System and method for removably inserting a sensor assembly into a compressor housing

Abstract

The present invention is entitled "System and method for removably inserting a sensor assembly into a compressor casing." A measurement system (13) for a gas turbine engine (11) is provided herein. The measurement system (13) includes a sensor assembly (48). The measurement system (13) also includes a plurality of sensors (64) coupled to the sensor assembly (48). The sensor assembly (48) is configured to be removably inserted into a space defined by a circumferential track (44, 52, 54) embedded within the inner diameter of a compressor casing (42) of the gas turbine engine (11) without having to disassemble the compressor casing (42).

Description

Background Art

[0001] The subject matter disclosed herein relates to gas turbine systems, and more particularly, to systems and methods for removably inserting a sensor assembly into a casing of a gas turbine system.

[0002] Gas turbines are used to generate electricity for a variety of applications. These gas turbines are typically tested and validated before being used (e.g., in a power plant). Effective testing and validation can improve the efficiency and productivity of the gas turbine and, consequently, the power plant. Measurement systems can sometimes be invasively coupled to the gas turbine, requiring the turbine to be disassembled to connect the measurement system and / or holes to be introduced into the casing for the sensors. Furthermore, removing the measurement system may also require disassembling the casing and / or shutting down the gas turbine. Consequently, testing and validating gas turbines can be time-consuming and expensive, and may risk damaging the gas turbine engine. Summary of the Invention

[0003] Certain embodiments comparable in scope to the initially claimed subject matter are summarized below. These embodiments are not intended to limit the scope of the claimed subject matter, but rather are intended only to provide a brief overview of possible forms of the subject matter. Indeed, the subject matter may include various forms that may be similar or different from the embodiments set forth below.

[0004] In one embodiment, a measurement system for a gas turbine engine is provided. The measurement system includes a sensor assembly. The measurement system also includes a plurality of sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted into a space defined by a circumferential track embedded within the inner diameter of a casing of the gas turbine engine without requiring disassembly of the casing.

[0005] In another embodiment, a system is provided. The system includes a gas turbine engine comprising a compressor, the compressor comprising a compressor housing having an inner diameter, a combustor downstream of the compressor, and a turbine downstream of the combustor. The gas turbine engine also includes a circumferential track embedded within the inner diameter of the compressor housing, wherein the circumferential track extends around at least a portion of the inner diameter of the compressor housing in a circumferential direction relative to a longitudinal axis of the gas turbine engine. The system also includes a measurement system. The measurement system includes a sensor assembly comprising a plurality of sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted into the circumferential track without having to disassemble the compressor housing.

[0006] In another embodiment, a method is provided. The method includes inserting a sensor assembly having a plurality of sensors into a cavity formed by a circumferential track embedded within an inner diameter of a compressor casing of a gas turbine engine without disassembling the compressor casing. The method also includes acquiring baseline data via the plurality of sensors for use in verifying operation of the gas turbine engine independently of a control system for the gas turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] These and other features, aspects, and advantages of the present subject matter will be better understood when the following detailed description is read with reference to the accompanying drawings, in which like characters represent like parts throughout, and in which:

[0008] Figure 1 is a block diagram of an embodiment of a turbine system having a removable aerodynamic measurement system;

[0009] Figure 2 is a removable aerodynamic measurement system such as Figure 1 a cross-sectional side view of an embodiment of the turbine system shown;

[0010] Figure 3 is a perspective view of an embodiment of an inner surface of a portion of a casing (e.g., a compressor casing) for a gas turbine engine having a plurality of circumferential tracks;

[0011] Figure 4 is Figure 3 A perspective view of an embodiment of a portion of a circumferential track embedded in the inner surface of the housing, taken within line 4-4;

[0012] Figure 5 is a top schematic diagram of an embodiment of a sensor assembly disposed within a cavity defined by a circumferential track;

[0013] Figure 6 yes Figure 1 A schematic diagram of an embodiment of a measuring system of the invention, the measuring system being inserted into a cavity defined by a circumferential track and an inner surface of a housing;

