System and method for propeller feedback loop position detection

Abstract

A system and method for determining a position of a feedback ring of a propulsor of an aircraft engine is provided. The feedback ring is coupled to the propulsor to rotate with the propulsor and to shift along a longitudinal axis with adjustment of a blade angle. An engagement member is configured to engage the feedback ring and to shift along a longitudinal direction substantially parallel to the longitudinal axis with shifting of the feedback ring. A sensor includes a first member coupled to the engine and a second member coupled to the engagement member. The second member is movable relative to the first member along the longitudinal direction when the engagement member shifts. The sensor generates a signal indicative of a longitudinal position of the second member relative to the first member. A controller determines an axial position of the feedback ring from the sensor signal.

Description

TECHNICAL FIELD

[0001] The present application relates generally to a propeller feedback system for an aircraft engine, and more particularly, to a system and method for detecting a feedback ring position. BACKGROUND

[0002] Some aircraft engines have propellers with variable pitch, referred to as propeller blade (or beta) angle. In such engines, precise control of the beta angle is important for proper engine operation. For example, control of the beta angle can allow control of the blade angle according to a desired engine power setpoint. Precise measurement of the blade angle also ensures that the propeller is not inadvertently commanded to transition to a low beta angle or a reverse beta angle, which would result in a potentially serious fault condition for the aircraft.

[0003] Various methods can be used to measure the blade angle. One such method involves the use of a feedback ring that is mounted for rotation with the propeller and is axially movable with adjustment of the blade angle. In particular, the blade angle can be obtained from a measurement of the axial displacement of the feedback ring. However, existing devices that measure this displacement have drawbacks, including that they are susceptible to magnetic noise.

[0004] Accordingly, there is a need for a system and method for determining the position of a feedback ring of a propeller. SUMMARY

[0005] According to one aspect, a feedback ring position detection system for a propeller of an aircraft engine is provided. The propeller is rotatable about a longitudinal axis and has an adjustable blade angle. The system includes a feedback ring coupled to the propeller for rotation with the propeller and displacement along the longitudinal axis with adjustment of the blade angle, an engagement member configured to engage the feedback ring and displace along a longitudinal direction substantially parallel to the longitudinal axis with displacement of the feedback ring, a sensor including a first member coupled to the aircraft engine and a second member coupled to the engagement member, the first member being fixed and the second member being movable relative to the first member along the longitudinal direction as the engagement member displaces, the sensor being configured to generate a sensor signal indicative of a longitudinal position of the second member relative to the first member, and a controller configured to receive the sensor signal and determine an axial position of the feedback ring along the longitudinal axis based on the longitudinal position of the second member relative to the first member.

[0006] In some embodiments, the feedback ring has a channel formed about a circumferential portion thereof.

[0007] In some embodiments, the engagement member is configured to be retained in the channel.

[0008] In some embodiments, the channel is U-shaped and the engagement member is a block.

[0009] In some embodiments, the sensor is a linear variable differential transformer, the first member includes a plurality of solenoid coils, and the second member includes a ferromagnetic core.

[0010] In some embodiments, the first member is fixed to a gearbox of the aircraft engine.

[0011] In some embodiments, the sensor is configured to generate a sensor signal indicative of a longitudinal displacement of the second member relative to a reference position of the first member.

[0012] According to one aspect, an aircraft engine is provided. The aircraft engine includes a propulsor rotatable about a longitudinal axis and having blades with an adjustable blade angle, a feedback ring coupled to the propulsor to rotate with the propulsor and to displace along the longitudinal axis with adjustment of the blade angle, an engagement member configured to engage the feedback ring and to displace along a longitudinal direction substantially parallel to the longitudinal axis with displacement of the feedback ring, a sensor including a first member coupled to the aircraft engine and a second member coupled to the engagement member, the first member being fixed and the second member being movable relative to the first member along the longitudinal direction with displacement of the engagement member, the sensor being configured to generate a sensor signal indicative of a longitudinal position of the second member relative to the first member, and a controller configured to receive the sensor signal and to determine an axial position of the feedback ring along the longitudinal axis based on the longitudinal position of the second member relative to the first member.

[0013] In some embodiments, the feedback ring has a channel formed about a circumferential portion thereof.

