System and method for servicing aircraft engine

Abstract

An apparatus for servicing internal components of an aircraft engine, comprising: a flexible hollow tube; a latch mechanism connected to or combined with the flexible hollow tube; and a service device for insertion through the flexible hollow tube. The service device is free to move through the flexible hollow tube and is decoupled from the latch mechanism. The shape and configuration of the flexible hollow tube enable proximity positioning of the flexible hollow tube relative to the rotatable component of the aircraft engine, allowing attachment of the flexible hollow tube to the rotatable component via the latch mechanism upon insertion of the flexible hollow tube through the access port of the aircraft engine.

Description

[0001] This application is a divisional application of the invention patent application filed on January 24, 2025, with application number 202510117991.X and invention title "System and method for repairing aircraft engines". Technical Field

[0002] This technical field relates to the maintenance of aircraft engines. Background Technology

[0003] General engines and aircraft engines require different maintenance methods. For example, it may be necessary to inspect internal aircraft engine components for damage. If damage is detected, maintenance operations can sometimes be performed to repair it. For example, drills or other tools may be used. Other types of maintenance operations may also be performed. Attached Figure Description

[0004] By providing methods for repairing aircraft engines, especially when studied in conjunction with the accompanying drawings, various needs are at least partially met. The complete and feasible disclosure of all aspects of this specification, including its best mode, to a person skilled in the art, is set forth in the description with reference to the accompanying drawings, wherein:

[0005] Figure 1 Schematic diagrams of systems for servicing aircraft engines, including various embodiments based on these teachings;

[0006] Figure 2 Including cross-sectional views of flexible hollow tubes including maintenance devices according to various embodiments of these teachings;

[0007] Figure 3 Including schematic diagrams of systems for servicing aircraft engines deployed within the engine, according to various embodiments of these teachings;

[0008] Figure 4 Including schematic diagrams of systems for servicing aircraft engines deployed within the engine, according to various embodiments of these teachings;

[0009] Figure 5 A schematic diagram of the distal end of a maintenance device having multiple openings, including various embodiments based on these teachings;

[0010] Figure 6 Including schematic diagrams of latching mechanisms according to various embodiments of these teachings;

[0011] Figure 7 Including flowcharts of methods for servicing aircraft engines according to various embodiments of these teachings; and

[0012] Figure 8Schematic diagrams of aircraft engines, including various embodiments based on these teachings.

[0013] The elements in the accompanying drawings are shown for simplicity and clarity and are not necessarily drawn to scale. For example, the size and / or relative position of some elements in the drawings may be exaggerated relative to other elements to aid in understanding the various embodiments of this teaching. Furthermore, common but well-understood elements that are useful or necessary in commercially viable embodiments are generally not depicted to facilitate less obstructed observation of these different embodiments of this teaching. Certain actions and / or steps may be described or depicted in a particular sequence of occurrence, but those skilled in the art will understand that such specificity regarding the sequence is not actually necessary. Detailed Implementation

[0014] The methods provided in this article for servicing aircraft engines include servicing (e.g., inspecting and / or repairing) the internal components of these engines. For example, these methods allow for the inspection of the shroud above the high-pressure turbine (HPT) blades using the duct sight glass (BSI) ports of these engines. Advantageously, cost savings are achieved because faults in engine components can be quickly and easily identified without the need for complex insertion tools or procedures. These methods can also be customized for different engine types and other compressor and turbine stages.

[0015] In the methods provided herein, a flexible hollow tube with a latching mechanism (e.g., a hook) at the distal end of the tube is provided. A service device (e.g., a duct mirror) is inserted through an opening in the proximal end of the tube, passes through the tube, and exits the tube through an opening near the distal end, or uses the line of sight provided by the opening near the distal end of the tube. The flexible hollow tube acts as a sleeve to protect the service device. The flexible hollow tube includes a latching mechanism for securing the flexible hollow tube to a rotor blade or other engine component. Furthermore, when the rotor rotates (e.g., 360 degrees), the flexible hollow tube acts as a tether to the rotor blade. Even when the flexible hollow tube is engaged with the rotor blade through an opening near the proximal end of the duct, the service device can be inserted into or removed from the flexible hollow tube. When the service device includes a camera, these methods allow for removal of the camera from the tube, alteration of the optical tip of the duct mirror, or change of the viewing orientation of the service device, and return of the attached tube to the same working position via its distal end. Advantageously, the methods and apparatus described herein decouple the movement of the service device from the latching mechanism. Even when the distal end of the flexible hollow tube is locked to the blade (or other structure), the maintenance device can move inside the hollow flexible tube.