[0014] Figure 7 is a schematic diagram of an embodiment of a port coupled to a cavity defined by a circumferential track and an inner surface of a housing;

[0015] Figure 8 It is the use of Figure 1 A flow chart of an embodiment of a method of a measurement system;

[0016] Figure 9 is a schematic diagram of an embodiment of a sensor socket coupled to a guide tube;

[0017] Figure 10is a schematic diagram of an embodiment of a sensor coupled to a portion of a cable;

[0018] Figure 11 is connected to the cable Figure 10 A schematic diagram of an embodiment of a sensor;

[0019] Figure 12 is connected to Figure 9 The sensor socket Figure 10 Schematic diagram of the sensor in;

[0020] Figure 13 is a schematic diagram of an embodiment of a guide tube for a sensor, the guide tube extending from a port into a cavity between a circumferential track and an inner surface of a housing; and

[0021] Figure 14 It extends from the port Figure 13 Schematic diagram of an embodiment of a guide tube. DETAILED DESCRIPTION

[0022] One or more specific embodiments will be described below. In order to provide a concise description of these embodiments, not all features of an actual implementation may be described in the specification. It should be understood that in the development of any such actual implementation, as in any engineering or design project, many implementation-specific decisions must be made to achieve the developer's specific goals, such as complying with system-related and business-related constraints, which may vary from implementation to implementation. Furthermore, it should be understood that such development work may be complex and time-consuming, but remains a routine task for design, fabrication, and manufacturing for those of ordinary skill having the benefit of this disclosure.

[0023] When introducing elements of various embodiments of the present disclosure, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the elements. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements.

[0024] Embodiments of the present disclosure include a measurement system (e.g., an aerodynamic measurement system) for verifying the operation of a gas turbine engine. The measurement system may include a sensor assembly (e.g., a line, a tube, or a chain) to which a plurality of sensors are coupled. The sensor assembly is configured to be inserted into a circumferential track embedded within the inner diameter of a casing (e.g., a compressor casing) of the gas turbine engine. Specifically, the sensor assembly is inserted into a space or cavity defined between the inner diameter of the casing and the circumferential track. The circumferential track extends in a circumferential direction relative to the longitudinal axis of the gas turbine engine. The sensor assembly is configured to be inserted and / or removed via a single port without disassembling the casing and / or shutting down the engine, the single port being coupled to and communicating with the space or cavity formed by the circumferential track.

[0025] The measurement system can collect validation data (e.g., data associated with one or more operating parameters of the gas turbine engine) independently of the control system used for the gas turbine engine. Furthermore, the data collected by the measurement system can be collected after the sensor assembly is removed from the housing, thereby avoiding the use of slip rings or telemetry. The measurement system can be rapidly deployed. Furthermore, the measurement system is configured for use with gas turbine engines of varying sizes and from different manufacturers.

[0026] Go to the attached figure, Figure 1 is a block diagram of an embodiment of a turbine system 10 having a gas turbine engine 11. For reference, the gas turbine engine 11 may be axially oriented in an axial direction 30 (eg, relative to a longitudinal axis 36 of the gas turbine engine 11, see Figure 2 ), radial directions 32 toward or away from the longitudinal axis 36, and circumferential directions 34 about the longitudinal axis 36. As described in detail below, the disclosed turbine system 10 employs a removable measurement system 13 (e.g., an aerodynamic measurement system). The measurement system 13 may include a sensor assembly (wire or tube or chain) to which a plurality of sensors are coupled that measure various operating parameters used to provide baseline data in verifying the operation of the gas turbine engine 11. The measurement system 13 operates independently of the control system for the gas turbine engine 11. In certain embodiments, the measurement system 11 may be coupled to the control system of the gas turbine engine 11 to enable real-time monitoring and / or control.