[0014] In some embodiments, the engagement member is configured to be retained in the channel.

[0015] In some embodiments, the channel is U-shaped and the engagement member is a block.

[0016] In some embodiments, the sensor is a linear variable differential transformer, the first member includes a plurality of solenoid coils, and the second member includes a ferromagnetic core.

[0017] In some embodiments, the first member is fixed to a gearbox of the aircraft engine.

[0018] In some embodiments, the sensor is configured to generate a sensor signal indicative of a longitudinal displacement of the second member relative to a reference position of the first member.

[0019] According to one aspect, a method for determining the axial position of a feedback loop of a thruster of an aircraft engine. The thruster is rotatable about a longitudinal axis and has an adjustable blade angle. The method includes: displacing a movable sensor member relative to a fixed sensor member, the fixed sensor member being coupled to the aircraft engine, and the movable sensor member being displaced relative to the fixed sensor member in a longitudinal direction substantially parallel to the longitudinal axis as the feedback loop is displaced along the longitudinal axis; receiving a sensor signal indicating the longitudinal position of the movable sensor member relative to the fixed sensor member; and determining the axial position of the feedback loop along the longitudinal axis based on the longitudinal position of the movable sensor member relative to the fixed sensor member as obtained from the sensor signal.

[0020] In some embodiments, the sensor signal indicates the longitudinal displacement of the movable sensor member relative to a reference position of the fixed sensor member.

[0021] In some embodiments, the axial position of the feedback loop is determined based on the longitudinal displacement of the movable sensor component relative to a reference position of the fixed sensor component.

[0022] In some embodiments, shifting a movable sensor component relative to a fixed sensor component includes shifting the movable sensor component relative to a reference position of the fixed sensor component, the movable sensor component including a ferromagnetic core of a linearly variable differential transformer, and the fixed sensor component including a plurality of solenoid coils of a linearly variable differential transformer. Attached Figure Description

[0023] Please refer to the attached diagram, in which:

[0024] Figure 1 This is a schematic cross-sectional view of a gas turbine engine;

[0025] Figure 2 This is a schematic cross-sectional view of a thruster assembly including a reduction gearbox according to an illustrative embodiment;

[0026] Figure 3 This is a schematic illustration of a thruster assembly including a feedback loop according to an illustrative embodiment;

[0027] Figure 4A This is a schematic illustration of a thruster assembly according to an illustrative embodiment, the thruster assembly including... Figure 2 The reduction gearbox Figure 3 The feedback loop and the sensor used to measure the position of the feedback loop;

[0028] Figure 4B , 4C And 4D is shown Figure 4A A schematic diagram of the feedback loop and the longitudinal movement of the sensor;

[0029] Figure 5 This is a flowchart of a method for determining the axial position of a feedback loop according to an illustrative embodiment; and

[0030] Figure 6 This is for implementation according to the embodiments. Figure 5 A block diagram of an example computational system for the method. Detailed Implementation

[0031] Figure 1 The illustration depicts a gas turbine engine 10 typically configured for subsonic flight, comprising an inlet 12 through which ambient air is propelled; a compressor section 14 for pressurizing the air; a combustion chamber 16 in which compressed air is mixed with fuel and ignited to generate an annular flow of hot combustion gases; and a turbine section 18 for extracting energy from the combustion gases. The turbine section 18 illustratively includes a compressor turbine 20 driving the compressor assembly and accessories, and at least one powered or free turbine 22, independent of the compressor turbine 20 and rotatably driving a rotor shaft 24 about a longitudinal propeller shaft axis A via a reduction gearbox 26. The hot gases are then exhausted through an exhaust stub 28. The gas generator of the engine 10 illustratively includes the compressor section 14, the combustion chamber 16, and the turbine section 18. A rotor 30, in the form of a propeller through which ambient air is propelled, is carried in a propeller hub 32. The rotor 30 may, for example, comprise a propeller for a fixed-wing aircraft or a main (or tail) rotor for a rotorcraft such as a helicopter. The rotor 30 may include a plurality of circumferentially arranged blades connected to and extending radially from a hub or any suitable device. The blades may also rotate about their own radial axis by a plurality of blade angles, which can be varied to achieve operating modes such as feathering, full reversing, and forward thrust.

