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

Technical Field

[0001] This technical field relates to the repair of aircraft engines. Background Art

[0002] General engines and aircraft engines need to be repaired in different ways. For example, it may be necessary to inspect the internal aircraft engine components to check for damage. If damage is detected, repair operations can sometimes be performed to fix the damage. For example, a drill or other tool can be used. Other types of maintenance operations can also be performed. Brief Description of the Drawings

[0003] By providing a method for repairing an aircraft engine, various needs are at least partially met, especially when studied in conjunction with the accompanying drawings. In the specification with reference to the drawings, a complete and enabling disclosure of the aspects of this specification for those of ordinary skill in the art is set forth, including its best mode, wherein:

[0004] Figure 1 A schematic diagram of a system for repairing an aircraft engine including various embodiments according to these teachings;

[0005] Figure 2 A cross-sectional view of a flexible hollow tube including a repair device according to various embodiments according to these teachings;

[0006] Figure 3 A schematic diagram of a system for repairing an aircraft engine deployed within an engine according to various embodiments according to these teachings;

[0007] Figure 4 A schematic diagram of a system for repairing an aircraft engine deployed within an engine according to various embodiments according to these teachings;

[0008] Figure 5 A schematic diagram of the distal end of a repair device having multiple openings according to various embodiments according to these teachings;

[0009] Figure 6 A schematic diagram of a latch mechanism according to various embodiments according to these teachings;

[0010] Figure 7 A flowchart of a method for repairing an aircraft engine according to various embodiments according to these teachings; and

[0011] Figure 8 A schematic diagram of an aircraft engine according to various embodiments according to these teachings.

[0012] The elements in the figures are shown for simplicity and clarity and are not necessarily drawn to scale. For example, the dimensions and / or relative positions of some of the elements in the figures may be exaggerated relative to other elements to assist in improving the understanding of the various embodiments of the present teachings. Additionally, common but well-understood elements that are useful or necessary in commercially viable embodiments are often not depicted so as to provide a less obstructed view of these different embodiments of the present teachings. Certain acts and / or steps may be described or depicted in a particular order of occurrence, but those skilled in the art will understand that no such specificity as to sequence is actually required. Detailed Description

[0013] The methods provided herein for servicing aircraft engines include servicing (e.g., inspecting and / or repairing) internal components of these engines. For example, these methods allow inspection of the shroud above the high-pressure turbine (HPT) blades using the borescope inspection (BSI) ports of these engines. Advantageously, cost savings are achieved due to the ability to quickly and easily determine faults in engine components without the use of complex insertion tools or procedures. These methods can also be customized for different engine types and other compressor and turbine stages.

[0014] In the methods provided herein, a flexible hollow tube having a latch mechanism (e.g., a hook) at its distal end is provided. A servicing device (e.g., a borescope) 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 of the tube, 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 servicing device. The flexible hollow tube includes a latch mechanism for securing the flexible hollow tube to a rotor blade or other engine component. Additionally, when the rotor rotates (e.g., 360 degrees), the flexible hollow tube serves as a tether attached 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 conduit, the servicing device can be inserted into or removed from the flexible hollow tube. When the servicing device includes a camera, these methods allow removal of the camera from the tube, changing the optical tip of the borescope or changing the view orientation of the servicing device, and returning to the same working position with the tube remaining attached at its distal end. Advantageously, the methods and devices described herein decouple the movement of the servicing device from the latch mechanism. Even when the distal end of the flexible hollow tube is locked to a blade (or other structure), the servicing device can move within the hollow flexible tube.

[0015] In many of these embodiments, an apparatus for inspecting internal components of an aircraft engine includes: a flexible hollow tube; a latch mechanism that is connected to or incorporated with the flexible hollow tube; and a servicing device that extends through the flexible hollow tube. The servicing device is movable freely through the flexible hollow tube and is decoupled from the latch mechanism. The flexible hollow tube is shaped and configured such that the flexible hollow tube can be positioned in proximity to a rotatable component of the aircraft engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latch mechanism after the flexible hollow tube is inserted through an access port of the aircraft engine.

[0016] In some aspects, the latch mechanism includes a hook or a wedge mechanism. Other examples of the latch mechanism are possible.

