An inflatable device with a guiding mechanism for effective engine cleaning.

Abstract

An inflatable device equipped with a guiding mechanism and a method for installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, the inflatable device includes a frame and an inflatable bladder connected thereto. The frame is formed of a flexible and non-stretchable material. The inflatable bladder is formed of an inflatable material. To install the inflatable device within the annular chamber of the gas turbine engine, the frame is inserted into a first access port of the engine and moved circumferentially around the chamber. The frame is retracted through a second access port. By pushing the frame into the first access port and / or pulling the frame out from the second access port, the inflatable bladder is moved to the appropriate position within the chamber. Once positioned, the inflatable bladder is inflated to form an annular seal.

Description

Technical Field

[0001] This topic generally relates to gas turbine engines, and more specifically, to inflatable devices and methods of using such inflatable devices to create an in-situ temporary barrier within a gas turbine engine. Background Technology

[0002] Gas turbine engines require regular cleaning to remove environmental and self-generated contaminants, including films, particles, dirt, metals, and combustion products deposited on the engine's compressor, combustion, and / or turbine sections. For example, aviation gas turbine engines sometimes undergo "online" foam cleaning or wing-mounted foam cleaning. Foam cleaning can improve engine cycle efficiency, which lowers exhaust gas temperatures. Consequently, fuel consumption can be reduced, and engine on-wing time can be extended. Foam injected into or otherwise introduced into the engine can flow through certain sections of the engine's core to clean various components therein. The inventors of this disclosure have invented an inflatable device and a method of using the inflatable device to facilitate the cleaning of gas turbine engines, such as foam cleaning. Summary of the Invention

[0003] Aspects and advantages of the invention will be set forth in part in the description which follows, or will be obvious from the description, or may be learned by practice of the invention.

[0004] In one aspect, a method is provided for forming an in-situ temporary barrier within a gas turbine engine. The method includes installing an inflatable device within the gas turbine engine, the inflatable device having a frame and an inflatable bladder connected to the frame. Furthermore, the method includes inflating the inflatable bladder with an inflation fluid, causing the inflatable bladder to form a seal along the fluid path of the gas turbine engine.

[0005] In another aspect, an inflatable device is provided for forming an in-situ temporary barrier within a gas turbine engine. The inflatable device includes a frame and an inflatable bladder longitudinally connected to the frame and operable to receive inflation fluid. The inflatable bladder is formed of an inflatable or foldable material.

[0006] In another aspect, a method is provided for forming an in-situ temporary barrier within a gas turbine engine. The method includes installing an inflatable device within an annular chamber defined by the gas turbine engine. The inflatable device has a frame and an inflatable bladder connected to the frame, the inflatable bladder being formed of an inflatable or foldable material. Installing the inflatable device within the annular chamber includes guiding a free section of the frame through a first access port of the gas turbine engine and circumferentially through the annular chamber, the free section being a section along which the inflatable bladder is not connected; retracting a portion of the free section of the frame through a second access port of the gas turbine engine, positioning a portion of the free section outside the annular chamber; and moving the inflatable device such that the inflatable bladder extends annularly or substantially annularly within the annular chamber by performing at least one of the following: pulling a portion of the free section extending from the second access port to the outside of the annular chamber; and pushing a portion of the inflatable device extending from the first access port to the outside of the annular chamber. Furthermore, the method includes inflating the inflatable bladder with an inflation fluid, thereby forming an annular seal within the annular chamber.

[0007] These and other features, aspects, and advantages of the invention will be better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0008] This specification, with reference to the accompanying drawings, sets forth the complete and discloseable contents of the invention for those skilled in the art, including its preferred mode, wherein:

[0009] Figure 1 Schematic cross-sectional views of exemplary aero gas turbine engines according to various embodiments of this subject are provided;

[0010] Figure 2 Provided Figure 1 A schematic cross-sectional view of the rear end of the compressor section, combustion section and high-pressure turbine section of a gas turbine engine;

[0011] Figure 3 A schematic diagram of an example inflatable device according to an exemplary embodiment of this subject is provided;

[0012] Figure 4 Provided along Figure 3 A schematic cross-sectional view of an inflatable device taken from line 4-4;