[0032] like Figure 2As depicted, rotor 30 is part of propeller assembly 36. Rotor 30 is mounted to propeller shaft 38 via mounting flange 40. Propeller shaft 38 is received in reduction gearbox 26. Reduction gearbox 26 receives power from input shaft 44, which rotates and drives propeller shaft 38 via gear train 46. Propeller shaft 38 and rotor 30 rotate about longitudinal propeller axis A. As used herein, reference to the longitudinal direction refers to a direction substantially parallel to longitudinal propeller axis A. Gear train 46 reduces angular velocity so that rotor 30 rotates at a lower speed than input shaft 44. As depicted, gear train 46 includes two sets of reduction gears. However, gear train 46 can have any number of reduction gears. Alternatively or additionally, gear train 46 may include one or more planetary gear sets. Reduction gearbox 26 has housing 48 with front wall 50. Propeller shaft 38 is received through an opening in front wall 50 and carried by bearing 52, which fixes the longitudinal position of drive shaft 38 relative to housing 48. The reduction gearbox 26 can vary depending on the actual implementation method.

[0033] like Figure 3 As depicted, the thruster 30 includes a plurality of angled blades 110, each blade 110 being rotatable about a radially extending axis R by a plurality of adjustable blade angles. The blade angle is the angle between a chord of the thruster blade portion (i.e., a line drawn between the leading and trailing edges of the blade) and a plane perpendicular to the thruster's axis of rotation. The thruster 30 can be a reversing thruster 30 with multiple operating modes, such as feathering, full reversing, and forward thrust. In some operating modes, such as feathering, the blade angle is positive. The thruster 30 can operate in a reversing mode, where the blade angle is negative.

[0034] Feedback ring 104 is supported for rotation with thruster 30 about longitudinal axis A. Feedback ring 104 is annular and may be referred to as a beta ring or beta feedback ring. Feedback ring 104 is also supported (e.g., by support members) for longitudinal sliding movement along longitudinal axis A, such as a series of circumferentially spaced beta feedback rods 106 extending along longitudinal axis A. Compression springs 108 surround the end of each rod 106. Feedback ring 104 is mounted to shift longitudinally when the beta angle of the thruster blade is adjusted. Specifically, adjustment of the beta angle causes a corresponding axial movement of rod 106 substantially parallel to axis A, and thus causes a corresponding axial movement of feedback ring 104 substantially parallel to axis A. Conversely, adjustment of the beta angle in a first direction causes feedback ring 104 to move forward (e.g., toward thruster 30), and adjustment of the beta angle in the opposite direction causes feedback ring 104 to move backward (e.g., away from thruster 30). In the example, when blade 110 is at its minimum (or most negative) beta angle, rod 106 and feedback loop 104 move to the maximum forward position, and when blade 110 is at its maximum (or most positive) beta angle, rod 106 and feedback loop 104 move to the maximum rearward position. It will be apparent that in other embodiments, this orientation may be reversed. Feedback loop 104 can be used to provide blade (or beta) angle position feedback from the axial position of feedback loop 104 along axis A.

[0035] For further reference Figure 4A Sensor 200 is used to determine the axial position of feedback loop 104. Sensor 200 includes a first member 202 and a second member 204, both extending in a longitudinal direction. The first member 202 is illustratively fixed, and the second member 204 is displaceable in the longitudinal direction and movable relative to the first member 202. The first member 202 is coupled to engine 10 in any suitable manner. In the illustrated embodiment, the first member 202 is fixed to gearbox 26. Sensor 200 is configured such that when feedback loop 104 moves along longitudinal axis A, second member 204 is movable in the longitudinal direction relative to first member 202. For example, first member 202 may include a tube, and second member 204 may include an arm (e.g., rod, shaft, bar, etc.). The arm may be configured to be received in the tube and displaceable in the longitudinal direction, entering and exiting the tube, as feedback loop 104 moves along axis A.