[0017] In a further aspect, the apparatus further includes an adapter. The adapter is for an engine having a plurality of housings to direct the flexible hollow tube into the engine and into the blades. In one example, the adapter is at least partially positioned within the engine, between an inner housing and an outer housing, and is configured to provide a guiding path for the flexible hollow tube after the flexible hollow tube is inserted through the access port of the engine.

[0018] In an example, the rotatable component includes a plurality of blades and the latch mechanism is coupled to a trailing edge of one or more of the plurality of blades. In other examples, the rotatable component includes a plurality of blades and the latch mechanism is coupled to a leading edge of one or more of the plurality of blades. Other attachment locations of the flexible hollow tube are possible.

[0019] In other aspects, during operation, the servicing device is removed from the flexible hollow tube and another servicing device is inserted into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine. The servicing devices can also be different. For example, one servicing device can be a borescope with a camera and another servicing device can be configured to perform repairs.

[0020] The flexible hollow tube can be made of various different materials. For example, the flexible hollow tube can be composed of silicone rubber or thermoplastic elastomer (TPE), including thermoplastic polyurethane (TPU) or ethylene vinyl acetate (EVA). Other examples are possible.

[0021] As described above, the servicing device can be several different devices, where these different devices have different types, different configurations, and / or perform different operations. For example, the servicing device can be a borescope. In some aspects, the borescope includes a camera and captures an image of the shroud of the engine. In other examples, the servicing device is configured to perform engine repair or maintenance operations (e.g., by drilling).

[0022] In other embodiments among these embodiments, a method for servicing an internal component of an aircraft engine includes inserting a flexible hollow tube into an inspection port of the aircraft engine. The flexible hollow tube has a latch mechanism connected to or integrated with 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 latch mechanism. A servicing device is inserted through the flexible hollow tube. The servicing device is free to move through the flexible hollow tube and is disengaged from the latch mechanism.

[0023] In a further aspect, the adapter can be at least partially inserted into the engine to provide a guiding path for the flexible hollow tube upon insertion at the access port. In a further aspect, the servicing device is removed from the flexible hollow tube and another servicing device is inserted into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

[0024] Except where different specific meanings have been otherwise set forth herein, the terms and expressions used herein have the ordinary technical meanings given to such terms and expressions by those skilled in the above-mentioned technical field. Unless specifically indicated otherwise, the word "or" as used herein shall be interpreted with a disjunctive construction rather than a conjunctive construction. Unless otherwise stated herein, the terms "coupled," "fixed," "attached to," etc. refer to both direct coupling, fixing, or attachment and indirect coupling, fixing, or attachment through one or more intermediate components or features.

[0025] Unless the context clearly dictates otherwise, the singular forms "a," "an," and "the" include plural references.

[0026] As used throughout this specification and the claims, approximating language is applied to modify any quantitative representation that can vary without resulting in a change in the basic function associated therewith. Thus, values modified by terms such as "about," "approximately," and "substantially" are not limited to the specified exact values. In at least some instances, the approximating language can 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 components and / or systems. For example, the approximating language can refer to within a 10% margin.

[0027] The above and other benefits may become more apparent upon a thorough review and study of the following detailed description.

[0028] Now refer jointly to Figure 1 、 Figure 2 、 Figure 3 and Figure 4, an example of a device 100 for servicing internal components of an aircraft engine is described. 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 of the flexible hollow tube 102, and a latch mechanism 106.

[0029] Figure 2 A cross-sectional view taken along line 103 of the flexible hollow tube 102 is shown (as Figure 1 shown). In this view, the servicing device 104 is disposed within the flexible hollow tube 102.

[0030] As specifically referenced Figure 3 and Figure 4 shown, the device 100 is inserted into the 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 this example, the engine 109 includes a housing 108 (having a port or opening 122) and an inner housing 110 (having a port or opening 123). An adapter 120 is located between the housing 108 and the inner housing 110, allowing the flexible hollow tube 102 to be guided between the port 122 and the port 123. If there is a single housing, the adapter 120 is not required. The adapter 120 can be constructed of a rigid material and inserted through the port 122 while inserting the servicing device 104. In other respects, the adapter 120 can be pre-positioned between the housing 108 and the inner housing 110 during the manufacture and / or assembly of the engine or at some other convenient time.

