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

Abstract

To provide a measurement system (13) for a gas turbine engine (11).SOLUTION: The measurement system (13) comprises a sensor assembly (48). The measurement system (13) also includes multiple 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 in an inner diameter of a compressor casing (42) of the gas turbine engine (11) without having to disassemble the compressor casing (42).SELECTED DRAWING: Figure 2

Description

Technical Field

[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.

Background Art

[0002] Gas turbines are used to generate power for various applications. Typically, tests and verifications are performed before these gas turbines are utilized (e.g., at a power plant). Effective tests and verifications can improve the efficiency and productivity of the gas turbine as well as the power plant. In some cases, a measurement system may be invasively coupled to the gas turbine, which requires the disassembly of the turbine for the coupling of the measurement system and / or the introduction of holes for sensors into the casing. In addition, the removal of the measurement system may also require the disassembly of the casing and / or the shutdown of the gas turbine. Therefore, testing and verifying gas turbines can be time-consuming and costly, and there may be a risk of damaging the gas turbine engine.

Summary of the Invention

[0003] Certain embodiments corresponding to the scope of the claimed subject matter are summarized below. These embodiments are not intended to limit the scope of the claimed subject matter; rather, these embodiments are only intended to provide an overview of possible forms of the subject matter. Indeed, the subject matter can encompass various forms that may be similar to or different from the embodiments described 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 the casing of the gas turbine engine without the need to disassemble the casing.

[0005] In another embodiment, a system is provided. The system includes a compressor including a compressor casing having an inner diameter, a combustor downstream of the compressor, and a gas turbine engine including a turbine downstream of the combustor. The gas turbine engine also includes a circumferential track embedded within the inner diameter of the compressor casing, the circumferential track extending circumferentially around at least a portion of the inner diameter of the compressor casing with respect to the longitudinal axis of the gas turbine engine. The system also includes a measurement system. The measurement system includes a sensor assembly and a plurality of sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted into the circumferential track without the need to disassemble the compressor casing.

[0006] In a further 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 the inner diameter of a compressor casing of a gas turbine engine without the need to disassemble the compressor casing. The method also includes obtaining baseline data for verifying the operation of the gas turbine engine independently of a control system of the gas turbine engine via the plurality of sensors.

[0007] These and other features, aspects, and advantages of the present subject matter will be better understood upon reading the following detailed description with reference to the accompanying drawings. In the accompanying drawings, like reference numerals represent like parts throughout the drawings.

Brief Description of the Drawings

[0008]

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Best Mode for Carrying Out the Invention

[0009] One or more specific embodiments will be described below. Despite efforts to provide a concise description of these embodiments, it is not possible to describe all features of the actual implementation in this specification. In the development of an actual implementation, such as an engineering or design project, numerous implementation-specific decisions must be made to achieve the developer's specific objectives, for example, to address system-related and business-related constraints, and it should be understood that these constraints may vary from one implementation to another. Furthermore, such development efforts are complex and time-consuming, but it should be understood that they are still routine work in design, fabrication, and manufacturing for those skilled in the art who will benefit from this disclosure.

[0010] When introducing elements of various embodiments of the present disclosure, the articles "a," "an," "the," and "said" are intended to mean that there is one or more of such elements. The terms "comprising," "including," and "having" are intended to be inclusive and to mean that there may be additional elements other than those listed.

[0011] 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 wire rope, 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. In particular, 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 circumferentially with respect to the longitudinal axis of the gas turbine engine. The sensor assembly is configured to be coupled to and communicate with the space or cavity formed by the circumferential track through a single port and inserted and / or removed without disassembling and / or stopping the casing.

[0012] The measurement system can collect verification data (e.g., data related to one or more operating parameters of the gas turbine engine) independently of a control system for the gas turbine engine. Additionally, since the data collected by the measurement system can be collected after removing the sensor assembly from the casing, the use of slip rings or telemetry methods is avoided. The measurement system can be deployed quickly. Additionally, the measurement system is configured to be utilized with gas turbine engines of different sizes and from different manufacturers.