[0036] Sensor 200 generates a signal indicating the longitudinal position of the second member 204 relative to the first member 202. Therefore, this signal can indicate the longitudinal displacement of the second member 204 relative to a reference position of the first member 202. The reference position can be arbitrary. When the position of the second member 204 is aligned with any reference position of the first member 202, the signal generated by sensor 200 indicates no displacement. When the second member 204 moves from the first position to the second position, in response to the displacement of the feedback loop 104 along the longitudinal axis A, sensor 200 generates a signal indicating the second position and thus the displacement of the second member 204 relative to the reference position of the first member 202. It should be understood that the second member 204 can be axially displaced in the longitudinal direction to be positioned in multiple positions other than the first and second positions.

[0037] The second component 204 is coupled to the engaging component 210, which is configured to engage the feedback loop 104. The second component 204 can be coupled to the engaging component 210 by any suitable mechanism. For example, in the illustrated embodiment, a fastener 212 is used to engage the second component 204 to the engaging component 210. The fastener 212 can be a pin, screw, bolt, etc.

[0038] According to an embodiment, the feedback loop 104 has a channel 220 formed around its circumferential portion, the channel 220 being configured to retain the engagement member 210. In the illustrated embodiment, the channel 220 is U-shaped. However, the configuration of the channel 220 may vary depending on the actual implementation. The engagement member 210 is a ring engagement member configured to move along the longitudinal axis A with the feedback loop 104, and remains retained in the channel 220 as the feedback loop 104 rotates. The engagement member 210 may be made of any suitable material(s). In some embodiments, the engagement member 210 is a block. According to specific and non-limiting examples of the embodiment, the block is made of carbon.

[0039] A computing device 400 is connected to a sensor 200 to receive signals generated by the sensor 200. The computing device 400 may be referred to as a controller. The computing device 400 is configured to determine the axial position of the feedback loop from the signals generated by the sensor 200. As described elsewhere in this document, the sensor signals indicate the position of the second member 204 relative to the first member 202. Therefore, the axial position of the feedback loop 104 along the longitudinal axis A can be determined from the sensor signals. For example, when the second member 204 is in a first position and aligned with a reference position of the first member 202 (i.e., the second member 204 has no displacement relative to the reference position of the first member 202), this corresponds to a first axial position of the feedback loop 104. When the second member 204 is in a second position corresponding to a given displacement of the second member 204 relative to the reference position of the first member 202, this corresponds to a second axial position of the feedback loop. Therefore, the relationship between the displacements of the second member 204 relative to the reference position of the first member 202 can be used to determine the axial position of the feedback loop. For example, the axial position of the feedback loop can be determined from the displacement of the second component 204 relative to the reference position of the first component 202 using lookup tables, formulas, or equations.

[0040] The position of the feedback loop 104 can be determined based on the known geometry of the engine and / or the various components described herein. For example, the sensor 200's position relative to a propeller surface reference (e.g., Figure 3 The position of the second member 204 (defined by axis R) can be used to provide a constant value (e.g., the distance between the propeller surface reference position and sensor 200). The measured displacement of the second member 204 relative to the reference position of the first member 202 can be added to this constant value to determine the position of the feedback loop 104. In some embodiments, relative movement can be used to determine the position of the feedback loop 104 when a repeatable starting position of the feedback loop exists. A given axial position of the feedback loop corresponds to a given blade angle, and therefore the blade angle can be determined from the axial position of the feedback loop 104 by the computing device 400. The configuration of the computing device 400 is described in further detail elsewhere in this document.

[0041] In some embodiments, sensor 200 is a linear variable differential transformer (LVDT). A first component 202 may include three solenoid coils, and a second component 204 may include a cylindrical ferromagnetic core. The three solenoid coils may be positioned around a tube. The core may be attached to an arm (e.g., a rod, shaft, bar, etc.), and the arm may be coupled to a connecting component 210. The three solenoid coils include a center coil and two outer coils, the center coil being a primary coil and the two outer coils being top and bottom secondary coils. The core is configured to slide along axis A and may be configured to move into and out of the tube around which the three solenoid coils are wound. Alternating current drives the primary coils and induces a voltage in each secondary coil that is proportional to the length of the core associated with the secondary coil. As the core moves, the association between the primary coil and the two secondary coils changes, causing a change in the induced voltage. In this embodiment, the signal generated by sensor 200 is an output voltage, which is the difference between the top secondary voltage and the bottom secondary voltage. The output voltage varies depending on the position of the second component 204 relative to the first component 202. For example, the value of the output voltage can vary linearly with the amount of axial displacement of the second component 204 relative to the reference position of the first component 202. Therefore, a given value of the output voltage can correspond to a given axial position of the feedback loop 104.