[0013] Figure 5 A schematic diagram of another example inflatable device according to an example embodiment of this subject is provided;

[0014] Figure 6A flowchart is provided for a method of forming an in-situ temporary barrier within a gas turbine engine using an inflatable device, according to an example embodiment of this subject matter; and

[0015] Figures 7 to 10 Provided according to Figure 6 A schematic axial cross-sectional view of an inflatable device installed and inflated within a gas turbine engine. Detailed Implementation

[0016] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Detailed description uses numerals and letter names to refer to features in the drawings. Similar or analogous reference numerals in the drawings and description are used to refer to similar or analogous parts of the invention. As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of a single component. The terms “upstream” and “downstream” refer to the relative flow direction of fluid flow in a fluid path. For example, “upstream” refers to the flow direction from which the fluid flows, and “downstream” refers to the flow direction to which the fluid flows. “HP” indicates high pressure, and “LP” indicates low pressure.

[0017] Furthermore, as used herein, the term "axial" or "axially" refers to a dimension along the longitudinal axis of the engine. The term "forward," used with "axial" or "axially," refers to the direction toward the engine inlet, or a component relatively closer to the engine inlet compared to another component. The term "rear," used with "axial" or "axially," refers to the direction toward the engine nozzle, or a component relatively closer to the engine nozzle compared to another component. The term "radial," or "radially," refers to a dimension extending between the engine's central longitudinal axis (or centerline) and the engine's outer circumference. Radial inward is the direction toward the longitudinal axis, and radial outward is the direction away from the longitudinal axis.

[0018] The approximate language used in this specification and claims is intended to modify any quantitative expression that may be varied without altering the underlying function. Therefore, values ​​modified by one or more terms, such as “approximately,” “about,” and “substantially,” are not limited to specified precise values. In at least some instances, 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 1, 2, 4, 10, 15, or 20%.

[0019] Various aspects of this disclosure relate to an inflatable device equipped with a guiding mechanism, and a method of installing the inflatable device to form an in-situ temporary barrier within a gas turbine engine. This inflatable device can facilitate the cleaning of gas turbine engines. In particular, the inventors have recognized that a challenge of foam cleaning of gas turbine engines is that foam often fails to penetrate and clean the small secondary cooling passages of the engine's combustor and turbine modules. Instead, foam tends to partially accumulate and collapse into liquid within the combustor volume, partially flowing into the combustor chamber and through the turbine flow path, but resulting in very little foam flowing through the cavities and passages of the turbine nozzles, shrouds, and blades within the turbine section. Therefore, the inventors have invented an inflatable device that can be positioned within a gas turbine engine to facilitate its cleaning, particularly in areas that are traditionally difficult to clean, such as the cavities and passages of components located within the turbine section of the engine.

[0020] In one aspect, the inflatable device includes a frame and an inflatable bladder connected thereto. The frame can be formed of a material that allows it to bend conformally to, for example, a surface that slides into contact with the frame, and is non-stretchable under tension. In other words, the frame can be formed of a flexible and non-stretchable material. The frame can be flexible because it can bend to conform to the contours of a surface (e.g., the curved surface of a burner liner). However, the flexible frame can have stiffness so that it does not deform or collapse when moved, for example, when pushed. The frame can be non-stretchable so that it does not stretch (or the stretching effect is negligible) when placed under tension. In this respect, when the frame is pulled, it results in immediate movement or displacement of the frame. The inflatable bladder is formed of an inflatable material or acts as a foldable bag. Thus, when the inflatable bladder is inflated with an inflation fluid, it can expand or unfold, forming a seal along the fluid path of the gas turbine engine. For example, the seal formed by the inflatable bladder can be an annular seal.

[0021] The frame extends longitudinally between a first end and a second end. The inflatable bladder also extends longitudinally between the first end and the second end. The inflatable bladder is connected to the frame along its longitudinal length. The frame may include a bladder support segment to which the inflatable bladder is connected. The frame also includes one or more "free" segments or sections to which the inflatable bladder is not connected. For example, the frame may include a free segment extending from a first end of the frame across the bladder support segment and a free extension segment extending from a second end of the frame across the bladder support segment. In this respect, the bladder support segment is positioned between the free segment and the free extension segment.