[0031] The engine 109 further includes a vane 112 and a blade 114. For simplicity, only a single blade and vane are shown, but it should be understood that the engine 109 includes multiple vanes and blades. The engine 109 also includes a shroud 116, which is deployed above (or radially outside) the blade 114 and extends completely around all of the rotor blades. The blade 114 is connected to a shaft 118, and the shaft 118 rotates to move the blade 114 (and other blades coupled to the shaft 118). The blade 114 also includes a leading edge 130 and a trailing edge 132.

[0032] The engine 109 can be any type of aircraft engine, including but not limited to a ducted turbofan aircraft engine and a non-ducted turbofan aircraft engine, to name just two examples. Other examples of engine types are also possible.

[0033] In some aspects, the flexible hollow tube 102 is made of a flexible material such as silicone rubber or thermoplastic elastomer (TPE) (such as 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 components, then winch friction may affect its behavior, and thus a material with a low coefficient of friction is preferred. In other aspects, the elastic modulus range of the material (such as 0.0005 - 5 GPa) is used to construct the flexible hollow tube 102. Other ranges of examples are also possible.

[0034] The cross-section of the flexible hollow tube 102 can be circular, but other cross-sections are also possible, for example, cross-sections with different shaped cross-sections are possible. For example, another example cross-section includes a flat surface that allows the flexible hollow tube 102 to sit on internal engine components in a defined orientation when positioned in the engine 109.

[0035] In other aspects, the flexible hollow tube 102 is capable of returning to its original shape after being temporarily deformed by being inserted into the engine 109 (for example, by being extruded through ports 122, 123, and / or adapter 120). In these aspects, the flexible hollow tube 102 can initially be formed and / or constructed to have a specific shape such that when the flexible hollow tube 100 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 the preformed shape), thus allowing for the easy attachment of the blade 114 and the deployment of the repair device 104. Then, the repair device 104 can be deployed in the correct or convenient position within the engine 109, allowing the repair device 104 to perform its task. For example, if the repair device 104 includes a camera, the preformed shape of the flexible hollow tube 102 allows the flexible hollow tube 104 to be easily attached to the blade 114, and the camera can obtain an image of the shroud 116. The behavior of the flexible hollow tube 102 can be considered to have hyperelastic properties because after the flexible hollow tube 102 has been stressed into a different shape (by inserting it through ports 122 and 123), after the stress is removed (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.

[0036] The servicing device 104 is any type of device that allows any type of work or operation to be performed within the engine 109. For example, the servicing device 104 can be a borescope and / or include a camera. The camera can acquire single or multiple images (e.g., movies or videos). In other aspects, the servicing device 104 can perform repair operations on engine components. For example, the servicing device 104 can include a drill, a sealant dispenser, a laser energy device, or other devices that can repair damage to engine components.

[0037] When the flexible hollow tube 102 is deployed within the engine 109, various types of servicing devices 104 can be deployed within the flexible hollow tube 102, removed from the flexible hollow tube 103, and then different servicing devices 104 inserted into the flexible hollow tube 102. For example, a first servicing device 104 (e.g., a borescope with a camera to acquire images) can be inserted within the flexible hollow tube 102 and operated within the flexible hollow tube 102; the first servicing device 104 can be removed from the flexible hollow tube 102, and then a second servicing device 104 (e.g., a maintenance device with a drill) can be inserted within the flexible hollow tube 102. The second servicing device 104 can be used to perform the repairs identified by the first servicing device 104.

[0038] The flexible hollow tube 102 can be manually inserted into the engine 109 through ports 122 and 123. The adapter 120 can also be manually inserted either before or while inserting 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. The removal of the flexible hollow tube 102 can be done manually or by a robot or machine.

[0039] 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 blade 114, the rotor can be rotated. The rotation of the rotor can be achieved by rotating the shaft 118 of the engine 109. When the shaft 118 rotates, all of the blades of the rotor attached to the shaft 118 (including the blade 114) rotate. For example, in one operation, the flexible hollow tube 102 is attached to the blade 114. A person (or machine) rotates the shaft 118 of the engine 109, thereby rotating the blade 114 attached to the shaft 118. When the rotation is performed, the camera of the servicing device 104 acquires images (e.g., movies or videos) of the shroud 116 (e.g., the entire shroud or multiple portions of the shroud 116).

