TURBINE ENGINE EXHAUST GAS TEMPERATURE SENSOR

Abstract

A gas turbine engine (10) may have a compressor section (16), a combustor section (20), and a turbine section (18) in a series flow arrangement, the combustor section (20) having a combustion chamber (34) defining an exhaust gas flow path through which a combustion exhaust gas flows. An exhaust gas temperature sensor (40) is located within the exhaust gas flow path. A housing (54) defines an interior (100, 102), a spring (84) located in the interior (100, 102), and a temperature probe (72) extending through the interior (100, 102) and thermally coupled to the exhaust gas flow path. The spring biases a probe housing of the probe against the housing. Figure for abstract: Fig 4

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] TECHNICAL CONTEXT

[0003] Turbine engines, and in particular gas turbine engines, also known as combustion turbine engines, are rotary engines that extract energy from a flow of combustion gases passing through the engine over a multitude of turbine blades. Gas turbine engines are used for land and water locomotion as well as power generation, and are commonly used for aeronautical applications, such as aircraft propulsion.

[0004] During operation of gas turbine engines, fuel is burned to generate a flow of combustion exhaust gases that provides thrust and rotational energy through a set of turbines. To ensure or confirm that the gas turbine engine is operating as desired, 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 exhaust gas temperature and may provide a signal or measurement value to another system, such as an engine control system. The temperature sensor output may also be used, for example, to protect downstream engine components from temperatures that would exceed their design capabilities. BRIEF DESCRIPTION OF THE FIGURES

[0005] A complete and adequate disclosure of the present disclosure, including the best mode thereof, directed to those skilled in the art, is set forth in the specification, which refers to the appended figures, in which:

[0006] [Fig.l] is a sectional view of a gas turbine engine according to various aspects described herein.

[0007] [Fig.2] is a schematic 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.

[0008] [Fig. 3] is an exploded perspective view of the EGT sensor of [Fig. 2] according to various aspects described herein.

[0009] [Fig.4] is a cross-sectional view of the assembled EGT sensor of [Fig.3] according to various aspects described herein. DETAILED DESCRIPTION

[0010] The described embodiments of the present disclosure relate to a temperature sensor and probe assembly. For purposes of illustration, an example environment within 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 unducted fan in non-limiting examples. It will be understood, however, that aspects of the disclosure described herein are not limited thereto and may have general applicability. For example, the disclosure may be applicable to a temperature sensor in other engines or vehicles and may be used to provide benefits in industrial, commercial, and residential applications.

[0011] Exhaust gas temperature (EGT) sensors generally include a housing surrounding a thermocouple element and are configured to extend or project into a combustion gas flow for measuring temperatures in the flow. EGT sensors immersed in the combustion gas flow produce drag and are exposed to strong flow and vibration forces due to fluid movement past the sensor housing. Due to the immersion of the EGT sensors in the combustion gas flow, deformations and stresses may be generated within the housing and these deformations and stresses may produce fining, plastic deformation, crack initiation and / or crack propagation within the EGT sensor housing.Such fluid movements can cause component wear on the EGT sensor, which can increase maintenance time and costs, as well as affect measurement accuracy. In addition, such fluid movements can cause fluid swirls, shedding, turbulent flow, or other flow disturbances in the combustion gases downstream of the EGT sensor, which can negatively affect engine efficiency.

[0012] Furthermore, EGT sensors are exposed to hot combustion gases that can reach a temperature of between 500°C and 2,500°C, or even higher in some examples. Such sensors may be necessary to protect components to enable accurate measurement of combustion gas flows while withstanding the hot environment during repeated use. Positioning the EGT sensor as close as possible to the combustion chamber increases the accuracy of the combustion gas temperature measurements. However, temperatures inside or in the immediate vicinity of the combustion chamber may be greater than those which the sensor materials can withstand.

[0013] Aspects of the disclosure provide an improved EGT sensor capable of operating within the turbine engine combustion chamber environment with potentially increased component life, decreased stress on parts, and / or reduced costs. Turbine engines with the improved EGT sensor described herein may exhibit improved engine efficiency and superior engine efficiency compared to engines using conventional EGT sensors.