[0016] In many of these embodiments, the apparatus for inspecting internal components of an aircraft engine includes: a flexible hollow tube; a latching mechanism connected to or coupled to the flexible hollow tube; and a maintenance device extending through the flexible hollow tube. The maintenance device is freely movable through the flexible hollow tube and is disconnected from the latching mechanism. The shape and construction of the flexible hollow tube allow it to be approached and positioned relative to rotatable components of the aircraft engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latching mechanism after it has been inserted through the aircraft engine's inlet port.

[0017] In some respects, latching mechanisms include hooks or wedges. Other examples of latching mechanisms are also possible.

[0018] In a further aspect, the device further includes an adapter. The adapter is used in an engine having multiple housings to guide the flexible hollow tube into the engine and to the blades. In one example, the adapter is at least partially located within the engine, between the inner and outer housings, and is configured to provide a guidance path for the flexible hollow tube after it has been inserted through the engine's inlet port.

[0019] In one example, the rotatable component includes multiple blades, and a latching mechanism is coupled to the trailing edge of one or more of the blades. In other examples, the rotatable component includes multiple blades, and a latching mechanism is coupled to the leading edge of one or more of the blades. Other attachment locations for the flexible hollow tube are also possible.

[0020] In other aspects, during operation, the maintenance device is removed from the flexible hollow tube, and another maintenance device is inserted into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine. The maintenance devices can also be different. For example, one maintenance device could be a duct mirror with a camera, and another maintenance device could be configured to perform repairs.

[0021] Flexible hollow tubes can be made from a variety of different materials. For example, flexible hollow tubes can be made of silicone rubber or thermoplastic elastomers (TPEs), including thermoplastic polyurethane (TPU) or ethylene vinyl acetate (EVA). Other examples are also possible.

[0022] As described above, a repair device can be several different devices, which have different types, different constructions, and / or perform different operations. For example, a repair device can be a duct mirror. In some aspects, a duct mirror includes a camera and takes images of the engine cover. In other examples, the repair device is configured to perform engine repair or maintenance operations (e.g., by drilling).

[0023] In other embodiments of these examples, a method for servicing internal components of an aircraft engine includes inserting a flexible hollow tube into an inspection port of the aircraft engine. The flexible hollow tube has a latching mechanism connected to or coupled to the flexible hollow tube. The flexible hollow tube is positioned near a rotatable component of the aircraft engine. The flexible hollow tube is attached to the rotatable component via the latching mechanism. A servicing device is inserted through the flexible hollow tube. The servicing device is freely movable through the flexible hollow tube and disengaged from the latching mechanism.

[0024] In a further aspect, the adapter can be at least partially inserted into the engine to provide a guide path for the flexible hollow tube after insertion at the inlet port. In a further aspect, the maintenance device is removed from the flexible hollow tube, and another maintenance device is inserted into the flexible hollow tube while it remains inside the aircraft engine.

[0025] Unless otherwise specified herein, the terms and expressions used herein have the ordinary technical meanings that those skilled in the art would assign to them. Unless otherwise specifically indicated, the word "or" as used herein should be interpreted as having a disjunctive structure rather than a conjunctive structure. Unless otherwise stated herein, the terms "connection," "fixed," "attached," etc., refer both to direct connection, fixation, or attachment, and to indirect connection, fixation, or attachment via one or more intermediate components or features.

[0026] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0027] As used herein throughout the specification and claims, approximate language is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by terms such as “about,” “approximate,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 10%.

[0028] The above and other benefits may become clearer after a thorough review and study of the following detailed description.