[0022] In some embodiments, the free section may extend longitudinally at least the longitudinal length of the inflatable bladder. In other embodiments, the free section may extend longitudinally at least half the longitudinal length of the inflatable bladder. The frame may be formed as a single continuous portion or may be formed as segments connected by connecting members (such as hinges). The frame may have any suitable cross-sectional shape. For example, the frame may have a non-circular cross-section, such as a rectangular cross-section. In some embodiments, the frame has at least one flat or planar surface. In such embodiments, the flat surface is the surface of the frame opposite to the surface where the inflatable bladder is attached. The cross-sectional size of the frame is configured such that the frame and the inflatable bladder can be received within the access port.

[0023] To install the inflatable device in the annular chamber of a gas turbine engine (e.g., the annular combustion chamber of its combustor), a first end of the skeleton is inserted into a first access port of the engine, and a free section is circumferentially moved around the annulus of the annular chamber. That is, the free section can be moved such that the first end of the skeleton traverses at least 360° within the annular chamber. In this way, the free section of the skeleton is guided through the first access port of the gas turbine engine and circumferentially through the annular chamber. After circumferentially traversing the combustion chamber, the first end of the skeleton is retracted through a second access port axially aligned with and circumferentially spaced from the first access port. For example, the first and second access ports could be ignition ports. A tool, such as a spring-loaded claw, can be inserted through the second access port and used to grasp the free section of the skeleton. This tool can be used to retract the first end of the skeleton through the second access port or to pull the first end of the skeleton out of the combustion chamber. Other tools can also be considered for retracting the skeleton. As an example, a hook can be used to retract a nickel-titanium alloy ring attached to one end of the skeleton. As another example, a magnetic head or material can be attached to or integrated with the skeleton, and a magnetic tool can be used to retract the skeleton by attracting the magnetic head.

[0024] In some implementations, the inflatable bladder is moved into position within the annular chamber by grasping the free extension section and further pushing the frame and the inflatable bladder connected thereto into a first access port and / or further pulling the free section of the frame out of a second access port. The pushing and pulling motion causes the inflatable bladder to move circumferentially around the annulus of the combustion chamber. When positioned, the inflatable bladder is inflated with an inflation fluid, such as compressed air. The inflated bladder forms a seal, acting as a temporary in-situ barrier along the core airflow path of the gas turbine engine. For example, the seal may be an annular seal. With the inflatable bladder inflated to form an annular seal, one or more service operations can be performed. For example, a foam cleaning operation can be performed with the inflatable bladder inflated to form an annular seal, which can ultimately result in more effective foam cleaning, particularly in the turbine section. In particular, the annular seal formed by the inflatable bladder prevents foam from entering and accumulating in the combustion chamber, which ultimately increases the foam volume flowing into the cavities of components located downstream of the combustion section. In some embodiments, the annular seal can thereby prevent at least fifty percent (50%) of the working fluid (e.g., foam volume) from passing through. In some embodiments, the annular seal can prevent at least seventy percent (70%) of the working fluid from passing through. In other embodiments, the annular seal can prevent at least ninety percent (90%) of the working fluid from passing through. In a further embodiment, the annular seal can prevent one hundred percent (100%) of the working fluid from passing through.

[0025] In some alternative embodiments, the frame can be inserted through an access port, guided circumferentially through the chamber, and retracted from the same access port. In such embodiments, the inflatable bladder can be moved into position within the annular chamber by further pushing the frame and the inflatable bladder connected thereto into the access port and / or further pulling the free section of the frame out of the same access port. In other embodiments, the frame can be inserted through the access port and guided into the chamber without needing to be retracted through the access port.

[0026] Now refer to the attached diagram, Figure 1 A schematic cross-sectional view of a gas turbine engine 100 according to an exemplary embodiment of this subject is provided. Figure 1 In one embodiment, the gas turbine engine 100 is a high-bypass turbofan jet engine for aviation, configured to be mounted on an aircraft, such as an underwing configuration or a tail-mounted configuration. Figure 1 As shown, for reference, the gas turbine engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C extending 360 degrees around the longitudinal centerline 102 of the gas turbine engine 100, which are parallel to or coaxial with the longitudinal centerline 102 of the gas turbine engine 100.