[0014] As used herein, the term "set" or a "set" of elements may refer to any number of elements, including a single one. Further, as used herein, the term "upstream" refers to a direction that is opposite to the direction of fluid flow and the term "downstream" refers to a direction that is in the same direction as the fluid flow. The term "in front" or "forward" means in front of something and the term "in back" or "backward" means behind something. For example, when referring to fluid flow, the term "at / forward" may mean upstream and the term "at / backward" may mean downstream.

[0015] Further, as used herein, a "controller" or "controller module" may include a component configured or adapted to provide instruction, control, operation, or any form of communication for operable components to affect the operation thereof. A controller 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 electronic motor control (FADEC), a proportional-derivative (PI) controller, a proportional-derivative (PD) controller, a proportional-integral-derivative (PID) controller, a hardware-accelerated logic controller (e.g., for encoding, decoding, transcoding, etc.), and the like, or any combination thereof.Non-limiting examples of a controller module may be configured or adapted to operate, operate, or otherwise execute program code to achieve operational or functional results, including performing various processes, functionalities, processing tasks, calculations, comparisons, detections or measurements of values, or the like, to enable or perform the 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. false or otherwise. Although “program code” is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., which have the technical effect of performing particular tasks or implementing particular abstract data types. In another non-limiting example, a controller module may also include a data storage component accessible by the processor, including memory, whether transient, volatile, non-transient, or non-volatile memory.Additional 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 drives, universal serial bus (USB) drives, or the like, or any suitable combination of these types of memory. In one example, the program code may be stored in the memory in a machine-readable format accessible by the processor. In addition, the memory may store various data, data types, sensed or measured data values, inputs, generated or processed data, or the like, accessible by the processor in providing an instruction, control, or operation to achieve a functional or operable result, as described herein.

[0016] Further, as used herein, although the sensors may be described as "sensing" or "measuring" a respective value, the sensing or measuring may include determining a value indicative of or related to the respective value, rather than directly sensing or measuring the value itself. The sensed or measured values may further be 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 representative value or electrical characteristic representative of said value. Such forward / backward provision may be via wired or wireless communication, in non-limiting examples.

[0017] 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 assist the reader in understanding the disclosure and do not create limitations, particularly as to the position, orientation, or use thereof. Unless otherwise indicated, references to a connection, e.g., attached, coupled, connected, and joined, are to be interpreted broadly and may include intermediate members between a set of elements and relative movement between elements. Thus, references to a connection do not necessarily imply that these two elements are directly connected and fixed relative to each other. The illustrative drawings are provided for illustration purposes only and the dimensions, positions, order and relative sizes shown in the drawings accompanying this document may vary.

[0018] [Fig. 1] is a schematic cross-sectional diagram of a turbine engine 10 for an aircraft, which may be a gas turbine engine. The turbine engine 10 includes, in a downstream series flow relationship, a fan section 12 including a fan 14, a low pressure (LP) pre-compressor or compressor 16, a high pressure (HP) compressor 18, a combustion section 20, an HP turbine 22, and an LP turbine 24. The combustion section 20 may define a combustion chamber 34. An HP shaft or HP spool 26 drivingly connects the HP turbine 22 to the HP compressor 18, and an LP shaft or LP spool 28 drivingly connects the LP turbine 24 to the LP compressor 16 and the fan 14. The HP turbine 22 includes a rotor 30 having turbine blades 32 mounted at a periphery of the rotor 30.

[0019] The turbine engine 10 may further include an exhaust gas temperature, EGT, sensor 40, shown in a sketch plan. The EGT sensor 40 is positioned within the combustion section 20, although use is contemplated in any advantageous portion of the turbine engine 10. In a non-limiting example, the EGT sensor 40 may also be positioned upstream or downstream of the combustion section 20. In a further non-limiting example, multiple EGT sensors 40 may be arranged around the turbine engine 10, for example, spaced around a circumference of the turbine engine 10 or spaced at different forward or aft positions.

[0020] The turbine engine 10 may operate such that rotation of the fan 14 injects air into the LP compressor 16. The LP compressor 16 and the HP compressor 18 compress the air, and the HP compressor 18 supplies the 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, causing it to expand and generating high-temperature combustion exhaust gases. The combustion exhaust gases flow downstream, past the EGT sensor 40 and through the HP and LP turbines 22, 24, generating the mechanical force necessary to drive the respective HP and LP spools 26, 28. Finally, the combustion exhaust gases may be expelled from the rear of the turbine engine 10.