[0029] Now for joint reference Figure 1 , Figure 2 , Figure 3 and Figure 4This describes an example of a device 100 for servicing internal components of an aircraft engine. As shown in these figures, the device 100 includes a flexible hollow tube 102, a servicing device 104 (having a distal portion 105) extending through an opening 107 through the flexible hollow tube 102, and a latching mechanism 106.

[0030] Figure 2 The flexible hollow tube 102 is shown along line 103 (e.g.) Figure 1 (Shown) A cross-sectional view. In this view, the maintenance device 104 is disposed within the flexible hollow tube 102.

[0031] For special reference Figure 3 and Figure 4 As shown, device 100 is inserted into engine 109 (for simplicity, Figure 3 and Figure 4 Only a portion of the engine 109 related to the turbine section of the engine 109 is shown in the image. In this example, the engine 109 includes a housing 108 (with a port or opening 122) and an inner housing 110 (with a port or opening 123). An adapter 120 is located between the housing 108 and the inner housing 110, allowing a flexible hollow tube 102 to be guided between ports 122 and 123. If a single housing is present, the adapter 120 is not required. The adapter 120 may be made of a rigid material and is inserted through port 122 simultaneously with the insertion of the service device 104. In other respects, the adapter 120 may be pre-positioned between the housing 108 and the inner housing 110 during engine manufacturing and / or assembly, or at some other convenient time.

[0032] Engine 109 further includes impeller blades 112 and blades 114. For simplicity, only a single blade and impeller are shown, but it should be understood that engine 109 includes multiple impeller blades and blades. Engine 109 also includes a shroud 116, which is deployed above (or radially outward) the blades 114 and extends completely around all rotor blades. Blades 114 are connected to a shaft 118, which rotates to move blades 114 (and other blades coupled to the shaft 118). Blades 114 also include a leading edge 130 and a trailing edge 132.

[0033] Engine 109 can be any type of aircraft engine, including but not limited to ducted turbofan engines and non-ducted turbofan engines; to name just two examples. Other examples of engine types are also possible.

[0034] In some aspects, the flexible hollow tube 102 is made of a flexible material, such as silicone rubber or thermoplastic elastomer (TPE) (e.g., thermoplastic polyurethane (TPU) or ethylene vinyl acetate (EVA)). The material used to construct the flexible hollow tube 102 may have a coefficient of friction in the range of 0.05-0.5. When the flexible hollow tube 102 is deployed, if the coefficient of friction is high, and if it rubs against stationary parts, winch friction may affect its behavior; therefore, a material with a low coefficient of friction is preferred. In other aspects, the elastic modulus of the material is used in the range of (e.g., 0.0005-5 GPa) to construct the flexible hollow tube 102. Examples of other ranges are also possible.

[0035] The cross-section of the flexible hollow tube 102 can be circular, but other cross-sections are also possible, such as cross-sections with different shapes. For example, another example cross-section includes a flat surface that allows the flexible hollow tube 102 to sit on an internal engine component in a defined orientation when positioned in the engine 109.

[0036] In other respects, the flexible hollow tube 102, after being temporarily deformed by insertion into the engine 109 (e.g., by compression through ports 122, 123 and / or adapter 120), is able to return to its original shape. In these respects, the flexible hollow tube 102 may initially be formed and / or configured to have a specific shape such that, when the flexible hollow tube 102 is inserted into the engine 109, this shape allows the distal portion 113 of the flexible hollow tube 102 to be positioned near the blade 114 (due to its pre-formed shape), thereby allowing easy attachment of the blade 114 and deployment of the maintenance device 104. The maintenance device 104 can then be deployed in the correct or convenient location within the engine 109, allowing the maintenance device 104 to perform its tasks. For example, if the maintenance device 104 includes a camera, the pre-formed shape of the flexible hollow tube 102 allows the flexible hollow tube 104 to be easily attached to the blade 114, and the camera to acquire an image of the shroud 116. The behavior of the flexible hollow tube 102 can be considered as hyperelastic because after the flexible hollow tube 102 has been stressed into different shapes (by inserting it through ports 122 and 123), after the stress is relieved (because the flexible hollow tube 102 has emerged from ports 122 and 124), the flexible hollow tube 102 then returns to its original preformed shape.

