Patent ID: 12195202

Elements in the figures are illustrated for simplicity and clarity and have not necessarily been drawn to scale. For example, the dimensions and/or relative positioning of some of the elements in the figures may be exaggerated relative to other elements to help to improve understanding of various embodiments of the present teachings. Also, common but well-understood elements that are useful or necessary in a commercially feasible embodiment are often not depicted in order to facilitate a less obstructed view of these various embodiments of the present teachings. Certain actions and/or steps may be described or depicted in a particular order of occurrence while those skilled in the art will understand that such specificity with respect to sequence is not actually required.

DETAILED DESCRIPTION

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

In the approaches provided herein, a flexible hollow tube with a latching mechanism (e.g., a hook) at the distal end of the tube is provided. A servicing device (e.g., a borescope) is inserted through an opening in the proximal end of the tube and passes through the tube and exits the tube through, or uses a line of sight provided by, an 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 the latching mechanism to secure the flexible hollow tube onto a rotor blade or other engine component. Further, the flexible hollow tube serves as a tether to connect to the rotor blade while the rotor is rotated (e.g., through 360 degrees). The servicing device can be inserted into the flexible hollow tube or removed from the flexible hollow tube even when the flexible hollow tube is engaged to a rotor blade through the opening near the proximal end of the guide tube. When the servicing device includes a camera, these approaches allow for removing the camera from the tube, changing the optical tips of the borescope or changing the orientation of the view of the servicing device, and returning to the same working location through the tube which remains attached at its distal end. Advantageously, the approaches and devices described herein decouple the movement of servicing device and the latching mechanism. The servicing device can move inside the hollow flexible tube even when the distal end of the flexible hollow tube is latched on to a blade (or other structure).

In many of these embodiments, an apparatus for inspecting internal components of an aircraft engine includes a flexible hollow tube; a latching mechanism connected to or incorporated with the flexible hollow tube; and a servicing device extending through the flexible hollow tube. The servicing device is freely moveable through the flexible hollow tube and decoupled from the latching mechanism. The flexible hollow tube is shaped and configured so as to enable proximate positioning of the flexible hollow tube with respect to a rotatable component of an aircraft engine allowing attachment of the flexible hollow tube to the rotatable component via the latching mechanism after the flexible hollow tube is inserted through an entry port of the aircraft engine.

In aspects, the latching mechanism comprises a hook or a wedge mechanism. Other examples of latching mechanisms are possible.

In further aspects, the apparatus further comprises an adapter. The adapter is used in engines with multiple casings to guide the flexible hollow tube into the engine and to the blades. In one example, the adapter is positioned at least partially within the engine between an inner casing and outer casing and is configured to provide a guide path for the flexible hollow tube after the flexible hollow tube is inserted through an entry port of the engine.

In examples, the rotatable component comprises a plurality of blades and the latching mechanism couples to a trailing edge of the one or more of the plurality of blades. In other examples, the rotatable component comprises a plurality of blades and the latching mechanism couples to a leading edge of the one or more of the plurality of blades. Other attachment locations are possible for the flexible hollow tube.

In still other aspects, during operations 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 may also be different. For example, one servicing device may be a borescope with a camera and the other servicing device may be configured to perform repairs.

The flexible hollow tube can be constructed of a variety of different materials. For example, the flexible hollow tube may be constructed of Silicone rubber or Thermoplastic elastomers (TPE), including Thermoplastic polyurethane (TPU) or Ethylene vinyl acetate (EVA). Other examples are possible.

As mentioned, the servicing devices may be a number of different devices where these different devices are of different types, are of different configurations, and/or perform different operations. For example, the servicing device may be a borescope. In aspects, the borescope includes a camera and an image is taken of a shroud of the engine. In other examples, the servicing device is configured to perform engine repairs or maintenance operations (e.g., by drilling).

In others of these embodiments, an approach for servicing internal components of an aircraft engine includes inserting a flexible hollow tube into an inspection port of an aircraft engine. The flexible hollow tube has a latching mechanism connected to or incorporated with the flexible hollow tube. The flexible hollow tube is positioned proximate to 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 moveable through the flexible hollow tube and decoupled from the latching mechanism.