[0027] The sensor assembly can be removably and quickly inserted into a space or cavity defined by a circumferential track embedded within the inner surface or diameter of a casing (e.g., a compressor casing) of the gas turbine engine 11. The circumferential track extends in a circumferential direction 34 relative to the longitudinal axis 36 of the gas turbine engine 11. In certain embodiments (e.g., Figure 3), the housing may include a plurality of circumferential tracks spaced apart from one another in the axial direction 30. The sensor assembly may be utilized in any of the circumferential tracks. In certain embodiments, the measurement system 13 may include a plurality of sensor assemblies, each having a plurality of sensors, wherein the sensor assemblies may be inserted into the plurality of circumferential tracks.

[0028] The number of sensors may range from tens to hundreds to thousands of sensors. At least some of the sensors may employ optical devices and / or optical fibers. The operating parameters measured by the sensors may include blade tip timing (e.g., for displacement, stress, frequency, etc.), blade tip clearance, temperature, dynamic pressure, static pressure, rotor vibration, stall detection, and rotor speed. The sensors may acquire data, and once the sensor assembly is removed from the circumferential track, data may be collected from the sensors, thereby avoiding the need for slip rings or telemetry. In certain embodiments, an extension of the wiring may be connected from the exterior of the gas turbine engine 11 to the measurement system 13 to enable real-time monitoring.

[0029] The turbine system 10 can use liquid or gaseous fuels, such as natural gas and / or synthetic gas, to drive the turbine system 10. As shown, one or more fuel nozzles 12 in the combustor 16 draw in a fuel supply 14, partially mix the fuel with air, and distribute the fuel and air-fuel mixture to the combustor 16, where further mixing occurs between the fuel and air. The air-fuel mixture is burned in a chamber within the combustor 16, thereby producing hot pressurized exhaust gas. The combustor 16 guides the exhaust gas through a turbine 18 toward an exhaust outlet 20. As the exhaust gas passes through the turbine 18, the gas drives the turbine blades to rotate a shaft 22 along the axis of the turbine system 10. As shown, the shaft 22 is connected to various components of the turbine system 10, including a compressor 24. The compressor 24 also includes blades coupled to the shaft 22. The blades in the compressor 24 rotate as the shaft 22 rotates, thereby compressing air from an air inlet 26 through the compressor 24 and compressing the air into the fuel nozzles 12 and / or the combustor 16. The shaft 22 may also be connected to a load 28 , which may be a vehicle or a stationary load such as, for example, a generator in a power plant or a propeller on an aircraft. The load 28 may include any suitable device capable of being powered by the rotational output of the turbine system 10 .

[0030] Figure 2 Yes Figure 1A cross-sectional side view of an embodiment of the gas turbine engine 11 is shown. The gas turbine engine 11 has a longitudinal axis 36. In operation, air enters the gas turbine engine 11 through the air intake 26 and is pressurized in the compressor 24. The compressed air is then mixed with gas for combustion within the combustor 16. For example, the fuel nozzle 12 can inject the fuel-air mixture into the combustor 16 at a suitable ratio to achieve optimal combustion, emissions, fuel consumption and / or power output. The combustion process produces hot pressurized exhaust gases, which then drive turbine blades 38 within the turbine 18 to rotate the shaft 22 and thereby the compressor 24 and the load 28. The rotation of the turbine blades 38 causes the shaft 22 to rotate, thereby causing blades 40 (e.g., compressor blades) within the compressor 24 to draw in and pressurize the air received by the air intake 26.

[0031] As shown, a housing 42 (e.g., a compressor housing) surrounds blades 40 (and stator blades) of compressor 24. Housing 42 may include multiple sections (e.g., two halves) that together extend completely around longitudinal axis 36 to define the interior of compressor 24. A circumferential track 44 is embedded within an inner surface or diameter 46 of housing 42. Measurement system 13 includes a sensor assembly 48 having a plurality of sensors disposed within a space or cavity defined between circumferential track 44 and inner diameter 46 of housing 42. Sensor assembly 48 is at least slightly flexible or bendable, enabling it to flex in a circumferential direction 34 when disposed within the space or cavity. Circumferential track 44 is disposed axially 30 between rows of stator blades (not separately numbered) such that circumferential track 44 and the sensors of sensor assembly 48 are in the plane of (and aligned axially 30 with) the rotating blades 40. Circumferential track 44 extends in a circumferential direction 34 around at least a portion of inner diameter 46 of housing 42. In certain embodiments, the circumferential track 44 extends around the entire inner diameter 46 of the housing 42 .