[0013] Referring to the figures, FIG. 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 can extend in an axial direction 30 (e.g., with respect to the longitudinal axis 36 of the gas turbine engine 11, see FIG. 2), a radial direction 32 toward or away from the longitudinal axis 36, and a circumferential direction 34 around the longitudinal axis 36. As will be 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 rope or tube or chain) coupled with a plurality of sensors that measure various operating parameters used to provide baseline data when verifying the operation of the gas turbine engine 11. The measurement system 13 operates independently of the control system of the gas turbine engine 11. In certain embodiments, the measurement system 13 can be coupled to the control system of the gas turbine engine 11 to enable real-time monitoring and / or control.

[0014] The sensor assembly can be removably and quickly inserted into a space or cavity defined by a circumferential track embedded within or within the diameter of the casing (e.g., compressor casing) of the gas turbine engine 11. The circumferential track extends in the circumferential direction 34 with respect to the longitudinal axis 36 of the gas turbine engine 11. In certain embodiments (shown in FIG. 3), the casing may include a plurality of circumferential tracks spaced apart from each other in the axial direction 30. The sensor assembly can 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, and the sensor assemblies can be inserted into the plurality of circumferential tracks.

[0015] The number of sensors can range from dozens to hundreds or thousands of sensors. At least some of the sensors can employ an optical system and / or an optical fiber. The operating parameters measured by the sensors can include the timing of the blade tip (e.g., displacement, stress, frequency, etc.), the clearance of the blade tip, temperature, dynamic pressure, static pressure, rotor vibration, stall detection, and rotor speed. The sensors can acquire data, and since the data can be collected from the sensors when the sensor assembly is removed from the circumferential track, the need for slip rings or telemetry methods is avoided. In certain embodiments, an extension of the cable wiring can be coupled from outside the gas turbine engine 11 to the measurement system 13 to enable real-time monitoring.

[0016] The turbine system 10 can use a liquid or gas fuel such as natural gas and / or synthetic gas to drive the turbine system 10. As shown, one or more fuel nozzles 12 within the combustor 16 take in the 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 burns in the combustion chamber within the combustor 16 to produce high-temperature, pressurized exhaust gas. The combustor 16 sends the exhaust gas through the turbine 18 toward the exhaust outlet 20. As the exhaust gas passes through the turbine 18, the gas applies a force to the turbine blades, rotating the 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 the compressor 24. The compressor 24 also includes blades coupled to the shaft 22. As the shaft 22 rotates, the blades within the compressor 24 also rotate, thereby compressing the air passing through the compressor 24 from the air intake 26 and sending it to 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 within a power generation plant or an aircraft propeller. The load 28 may include any suitable device that can be powered by the rotational output of the turbine system 10.

[0017] Figure 2 is a cross-sectional side view of an embodiment of the gas turbine engine 11 shown in FIG. 1. The gas turbine engine 11 has a longitudinal axis 36. During operation, air enters the gas turbine engine 11 through the intake 26 and is pressurized within the compressor 24. Next, the compressed air is mixed with gas for combustion within the combustor 16. For example, the fuel nozzle 12 can inject a fuel-air mixture into the combustor 16 at an appropriate ratio for optimal combustion, emissions, fuel consumption, and / or power output. The combustion process produces hot pressurized exhaust gases, which then drive the turbine blades 38 within the turbine 18 to rotate the shaft 22, and thus rotate the compressor 24 and the load 28. The rotation of the turbine blades 38 causes the rotation of the shaft 22, whereby the blades 40 (e.g., compressor blades) within the compressor 24 draw in and pressurize the air received by the intake 26.

