flow path through the interior.

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