[0040] A controller 101 (such as a microprocessor, etc.) can be coupled to a servicing device 104. The controller 101 can control the movement / insertion of the servicing device 104 (e.g., by moving the servicing device), control the operation of the servicing device 104 (e.g., when the servicing device 104 includes a drill bit, control the drilling of the servicing device 104), and / or analyze data from the servicing device 104 (e.g., when the servicing device 104 includes a camera, receive images from the servicing device 104 and present these images to the user on a display).

[0041] The latch mechanism 106 can be any type of device or mechanism for attaching, wedging, and / or securing the flexible hollow tube 102 to the vane 114 (or between one or more vanes). In various aspects and as shown in the examples of Figure 1 , Figure 2 , Figure 3 and Figure 4 , the latch mechanism 106 is a hook. The hook is sized to be able to attach to the vane of the engine. However, Figure 6 shows another example of a latch mechanism that is not a hook and secures the flexible hollow tube 102 via a wedging mechanism between the blade 112 and the vane 114. The latch mechanism 106 can be formed with the flexible hollow tube 102 (e.g., as an integral structure), or can be a separate part or component attached or bonded to the flexible hollow tube 102 (e.g., via threaded fasteners, adhesives, etc.). Another example of a latch mechanism can be an inflatable bag or balloon that is attached to or formed as part of the body of the tube 102 at or near the distal end of the tube 102.

[0042] In one example of use of the device 100, the shroud 116 in the high pressure turbine (HPT) is inspected through access ports 122 and 123. An adapter 120 having an internal passage connects ports 122 and 123 and guides the flexible hollow tube 102.

[0043] The flexible hollow tube 102 is inserted through port 122, adapter 120, and port 123. The flexible hollow tube 102 has been preformed into a specific shape, deforms as it passes through port 122, adapter 120, and port 123, and then reforms into a preset shape after exiting port 123. The preformed shape has been selected such that when the flexible hollow tube 102 resumes its original shape, the flexible hollow tube 102 will be positioned in the engine 109 to allow for easy attachment to the vane 114 and / or easy inspection of the shroud 116 by the servicing device 104. In one example, the preformed shape can be curved, but a wide variety of shapes, configurations, and dimensions can be employed.

[0044] A latch mechanism 106 having a hook-like feature at a distal portion 113 attaches the flexible hollow tube 102 to the vane 114. This can be performed manually or automatically.

[0045] Rotate the shaft 118 of the engine 109 to move the rotor and position the rotor blades (including vane 114) relative to the stator blades (including stator blade 112) in a predefined position. The adapter 120 is fitted into the port 122 and the flexible hollow tube 102 is inserted into the internal channel of the adapter 120 along a predefined orientation that guides the flexible hollow tube 102 towards the rotor blade including vane 114.

[0046] Push the flexible hollow tube 102 into the adapter 120 until a predefined length is reached, allowing the flexible hollow tube 101 to slide between the rotor blades (including vane 114) and positioning the latch mechanism (such as the hook-like feature) near the trailing edge 132 of the rotor blade 114.

[0047] The shaft 118 of the engine 109 is rotated manually or automatically in a predefined direction to engage the latch mechanism (such as the hook) and pull the flexible hollow tube 102 and the rotor blade. In some aspects, when the latch mechanism 106 is a hook, the hook can be located at or near the tip of the flexible hollow tube 102 and the opening 107 is located behind the hook. Insert the servicing device 104 (e.g., a borescope) through the flexible hollow tube 102 until the distal portion 105 of the servicing device 104 exits through the opening 107 near or at the distal portion 113 of the flexible hollow tube 102.

[0048] Then, the rotor of the engine 109 is rotated again. The servicing device 104 captures multiple images / videos of the shroud 116 during this rotational movement, such as a 360-degree rotor rotation. After performing the inspection and / or repair operation, the servicing device 104 (e.g., a borescope) is removed from the flexible hollow tube 102. The shaft 118 of the engine 109 is rotated in a direction opposite to the original rotation direction to retract the flexible hollow tube 102 from the engine 109. In some aspects, during the initial rotation, more of the flexible hollow tube 102 is pulled into the engine, while the opposite occurs during removal. In other aspects, friction holds the latch mechanism 106 in place on the vane, preventing the vane from sliding along the blade.