[0037] Repair device 104 is any type of device that allows any type of work or operation to be performed within engine 109. For example, repair device 104 may be a pipe mirror and / or include a camera. The camera may capture single or multiple images (e.g., film or video). In other respects, repair device 104 may perform repair operations on engine components. For example, repair device 104 may include a drill bit, a sealant dispenser, a laser energy device, or other devices that can repair damage to engine components.

[0038] When the flexible hollow tube 102 is deployed within the engine 109, various types of maintenance devices 104 can be deployed within the flexible hollow tube 102, removed from the flexible hollow tube 103, and then inserted into the flexible hollow tube 102. For example, a first maintenance device 104 (e.g., a pipe mirror with a camera to acquire images) can be inserted into and operate within the flexible hollow tube 102; the first maintenance device 104 can be removed from the flexible hollow tube 102, and then a second maintenance device 104 (e.g., a maintenance device with a drill bit) can be inserted into the flexible hollow tube 102. The second maintenance device 104 can be used to perform repairs identified by the first maintenance device 104.

[0039] The flexible hollow tube 102 can be manually inserted into the engine 109 via ports 122 and 123. The adapter 120 can also be manually inserted before or simultaneously with the insertion of the flexible hollow tube 102. Alternatively, the flexible hollow tube 102 and / or the adapter 120 can be inserted using a robot or other machine. Removal of the flexible hollow tube 102 can be done manually or by a robot or machine.

[0040] In other aspects and some operations, once the flexible hollow tube 102 has been inserted into the rotor section of the engine 109 and attached to the blades 114, the rotor can be rotated. Rotation of the rotor can be achieved by rotating the shaft 118 of the engine 109. When the shaft 118 rotates, all the blades of the rotor attached to the shaft 118 (including blades 114) rotate. For example, in one operation, the flexible hollow tube 102 is attached to the blades 114. A person (or machine) rotates the shaft 118 of the engine 109, thereby rotating the blades 114 attached to the shaft 118. While the rotation is being performed, a camera on the maintenance device 104 acquires images (e.g., movies or videos) of the shroud 116 (e.g., the entire shroud or multiple sections of the shroud 116).

[0041] A controller 101 (e.g., a microprocessor) may be coupled to the repair device 104. The controller 101 may control the movement / insertion of the repair device 104 (e.g., by moving the repair device), control the operation of the repair device 104 (e.g., controlling the drilling of the repair device 104 when the repair device 104 includes a drill bit), and / or analyze data from the repair device 104 (e.g., receiving images from the repair device 104 when the repair device 104 includes a camera and presenting these images to the user on a display).

[0042] The latching mechanism 106 can be any type of device or mechanism for attaching, wedging, and / or securing the flexible hollow tube 102 to the blade 114 (or between one or more blades). In all aspects and as such Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown in the example, the latching mechanism 106 is a hook. The hook is sized to allow it to attach to the engine blades. However, Figure 6 Another example of a latching mechanism is shown, which is not a hook and secures the flexible hollow tube 102 via a wedge-shaped mechanism between the impeller 112 and the blade 114. The latching mechanism 106 may be formed together with the flexible hollow tube 102 (e.g., as an integral structure), or it may be a separate part or component attached to or integrated with the flexible hollow tube 102 (e.g., via threaded fasteners, adhesives, etc.). Another example of a latching mechanism may be an inflatable bag or balloon attached to or formed as part of the body of the tube 102 at or near the distal end of the tube 102.

[0043] In one example of the use of device 100, the shroud 116 in the high-pressure turbine (HPT) is inspected via access ports 122 and 123. An adapter 120 with internal channels connects to ports 122 and 123 and guides the flexible hollow tube 102.

[0044] A flexible hollow tube 102 is inserted through port 122, adapter 120, and port 123. The flexible hollow tube 102 is pre-formed into a specific shape, deforms as it passes through port 122, adapter 120, and port 123, and then reforms into the preset shape after exiting port 123. The pre-formed shape has been selected such that when the flexible hollow tube 102 returns to its original shape, it will be positioned in the engine 109 to allow easy attachment to the blade 114 and / or easy inspection of the shield 116 via the maintenance device 104. In one example, the pre-formed shape may be curved, but a wide variety of shapes, configurations, and sizes are possible.