[0018] As shown, a casing 42 (e.g., a compressor casing) surrounds the blades 40 (and stator vanes) of the compressor 24. The casing 42 may include a plurality of sections (e.g., two halves) that extend completely around each other about the longitudinal axis 36 to define the interior of the compressor 24. A circumferential track 44 is embedded within the inner surface of the casing 42 or within the diameter 46. The measurement system 13 includes a sensor assembly 48 having a plurality of sensors disposed within a space or cavity defined between the circumferential track 44 and the inner diameter 46 of the casing 42. The sensor assembly 48 is at least slightly flexible or bendable such that it can be bent in the circumferential direction 34 when disposed within the space or cavity. The circumferential track 44 is axially disposed 30 between rows of stator vanes (not individually numbered), and thus the sensors of the circumferential track 44 and the sensor assembly 48 are in the plane of the rotating blade 40 (and axially aligned 30 with the rotating blade 40). The 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, the circumferential track 44 extends around the entire inner diameter 46 of the casing 42.

[0019] FIG. 3 is a perspective view of one 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. The stator vanes and their respective slots for receiving them are not shown. The number of circumferential tracks 44 can vary. In certain embodiments, the number of circumferential tracks 44 can correspond to the number of stages of the blades 40. In other embodiments, the number of circumferential tracks 44 can be less than or greater than the number of stages of the blades 40. As shown, the circumferential tracks 44 are arranged axially 30 and spaced from each other with respect to the longitudinal axis 36. As described above, each circumferential track 44 is arranged axially 30 between rows of stator vanes, and thus each circumferential track 44 and the sensors of the sensor assembly 48 are in the plane of the rotating blade 40 (and aligned axially 30 with the rotating blade 40). Each circumferential track 44 extends circumferentially 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.

[0020] In certain embodiments, the circumferential track 44 is a single segment 50 as illustrated by circumferential track 52. In other embodiments, the circumferential track 44 may include a plurality of segments 50 as illustrated by circumferential track 54. Each circumferential track 44 includes an opening 56 that enables a sensor of the sensor assembly 48 (see also FIG. 5) to face the interior of the compressor 24 (e.g., the blades 40) when the sensor assembly 48 is properly inserted into the space defined by the circumferential track 44 and the inner diameter 46 of the casing 42. The opening 56 can include a larger opening 58 and a smaller opening 60 that are sized for a particular sensor. In certain embodiments, the opening 56 can be aligned in the circumferential direction 34 or the axial direction 30. Each opening 56 represents a measurement point that consists of a sensor head and a sensor receptacle for receiving the sensor head, as will be described in more detail below. The opening 56 provides a viewport for each sensor head when inserted into the sensor receptacle. The position of each sensor receptacle can be permanently fixed. Each sensor receptacle can be integrated within the circumferential track 44 or directly embedded within the inner diameter 46 of the casing 42.

[0021] As illustrated in FIG. 4, a space or cavity 62 is defined between the circumferential track 44 and the inner surface 46 of the casing 42. The sensor assembly 48 can be inserted into and / or removed from the space or cavity 62. As illustrated in FIG. 5, the sensors 64 coupled to the sensor assembly 48 are spaced or spatially arranged such that the sensors 64 are aligned with the openings 56 on the circumferential track 44 when the sensor assembly 48 is fully inserted into the space or cavity 62.

[0022] FIG. 6 is a schematic view of a measurement system 13 inserted into a cavity 62 defined by a circumferential track 44 and an inner surface 46 of a casing 42. A sensor assembly 48 with a sensor 64 is inserted into the cavity defined by the circumferential track 44 and the inner surface of the casing 42 through a single port 68 coupled to the cavity 62 from the outside of the casing 42 (e.g., with the entire gas turbine engine 11 assembled), as indicated by arrow 66. The sensor assembly 48 is supplied through port 68 and curves circumferentially 34 within cavity 62. The sensor assembly 48 can be removed in the opposite direction through the same port 68, as indicated by arrow 70.

[0023] As shown, port 68 (e.g., a funnel) is external to the casing 42. In certain embodiments, as shown in FIG. 7, the casing 42 defines a port 72 that extends into a cavity 62 defined by the circumferential track 44 and the inner surface 46 of the casing 42. Inserting an external port (e.g., a funnel such as port 68) into port 72 can assist in guiding the insertion and / or removal of the sensor assembly 48 from within the space or cavity 62.