[0027] The gas turbine engine 100 includes a fan section 104 and a core engine 106 disposed downstream of the fan section 104. The core engine 106 includes a generally tubular core shroud 108 defining an annular core inlet 110. The core shroud 108 encloses, in a series flow relationship: a compressor section 112 including a turbocharger or low-pressure compressor 114 and a high-pressure compressor 116; a combustion section 118; a turbine section 120 including a high-pressure turbine 122 and a low-pressure turbine 124; and an exhaust nozzle section 126. A high-pressure shaft or spool 128 drivesly connects the high-pressure turbine 122 to the high-pressure compressor 116. An LP shaft or spool 130 drivesly connects the LP turbine 124 to the LP compressor 114. The compressor section 112, combustion section 118, turbine section 120, and exhaust nozzle section 126 collectively define a core airflow path 132 through the core engine 106.

[0028] Fan section 104 includes a fan 134 having a plurality of fan blades 136 circumferentially spaced and coupled to a fan rotor 138. The fan blades 136 and the fan rotor 138 are rotatable together about a longitudinal centerline 102. The fan rotor 138 may be operatively coupled to or may form part of an LP shaft 130. As an example, the fan rotor 138 may be operatively coupled to the LP shaft 130 in a direct-drive configuration. As another example, the fan rotor 138 may be operatively coupled to a gearbox. Fan section 104 also includes a rotatable rotating body or forward nacelle 144 having an aerodynamic shape to facilitate airflow through the plurality of fan blades 136. Furthermore, fan section 104 includes an annular fan casing or outer nacelle 146 that circumferentially surrounds at least a portion of the fan 134 and / or the core engine 106. The nacelle 146 is supported relative to the core engine 106 by a plurality of circumferentially spaced outlet guide vanes 148. In addition, the downstream section 150 of the nacelle 146 extends to the outside of the core engine 106 to define a bypass airflow passage 152 therebetween.

[0029] During operation of the gas turbine engine 100, a certain amount of air 154 enters the gas turbine engine 100 through the nacelle 146 and / or the relevant inlet 156 of the fan section 104. As the certain amount of air 154 passes through the fan blades 136, a first portion of the air 154, as indicated by arrow 158, is directed or diverted to the bypass airflow passage 152, while a second portion of the air 154, as indicated by arrow 160, is directed or diverted to the annular core inlet 110 and enters the low-pressure compressor 114. The pressure of the second portion of air 160 is increased as it is diverted through the high-pressure compressor 116 and enters the combustion section 118.

[0030] The second portion 160 of the compressed air from the compressor section mixes with the fuel and enters the combustion chamber 198. Figure 2 Combustion occurs within a combustion chamber 198, defined by a burner 176 positioned within a combustion section 118, to provide combustion gas 162. The combustion gas 162 is guided from the combustion section 118 along a hot gas path 174 through a high-pressure turbine 122, where a portion of thermal and / or kinetic energy is extracted from the combustion gas 162 via a series of high-pressure turbine stator blades 164 and high-pressure turbine rotor blades 166 connected to a high-pressure shaft or spindle 128, thereby rotating the high-pressure shaft or spindle 128 to support the operation of the high-pressure compressor 116. The combustion gas 162 is then guided to a low-pressure turbine 124, where a second portion of thermal and kinetic energy is extracted from the combustion gas 162 via a series of low-pressure turbine stator blades 168 and low-pressure turbine rotor blades 170 connected to a low-pressure shaft or spindle 130, thereby rotating the low-pressure shaft or spindle 130 to support the operation of the low-pressure compressor 114 and / or the rotation of the fan 134.

[0031] Combustion gas 162 is then directed through the injection exhaust nozzle section 126 of the core engine 106 to provide propulsive thrust. Simultaneously, the pressure of the first portion 158 of air is significantly increased as it is directed through the bypass airflow passage 152 before exiting from the fan nozzle exhaust section 172 of the gas turbine engine 100, also providing propulsive thrust. The high-pressure turbine 122, the low-pressure turbine 124, and the injection exhaust nozzle section 126 at least partially define the hot gas path 174 for directing combustion gas 162 through the core engine 106.