[0032] Figure 31 is a perspective view of an embodiment of an inner surface 46 of a portion of a casing 42 (e.g., a compressor casing) for a gas turbine engine 11 having a plurality of circumferential tracks 44. Stator blades and corresponding slots for receiving the stator blades are not shown. The number of circumferential tracks 44 may vary. In certain embodiments, the number of circumferential tracks 44 may correspond to the number of stages of blades 40. In other embodiments, the number of circumferential tracks 44 may be less than or greater than the number of stages of blades 40. As shown, the circumferential tracks 44 are axially 30 spaced apart from each other relative to the longitudinal axis 36. As described above, each circumferential track 44 is axially 30 disposed between rows of stator blades such that the corresponding circumferential track 44 and the sensors of the sensor assembly 48 are in the plane of the rotating blades 40 (and aligned axially 30 with the rotating blades). Each circumferential track 44 extends in the circumferential direction 34 around at least a portion of the inner diameter 46 of the casing 42. In certain embodiments, at least one of the circumferential tracks 44 extends around the entire inner diameter 46 of the casing 42.

[0033] In some embodiments, the circumferential track 44 is a single segment 50 as depicted by circumferential track 52. In other embodiments, the circumferential track 44 may include multiple segments 50 as depicted by circumferential track 54. Each circumferential track 44 includes an opening 56 that allows the sensor of the sensor assembly 48 (see also FIG. 1 ) to be inserted into the space defined by the circumferential track 44 and the inner diameter 46 of the housing 42. Figure 5 ) can face the interior of the compressor 24 (e.g., toward the blades 40). The openings 56 may include a larger opening 58 and a smaller opening 60 sized for a specific sensor. In certain embodiments, the openings 56 may be aligned in the circumferential direction 34 or the axial direction 30. Each opening 56 represents a measurement point consisting of a sensor head and a sensor socket for receiving the sensor head, as described in more detail below. The openings 56 provide a viewport for the corresponding sensor head when inserted into the sensor socket. The position of each sensor socket can be permanently fixed. Each sensor socket can be integrated into the circumferential track 44 or directly embedded into the inner diameter 46 of the housing 42.

[0034] like Figure 4 As shown, a space or cavity 62 is defined between the circumferential track 44 and the inner surface 46 of the housing 42. The sensor assembly 48 can be inserted and / or removed into the space or cavity 62. Figure 5 As shown, the sensors 64 coupled to the sensor assembly 48 are spaced or spatially arranged such that when the sensor assembly 48 is fully inserted into the space or cavity 62 , the sensors 64 are aligned with the openings 56 on the circumferential track 44 .

[0035] Figure 6FIG1 is a schematic diagram of measurement system 13 inserted into cavity 62 defined by circumferential rail 44 and inner surface 46 of casing 42. As indicated by arrow 66, sensor assembly 48 having sensor 64 is inserted into the cavity defined by circumferential rail 44 and inner surface 46 of casing 42 from outside casing 42 (e.g., when the entire gas turbine engine 11 is assembled) via a single port 68 coupled to cavity 62. Sensor assembly 48 is fed through port 68 and bent in circumferential direction 34 within cavity 62. As indicated by arrow 70, sensor assembly 48 can be removed in the opposite direction via the same port 68.

[0036] As shown, the port 68 (e.g., funnel) is external to the housing 42. In certain embodiments, such as Figure 7 As shown, housing 42 defines a port 72 that extends into cavity 62 defined by circumferential rail 44 and interior surface 46 of housing 42. An external port (e.g., a funnel, such as port 68) may be inserted into port 72 to help guide insertion and / or removal of sensor assembly 48 from within space or cavity 62.

[0037] In certain embodiments, where the inner surface 46 of the housing 42 has more than one circumferential track 44, the housing 42 may include multiple ports, with a single port dedicated to (i.e., for exclusive use of) each respective circumferential track 44 for insertion and / or removal of a respective sensor assembly 48. In other embodiments, where the circumferential track 44 includes two or more segments 50, a plurality of ports 72 may be provided in communication with respective cavities 62 defined by the cavities 62 of the segments 50.