[0024] In certain embodiments, if the inner surface 46 of the casing 42 has two or more circumferential tracks 44, the casing 42 may include a plurality of ports each with a single port dedicated (i.e., for exclusive use) to each respective circumferential track 44 for insertion and / or removal of each respective sensor assembly 48. In other embodiments, if the circumferential track 44 includes two or more segments 50, the plurality of ports 72 may be arranged in communication with each respective cavity 62 defined by the cavity 62 of the segment 50.

[0025] FIG. 8 is a flowchart of one embodiment of a method 74 for using the measurement system 13. The method 74 includes inserting a sensor assembly 48 having a sensor 64 into a cavity 62 formed by a circumferential track 44 and an inner diameter 46 of a casing 42 without the need to disassemble the casing 42 and / or without the need to stop the gas turbine engine 11 (block 76). The insertion is performed through a single port coupled to or in communication with the cavity 62.

[0026] The method 74 also includes obtaining baseline data (e.g., during operation of the gas turbine engine 11) for verifying the operation of the gas turbine engine 11 via the sensor 64 (block 78). The data is obtained independently of the control system of the gas turbine engine 11. The data is stored in a memory.

[0027] The method 74 further includes removing the sensor assembly 48 from the cavity 62 (e.g., through the same port used for insertion) without the need to disassemble the casing 42 and / or without the need to stop the gas turbine engine 11 (block 80).

[0028] Furthermore, the method 74 includes collecting the baseline data obtained from the sensor 64 after removing the sensor assembly 48 from the cavity 62 (block 82). In other embodiments, the data can be collected from the sensor 64 in real time while the sensor assembly 48 remains installed within the cavity 62 of the circumferential track 44.

[0029] FIG. 9 is a schematic view of one embodiment of a sensor receptacle 84 coupled to a guide tube 86. Each sensor receptacle 84 can be integrated within the circumferential track 44 or directly embedded within the inner diameter 46 of the casing 42. The position of each sensor receptacle 84 can be permanently fixed. The sensor receptacle 84 includes a sensor viewport or opening 88 (e.g., the opening 56 of FIGS. 3-5) that provides a viewport for the sensor head when the sensor head is inserted within the sensor receptacle 84. The sensor receptacle 84 is coupled to a guide tube 86 that includes an internal passage 90 for receiving the sensor head. The guide tube 86 has an inner diameter 91 that is larger than the sensor passing through. The guide tube 86 is generally flexible or semi-flexible to allow for wiring. As will be described in more detail below, the guide tube 86 is circumferentially wired within a machined passage within the casing 42 to a point that reaches outside through a port within the casing, thereby providing access. In a particular embodiment, the guide tube 86 may be inside the track 44 installed in the inner diameter 46 of the casing 42.

[0030] The sensor receptacle 84 includes an alignment function 92 (e.g., a clocking key) for orienting the sensor head within the sensor receptacle 84 such that the sensor head is aligned with the viewport 88. The sensor head includes a corresponding function (e.g., a keyway) that engages the alignment function 92. The operator may need to twist the cable associated with the sensor head to align the alignment function and the keyway. In a particular embodiment, the sensor receptacle 84 and / or the sensor head may include a self-aligning function that automatically pivots the sensor head to the appropriate orientation.

[0031] The sensor receptacle 84 also includes a feature 94 (e.g., a locking feature) for locking the inserted sensor head. In certain 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 force or released by an unlocking mechanism. As shown in FIG. 9, the feature 94 is one or more spring-loaded ball detents 96 (e.g., two ball detents are shown in FIG. 9). Each ball detent 96 includes a ball 98 and one or more springs 100. The spring-loaded ball detents 96 engage corresponding features within the sensor head. The spring load of the balls 98 is sufficient to prevent the sensor cable from being inadvertently pulled and the sensor head from disengaging from the sensor receptacle 84. In certain embodiments, an intentional and sufficiently large pulling force can overcome the spring-loaded ball detents 96 and release the sensor head from the sensor receptacle 84.