[0049] Now referring to Figure 5 , an example of a flexible hollow tube 102 having multiple openings is described. In Figure 1 , Figure 2 , Figure 3 and Figure 4 's examples, the flexible hollow tube 102 has a single opening 107 at the distal portion 113 of the flexible hollow tube 102. In Figure 5In the example, the flexible hollow tube 102 has openings 140, 142, and 144. A user can select which opening 140, 142, or 144 the servicing device 104 should emerge from. Additionally, one servicing device 104 can use one of the openings 140, 142, and 144, while a second and / or different servicing device 104 can use a different one of the openings 140, 142, and 144.

[0050] The openings 140, 142, and 144 can be located at the distal portion 113 of the flexible hollow tube, but it should be understood that the openings can be placed anywhere along the length of the flexible hollow tube 102. Additionally, although three openings 140, 142, and 144 are shown, it should be understood that any number of openings can be used. The openings 140, 142, and 144 can be located on different sides of the flexible hollow tube 102, allowing the servicing device 104 (or servicing devices) to exit the flexible hollow tube 102 in different directions.

[0051] Using multiple openings can facilitate the deployment of the flexible hollow tube 102 within the engine 109 and then leaving the flexible hollow tube 102 in place, providing a series of apertures aligned with engine features, such as nozzle leading edge features, for example having a similar angular periodicity, and then sequentially moving inspection or repair devices to each aperture of the tube for some 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, for example a cross-section having a flat outer surface to sit on internal engine components (e.g., sitting on the gas path inner diameter), and thereby control the orientation of the flexible hollow tube 102.

[0052] Now referring to Figure 6 , an example of a latch mechanism 106 that is not a hook is described. In the examples of Figure 1 , Figure 2 , Figure 3 and Figure 4 , the latch mechanism 106 uses a hook. However, in the example of Figure 6 , the latch mechanism 106 uses a wedge 121 to wedge or secure the flexible hollow tube 102 between the vane 114 and another vane 119. The wedge 121 can be constructed of any suitable material that is soft enough to pass through the ports 122 and 123, but strong enough to allow the flexible hollow tube 102 to be secured.

[0053] Other options for the latch mechanism are possible, including suction or magnetic-based structures attached or incorporated with the flexible hollow tube 102 that allow attachment to the vane 114. In other aspects, the flexible hollow tube 102 can be attached to other structures within the engine 109.

[0054] Now referring toFigure 7 , an example of a method for servicing an aircraft engine is described. At step 702, a flexible hollow tube 102 is inserted into a port in the engine 109. The flexible hollow tube 102 has a latch mechanism 106 that is connected to or integral with the flexible hollow tube 102.

[0055] At step 704, the flexible hollow tube 102 is positioned adjacent to a rotatable component of the aircraft engine 109, such as a blade 114. At step 706, the flexible hollow tube 102 is attached to the rotatable component (e.g., blade 114) via the latch mechanism 106. In the example, the latch mechanism 106 is a hook. Other examples are possible.

[0056] At step 708, a servicing device 104 is inserted through the flexible hollow tube 102. The servicing device 104 is free to move through the flexible hollow tube 102 and is decoupled from the latch mechanism 106.

[0057] At step 710, the blade is rotated. At step 712, data can be collected from the servicing device 104 and the data can be analyzed.

[0058] In other examples, an 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 the latch mechanism 106 is coupled to the trailing edge 132 of one or more of the plurality of blades. In additional examples, the rotatable component is a plurality of blades, and the latch mechanism 106 is coupled to the leading edge 130 of one or more of the plurality of blades.

[0059] In other aspects, after the servicing device 104 is removed from the flexible hollow tube 102, another servicing 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 servicing devices 104.

[0060] Now referring to Figure 8 , a schematic cross-sectional view of a conventional gas turbine engine 810 for an aircraft in which the imaging and inspection system described herein can be operated is described. The gas turbine engine 810 has a generally longitudinally extending axis or centerline 812 that extends from a front portion 814 to a rear portion 816. The gas turbine engine 810 includes, in downstream serial flow relationship: a fan section 818 that includes a fan 820; a compressor section 822 that includes a booster or low pressure (LP) compressor 824 and a high pressure (HP) compressor 826; a combustion section 828 that includes a burner 830; a turbine section 832 that includes an HP turbine 834 and an LP turbine 836; and an exhaust section 838.