[0038] Figure 8 is a flow chart of an embodiment of a method 74 for utilizing the measurement system 13. The method 74 includes inserting the sensor assembly 48 having the sensor 64 into the cavity 62 formed by the circumferential rail 44 and the inner diameter 46 of the casing 42 without having to disassemble the casing 42 and / or without having to shut down the gas turbine engine 11 (block 76). The insertion occurs via a single port coupled to or in communication with the cavity 62.

[0039] The method 74 also includes acquiring baseline data via the sensors 64 (e.g., during operation of the gas turbine engine 11) for use in verifying the operation of the gas turbine engine 11 (block 78). The data is acquired independently of the control system of the gas turbine engine 11. Is the data stored in memory?

[0040] The method 74 also includes removing the sensor assembly 48 from the cavity 62 (eg, via the same port used for insertion) without disassembling the housing 42 and / or without shutting down the gas turbine engine 11 (block 80 ).

[0041] Method 74 also includes collecting acquired baseline data from sensor 64 after removing sensor assembly 48 from cavity 62 (block 82). In other embodiments, data may be collected from sensor 64 in real time while sensor assembly 48 remains installed within cavity 62 of circumferential track 44.

[0042] Figure 9 is a schematic diagram of an embodiment of a sensor receptacle 84 coupled to a guide tube 86. Each sensor receptacle 84 may be integrated within the circumferential track 44 or embedded directly within the inner diameter 46 of the housing 42. The position of each sensor receptacle 84 may be permanently fixed. The sensor receptacle 86 includes a sensor viewport or opening 88 (e.g., Figures 3 to 5 86 is a circumferentially extending member 84 that extends from the housing 42 to the exterior of the housing 42. The guide tube 86 is a circumferentially extending member 86 ...

[0043] The sensor receptacle 84 includes an alignment feature 92 (e.g., a clock key) for orienting the sensor head within the sensor receptacle 84 so that the sensor head is aligned with the viewport 88. The sensor head includes a corresponding feature (e.g., a keyway) for engaging the alignment feature 92. The operator may need to twist the cable associated with the sensor head to align the alignment feature and the keyway. In some embodiments, the sensor receptacle 84 and / or the sensor head may include a self-aligning feature that automatically rotates the sensor head to the correct orientation.

[0044] The sensor receptacle 84 also includes a feature 94 (e.g., a locking feature) for locking the inserted sensor head. In some embodiments, the feature 94 can be a one-time, irreversible locking feature. In other embodiments, the feature 94 can be a reversible locking feature that can be overcome by a force or released by an unlocking mechanism. Figure 9 As shown, feature 94 includes one or more spring loaded ball detents 96 (e.g., Figure 9 (Two ball detents are shown in FIG. ). Each ball detent 96 includes a ball 98 and one or more springs 100. The spring-loaded ball detents 96 engage corresponding features in the sensor head. The spring load of the balls 98 is sufficient to prevent accidental pulling on the sensor cable from dislodging the sensor head from the sensor receptacle 84. In some embodiments, an intentional and sufficient pulling force can overcome the spring-loaded ball detents 96 to release the sensor head from the sensor receptacle 84.

[0045] Figure 10 and Figure 11 1 is a schematic diagram of an embodiment of a sensor 102 coupled to a cable 104. Specifically, the sensor 102 is part of a sensor head 106 coupled to the cable 104. The sensor head 106 includes a corresponding alignment feature 108 (e.g., a keyway slot) that, when interacting with the alignment feature 92, enables the sensor 102 to be aligned with the viewport 88 as described above. The sensor head 106 also includes a corresponding locking feature 110 (e.g., a ball detent locking feature) that interacts with the locking feature 94 to lock the sensor head 106 in place with the sensor receptacle 84. For example, the corresponding locking feature 110 includes a groove 112 on an outer surface 114 of the sensor head 106.