[0032] FIGS. 10 and 11 are schematic views of one embodiment of a sensor 102 coupled to a cable 104. In particular, 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 enables alignment of the sensor 102 with the viewport 88 as described above when interacting with the alignment feature 92. 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 a predetermined position with the sensor receptacle 84. For example, the corresponding locking feature 110 includes a groove 112 on the outer surface 114 of the sensor head 106.

[0033] The cable 104 functions as a conduit for signals 116 to pass from the sensor to a remotely located data recording system. The signals can 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 FIG. 11) that interfaces with the data recording system 122.

[0034] The semi-flexible, semi-rigid cable 104 connected to the sensor head 106 allows the operator to push the sensor head 106 (and cable 104) down to the length of the guide tube 86. When the sensor head 106 reaches the sensor receptacle 84, the operator first feels resistance when the sensor head 106 presses against the spring-loaded ball detent 96. As shown in FIG. 12, with a moderate amount of force, the sensor head 106 seats within the sensor receptacle 84 and the ball detent 96 engages the sensor head 106. Additionally, as illustrated in FIG. 12, the sensor 102 aligns with the sensor viewing port 88 due to the interaction between the alignment features 92, 108. The same cable 104 also allows for removal of the sensor head from the guide tube 86. For example, if the sensor 102 fails or at the end of a test, the operator can pull out the sensor head 106 from the guide tube 86 by pulling on the cable 104 attached to the sensor head 106. In certain embodiments, the sensor head 106 and / or the sensor receptacle 84 may include a release feature that unlocks the sensor head 106 from the sensor receptacle 84.

[0035] The operator can confirm that the sensor head 106 is seated in several ways. In certain embodiments, the sensor head 106 seats via the operator's sense of touch and the operator's experience regarding how the ball detent 96 operates. In other embodiments, the operator can receive feedback from the sensor 102 indicating that the target (i.e., the sensor receptacle 84) can be seen. In some embodiments, the sensor head 106 and / or the sensor receptacle 84 may include simple electrical contacts that provide confirmation (e.g., via completion of an electrical circuit) that the sensor head 106 is properly seated.

[0036] FIG. 13 is a schematic view of one embodiment of a guide tube 86 for a sensor 102 extending from port 72 into a cavity between the circumferential track 44 and the inner surface 46 of the casing 42. Only a portion of the casing 42 and the circumferential track 44 are shown as illustrated. The circumferential track 44 includes several receptacles 84 (e.g., receptacles A, B, C, D, and E) for receiving the sensor 102. In a particular embodiment, the receptacles 84 can be embedded in the inner surface 46 of the casing 42. The casing 42 includes the opening or port 72 as described above that extends from the cavity between the circumferential track 44 and the inner surface 46 of the casing 42 to the outer surface of the casing 42. The external port, receptacle, 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 casing 42 to the outside of the casing 42. As shown in FIG. 13 (and more particularly in FIG. 14), a plurality of guide tubes 86 for a plurality of 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 casing 42 (as described above) and extend from the external port 68. The operator supplies the sensor head 106 to an appropriate guide tube 86 accessible from the outside of the casing 42 through the external port 68. In an embodiment with a plurality of guide tubes 86, the guide tubes can be labeled or mapped. In a particular embodiment, instead of the guide tube 86, a separate passage for receiving the sensor head 106 and the associated sensor cable 104 can be fabricated within the circumferential track 44.

[0037] The technical effects of the disclosed embodiments include providing an aerodynamic measurement system that can be quickly deployed to 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 of the gas turbine engine. The measurement system includes a sensor assembly having a plurality of combined sensors. The sensor assembly can be inserted into a cavity or space defined between a circumferential track embedded in the inner surface of the casing and the inner surface of the casing, and then withdrawn therefrom (e.g., through the same port). The sensor assembly can be inserted and removed without the need to disassemble the gas turbine engine. Thereby, baseline data can be collected without the need to utilize slip rings or telemetry methods. The measurement system is adaptable for use in gas turbine engines of different sizes from different manufacturers. In addition, the measurement system can reduce the costs and time associated with testing and validating gas turbine engines.