[0032] like Figure 1 As further shown, the gas turbine engine 100 may include a plurality of access ports defined through its housing and / or frame for providing internal access to the core engine 106. For example, the gas turbine engine 100 may include a plurality of access ports 222 defined through its housing 140. Figure 1 (Only six of them are shown in the image) are used to provide internal access to one or two of the compressors 114, 116, one or two of the turbines 122, 124, and / or the combustor 176 of the combustion section 118. The core cover 108 can be opened to expose the shell or housing 140 to provide access to the access port 222.

[0033] In some embodiments, access ports 222 may be spaced apart along the axial direction A of the core engine 106. For example, access ports 222 may be spaced apart along the axial direction A along each compressor 114, 116, combustor 176, and / or each turbine 122, 124, such that at least one access port 222 is located at each compressor stage, combustor 176, and / or turbine stage to provide access to internal components located at that stage. Furthermore, access ports 222 may also be spaced apart around the core engine 106 in the circumferential direction C. For example, multiple access ports 222 may be circumferentially spaced around each compressor stage, combustor 176, and / or turbine stage. For example, the access port 222 providing access to the combustor 176 may be an igniter port. In some embodiments, the diameter of the igniter port may be less than one inch. It should be understood that although access port 222 is generally described herein with reference to providing internal access to one or both of the compressors 114, 116, the burner 176 and / or the turbines 122, 124, the gas turbine engine 100 may include access port 222 providing access to any suitable internal location of the engine 100.

[0034] Furthermore, it is understandable that Figure 1 The exemplary gas turbine engine 100 described herein is provided by way of example only, and in other exemplary embodiments, the gas turbine engine 100 may have any other suitable configuration. Furthermore or alternatively, aspects of this disclosure can be used in any other suitable aero gas turbine engine, such as a turboshaft engine, turboprop engine, turbojet engine, etc. Moreover, aspects of this disclosure can also be further used in any other land-based gas turbine engine, such as a power generation gas turbine engine, or any aerospace-derived gas turbine engine, such as a marine gas turbine engine.

[0035] Figure 2 Provided Figure 1 A schematic cross-sectional view of the rear portion of the compressor section 112, combustion section 118, and turbine section 120 of the core engine 106. More specifically, Figure 2 The diagram shows the rear end of the high-pressure compressor 116, the combustion section 118, and the high-pressure turbine 122.

[0036] like Figure 2 The high-pressure compressor 116 depicted includes a diffuser 178 at its rear or downstream end. In the gas turbine engine 100 ( Figure 1 During operation, compressed air exits the high-pressure compressor 116 through diffuser 178. Diffuser 178 diffuses the compressed air into the combustion zone 118. Furthermore, as described below, in the gas turbine engine 100 ( Figure 1During the foam cleaning process, the foam can leave the high-pressure compressor 116 through the diffuser 178 and flow downstream into the combustion section 118.

[0037] The combustion section 118 of the core engine 106 is annularly enclosed by a radially arranged inner burner housing 180 and an outer burner housing 182. Both the inner burner housing 180 and the outer burner housing 182 extend longitudinally or along the length direction A and surround the burner assembly 184 in an annular ring. The inner burner housing 180 and the outer burner housing 182 are connected together at an annular diffuser 178 at the front end of the combustion section 118.

[0038] Burner assembly 184 includes an inner liner 186 and an outer liner 192. The inner liner 186 extends along an axial direction A between a rear end 188 and a front end 190. The outer liner 192 also extends along an axial direction A between a rear end 194 and a front end 196. The outer liner 192 is positioned outside the inner liner 186 in a radial direction R. The inner liner 186 and the outer liner 192 together form burner 176 and at least partially define a combustion chamber 198 between them. The inner liner 186 and the outer liner 192 are attached to a front radial wall 200, which is generally referred to as the dome or dome plate of burner 176.