[0021] [Fig. 2] illustrates a schematic side view of the EGT sensor 40. In some examples, the EGT sensor 40 may be in signal communication or coupled in communication with other components of the turbine engine 10, illustrated by a dotted line as being communicatively coupled with an avionics system 44. The EGT sensor 40 may be in communication with any suitable component inside or outside the turbine engine 10. In one example, a controller module 46 may be configured to receive a sensed or measured temperature, or a value representative or indicative thereof, from the EGT sensor 40. The controller module 46 may also perform additional or separate functionality based on the sensed or measured temperature. In some examples, the controller module 46 may sum, average, or merge temperatures or values received from or provided by multiple sets of temperature sensing probes, including the EGT sensor 40.In another non-limiting example, it is contemplated that multiple EGT sensors 40 are in communication with the avionics system 44, the controller module 46, other parts of the turbine engine or aircraft, or with each other.

[0022] An exhaust gas passage 50 may be defined at least in part by an engine wall 52, which may be a wall within the combustion section 20 of [Fig. 1], for example. In additional non-limiting examples, the engine wall 52 may include an inner engine wall, an outer engine wall, a combustor liner, a low-pressure turbine housing, a high-pressure turbine housing, or the like. Further, a bleed air passage 48 may extend through the engine wall 52, separating the engine wall 52 into an inner shell 36 and an outer shell 38.

[0023] The EGT sensor 40 may include an upper housing portion 54 that is coupled to the engine wall 52 at the outer shell 38, and an element support housing 56 that extends through the inner shell 36 and the outer shell 38, into the combustion exhaust gases 42. With reference to [Fig. 3], the element support housing 56 structurally supports a thermocouple element such as a temperature probe. In the non-limiting example shown, the upper housing portion 54 may be external to the exhaust gas passageway 50, while the element support housing 56 may be disposed within, extend into, or be exposed to the exhaust gas passageway 50. The EGT sensor 40 may have any suitable configuration, including, but not limited to, at least one of the EGT sensor 40, the upper housing portion 54, or the element support housing 56 supported by the engine wall 52.Further, although a single continuous engine wall 52 is illustrated, the engine wall 52 may include multiple independent or distinct walls in certain non-limiting examples with varying or different dimensions than those shown.

[0024] The element support housing 56 may define a housing axis 58 as illustrated. The element support housing 56 may extend into the exhaust gas passage 50. Combustion exhaust gases 42 may flow through the exhaust gas passage 50 and encounter the element support housing 56. In other examples, any suitable fluid or gas may flow within the passage into which the element support housing 56 extends.

[0025] [Fig. 3] shows the EGT sensor 40 in an exploded view, better illustrating the assembly of the EGT sensor 40. The upper housing portion 54 may be separated into an upper body 60 and a lower body 62. A pair of terminals 64 extends from the upper body 60, which may be coupled to the avionics system 44 or the controller module 46 of [Fig. 2]. The pair of terminals 64 may be mounted or otherwise coupled to the upper body 60. In alternative embodiments, any number of terminals, or pairs thereof, are provided, including one terminal, or no terminals when another form of communication is contemplated, such as wireless communication.

[0026] The upper body 60 includes a bottom wall 66 having a solder 68 and a pair of extensions 70. A probe 72 may extend through the bottom wall 66, the solder 68 securing the probe 72, operatively coupled to the terminals 64 within the upper body 60. The solder 68 secures and seals the probe 72 at the bottom wall 66, sealing the interior of the upper body 60. At least a portion of the probe 72 may be coiled or helical, defining a helical portion 88 having a diameter. The lower body 62 includes a base wall 74, a side wall 76 extending from the base wall 74 may be annular. The base wall 74 has a central opening 78, as well as a pair of flanges 80 extending beyond the diameter of the side wall 76. In alternative non-limiting embodiments, an off-center alignment for the central opening 78 is contemplated.A fastening opening 82 is located inside each of the pair of flanges 80.