[0046] The cable 104 serves as a conduit for transmitting the signal 116 from the sensor to a remotely located data logging system. The signal may be optical, electrical, or any other form of data / power transmission. The end 118 of the cable 104 opposite the sensor head 106 includes a connector interface 120 (see Figure 11 ) to interact with the data recording system 122.

[0047] The semi-flexible, semi-rigid cable 104 connected to the sensor head 106 enables the operator to push the sensor head 106 (and the cable 104) down the length of the guide tube 86. When the sensor head 106 reaches the sensor receptacle 84, the operator will initially feel resistance as the sensor head 106 pushes against the spring-loaded ball stop 96. With a reasonable amount of force, the sensor head 106 will seat in the sensor receptacle 84 and the ball stop 96 will engage the sensor head 106, as shown in FIG. Figure 12 In addition, Figure 12 As shown, due to the interaction between the alignment features 92, 108, the sensor 102 is aligned with the sensor viewport 88. The same cable 104 also enables the sensor head to be removed from the guide tube 86. For example, if the sensor 102 fails or at the end of a test, the operator can retract the sensor head 106 from the guide tube 86 by pulling on the cable 104 attached to the sensor head 106. In some embodiments, the sensor head 106 and / or the sensor receptacle 84 may include a release feature to unlock the sensor head 106 from the sensor receptacle 84.

[0048] The operator can confirm that the sensor head 106 is seated in a variety of ways. In some embodiments, the sensor head 106 is seated via the operator's feel and experience with how the ball detent 96 operates. In other embodiments, the operator can receive feedback from the sensor 102 indicating that the operator can see the target (i.e., the sensor receptacle 84). In some embodiments, the sensor head 106 and / or the sensor receptacle 84 can be equipped with simple electrical contacts that provide confirmation that the sensor head 106 is properly seated (e.g., by completing an electrical circuit).

[0049] Figure 13 Schematic diagram of an embodiment of a guide tube 86 for a sensor 102 that extends from a port 72 into a cavity between the circumferential track 44 and the inner surface 46 of the housing 42. As shown, only a portion of the housing 42 and the circumferential track 44 are shown. The circumferential track 44 includes a plurality of sockets 84 (e.g., sockets A, B, C, D, and E) for receiving the sensors 102. In certain embodiments, the sockets 84 may be embedded in the inner surface 46 of the housing 42. The housing 42 includes an opening or port 72 as described above that extends from the cavity between the circumferential track 44 and the inner surface 46 of the housing 42 to the outer surface of the housing 42. An external port, socket, or funnel 68 is disposed within the port 72 and extends from the cavity between the circumferential track 44 and the inner surface 46 of the housing 42 to the exterior of the housing 42. As shown Figure 13 shown (and in Figure 14 4 (described in more detail in ), multiple guide tubes 86 for multiple sensors 102 (e.g., sensors A, B, C, D, and E) can be disposed within the cavity between the circumferential track 44 and the inner surface 46 of the housing 42 (as described above) and extend from the external port 68. An operator feeds the sensor heads 106 through the external port 68 into appropriate guide tubes 86 accessible on the exterior of the housing 42. In embodiments having multiple guide tubes 86, the guide tubes can be marked or mapped. In certain embodiments, instead of guide tubes 86, discrete channels can be made within the circumferential track 44 for receiving the sensor heads 106 and associated sensor cables 104.

[0050] The technical effects of the disclosed embodiments include providing an aerodynamic measurement system that can be quickly deployed on a gas turbine engine to obtain baseline data for verifying the operation of the gas turbine engine. The measurement system can collect data independently of the control system for the gas turbine engine. The measurement system includes a sensor assembly having a plurality of sensors coupled thereto. The sensor assembly can be inserted into and subsequently withdrawn from a cavity or space defined between a circumferential track embedded within the inner surface of a casing and the inner surface of the casing (e.g., via the same port). The sensor assembly can be inserted and removed without having to disassemble the gas turbine engine. This enables baseline data to be collected without having to utilize slip rings or telemetry. The measurement system is suitable for use with gas turbine engines of different sizes and from different manufacturers. In addition, the measurement system can reduce the cost and time associated with testing and verifying gas turbine engines.