In further aspects, an adapter may be inserted at least partially within the engine so as to provide a guide path for the flexible hollow tube after being inserted at the entry port. In still further aspects, 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 terms and expressions used herein have the ordinary technical meaning as is accorded to such terms and expressions by persons skilled in the technical field as set forth above except where different specific meanings have otherwise been set forth herein. The word “or” when used herein shall be interpreted as having a disjunctive construction rather than a conjunctive construction unless otherwise specifically indicated. The terms “coupled,” “fixed,” “attached to,” and the like refer to both direct coupling, fixing, or attaching, as well as indirect coupling, fixing, or attaching through one or more intermediate components or features, unless otherwise specified herein.

The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise.

Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and/or systems. For example, the approximating language may refer to being within a 10 percent margin.

The foregoing and other benefits may become clearer upon making a thorough review and study of the following detailed description.

Referring now collectively toFIG.1,FIG.2,FIG.3, andFIG.4, one example of an apparatus100for servicing internal components of an aircraft engine is described. As shown in these figures, the apparatus100includes a flexible hollow tube102, a servicing device104(having a distal end portion105) extending through an opening107of the flexible hollow tube102, and a latching mechanism106.

FIG.2shows a cross sectional view of the flexible hollow tube102taken along a line103(as shown inFIG.1). In this view, the servicing device104is disposed within the flexible hollow tube102.

As shown especially with respect toFIG.3andFIG.4, the apparatus100is inserted into an engine109(for simplicity, only a portion of the engine109relating to the turbine section of the engine109is shown inFIG.3andFIG.4). In this example, the engine109includes an outer casing108(with a port or opening122) and an inner casing110(with a port or opening123). An adapter120is positioned between the outer casing108and the inner casing110allowing the flexible hollow tube102to be guided between the port122and the port123. If there is a single casing, the adapter120is not needed. The adapter120may be constructed of a rigid material and inserted through the port122at the same time the servicing device104is inserted. In other aspects, the adapter120may be pre-positioned between the outer casing108and the inner casing110during manufacturing and/or assembly of the engine or at some other convenient time.

The engine109further includes a vane112and a blade114. For simplicity, only a single blade and vane are shown, but it will be appreciated that the engine109includes multiple vanes and blades. The engine109also includes a shroud116deployed above (or radially outward of) the blade114and extending completely around all the rotor blades. The blade114is connected to a shaft118, which rotates thereby moving the blade114(and the other blades coupled to the shaft118). The blade114also includes a leading edge130and a trailing edge132.

The engine109may be any type of aircraft engine including, but not limited to a ducted turbofan aircraft engine and an unducted turbofan aircraft engine to mention two examples. Other examples of engine types are possible.

In aspects, the flexible hollow tube102is constructed of a flexible material such as Silicone rubber or Thermoplastic elastomers (TPE) (e.g., Thermoplastic polyurethane (TPU) or Ethylene vinyl acetate (EVA)). The material used to construct the flexible hollow tube102may have coefficients of friction in the range of 0.05-0.5. As the flexible hollow tube102deploys, capstan friction may affect its behaviour if the coefficient of friction is high and if it rubs on a stationary component so that material with a low coefficient of friction is preferred. In still other aspects, a range of modulus of elasticity (e.g., 0.0005-5 GPa) for the material is used to construct the flexible hollow tube102. Other examples of ranges are possible.

The flexible hollow tube102may be circular in cross section but other cross sections are possible such as cross sections having differently shaped cross sections are possible. For example, another example cross section includes a flat surface allowing the flexible hollow tube102to sit on internal engine components in a defined orientation when positioned in the engine109.

In yet other aspects, the flexible hollow tube102has the ability to return to its original shape after being temporarily deformed by being inserted into the engine109(e.g., by being squeezed through the ports122,123, and/or the adapter120). In these regards, the flexible hollow tube102may be initially formed and/or configured to have a specific shape so that when the flexible hollow tube102is inserted into the engine109the shape allows distal portion113of the flexible hollow tube102to be positioned in vicinity of the blade114(by virtue of the pre-formed shape) allowing easy attachment of the blade114and deployment of the servicing device104. The servicing device104can then be deployed at a correct or convenient position within the engine109allowing the servicing device104to perform its task. For example, if the servicing device104includes a camera, then the pre-formed shape of the flexible hollow tube102allows for easy attachment of the flexible hollow tube102to the blade114and the ability of the camera to obtain images of the shroud116. The behaviour of the flexible hollow tube102can be considered to be a super elastic nature in that after the after the flexible hollow tube102has been stressed into a different shape (by inserting it through ports122and123), after this stress is removed (because the flexible hollow tube102has emerged from the ports122and123), the flexible hollow tube102then returns to its original, pre-formed shape.