[0042] refer to Figure 4B , 4C And 4D, the example illustration shows the longitudinal movement of the feedback loop 104 and the second component 204 of the sensor 200. In this example, the actuator 109 engages with the piston assembly 111 to adjust the beta angle of the blade. Specifically, the piston assembly 111 moves back and forth in the longitudinal direction and causes the blade 110 to rotate by sliding engagement with the actuator 109. In the depicted embodiment, the forward movement of the piston assembly 111 decreases the beta angle of the blade 110, and the backward movement increases the beta angle. However, in other embodiments, the opposite may be true. When the piston assembly 111 adjusts the beta angle, the piston assembly 111 also engages the rod 106. Figure 4B As shown, during a portion of the piston assembly 111's forward movement, the piston assembly 111 supports and abuts against a stop 113 mounted to the rod 106, thereby pulling the rod 106 and feedback ring 104 in a forward direction (as indicated by arrow 291) and compressing the spring 108. The second member 204 also moves forward as the feedback ring 104 moves forward. Figure 4C As shown, when the piston assembly 111 moves in a rearward direction (as indicated by arrow 292), the spring 108 pushes the rod 106 and the feedback wheel 104 rearward. The second member 204 also moves rearward as the feedback ring 104 moves rearward. In the depicted embodiment, the feedback wheel 104 reaches its maximum rearward position before the piston assembly 111 reaches its maximum rearward position. Figure 4C(as shown in the diagram). After the feedback ring 104 reaches its maximum rearward position, the piston assembly 111 moves away from contact with the stop 113, as shown in the diagram. Figure 4D As shown, further rearward movement of the piston assembly 111 thereafter does not cause movement of the feedback ring 104. Other suitable configurations for adjusting the beta angle and causing corresponding longitudinal movement of the feedback wheel 104 will be apparent to those skilled in the art.

[0043] refer to Figure 5 A flowchart illustrating an example method 300 for determining the axial position of feedback loop 104 is shown. While method 300 is described herein with reference to engine 10, it is for illustrative purposes only. Method 300 can be applied to any suitable engine. At step 302, a movable sensor component (also referred to herein as second component 204) is displaced relative to a fixed sensor component (also referred herein as first component 202). Fixed sensor component 202 is coupled to aircraft engine 10, and as feedback loop 104 is displaced along longitudinal axis A, movable sensor component 204 may be displaced relative to fixed sensor component 204 in a longitudinal direction substantially parallel to longitudinal axis A. A sensor signal indicating the longitudinal position of movable sensor component 204 relative to fixed sensor component 202 is generated at sensor 200. At step 304, a sensor signal indicating the position of movable sensor component 204 relative to fixed sensor component 202 is received. The sensor signal may be as described elsewhere in this document. At step 304, the axial position of feedback loop 104 is determined based on the longitudinal position of movable sensor component 204 relative to fixed sensor component 202. The axial position of feedback loop 104 can be determined as described elsewhere in this document. The axial position of feedback loop 104 can also be referred to as the longitudinal position of feedback loop 104. The thruster blade angle can then be determined based on the axial position of feedback loop 104. The determined thruster blade angle can be output to an aircraft computer, for example, to be displayed on an aircraft or cockpit display. The determined thruster blade angle can be used by controller 400 (or another engine controller and / or aircraft computer) for various engine and / or aircraft controls. For example, the determined thruster blade angle can be used for synchronization phasing to adjust the blade angle of each thruster of multiple engines in a multi-engine thruster driven aircraft. For example, one or more engine controllers and / or one or more aircraft computers can adjust the thruster blade angle of each engine based on the determined thruster blade angle of multiple engines.

[0044] In some embodiments, the sensor signal indicates a longitudinal displacement of the movable sensor member 204 relative to a reference position of the fixed sensor member 202. In some embodiments, the axial position of the feedback loop 104 is determined based on the longitudinal displacement of the movable sensor member 204 relative to the reference position of the fixed sensor member 202. In some embodiments, displacing the movable sensor member 204 relative to the fixed sensor 202 includes displacing the movable sensor member 204 (which includes a ferromagnetic core of a linearly variable differential transformer) relative to a reference position of the fixed sensor member 202 (which includes a plurality of solenoid coils of a linearly variable differential transformer).