[0051] This written description uses examples to disclose the disclosed subject matter, including the best mode, and also to enable any person skilled in the art to practice the disclosed subject matter, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosed subject matter is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims

1. A measurement system (13) for a gas turbine engine (11), comprising: sensor assembly (48); and A plurality of sensors (64) are coupled to the sensor assembly (48), wherein the sensor assembly (48) is configured to be removably inserted into a space defined by a circumferential track (44, 52, 54) embedded within an inner diameter of a casing (42) of the gas turbine engine (11) without having to disassemble the casing (42).

2. The measurement system (13) of claim 1, wherein the sensor assembly (48) is configured to be inserted into and removed from the housing (42) via a single port (72) coupled to the circumferential track (44, 52, 54).

3. The measurement system (13) of claim 1, wherein the measurement system (13) is configured to acquire baseline data for use in verifying operation of the gas turbine engine (11).

4. The measurement system (13) of claim 3, wherein the measurement system (13) is configured such that the baseline data is collected from the plurality of sensors (64) after the sensor assembly (48) is removed from the housing (42).

5. The measurement system (13) of claim 1, wherein the measurement system (13) is configured to operate independently of a control system of the gas turbine engine (11).

6. The measurement system (13) of claim 1, wherein the sensor assembly (48) is configured to extend along at least a portion of the circumference (34) of the housing (42) within the space defined by the circumferential track (44, 52, 54) relative to the longitudinal axis (36) of the gas turbine engine (11).

7. The measurement system (13) of claim 1, wherein each sensor (64) of the plurality of sensors (64) is spatially arranged such that each sensor (64) is configured to align with a corresponding opening (56) of a plurality of openings (56) on the circumferential track (44, 52, 54) facing an interior defined by the housing (42) when the sensor assembly (48) is inserted into the space.

8. The measurement system (13) of claim 1, wherein the housing (42) comprises a compressor housing.

9. A system comprising: A gas turbine engine (11), comprising: a compressor (24) comprising a compressor housing (42) having an inner diameter; a combustor (16) downstream of the compressor (24); a turbine (18) downstream of the combustor (16); and a circumferential track (44, 52, 54) embedded within an inner diameter of the compressor casing (42), wherein the circumferential track (44, 52, 54) extends around at least a portion of the inner diameter of the compressor casing (42) in a circumferential direction (34) relative to a longitudinal axis (36) of the gas turbine engine (11); and A measuring system (13), comprising: a sensor assembly (48); and A plurality of sensors (64) are coupled to the sensor assembly (48), wherein the sensor assembly (48) is configured to be removably inserted into the circumferential track (44, 52, 54) without having to disassemble the compressor housing (42).

10. The system of claim 9, wherein the circumferential track (44, 52, 54) is configured to enclose the sensor assembly (48) within a cavity defined by the circumferential track (44, 52, 54) and the inner diameter of the compressor housing (42) when the sensor assembly (48) is disposed within the circumferential track (44, 52, 54).

11. The system of claim 9, wherein the compressor housing (42) includes a single port (72) for both inserting and removing the sensor assembly (48) into and from the circumferential track (44, 52, 54).

12. The system of claim 11, further comprising a funnel (68) for engaging the single port (72), the funnel (68) being configured to facilitate insertion and removal of the sensor assembly (48).

13. The system of claim 9, wherein the circumferential track (44, 52, 54) includes a plurality of openings (56) facing the interior of the compressor (24) and spaced apart along the circumferential track (44, 52, 54) in the circumferential direction (34), and each sensor (64) of the plurality of sensors (64) is spatially arranged such that each sensor (64) is configured to align with a corresponding opening (56) of the plurality of openings (56) when the sensor assembly (48) is inserted into the circumferential track (44, 52, 54).

14. The system of claim 9, wherein the measurement system (13) is configured to acquire baseline data for use in verifying operation of the gas turbine engine (11).

15. The system of claim 9, wherein the measurement system (13) is configured to operate independently of a control system of the gas turbine engine (11).

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