[0027] When assembled, as shown in [Fig. 4], the lower body 62 is coupled to the upper body 60, encasing at least a portion of the probe 72, a biasing member 84 shown as a wave spring, and at least a portion of a piston 86 within the sidewall 76 of the lower body 62. The biasing member 84 may be coiled or helical, having a diameter that is greater than that of the helical portion 88 of the probe 72. In additional non-limiting examples, it is contemplated that the biasing member 84 may be a wave spring or a Belleville-type spring, or that the biasing member 84 utilizes a non-helical biasing design. The larger diameter of the biasing member 84 allows the biasing member 84 to be positioned around the outside of the probe 72, while remaining within the sidewall 76 of the lower body 62. In alternative embodiments, it is contemplated that the biasing member 84 and the probe 72 are switched, such that the biasing member 84 has a diameter that is less than that of the helical portion 88 of the probe 72.

[0028] The piston 86 may include a piston base wall 90 and a piston side wall 92 extending from the piston base wall 90. The piston side wall 92 may be annular, having a diameter that is greater than the biasing member 84, but less than the side wall 76 of the lower body 62, sized to receive or carry the biasing member 84. The piston side wall 92 may include a pair of grooves 94, configured to align with and receive the pair of extensions 70 extending from the bottom wall 66 of the upper body 60. A piston projection 96 extends from the piston base wall 90, opposite the piston side wall 92, having a diameter sized to be received within the central opening 78 of the lower body 62.A probe opening 98 is positioned in the piston projection 96, providing a space to allow the probe 72 to extend through the probe opening 98.

[0029] Referring to [Fig. 4], the upper body 60 surrounds or envelops an upper interior 100, while the lower body 62 at least partially surrounds or envelops a lower interior 102. The upper body 60 includes the bottom wall 66, which may generally define the upper interior 100 and the lower interior 102. The solder 68 may include a depression 104 facing the lower interior 102. A stack 106 extends from the bottom wall 66 into the upper interior 100 and at least partially defines the solder 68. The bottom wall 66, the base wall 74 of the lower body 62, and the side wall 76 of the lower body 62 collectively define the lower interior 102. Referring to [Fig. 3], the probe 72 may extend at least partially through the stack 106 and be communicatively coupled to the terminals 64.The stack 106 may be crimped to physically secure the probe 72 and a seal solder may be used to seal the solder 68 to the stack 106. In additional embodiments, it is contemplated that the EGT sensor 40 may not have a stack or may have a stack with different geometries than those shown in [Fig. 4].

[0030] A probe housing 110 may be coupled to the piston 86 at the piston projection 96. The probe housing 110 houses the probe 72 which extends into the hot gas flows. In the example shown, the probe 72 is spaced from the probe housing 110 with a constant spacing distance or clearance 112.

[0031] In operation, the biasing member 84 may bias the element support housing 56 against the inner shell 36, (see [Fig. 2]). The biasing force seals the bleed air passage 48 ([Fig. 2]) to prevent the passage of combustion exhaust gases 42 ([Fig. 2]). When operational forces, including, but not limited to, vibrational, thermal, pressure, or other physical forces generated by the exhaust flow within the exhaust gas passage 50 ([Fig. 2]), act on the probe housing 110, these forces are attenuated by the elastic force provided by the biasing member 84 biasing the piston 86. In this way, the biasing member 84 ensures the reduction of stresses exerted on the probe 72 itself, thereby decreasing the total stress to be supported by the probe 72.

[0032] Conventional EGT sensors do not use a spring such as that disclosed herein. These conventional EGT sensors require specialized manufacturing, requiring the sensors to be made of multiple materials in order to provide accurate sensor measurements, while withstanding the operating stresses of the EGT environment. For example, a sensor may have a first upper material that includes increased strength or durability, while the second lower portion, exposed to the EGT environment, has a different material that resists oxidation.

[0033] The aspects described herein provide an improved EGT sensor having multiple advantages. Use of the biasing member 84 described herein may reduce the overall stress to be supported by the probe 72. Therefore, a less specialized probe is required, such as the probe 72 described herein, which may be made of a single material, without sacrificing performance. Therefore, the biasing member 84 may allow for an overall decrease in system cost and complexity, despite the use of the biasing member 84 in addition to the probe 72. In additional non-limiting embodiments, it is contemplated that two or more materials may be used in the probe. In such embodiments, the reduced stresses placed on the probe allow for the use of different or less expensive materials than those currently used.Such materials may further include characteristics different from those generally used, wherein the reduction in stress may allow the use of less durable materials that would otherwise not be suitable for use with the EGT sensor 40. It will be understood that the use of non-homogeneous bimetallic materials for the probe 72 or a sheath for the probe 72 is contemplated.