[0045] refer to Figure 6 Method 300 can be implemented, at least in part, using a computing device 400 including a processing unit 412 and a memory 414, in which computer-executable instructions 416 are stored. The processing unit 412 may include any suitable means configured to implement the system such that the instructions 416, when executed by the computing device 400 or other programmable device, cause the functions / actions / steps of method 300 as described herein to be performed. The processing unit 412 may include, for example, any type of general-purpose microprocessor or microcontroller, digital signal processing (DSP) processor, central processing unit (CPU), integrated circuit, field-programmable gate array (FPGA), reconfigurable processor, other suitable programmable or programmable logic circuitry, or any combination thereof.

[0046] Memory 414 may include any suitable known or other machine-readable storage medium. Memory 414 may include non-transitory computer-readable storage media, such as, but not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or apparatuses, or any suitable combination thereof. Memory 414 may include any suitable combination of computer memories, whether internal or external to the device, such as random access memory (RAM), read-only memory (ROM), optical disc read-only memory (CDROM), electro-optical memory, magneto-optical memory, erasable programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), ferroelectric RAM (FRAM), etc. Memory 414 may include any storage device (e.g., apparatus) suitable for retrievably storing machine-readable instructions 416 executable by processing unit 412. In some embodiments, computing device 400 may be implemented as part of a full-authority digital engine control (FADEC) or other similar device, including electronic engine control (EEC), engine control unit (ECU), etc.

[0047] The methods and systems for determining the axial position of the feedback loop described herein can be implemented in a high-level program or an object-oriented programming or scripting language, or a combination thereof, to communicate with or assist the operation of a computer system (e.g., computing device 400). Alternatively, the methods and systems for determining the axial position of the feedback loop can be implemented in assembly language or machine language. The language can be a compiled or interpreted language. Program code for implementing the methods and systems for determining the axial position of the feedback loop can be stored on a storage medium or device, such as ROM, disk, optical disk, flash drive, or any other suitable memory medium or device. The program code can be read by a general-purpose or special-purpose programmable computer for configuring and operating the computer when the computer reads the storage medium or device to execute the program described herein. Embodiments of the methods and systems for determining the axial position of the feedback loop can also be considered as being implemented via a non-transitory computer-readable storage medium having a computer program stored thereon. This computer program may include computer-readable instructions that cause the computer, or in some embodiments, the processing unit 412 of computing device 400, to operate in a specific and predefined manner to perform the functions described herein.

[0048] Computer-executable instructions can take many forms, including program modules that are executed by one or more computers or other devices. Generally, program modules include routines, programs, objects, components, data structures, etc., that perform a specific task or implement a specific abstract data type. Typically, in various embodiments, the functionality of program modules can be combined or allocated as needed.

[0049] The above description is merely exemplary, and those skilled in the art will recognize that changes can be made to the described embodiments without departing from the scope of the disclosed invention. Other modifications falling within the scope of this invention will become apparent to those skilled in the art based on a review of this disclosure.

[0050] Various aspects of the methods and systems used to determine the axial position of the feedback loop can be used individually, in combination, or in various arrangements not specifically discussed in the embodiments described above, and therefore their application is not limited to the details and arrangements of the components set forth in the foregoing description or illustrated in the drawings. For example, aspects described in one embodiment can be combined in any way with aspects described in other embodiments. Although specific embodiments have been shown and described, it will be apparent to those skilled in the art that changes and modifications can be made without departing from the broader aspects of the invention. The scope of the following claims should not be limited to the embodiments illustrated by way of example, but should be interpreted with the broadest reasonable intent consistent with the entire specification.