[0038] This specification discloses the disclosed subject matter, including the best mode, and uses examples to enable those skilled in the art to practice the disclosed subject matter, including the making and using of any devices or systems and the performance of any associated methods. The patentable scope of the disclosed subject matter is defined by the claims and can 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 that do not have a substantial difference from the literal language of the claims.

Description of Reference Numerals

[0039] 10 Turbine system 11 Gas turbine engine 12 Fuel nozzle 13 Measurement system 14 Fuel supply 16 Combustor 18 Turbine 20 Exhaust outlet 22 Shaft 24 Compressor 26 Intake port 28 Load 30 Axial direction 32 Radial direction 34 Circumferential direction 36 Longitudinal axis 38 Turbine blade 40 Rotating blade 42 Casing 44 Circumferential track 46 Inner diameter, inner surface 48 Sensor assembly 50 Segment 52 Circumferential track 54 Circumferential track 56 Opening 58 Larger opening 60 Smaller opening 62 Cavity 64 Sensor 66 Arrow 68 External port, funnel 70 Arrow 72 Port 74 Method 76 Block 78 Block 80 Block 82 Block 84 Sensor receptacle 86 Guide tube 88 Sensor viewing port, opening 90 Internal passage 91 Inner diameter 92 Alignment function 94 Lock function 96 Spring-loaded ball detent 98 Ball 100 Spring 102 Sensor 104 Sensor cable 106 Sensor head 108 Alignment function 110 Lock function 112 groove 114 outer surface 116 signal 118 end 120 connector interface 122 data recording system

Claims

1. A system comprising a gas turbine engine (11) and a measurement system (13), wherein the gas turbine engine (11) comprises a compressor (24) comprising a compressor casing (42) having an inner diameter, a combustor (16) downstream of the compressor (24), a turbine (18) downstream of the combustor (16), and circumferential tracks (52, 54) embedded within the inner diameter of the compressor casing (42), the circumferential tracks (44, 52, 54) extending circumferentially (34) around at least a portion of the inner diameter of the compressor casing (42) with respect to the longitudinal axis (36) of the gas turbine engine (11) and the measurement system (13) comprises a sensor assembly (48), and a plurality of sensors (64) coupled to the sensor assembly (48), the sensor assembly (48) being configured to be removably inserted into the circumferential tracks (44, 52, 54) without the need to disassemble the compressor casing (42). A system.

2. The system according to claim 1, wherein the circumferential tracks (44, 52, 54) are configured to enclose the sensor assembly (48) within a cavity defined by the circumferential tracks (44, 52, 54) and the inner diameter of the compressor casing (42) when the sensor assembly (48) is disposed within the circumferential tracks (44, 52, 54).

3. The system according to claim 1, wherein the compressor casing (42) includes a single port (72) for coupling the sensor assembly (48) to and removing the sensor assembly (48) from the circumferential tracks (44, 52, 54).

4. The system according to claim 1, wherein the circumferential tracks (44, 52, 54) have a plurality of openings (56) facing the interior of the compressor (24) and spaced apart from each other circumferentially (34) along the circumferential tracks (44, 52, 54), and each sensor (64) of the plurality of sensors (64) is spatially arranged such that when the sensor assembly (48) is inserted into the circumferential tracks (44, 52, 54), each sensor (64) is aligned with a respective one of the plurality of openings (56). Claim 5 The system according to claim 1, wherein the measurement system (13) is configured to obtain baseline data for verifying the operation of the gas turbine engine (11). Claim 6 The system according to claim 5, wherein the measurement system (13) is configured such that, after removing the sensor assembly (48) from the casing (42), the baseline data is collected from the plurality of sensors (64). Claim 7 The system according to claim 1, wherein the measurement system (13) is configured to operate independently of the control system of the gas turbine engine (11). Claim 8 The system according to claim 1, wherein the sensor assembly (48) is configured to extend in a circumferential direction (34) within a space defined by the circumferential tracks (44, 52, 54) along at least a part of the casing (42) with respect to the longitudinal axis (36) of the gas turbine engine (11).

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