The servicing device104is any type of device that allows any type of work or operation to be performed within the engine109. For example, the servicing device104may be a borescope and/or include a camera. The camera may obtain single or multiple images (e.g., a movie or video). In other aspects, the servicing device104may perform repair operations with engine components. For example, the servicing device104may include a drill, sealant dispenser, laser energy device or other devices that can repair damage to engine components.

While the flexible hollow tube102is deployed within the engine109, various types of servicing devices104may be deployed within the flexible hollow tube102, removed from the flexible hollow tube102, and then different servicing devices104inserted into the flexible hollow tube102. For example, a first servicing device104(e.g., a borescope with a camera to obtain images) may inserted and operated within the flexible hollow tube102; the first servicing device104may be removed from the flexible hollow tube102, and then a second servicing device104(e.g., a maintenance device with a drill) may be inserted within the flexible hollow tube102. The second servicing device104may be used to perform repairs that have been identified by the first servicing device104.

The flexible hollow tube102may be manually inserted into engine109through the ports122and123. The adapter120may also be inserted manually either before the insertion of the flexible hollow tube102or with the insertion of the flexible hollow tube102. Alternatively, the flexible hollow tube102and/or adapter120may be inserted using a robot or other machine. Removal of the flexible hollow tube102may be accomplished either manually or by a robot or machine as well.

In other aspects and in some operations, once the flexible hollow tube102has been inserted into a rotor section of the engine109and attached to the blade114, the rotor may be rotated. Rotation of the rotor may be accomplished by turning the shaft118of the engine109. As the shaft118is rotated, all the blades of the rotor attached to the shaft118(including the blade114) are rotated. For example, in one operation the flexible hollow tube102is attached to the blade114. A person (or machine) rotates the shaft118of the engine109thereby rotating the blade114attached to the shaft118. As the rotation is performed, a camera of the servicing device104obtains images (e.g., a movie or video) of the shroud116(e.g., the entire shroud or multiple portions of the shroud116).

A controller101(e.g., a microprocessor or the like) may be coupled to the servicing device104. The controller101may control the movement/insertion of the servicing device104(e.g., by moving the service device), control operations of the servicing device104(e.g., control a drill of the servicing device104when the servicing device104includes a drill), and/or analyze data from the servicing device104(e.g., receive images from the servicing device104when the servicing device104includes a camera and render these images on a display to a user).

The latching mechanism106may be any type of device or mechanism used to attach, wedge, and/or secure the flexible hollow tube102to the blade114(or between one or more of the blades). In aspects and as shown in the example ofFIG.1,FIG.2,FIG.3, andFIG.4the latching mechanism106is a hook. The dimensions of the hook allow it to attach to a blade of the engine. However, another example of a latching mechanism is shown inFIG.6that is not a hook and secures the flexible hollow tube102via a wedge mechanism between the vane112and the blade114. The latching mechanism106may be formed with the flexible hollow tube102(e.g., as a monolithic structure), or may be a separate part or component that is attached or incorporated (e.g., via a threaded fastener, an adhesive, etc.) with the flexible hollow tube102. Another example of a latching mechanism may be an inflatable bag or balloon, either attached to or formed as part of the body of the tube102at or near the distal end of the tube102.

In one example of the use of the apparatus100, inspection of the shroud116in a high pressure turbine (HPT) is performed by accessing the ports122and123. The adapter120with an internal passage connects the ports122and123and guides the flexible hollow tube102.

The flexible hollow tube102is inserted through the port122, the adapter120, and the port123. The flexible hollow tube102has been pre-formed into a specific shape, deforms as it passes through the port122, adapter120, and port123and then reforms into the preset shape after exiting the port123. The pre-formed shape has been selected such that when the flexible hollow tube102returns to its original shape, the flexible hollow tube102will be positioned in the engine109so as to allow easy attachment to the blade114and/or easy inspection of the shroud116by the servicing device104. The pre-formed shape may be curved in one example, but may take on a large number of shapes, configurations, and dimensions.

The latching mechanism106with a hook feature at the distal portion113attaches the flexible hollow tube102to the blade114. This can be performed manually or automatically.