[0034] A system having a reduced overall weight is further possible, when it is envisaged that the total weight of the biasing element 84 and the probe 72 is less than that of a conventional EGT sensor. Specifically, due to its helical nature, the probe does not need to be as large, wide, tall, or coiled, which may allow for a reduction in the size of the upper housing portion 54 that houses the probe 72. Such a reduction decreases the weight of the system, as well as the overall space occupied by the EGT sensor 40. A smaller housing and sensor may be used, reducing the overall weight and material cost, despite the use of the biasing member 84. In addition, a smaller housing and sensor provide a weight reduction, which may allow for an increase in overall engine efficiency.

[0035] Additionally, the assembly may improve the performance of the EGT sensor, which has strong bonds, including crimps, welds, and rivets. These strong bonds maintain fining strength and margins, reducing overall maintenance cost and time. The less specialized temperature probe further allows the use of different materials for the probe housing 110 or a probe sheath, decreasing material costs without sacrificing performance.

[0036] Furthermore, the EGT sensor can simplify manufacturing. For example, the EGT sensor eliminates or reduces baking of the sealing elements, eliminating helical processing of a multi-material temperature probe, eliminates brazing requirements, reduces overall manufacturing time, eliminates welds and weld macrostructures associated with a specialized probe, and any additional processing of the probe.

[0037] To the extent not already described, the various features and structures of the various embodiments may be used in combination with each other if desired. The fact that a feature cannot be illustrated in all embodiments does not mean that it cannot be, this being for the purpose of ensuring conciseness of the description. Thus, the various features of the different embodiments may be mixed and matched if desired to form new embodiments, whether or not the new embodiments are expressly described. Combinations or permutations of features described herein are covered by this disclosure.

[0038] This written description uses examples to disclose aspects of the disclosure, including the best mode, and also to enable those skilled in the art to practice aspects of the disclosure, including making and using any device or system and carrying out any method incorporated therein.

[0039] Further aspects of the disclosure are provided by the subject matter of the following clauses:

[0040] A gas turbine engine comprising: a compressor section, a combustor section and a turbine section in a series flow arrangement, the combustion chamber section having a combustion chamber defining an exhaust gas flow path through which a combustion exhaust gas flows; and an exhaust gas temperature sensor comprising: a housing defining an interior; a probe housing extending from the housing and movable relative to the housing; and a biasing member biasing the probe housing relative to the housing.

[0041] A gas turbine engine according to any preceding clause wherein the exhaust gas temperature sensor further comprises a probe located in the probe housing and interior.

[0042] A gas turbine engine according to any preceding clause wherein the housing comprises an upper body and a separate lower body.

[0043] A gas turbine engine according to any preceding clause wherein the upper body has a lower wall separating the interior into an upper interior and a lower interior.

[0044] A gas turbine engine according to any preceding clause wherein the bottom wall has an opening and the temperature probe extends through the opening.

[0045] A gas turbine engine according to any preceding clause wherein the opening comprises a recess facing the lower interior and a stack extending into the upper interior at least partially defining the opening.

[0046] A gas turbine engine according to any preceding clause wherein the probe is mounted on the housing at the opening.

[0047] A gas turbine engine according to any preceding clause wherein the exhaust gas temperature sensor further comprises a piston coupled to the probe housing and carrying the biasing member.

[0048] A gas turbine engine according to any preceding clause wherein the piston has a piston projection extending through an opening in the lower body and coupled to the probe housing.

[0049] A gas turbine engine according to any preceding clause wherein the piston includes a sidewall having a width dimensioned to carry the biasing member.

[0050] A gas turbine engine according to any preceding clause wherein the temperature sensor is made of a single material.

[0051] A gas turbine engine according to any preceding clause, further comprising: a piston coupled to the probe and carrying the biasing member, and wherein the housing has an upper body and a lower body separate from the upper body, the upper body has a lower wall separating the interior into an upper interior and a lower interior, and wherein the biasing member is positioned in the lower interior and engages and extends between the bottom wall and a piston base wall so as to urge the probe housing against the housing.

[0052] A gas turbine engine according to any preceding clause wherein the helical portion of the probe is a single turn propeller.