[0039] The burner assembly 184 further includes a plurality of fuel nozzles 204. Figure 2 (Only one is shown in the image), a plurality of fuel nozzles 204 are spaced apart in the circumferential direction C and are at least partially positioned within corresponding openings defined by the front radial wall 200. More specifically, a plurality of fuel nozzles 204 are at least partially positioned in the radial direction R within corresponding openings of the front radial wall 200. During operation, compressed air from the compressor section 112 of the gas turbine engine 100 flows around or through the fuel nozzles 204, wherein the compressed air is mixed with fuel and ignited to produce combustion gases 162 in the combustion chamber 198. Figure 1 The burner assembly 184 includes a plurality of igniters 220 spaced apart from each other in the circumferential direction C. Figure 2 (Only one is shown in the image). Igniter 220 facilitates the ignition of the compressed air / fuel mixture within combustion chamber 198.

[0040] Furthermore, the core engine 106 also defines a chamber 206 surrounding the combustor assembly 184. Specifically, the chamber 206 is generally defined between the combustor housings 180, 182 and the bushings 186, 192. The outer combustor housing 182 and the outer bushing 192 define an outer chamber 208 generally disposed radially R outside the combustion chamber 198, and the inner combustor housing 180 and the inner bushing 186 define an inner chamber 210 generally disposed radially R inside the combustion chamber 198.

[0041] The high-pressure turbine 122 of the turbine section 120 includes a series of high-pressure turbine stator blades 164 and high-pressure turbine rotor blades 166. In this embodiment, the high-pressure turbine 122 includes two stages: a first stage 212 and a second stage 214. The first stage 212 has an annular array of first-stage HP turbine stator blades 164 disposed immediately downstream of the combustion chamber 198 and an annular array of first-stage HP turbine rotor blades 166 disposed immediately downstream of the first-stage HP turbine stator blades 164. The second stage 214 has an annular array of second-stage HP turbine stator blades 164 disposed immediately downstream of the first-stage HP turbine rotor blades 166 and an annular array of second-stage HP turbine rotor blades 166 disposed immediately downstream of the second-stage HP turbine stator blades 164. It is worth noting that the high-pressure turbine stator blades 164 and HP turbine rotor blades 166 of the two stages 212 and 214 may include various cavities, channels, fluid circuits, etc. For example, this cavity can provide cooling for the HP turbine stator blades 164 and HP turbine rotor blades 166 during operation. Furthermore, the first-stage turbine shroud 202 may include various cavities, channels, fluid circuits, etc., for cooling purposes.

[0042] Now for reference Figure 1 and Figure 2 During foam cleaning of the gas turbine engine 100, a foam solution or foam F ( Figure 2 The foam is introduced into the gas turbine engine 100, for example, through one or more compressor inlet ports while the HP shaft 128 is rotating. Depending on the one or more inlet ports into which the foam is introduced, the foam F can flow downstream through the LP compressor 114 and / or the HP compressor 166. The foam F can exit the HP compressor 166 through the diffuser 178 and can flow into the air chamber 206.

[0043] According to the inventive aspect of this disclosure, the inflatable device 300 (in) Figure 2(Indicated by dashed lines) can be installed and inflated to form a temporary in-situ barrier or annular seal, thereby preventing foam F from flowing into the annular combustion chamber 198 during cleaning operations. Therefore, foam F is forced to flow elsewhere. In particular, a portion of foam F is forced to flow into the inner chamber 210. That portion of foam F flowing in the inner chamber 210 flows downstream in the axial direction A and eventually reaches the HP turbine 120 of the turbine section 118. As shown, foam F can flow into the cavities (not shown or labeled) of the HP turbine stator blades 164 and HP turbine rotor blades 166 of the first stage 212. As a result, the cavities of the HP turbine stator blades 164 and HP turbine rotor blades 166 can be effectively cleaned with foam F. Furthermore, by sealing the combustion chamber 198 with the inflatable device 300, a portion of foam F can be forced to flow outward in the radial direction R into the outer chamber 208. That portion of foam F flowing in the outer chamber 208 flows downstream in the axial direction A and eventually reaches the HP turbine 120 of the turbine section. Foam F may flow into and / or pass through other cavities of interest (not shown or labeled), such as the cooling cavity of the shroud 202 or its shroud section that annularly surrounds the HP turbine rotor blades 166.