The shaft118of the engine109is turned to move the rotor and position the rotor blades (including the blade114) in a pre-defined position with respect to the vanes (including the vane112). The adapter120is fitted into the port122and the flexible hollow tube102is inserted into the internal passage of the adapter120along a pre-defined orientation that directs the flexible hollow tube102towards the rotor blades including the blade114.

The flexible hollow tube102is pushed into the adapter120until a pre-defined length is reached allowing the flexible hollow tube102to glide in between the rotor blades (including the blade114) and position the latching mechanism (e.g., a hook feature) near the trailing edge132of the rotor blade114.

The shaft118of the engine109is manually or automatically rotated in a pre-defined direction to engage the latching mechanism (e.g., hook) and pull the flexible hollow tube102along with the rotor blades. In aspects, when the latching mechanism106is a hook, the hook may be located at or near the tip of the flexible hollow tube102and the opening107located behind the hook. The servicing device104(e.g., a borescope) is inserted through the flexible hollow tube102until the distal end portion105of the servicing device104exits through the opening107near at the distal portion113of the flexible hollow tube102.

The rotor of the engine109is then rotated again. The servicing device104takes multiple images/videos of shroud116during this rotational movement through, for example, 360 degrees of rotor rotation. After inspection and/or the servicing operations are performed, the servicing device104(e.g., borescope) is removed from the flexible hollow tube102. The shaft118of the engine109is rotated in a direction opposite to the original direction of rotation to retrieve the flexible hollow tube102from the engine109. In aspects, during initial rotation more of the flexible hollow tube102is pulled into the engine and the opposite occurs during removal. In other aspects, friction hold the latching mechanism106in place on a blade preventing the blade from sliding along the blade.

Referring now toFIG.5, one example of a flexible hollow tube102having multiple openings is described. In the examples ofFIG.1,FIG.2,FIG.3, andFIG.4, the flexible hollow tube102has a single opening107at the distal end portion113of the flexible hollow tube102. In the example ofFIG.5, the flexible hollow tube102has openings140,142, and144. The user can select which opening140,142, or144the servicing device104should emerge. In addition, one servicing device104may use one of the openings140,142, and144, while a second and/or different servicing device104may use a different one of the openings140,142, and144.

The openings140,142, and144may be at the distal end portion113of the flexible hollow tube, but it will be appreciated that the openings can be placed at any location along the length of the flexible hollow tube102. Also, although three openings140,142, and144are shown, it will be understood that any number of openings may be used. The openings140,142, and144may be located on the different sides of the flexible hollow tube102allowing the servicing device104(or multiple servicing devices) to exit the flexible hollow tube102in different directions.

The use of multiple openings makes it convenient to deploy the flexible hollow tube102inside the engine109and then leave the flexible hollow tube102in place, providing a series of apertures aligned to engine features such as a nozzle leading edge feature, e.g., having a similar angular periodicity, and then move the inspection or repair device to each aperture of the tube in turn to perform some maintenance, inspection etc. The flexible hollow tube102may be circular in cross section but other cross sections (e.g., square, rectangular, hexagonal, etc.) are possible such as cross sections having a flat external surface to sit on internal engine components (e.g., to sit on a gas path internal diameter) and thereby control orientation of the flexible hollow tube102.

Referring now toFIG.6, an example of a latching mechanism106that is not a hook is described. In the example ofFIG.1,FIG.2,FIG.3, andFIG.4, the latching mechanism106used a hook. In the example ofFIG.6, however, the latching mechanism106uses wedges121to wedge or secure the flexible hollow tube102between the blade114and another blade119. The wedges121may be constructed of any suitable material that is flexible enough to fit through the ports122and123but strong enough to allow securement of the flexible hollow tube102.

Other options for the latching mechanism are possible including suction or magnetic-based structures attached or incorporated with the flexible hollow tube102that allow attachment to the blade114. In still other aspects, the flexible hollow tube102may be attached to other structures within the engine109.

Referring now toFIG.7, one example of an approach for servicing an aircraft engine is described. At step702, the flexible hollow tube102is inserted into a port in the engine109. The flexible hollow tube102has the latching mechanism106, which is connected to or incorporated with the flexible hollow tube102.

At step704, the flexible hollow tube102is positioned to be proximate to a rotatable component of the aircraft engine109such as the blade114. At step706, the flexible hollow tube102is attached to the rotatable component (e.g., the blade114) via the latching mechanism106. In examples, the latching mechanism106is a hook. Other examples are possible.