[0053] A gas turbine engine according to any preceding clause wherein the probe is formed from a single material and the helical portion of the probe is a single turn propeller.

[0054] An exhaust gas temperature sensor for determining a temperature in an exhaust gas flow path, the exhaust gas temperature sensor comprising: a housing defining an interior; a probe housing extending from the housing and movable relative to the housing; and a biasing member biasing the probe housing relative to the housing.

[0055] An exhaust gas temperature sensor according to any preceding clause wherein the probe comprises a helical portion located within the spring.

[0056] An exhaust gas temperature sensor according to any preceding clause further comprising a piston located within the interior.

[0057] An exhaust gas temperature sensor according to any preceding clause wherein the housing comprises an upper body and a separate lower body, and wherein the upper body comprises a lower wall separating the interior into an upper interior and a lower interior.

[0058] An exhaust gas temperature sensor according to any preceding clause wherein the bottom wall has an opening and the probe extends through the opening.

[0059] An exhaust gas temperature sensor according to any one of the preceding clauses wherein the temperature probe is made of a single material.

[0060] An exhaust gas temperature sensor for measuring an exhaust gas flow path, the exhaust gas temperature sensor comprising: a housing defining an interior; a biasing member located in the interior; and a temperature probe located at least partially in the interior and having a helical portion located within the biasing member.

[0061] An exhaust gas temperature sensor according to any one of the preceding clauses further comprising a piston located at least partly within the interior.

[0062] An exhaust gas temperature sensor according to any preceding clause wherein the piston has a sidewall dimensioned to carry the biasing member.

Claims

Claims

1. A gas turbine engine (10) comprising: a compressor section (16), a combustor section (20), a turbine section (18) in a series flow arrangement, the combustor section (20) having a combustion chamber (34) defining an exhaust gas flow path through which combustion exhaust gas flows; and an exhaust gas temperature sensor (40) comprising: a housing (54) defining an interior (100, 102), the housing (54) having an upper body (60) and a lower body (62) separated from the upper body (60), the upper body (60) having a bottom wall (66) separating the interior (100, 102) into an upper interior (100) and a lower interior (102); a probe housing (110) extending from the housing (54) and movable relative to the housing (54); a probe (72) located in the probe housing (110) and the interior (100, 102);and a biasing member (84) biasing the probe housing (110) relative to the housing (54).;

2. The gas turbine engine (10) of claim 1, wherein the probe (72) is made of a single material.

3. The gas turbine engine (10) of claim 1, wherein the bottom wall (66) includes a braze (68) and the temperature sensor (110) is coupled to the braze (68).

4. A gas turbine engine (10) according to claim 3, wherein the braze (68) includes a recess (104) facing the lower interior (102), and a stack (106) extending into the upper interior (100) at least partially defining the braze (68).

5. The gas turbine engine (10) of claim 1, wherein the exhaust gas temperature sensor (40) further comprises a piston (86) coupled to the probe housing (110) and carrying the biasing member (84).

6. The gas turbine engine (10) of claim 5, wherein the piston (86) has a piston projection (96) extending through an opening (78) in the housing (54) and coupled to the probe housing (110).

7. The gas turbine engine (10) of claim 6, wherein the piston (86) has a sidewall (92) having a width dimensioned to carry the biasing member (84).

8. An exhaust gas temperature sensor (40) for determining a temperature in an exhaust gas flow path (50), the exhaust gas temperature sensor (40) comprising: a housing (54) defining an interior (100, 102), the housing (54) having an upper body (60) and a separate lower body (62), and the upper body (60) having a bottom wall (66) separating the interior (100, 102) into an upper interior (100) and a lower interior (102); a probe housing (110) extending from the housing (54) and movable relative to the housing (54); a probe (72) located at least partially within the probe housing (110); and a biasing member (84) biasing the probe housing (110) relative to the housing (54).

9. The exhaust gas temperature sensor (40) of claim 8, wherein the probe (72) has a helical portion (88) located within the biasing member (84).

10. The exhaust gas temperature sensor (40) of claim 8, further comprising a piston (86) located within the interior (100, 102) and coupled to the probe housing (110).

11. The exhaust gas temperature sensor (40) of claim 8, wherein the bottom wall (66) includes a solder (68) and the probe (72) is coupled to the solder (68).

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