[0044] The inflatable device 300 can be installed through any suitable access port, such as Figure 1 One of the access ports 222 provided for internal access to the burner 176 is shown. For example, an access port providing access to the burner 176 could be an igniter port. Once installed, the inflatable device 300 can be inflated with an inflating fluid (e.g., compressed air) to form an annular seal, as will be explained below. In some embodiments, the inflatable device 300 can be installed, inflated to form an annular seal, and then left in place during a cleaning operation, for example, for effectively cleaning turbine components. In other embodiments, the inflatable device 300 can be installed, inflated to form an annular seal, and then removed at a point during the cleaning operation to ensure that the combustion chamber 198, in addition to the turbine components, is also effectively foam-cleaned. In still other embodiments, the inflatable device 300 can be installed in the outer air chamber 208, inflated with an inflating fluid to form a seal, and foam can be introduced downstream of the inflatable device 300, forcing the foam through the turbine shroud 202. In this respect, the foam can be driven forward rather than backward to clean the desired components. The following will provide example embodiments of the inflatable device 300 and the method of using the inflatable device 300.

[0045] Figure 3 A schematic diagram of an example inflatable device 300 according to an exemplary embodiment of this subject matter is provided. The inflatable device 300 includes a frame 310 and an inflatable bladder 350 attached to or connected to the frame 310. Generally, the frame 310 serves as a guide mechanism for mounting the inflatable device 300 to a gas turbine engine (such as...). Figure 1 The gas turbine engine 100 is located within the gas turbine engine. When the inflatable device 300 is positioned appropriately within the gas turbine engine... Figure 3 The deflated inflatable bladder 350 shown can be inflated with an inflation fluid (e.g., compressed air) so that the inflatable bladder 350 forms a seal along the fluid path of the gas turbine engine. For example, as Figure 2 As shown, the inflatable device 300 can be installed in the annular combustion chamber of the burner, and then the inflatable bladder 350 can be inflated to form an annular seal therein, serving as an in-situ temporary barrier within the gas turbine engine. Forming such a seal or barrier is advantageous for many applications, such as during foam engine cleaning.

[0046] The frame 310 extends longitudinally or lengthwise between a first end 312 and a second end 314. In this embodiment, the frame 310 is formed from a single continuous piece and has three sections, including a free section 316, a bladder support section 318, and a free extension section 320. The free section 316 extends longitudinally from the first end 312 to the bladder support section 318. The free section 316 is the "free end" of the frame 310, which is not attached to or connected to the inflatable bladder 350. As described below, the free section 316 can be used to "catch" or guide the inflatable device 300 circumferentially through the annular chamber. In some embodiments, the length of the free section 316 in the longitudinal or lengthwise direction is equal to or greater than the length of the bladder support section 318 of the frame 310 in the longitudinal or lengthwise direction.

[0047] The bladder support section 318 extends longitudinally between the free section 316 and the free extension section 320. The inflatable bladder 350 is connected to or attached to the bladder support section 318 of the skeleton 310. Specifically, the inflatable bladder 350 is connected to or attached to the first surface 322 of the skeleton 310. Figure 4 The inflatable airbag 350 can be longitudinally connected to or attached to the frame 310, or more specifically, as... Figure 3 As shown, the bladder support section 318 can be longitudinally connected to or attached to the frame 310. In some embodiments, the entire longitudinal length of the inflatable bladder 350 is connected to or attached to the frame 310.

[0048] The free extension section 320 of the frame 310 extends longitudinally between the bladder support section 318 and the second end 314. The free extension section 320 is also a "free end" and is not attached to or connected to the inflatable bladder 350. As described below, the free extension section 320 can be used by an operator or machine to push or move the inflatable device 300 through the access port and into position within the gas turbine engine chamber. Specifically, the operator or machine can grasp the free extension section 320 and push the inflatable device 300 into place.