[0045] A latching mechanism 106 with hook-like features at the distal portion 113 attaches the flexible hollow tube 102 to the blade 114. This can be performed manually or automatically.

[0046] The shaft 118 of the engine 109 is rotated to move the rotor and position the rotor blades (including blade 114) relative to the wheel blades (including wheel blade 112) in a predetermined position. The adapter 120 is adapted into the port 122, and the flexible hollow tube 102 is inserted into the internal channel of the adapter 120 along a predetermined orientation that guides the flexible hollow tube 102 toward the rotor blades including blade 114.

[0047] The flexible hollow tube 102 is pushed into the adapter 120 until a predetermined length is reached, allowing the flexible hollow tube 101 to slide between the rotor blades (including blade 114) and positioning the latching mechanism (e.g., a hook-like feature) near the trailing edge 132 of the rotor blade 114.

[0048] The shaft 118 of the engine 109 rotates manually or automatically in a predetermined direction to engage a latching mechanism (e.g., a hook) and pull the flexible hollow tube 102 and the rotor blades. In some aspects, when the latching mechanism 106 is a hook, the hook may be located at or near the tip of the flexible hollow tube 102, and the opening 107 is located behind the hook. A service device 104 (e.g., a duct mirror) is inserted through the flexible hollow tube 102 until the distal portion 105 of the service device 104 exits through the opening 107 near or at the distal portion 113 of the flexible hollow tube 102.

[0049] Then, the rotor of engine 109 rotates again. During this rotational motion, such as a 360-degree rotor rotation, the maintenance device 104 captures multiple images / videos of the shroud 116. After performing inspection and / or maintenance operations, the maintenance device 104 (e.g., a duct mirror) is removed from the flexible hollow tube 102. The shaft 118 of engine 109 rotates in the opposite direction to the original rotation to retract the flexible hollow tube 102 from engine 109. In some respects, more of the flexible hollow tube 102 is pulled into the engine during the initial rotation, while the opposite occurs during removal. In other respects, friction holds the latching mechanism 106 in place on the blade, preventing the blade from sliding along the blade.

[0050] Now for reference Figure 5 An example of a flexible hollow tube 102 with multiple openings is described. Figure 1 , Figure 2 , Figure 3 and Figure 4 In the example, the flexible hollow tube 102 has a single opening 107 at its distal portion 113. Figure 5In the example, the flexible hollow tube 102 has openings 140, 142, and 144. The user can select which opening 140, 142, or 144 the maintenance device 104 should appear in. Furthermore, one maintenance device 104 can use one of openings 140, 142, and 144, while a second and / or different maintenance device 104 can use a different one of openings 140, 142, and 144.

[0051] Openings 140, 142, and 144 may be located at the distal portion 113 of the flexible hollow tube, but it should be understood that the openings may be placed anywhere along the length of the flexible hollow tube 102. Furthermore, although three openings 140, 142, and 144 are shown, it should be understood that any number of openings may be used. Openings 140, 142, and 144 may be located on different sides of the flexible hollow tube 102, allowing the maintenance device 104 (or multiple maintenance devices) to exit the flexible hollow tube 102 in different directions.

[0052] Using multiple openings allows for convenient deployment of the flexible hollow tube 102 within the engine 109, leaving it in place and providing a series of orifices aligned with engine features, such as nozzle leading edge features, for example, having similar angular periodicity. Inspection or repair devices are then sequentially moved to each orifice of the tube for maintenance, inspection, etc. The cross-section of the flexible hollow tube 102 can be circular, but other cross-sections (e.g., square, rectangular, hexagonal, etc.) are also possible, such as a cross-section with a flat outer surface, to sit on internal engine components (e.g., on the inner diameter of the gas path), thereby controlling the orientation of the flexible hollow tube 102.

[0053] Now for reference Figure 6 An example of a latching mechanism 106 that is not a hook is described. Figure 1 , Figure 2 , Figure 3 and Figure 4 In the example, the latching mechanism 106 uses a hook. However, in Figure 6 In the example, the latching mechanism 106 uses a wedge 121 to wed or secure the flexible hollow tube 102 between blade 114 and another blade 119. The wedge 121 can be made of any suitable material that is flexible enough to pass through ports 122 and 123, but strong enough to allow the flexible hollow tube 102 to be secured.