At step708, the servicing device104is inserted through the flexible hollow tube102. The servicing device104is freely moveable through the flexible hollow tube102and decoupled from the latching mechanism106.

At step710, the blade is rotated. At step712, data may be gathered from the servicing device104and this data may be analyzed.

In other examples, the adapter120is inserted at least partially within the engine so as to provide a guide path for the flexible hollow tube102. In other aspects, the rotatable component is a plurality of blades (including the blade114) and the latching mechanism106couples to the trailing edge132of the one or more of the plurality of blades. In still other examples, the rotatable component is a plurality of blades and the latching mechanism106couples to the leading edge130of the one or more of the plurality of blades.

In other aspects, after removing the servicing device104from the flexible hollow tube102another servicing device104is inserted into the flexible hollow tube102while the flexible hollow tube102remains in the aircraft engine109. This can be repeated with a number of different servicing devices104.

Referring now toFIG.8, a schematic cross-sectional diagram of a conventional gas turbine engine810for an aircraft in which an imaging and inspection system described herein can operate is described. The gas turbine engine810has a generally longitudinally extending axis or centerline812extending forward814to aft816. The gas turbine engine810includes, in downstream serial flow relationship, a fan section818including a fan820, a compressor section822including a booster or low pressure (LP) compressor824and a high pressure (HP) compressor826, a combustion section828including a combustor830, a turbine section832including a HP turbine834and a LP turbine836, and an exhaust section838.

The fan section818includes a fan casing840surrounding the fan820. The fan820includes a plurality of fan blades842disposed radially about the centerline812.

The HP compressor826, the combustor830, and the HP turbine834form a core844of the gas turbine engine810which generates combustion gases. The core844is surrounded by core casing846which can be coupled with the fan casing840.

An HP shaft or spool848disposed coaxially about the centerline812of the gas turbine engine810drivingly connects the HP turbine834to the HP compressor826. An LP shaft or spool850, which is disposed coaxially about the centerline812of the gas turbine engine810within the larger diameter annular HP spool848, drivingly connects the LP turbine836to the LP compressor824and fan820.

The LP compressor824and the HP compressor826respectively include a plurality of compressor stages852,854, in which a set of compressor blades856,858rotate relative to a corresponding set of static compressor vanes860,862(also called a nozzle) to compress or pressurize the stream of fluid passing through the stage. In a single compressor stage852,854, multiple compressor blades856,858can be provided in a ring and extend radially outwardly relative to the centerline812, from a blade platform to a blade tip, while the corresponding static compressor vanes860,862are positioned downstream of and adjacent to the rotating blades856,858. It is noted that the number of blades, vanes, and compressor stages shown inFIG.8were selected for illustrative purposes only, and that other numbers are possible.

The HP turbine834and the LP turbine836respectively include a plurality of turbine stages864,866, in which a set of turbine blades868,870are rotated relative to a corresponding set of static turbine vanes872,874(also called a nozzle) to extract energy from the stream of fluid passing through the stage. In a single turbine stage864,866, multiple turbine blades868,870can be provided in a ring and extend radially outwardly relative to the centerline812, from a blade platform to a blade tip, while the corresponding static turbine vanes872,874are positioned upstream of and adjacent to the rotating blades868,870. It is noted that the number of blades, vanes, and turbine stages shown inFIG.8were selected for illustrative purposes only, and that other numbers are possible.

In operation, the rotating fan820supplies ambient air to the LP compressor824, which then supplies pressurized ambient air to the HP compressor826, which further pressurizes the ambient air. The pressurized air from the HP compressor826is mixed with fuel in the combustor830and ignited, thereby generating combustion gases. Some work is extracted from these gases by the HP turbine834, which drives the HP compressor826. The combustion gases are discharged into the LP turbine836, which extracts additional work to drive the LP compressor824, and the exhaust gas is ultimately discharged from the gas turbine engine810via the exhaust section838. The driving of the LP turbine836drives the LP spool850to rotate the fan820and the LP compressor824.

It will be appreciated that although not depicted inFIG.8, the gas turbine engine810may further define a plurality of openings allowing for inspection of various components within the gas turbine engine810. For example, the gas turbine engine810may define a plurality of insertion tool openings at various axial positions within the compressor section, the combustion section828, and/or the turbine section832. Additionally, as will be discussed below, the gas turbine engine810may include one or more igniter ports within, e.g., the combustion section828of the gas turbine engine810, that may allow for inspection of the combustion section828.