[0061] The fan section 818 includes a fan casing 840 that surrounds a fan 820. The fan 820 includes a plurality of fan blades 842 that are radially disposed about a centerline 812.

[0062] The HP compressor 826, combustor 830, and HP turbine 834 form a core 844 of a gas turbine engine 810 that generates combustion gases. The core 844 is surrounded by a core casing 846 that may be coupled to the fan casing 840.

[0063] An HP shaft or spool 848 that is coaxially disposed about the centerline 812 of the gas turbine engine 810 drivingly connects the HP turbine 834 to the HP compressor 826. An LP shaft or spool 850 that is coaxially disposed within the larger diameter annular HP spool 848 about the centerline 812 of the gas turbine engine 810 drivingly connects the LP turbine 836 to the LP compressor 824 and the fan 820.

[0064] The LP compressor 824 and HP compressor 826 each include a plurality of compressor stages 852, 854, where a set of compressor blades 856, 858 rotates relative to a corresponding set of stationary compressor vanes 860, 862 (also referred to as nozzles) to compress or pressurize a fluid flow through the stage. In a single compressor stage 852, 854, the plurality of compressor blades 856, 858 may be arranged in a ring and radially extend from a blade platform to a blade tip relative to the centerline 812, while the corresponding stationary compressor vanes 860, 862 are positioned downstream and adjacent to the rotating blades 856, 858. It should be noted that Figure 8 the number of blades, vanes, and compressor stages shown is only selected for illustrative purposes, and other numbers are possible.

[0065] The HP turbine 834 and LP turbine 836 each include a plurality of turbine stages 864, 866, where a set of turbine blades 868, 870 rotates relative to a corresponding set of stationary turbine vanes 872, 874 (also referred to as nozzles) to extract energy from a fluid flow through the stage. In a single turbine stage 864, 866, the plurality of turbine blades 868, 870 may be arranged in a ring and radially extend from a blade platform to a blade tip relative to the centerline 812, while the corresponding stationary turbine vanes 872, 874 are positioned upstream and adjacent to the rotating blades 868, 870. It should be noted that Figure 8 the number of blades, vanes, and turbine stages shown is only selected for illustrative purposes, and other numbers are possible.

[0066] In operation, the rotating fan 820 supplies ambient air to the LP compressor 824, and then the LP compressor 824 supplies the 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, generating 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 driving of the LP turbine 836 drives the LP spool 850 to rotate the fan 820 and the LP compressor 824.

[0067] It should be understood that although Figure 8 not depicted in, the gas turbine engine 810 may also define a plurality of openings that permit inspection of the various components within the gas turbine engine 810. For example, the gas turbine engine 810 may define a plurality of access tool openings at various axial positions within the compressor section, the combustor section 828, and / or the turbine section 832. Additionally, as will be discussed below, the gas turbine engine 810 may include, for example, one or more igniter ports within the combustor section 828 of the gas turbine engine 810, which may permit inspection of the combustor section 828.

[0068] Through these openings, the flexible hollow tube 102 may be inserted together with the servicing device 104, as described elsewhere herein. For example, one of these openings may be near the turbine section 832 and permit access to the turbine section 832. The latch mechanism 106 may be secured to one of the turbine blades 868, 870 and various operations may be performed using the servicing device 104. It should also be understood that these methods may be performed at any location within the gas turbine engine 810 where an opening is available, such as within the combustor section 828.

[0069] It should be further understood that Figure 8 the exemplary gas turbine engine 810 depicted in is only 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 inspected 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, a turboprop engine, a turbojet engine, etc., or may be an industrial gas turbine engine for power generation, fluid pumping, etc.

[0070] A further aspect of the invention is provided by the subject matter of the following clauses:

[0071] A device for repairing internal components of an aircraft engine, the device comprising: a flexible hollow tube; a latch mechanism connected to or integrated with the flexible hollow tube; a repair device for insertion through the flexible hollow tube, the repair device being able to move freely through the flexible hollow tube and being disconnectable from the latch mechanism; and wherein the shape and configuration of the flexible hollow tube enable the flexible hollow tube to be positioned proximate to a rotatable component of the aircraft engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latch mechanism after the flexible hollow tube is inserted through an access port of the aircraft engine.