Claims

1. A feedback loop position detection system for a thruster of an aircraft engine, the thruster being rotatable about a longitudinal axis and having an adjustable blade angle, the system comprising: A feedback loop is coupled to the thruster to rotate with the thruster and to shift along the longitudinal axis as the blade angle is adjusted; A connecting member configured to movably engage the feedback loop in a channel formed around a circumferential portion of the feedback loop, the connecting member being configured to be held in the channel as the feedback loop rotates and to shift in a longitudinal direction substantially parallel to the longitudinal axis as the feedback loop shifts. A sensor comprising a first component coupled to the aircraft engine and a second component coupled to the engagement member, the first component being fixed and the second component being movable relative to the first component in the longitudinal direction when the engagement member is displaced, the sensor being configured to generate a sensor signal indicating the longitudinal position of the second component relative to the first component; as well as A controller configured to receive the sensor signal and determine the axial position of the feedback loop along the longitudinal axis based on the longitudinal position of the second component relative to the first component. The sensor is a linear variable differential transformer, the first component includes multiple solenoid coils, and the second component includes a ferromagnetic core. The channel is U-shaped, and the connecting member is a block. The block is made of carbon.

2. The system according to claim 1, wherein, The first component is fixed to the gearbox of the aircraft engine.

3. The system according to claim 1, wherein, The sensor is configured to generate a sensor signal indicating the longitudinal displacement of the second member relative to a reference position of the first member.

4. An aircraft engine, comprising: A propeller that is rotatable about a longitudinal axis and has blades with an adjustable blade angle; A feedback loop is coupled to the thruster to rotate with the thruster and to shift along the longitudinal axis as the blade angle is adjusted; A connecting member configured to movably engage the feedback loop in a channel formed around a circumferential portion of the feedback loop, the connecting member being configured to be held in the channel as the feedback loop rotates and to shift in a longitudinal direction substantially parallel to the longitudinal axis as the feedback loop shifts. A sensor comprising a first component coupled to the aircraft engine and a second component coupled to the engagement member, the first component being fixed and the second component being movable relative to the first component in the longitudinal direction when the engagement member is displaced, the sensor being configured to generate a sensor signal indicating the longitudinal position of the second component relative to the first component; as well as A controller configured to receive the sensor signal and determine the axial position of the feedback loop along the longitudinal axis based on the longitudinal position of the second component relative to the first component. The sensor is a linear variable differential transformer, the first component includes multiple solenoid coils, and the second component includes a ferromagnetic core. The channel is U-shaped, and the connecting member is a block. The block is made of carbon.

5. The engine according to claim 4, wherein, The first component is fixed to the gearbox of the aircraft engine.

6. The engine according to claim 4, wherein, The sensor is configured to generate a sensor signal indicating the longitudinal displacement of the second member relative to a reference position of the first member.

7. A method for determining the axial position of a feedback loop of a thruster of an aircraft engine, the thruster being rotatable about a longitudinal axis and having an adjustable blade angle, and the feedback loop being rotatable with the thruster, the method comprising: The movable sensor component is displaced relative to the fixed sensor component, which is coupled to the aircraft engine, and the movable sensor component can be displaced relative to the fixed sensor component in a longitudinal direction substantially parallel to the longitudinal axis as the feedback loop is displaced along the longitudinal axis. Receive a sensor signal indicating the longitudinal position of the movable sensor component relative to the fixed sensor component; as well as Based on the longitudinal position of the movable sensor component relative to the fixed sensor component, as obtained from the sensor signal, the axial position of the feedback loop along the longitudinal axis is determined. The movable sensor component is coupled to the feedback loop via a coupling member so as the feedback loop shifts. The coupling member is configured to movably engage the feedback loop in a channel formed around a circumferential portion of the feedback loop, and the coupling member is configured to be held in the channel as the feedback loop rotates and to shift in a longitudinal direction substantially parallel to the longitudinal axis as the feedback loop shifts. The movable sensor component includes the ferromagnetic core of a linear variable differential transformer, and the fixed sensor component includes multiple solenoid coils of the linear variable differential transformer. The channel is U-shaped, and the connecting member is a block. The block is made of carbon.

8. The method according to claim 7, wherein, The sensor signal indicates the longitudinal displacement of the movable sensor component relative to the reference position of the fixed sensor component.

9. The method according to claim 8, wherein, The axial position of the feedback loop is determined based on the longitudinal displacement of the movable sensor component relative to the reference position of the fixed sensor component.

10. The method according to any one of claims 7 to 9, wherein, Displacing the movable sensor component relative to the fixed sensor component includes: shifting the movable sensor component relative to a reference position of the fixed sensor component.

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