[0054] Other options for the latching mechanism are possible, including attractive or magnetic base structures attached to or integrated with the flexible hollow tube 102, which allow attachment to the blade 114. In other respects, the flexible hollow tube 102 can be attached to other structures within the engine 109.

[0055] Now for reference Figure 7 This describes an example of a method for servicing an aircraft engine. In step 702, a flexible hollow tube 102 is inserted into a port in the engine 109. The flexible hollow tube 102 has a latching mechanism 106 connected to or combined with the flexible hollow tube 102.

[0056] In step 704, the flexible hollow tube 102 is positioned near a rotatable component, such as blade 114, of the aircraft engine 109. In step 706, the flexible hollow tube 102 is attached to the rotatable component (e.g., blade 114) via a latching mechanism 106. In this example, the latching mechanism 106 is a hook. Other examples are also possible.

[0057] In step 708, the maintenance device 104 is inserted through the flexible hollow tube 102. The maintenance device 104 is freely movable through the flexible hollow tube 102 and is disconnected from the latching mechanism 106.

[0058] In step 710, the blade is rotated. In step 712, data can be collected from the maintenance device 104 and analyzed.

[0059] In other examples, the adapter 120 is at least partially inserted into the engine to provide a guide path for the flexible hollow tube 102. In other aspects, the rotatable component is a plurality of blades (including blade 114), and a latching mechanism 106 is coupled to the trailing edge 132 of one or more of the blades. In yet another example, the rotatable component is a plurality of blades, and the latching mechanism 106 is coupled to the leading edge 130 of one or more of the blades.

[0060] In other respects, after the maintenance device 104 is removed from the flexible hollow tube 102, another maintenance device 104 is inserted into the flexible hollow tube 102 while the flexible hollow tube 102 remains in the aircraft engine 109. This can be repeated with several different maintenance devices 104.

[0061] Now for reference Figure 8 This diagram depicts a schematic cross-sectional view of a conventional gas turbine engine 810 for use in an aircraft, in which the imaging and inspection systems described herein can be operated. The gas turbine engine 810 has a generally longitudinally extending axis or centerline 812 extending from a front portion 814 to a rear portion 816. The gas turbine engine 810 includes, in downstream series flow relationships: a fan section 818 comprising a fan 820; a compressor section 822 comprising a supercharger or low-pressure (LP) compressor 824 and a high-pressure (HP) compressor 826; a combustion section 828 comprising a combustor 830; a turbine section 832 comprising an HP turbine 834 and an LP turbine 836; and an exhaust section 838.

[0062] Fan section 818 includes a fan housing 840 surrounding fan 820. Fan 820 includes a plurality of fan blades 842 arranged radially about a centerline 812.

[0063] HP compressor 826, burner 830, and HP turbine 834 form the core 844 of gas turbine engine 810 that generates combustion gases. The core 844 is surrounded by a core housing 846, which can be connected to a fan housing 840.

[0064] An HP shaft or spool 848, coaxially arranged around the centerline 812 of the gas turbine engine 810, drives the HP turbine 834 to the HP compressor 826. An LP shaft or spool 850, coaxially arranged within a larger diameter annular HP spool 848 around the centerline 812 of the gas turbine engine 810, drives the LP turbine 836 to the LP compressor 824 and the fan 820.

[0065] The LP compressor 824 and HP compressor 826 each include multiple compressor stages 852 and 854, respectively, in which a set of compressor blades 856 and 858 rotate relative to a corresponding set of static compressor impellers 860 and 862 (also referred to as nozzles) to compress or pressurize the fluid flow through the stage. In a single compressor stage 852 or 854, the multiple compressor blades 856 and 858 can be arranged in a ring and extend radially outward from the blade platform relative to the blade tip relative to the centerline 812, while the corresponding static compressor impellers 860 and 862 are positioned downstream of and adjacent to the rotating blades 856 and 858. It is worth noting that... Figure 8 The number of blades, impellers, and compressor stages shown is selected for illustrative purposes only, and other numbers are also possible.