Through these openings, the flexible hollow tube102can be inserted along with the servicing device104as has been described elsewhere herein. For example, one of these openings may be in the vicinity of and allow access to the turbine section832. The latching mechanism106may be secured to one of the turbine blades868,870and the various operations performed with the servicing device104. It will also be appreciated that these approaches may be performed at any location in the gas turbine engine810where the openings are available such as in the combustion section828.

It should further be appreciated that the exemplary gas turbine engine810depicted inFIG.8is by way of example only, and that in other exemplary embodiments, the gas turbine engine810may 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 with the tool described herein. For example, in other exemplary embodiments, the engine may not be a turbofan engine, and instead may be configured as a turboshaft engine, a turboprop engine, turbojet engine, etc., or may be an industrial gas turbine engine for electricity generation, fluid pumping etc.

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

An apparatus for servicing internal components of an aircraft engine, the apparatus comprising: a flexible hollow tube; a latching mechanism connected to or incorporated with the flexible hollow tube; a servicing device to be inserted through the flexible hollow tube, the servicing device being freely moveable through the flexible hollow tube and decoupled from the latching mechanism; and wherein the flexible hollow tube is shaped and configured so as to enable proximate positioning of the flexible hollow tube with respect to a rotatable component of an aircraft engine allowing attachment of the flexible hollow tube to the rotatable component via the latching mechanism after the flexible hollow tube is inserted through an entry port of the aircraft engine.

The apparatus of any of the preceding clauses, wherein the latching mechanism comprises a hook

The apparatus of any of the preceding clauses, wherein the hook is integrally formed with the flexible hollow tube.

The apparatus of any of the preceding clauses, wherein the latching mechanism comprises a wedge mechanism.

The apparatus of any of the preceding clauses, further comprising an adapter, the adapter to be positioned at least partially within the engine and being configured to provide a guide path for the flexible hollow tube after being inserted at the entry port.

The apparatus of any of the preceding clauses, wherein 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 apparatus of any of the preceding clauses, wherein the flexible hollow tube comprises openings at a distal end of the flexible hollow tube.

The apparatus of any of the preceding clauses, wherein the flexible hollow tube is constructed of Silicone rubber or Thermoplastic elastomers (TPEs).

The apparatus of any of the preceding clauses, wherein the servicing device is a borescope.

The apparatus of any of the preceding clauses, wherein the borescope includes a camera.

A method for servicing internal components of an aircraft engine, the method comprising: inserting a flexible hollow tube into a port in an aircraft engine, the flexible hollow tube having a latching mechanism connected to or incorporated with the flexible hollow tube; positioning the flexible hollow tube proximate to 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 moveable through the flexible hollow tube and decoupled from the latching mechanism.

The method of any of the preceding clauses, further comprising rotating the rotatable component to cause the latching mechanism to attach to the component.

The method of any of the preceding clauses, wherein the latching mechanism comprises a hook or a wedge mechanism.

The method of any of the preceding clauses, further comprising positioning an adapter at least partially within the engine so as to provide a guide path for the flexible hollow tube after being inserted at the entry port.

The method of any of the preceding clauses, wherein the rotatable component is a plurality of blades and the latching mechanism couples to a trailing edge of the one or more of the plurality of blades.

The method of any of the preceding clauses, wherein the rotatable component is a plurality of blades and the latching mechanism couples to a leading edge of the one or more of the plurality of blades.

The method of any of the preceding clauses, further comprising removing the servicing device from the flexible hollow tube and inserting another servicing device into the flexible hollow tube while the flexible hollow tube remains in the aircraft engine.

The method of any of the preceding clauses, wherein the flexible hollow tube is constructed of Silicone rubber or Thermoplastic elastomers (TPEs).

The method of any of the preceding clauses, wherein the servicing device is a borescope.

The method of any of the preceding clauses, wherein the borescope includes a camera and an image is taken of a shroud of the engine.

Those skilled in the art will recognize that a wide variety of modifications, alterations, and combinations can be made with respect to the above-described embodiments without departing from the scope of the invention, and that such modifications, alterations, and combinations are to be viewed as being within the ambit of the inventive concept.