[0072] The device according to any of the preceding clauses, wherein the latch mechanism comprises a hook portion.

[0073] The device according to any of the preceding clauses, wherein the hook portion is integrally formed with the flexible hollow tube.

[0074] The device according to any of the preceding clauses, wherein the latch mechanism comprises a wedge mechanism.

[0075] The device according to any of the preceding clauses, further comprising an adapter for at least partially positioning within the engine and configured to provide a guiding path for the flexible hollow tube after insertion at the access port.

[0076] The device according to any of the preceding clauses, wherein the repair device is removed from the flexible hollow tube and another repair device is inserted into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

[0077] The device according to any of the preceding clauses, wherein the flexible hollow tube includes an opening at a distal end of the flexible hollow tube.

[0078] The device according to any of the preceding clauses, wherein the flexible hollow tube is made of silicone rubber or thermoplastic elastomer (TPE).

[0079] The device according to any of the preceding clauses, wherein the repair device is a borescope.

[0080] The device according to any of the preceding clauses, wherein the borescope includes a camera.

[0081] A method for repairing 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 latch mechanism connected to or integrated with 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 latch mechanism; and inserting a repair device through the flexible hollow tube, the repair device being able to move freely through the flexible hollow tube and being disengaged from the latch mechanism.

[0082] The method according to any of the preceding clauses, further comprising rotating the rotatable component to attach the latch mechanism to the component.

[0083] The method according to any of the preceding clauses, wherein the latch mechanism comprises a hook or a wedge mechanism.

[0084] The method according to any of the preceding clauses, further comprising positioning an adapter at least partially within the engine to provide a guiding path for the flexible hollow tube after insertion at the inlet port.

[0085] The method according to any of the preceding clauses, wherein the rotatable component is a plurality of blades, and the latch mechanism is coupled to the trailing edge of one or more of the plurality of blades.

[0086] The method according to any of the preceding clauses, wherein the rotatable component is a plurality of blades, and the latch mechanism is coupled to the leading edge of one or more of the plurality of blades.

[0087] The method according to any of the preceding clauses, further comprising removing the repair device from the flexible hollow tube and inserting another repair device into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

[0088] The method according to any of the preceding clauses, wherein the flexible hollow tube is made of silicone rubber or thermoplastic elastomer (TPE).

[0089] The method according to any of the preceding clauses, wherein the repair device is a borescope.

[0090] The method according to any of the preceding clauses, wherein the borescope comprises a camera and captures an image of the shroud of the engine.

[0091] 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. An apparatus for repairing internal components of an aircraft engine, characterized in that, The device includes: A flexible hollow tube; A latch mechanism, the latch mechanism being connected to or integrated with the flexible hollow tube; A maintenance device for insertion through the flexible hollow tube, the maintenance device being capable of freely moving through the flexible hollow tube and being disengaged from the latch mechanism; Wherein the shape and configuration of the flexible hollow tube enable the flexible hollow tube to be positioned in proximity to a rotatable component of an aircraft engine, thereby allowing the flexible hollow tube to be attached to the rotatable component via the latch mechanism after the flexible hollow tube is inserted through an inlet port of the aircraft engine.

2. The device according to claim 1, characterized in that, Wherein the latch mechanism includes a hook portion.

3. The device according to claim 2, characterized in that, Wherein the hook portion is integrally formed with the flexible hollow tube.

4. The device according to claim 1, characterized in that, Wherein the latch mechanism includes a wedge mechanism.

5. The device according to claim 1, characterized in that, Further includes an adapter for at least partially positioning within the aircraft engine and configured to provide a guiding path for the flexible hollow tube after insertion at the inlet port.

6. The device according to claim 1, characterized in that, Wherein the flexible hollow tube includes an opening at a distal end of the flexible hollow tube.

7. The device according to claim 1, characterized in that, Wherein 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.

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

9. The device according to claim 1, characterized in that, Wherein the maintenance device is a borescope.

10. The device according to claim 9, characterized in that, Wherein the borescope includes a camera.

Images