[0066] HP turbine 834 and LP turbine 836 each comprise multiple turbine stages 864 and 866, respectively, in which a set of turbine blades 868 and 870 rotate relative to a corresponding set of static turbine blades 872 and 874 (also referred to as nozzles) to extract energy from the fluid flow passing through the stage. Within a single turbine stage 864 and 866, multiple turbine blades 868 and 870 may be arranged in a ring and extend radially outward from the blade platform relative to the blade tip relative to the centerline 812, while the corresponding static turbine blades 872 and 874 are positioned upstream of and adjacent to the rotating blades 868 and 870. It is worth noting that... Figure 8 The number of blades, impellers, and turbine stages shown is selected for illustrative purposes only, and other numbers are also possible.

[0067] In operation, the rotary fan 820 supplies ambient air to the LP compressor 824, which then supplies pressurized ambient air to the HP compressor 826, which further pressurizes the ambient air. The pressurized air from the HP compressor 826 is mixed with fuel in the combustor 830 and ignited to generate combustion gases. The HP turbine 834 extracts some work from these gases, which drives the HP compressor 826. The combustion gases are discharged into the LP turbine 836, which extracts additional work to drive the LP compressor 824, and the exhaust gases are finally discharged from the gas turbine engine 810 via the exhaust section 838. The drive of the LP turbine 836 drives the LP spool 850 to rotate the fan 820 and the LP compressor 824.

[0068] It should be understood that, despite Figure 8 Not depicted, but the gas turbine engine 810 may also define multiple openings that allow inspection of various components within the gas turbine engine 810. For example, the gas turbine engine 810 may define multiple insertion tool openings at various axial locations within the compressor section, combustion section 828, and / or turbine section 832. Additionally, as will be discussed below, the gas turbine engine 810 may include one or more ignition ports, for example, within the combustion section 828 of the gas turbine engine 810, which may allow inspection of the combustion section 828.

[0069] Through these openings, the flexible hollow tube 102 can be inserted together with the service device 104, as described elsewhere herein. For example, one of these openings may be near and allow access to the turbine section 832. The latching mechanism 106 may be secured to one of the turbine blades 868, 870, and various operations may be performed using the service device 104. It should also be understood that these methods can be performed at any location in the gas turbine engine 810 where the openings are available, such as in the combustion section 828.

[0070] It should be further understood that Figure 8 The exemplary gas turbine engine 810 depicted herein is merely an example, and in other exemplary embodiments, the gas turbine engine 810 may have any other suitable configuration, including, for example, any other suitable number of shafts or spools, turbines, compressors, etc. Additionally or alternatively, in other exemplary embodiments, any other suitable turbine engine may be examined using the tools described herein. For example, in other exemplary embodiments, the engine may not be a turbofan engine, but may be configured as a turboshaft engine, turboprop engine, turbojet engine, etc., or may be an industrial gas turbine engine for power generation, fluid pumping, etc.

[0071] Further aspects of the invention are provided by the subject matter of the following clauses:

[0072] An apparatus for servicing internal components of an aircraft engine, the apparatus comprising: a flexible hollow tube; a latching mechanism connected to or coupled to the flexible hollow tube; a servicing device for insertion through the flexible hollow tube, the servicing device being freely movable through the flexible hollow tube and disengaged from the latching mechanism; and wherein the shape and construction of the flexible hollow tube enable it to be approached and positioned relative to a rotatable component of the aircraft engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latching mechanism after insertion through an inlet port of the aircraft engine.

[0073] The device according to any of the foregoing clauses, wherein the latching mechanism includes a hook.

[0074] According to any of the foregoing clauses of the device, wherein the hook is integrally formed with the flexible hollow tube.

[0075] The device according to any of the foregoing clauses, wherein the latching mechanism includes a wedge mechanism.

[0076] The device according to any of the foregoing clauses further includes an adapter for at least partially positioning within the engine and configured to provide a guide path for the flexible hollow tube after insertion at the inlet port.

[0077] According to any of the foregoing clauses, the maintenance device is removed from the flexible hollow tube, and another maintenance device is inserted into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

[0078] According to any of the preceding clauses of the device, the flexible hollow tube includes an opening at the distal end of the flexible hollow tube.

[0079] According to any of the foregoing clauses, the flexible hollow tube is made of silicone rubber or thermoplastic elastomer (TPE).

[0080] The device described in any of the foregoing clauses, wherein the maintenance device is a pipe mirror.

[0081] The device according to any of the foregoing clauses, wherein the pipe mirror includes a camera.

[0082] A method for servicing internal components of an aircraft engine, the method comprising: inserting a flexible hollow tube into a port in the aircraft engine, the flexible hollow tube having a latching mechanism connected to or coupled to the flexible hollow tube; positioning the flexible hollow tube near a rotatable component of the aircraft engine; attaching the flexible hollow tube to the rotatable component via the latching mechanism; and inserting a servicing device through the flexible hollow tube, the servicing device being freely movable through the flexible hollow tube and disconnected from the latching mechanism.

[0083] The method according to any of the foregoing clauses further includes rotating the rotatable component to attach the latching mechanism to the component.

[0084] According to any of the preceding clauses, the latching mechanism includes a hook or a wedge mechanism.

[0085] The method according to any of the foregoing clauses further includes positioning the adapter at least partially within the engine to provide a guide path for the flexible hollow tube after insertion at the inlet port.

[0086] According to any of the preceding clauses of the method, the rotatable component is a plurality of blades, and the latching mechanism is coupled to the trailing edge of one or more of the plurality of blades.

[0087] According to any of the preceding clauses of the method, the rotatable component is a plurality of blades, and the latching mechanism is coupled to the leading edge of one or more of the plurality of blades.

[0088] The method according to any of the foregoing clauses further includes removing the maintenance device from the flexible hollow tube and inserting another maintenance device into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

[0089] According to any of the foregoing descriptions, the flexible hollow tube is made of silicone rubber or thermoplastic elastomer (TPE).

[0090] The repair device described in any of the foregoing clauses is a pipe mirror.

[0091] According to any of the foregoing descriptions, the duct mirror includes a camera and captures images of the engine shroud.

[0092] Those skilled in the art will recognize that various modifications, variations, and combinations can be made to the above embodiments without departing from the scope of the invention, and such modifications, variations, or combinations should be considered within the scope of the inventive concept.

Claims

1. A device for repairing internal components of a turbine engine, characterized in that, The device includes: A flexible hollow tube having a length, wherein the flexible hollow tube includes a plurality of openings disposed along the length of the flexible hollow tube; A latching mechanism, which is connected to or combined with the flexible hollow tube; A maintenance device for insertion through the flexible hollow tube, the maintenance device being able to move freely through the flexible hollow tube and being disconnected from the latching mechanism; The shape and construction of the flexible hollow tube enable it to be positioned close to the rotatable component of the turbine engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latching mechanism after it has been inserted through the turbine engine's inlet port. The latching mechanism is configured to attach to the rotatable component when the rotatable component rotates; and After positioning, the maintenance device is used to operate through different openings among the plurality of openings at different times.

2. The device according to claim 1, characterized in that, The plurality of openings are located on different sides of the flexible hollow tube.

3. The device according to claim 2, characterized in that, The plurality of openings are arranged such that the maintenance device moves away from the flexible hollow tube in different directions.

4. The device according to claim 1, characterized in that, The latching mechanism includes a hook.

5. The device according to claim 4, characterized in that, The hook portion is integrally formed with the flexible hollow tube.

6. The device according to claim 1, characterized in that, The latching mechanism includes a wedge mechanism.

7. The device according to claim 1, characterized in that, It further includes an adapter for at least partially positioning within the turbine engine and configured to provide a guide path for the flexible hollow tube after insertion at the inlet port.

8. The device according to claim 1, characterized in that, The maintenance device is a first maintenance device, and while the flexible hollow tube is held in the turbine engine, the first maintenance device is removed from the flexible hollow tube, and a second maintenance device is inserted into the flexible hollow tube.

9. The device according to claim 1, characterized in that, The flexible hollow tube is made of silicone rubber or thermoplastic elastomer (TPE).

10. The device according to claim 1, characterized in that, The maintenance device mentioned above is a pipe mirror.

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