[0049] In some embodiments, the skeleton 310 is formed of a flexible and non-stretchable material. For example, in some embodiments, the skeleton 310 is formed of a material having a flexural modulus in the range of 100-1000 ksi. Additionally, or alternatively, in some embodiments, the skeleton is formed of a material having a tensile strength greater than 46 MPa (6672 psi). Thus, in some embodiments, the skeleton 310 is formed of acrylonitrile-butadiene-styrene (ABS) material. In other embodiments, the skeleton 310 is formed of nylon material. Furthermore, in some embodiments, the skeleton 310 may be prefabricated. For example, in some embodiments, the skeleton 310 may be prefabricated to have a circular or substantially circular shape. For example, prefabricating the skeleton 310 into a circular shape can advantageously facilitate the movement of the inflatable device 300 through the annular chamber. In some embodiments, the free section 316 and the bladder support section 318 of the skeleton 310 are formed of the same material. In some embodiments, the free section 316, the bladder support section 318, and the free extension section 320 are all formed of the same material. In other embodiments, the free section 316 and the bladder support section 318 of the skeleton 310 are formed of different materials. As an example, the free section 316 may be formed of leads, chains, ropes, etc., while the bladder support section 318 may be formed of ABS material.

[0050] Figure 4 Provided along Figure 3 A schematic cross-sectional view of the inflatable device 300, taken from line 4-4. As shown, the frame 310 has a non-circular cross-section. In particular, in this embodiment, the frame 310 has a rectangular cross-section. The frame 310 has a first surface 322 and a second surface 324 positioned opposite to the first surface 322. As described above, the inflatable bladder 350 is connected to or attached to the first surface 322. The frame 310 also has sidewalls, including a first sidewall 326 and a second sidewall 328 positioned opposite to the first sidewall 326. It is noteworthy that the non-circular cross-section of the frame 310, or in this example, the rectangular cross-section of the frame 310, has increased stiffness, which is designed to prevent or reduce the twisting of the frame 310 as it moves through the annular chamber, and the rectangular cross-section reduces bending stiffness to conform to the annular flow path of the burner. The flat second surface 324 and the flat first sidewall 326 and second sidewall 328 can be used with surfaces defining the annular chamber (e.g., the liner 186 defining the combustion chamber 198; see Figure 2 It can be joined together and can prevent the skeleton 310 from twisting.

[0051] for Figure 4 In the depicted embodiment, the lateral width W1 of the frame 310 is greater than the thickness T1 of the frame 310. In this way, the second surface 324 is more likely to be the surface of the frame 310 defining the annular chamber (e.g., the liner 186 defining the combustion chamber 198; see...). Figure 2 The surfaces that engage and maintain this engagement further prevent or reduce twisting of the skeleton 310 during circumferential movement within the annular chamber. In some embodiments, the lateral width W1 of the skeleton 310 is less than twenty-five millimeters (25 mm; 1 inch).

[0052] In some embodiments, the frame 310 has at least one flat surface, wherein the flat surface is not a surface on which the frame 310 is connected or attached to the inflatable bladder 350. For example, the second surface 324 may be a flat surface. The flat second surface 324 may facilitate movement of the frame 310, thereby allowing the inflatable device 300 to pass through the chamber. The first surface 322, as well as the first sidewall 326 and the second sidewall 3328, may also have flat surfaces, or in this embodiment, curved surfaces.

[0053] In addition, such as Figure 3 As shown, the inflatable bladder 350 extends longitudinally or lengthwise between the first end 352 and the second end 354. It should be noted that the inflatable bladder 350 is connected to or attached to the frame 310. In this embodiment, the inflatable bladder 350 is longitudinally connected to the first surface 322 of the bladder support section 318 of the frame 310. Figure 4 In some embodiments, the inflatable bladder 350 is connected to or attached to the frame 310 for at least one-quarter of its total longitudinal length. In other embodiments, the inflatable bladder 350 is connected to or attached to the frame 310 for at least half of its total longitudinal length. In still other embodiments, the inflatable bladder 350 is connected to or attached to the frame 310 for at least three-quarters of its total longitudinal length.

[0054] The inflatable bladder 350 can be inflated using an inflatable fluid, such as compressed air or liquid. Figure 10 As shown, inflation fluid can be supplied to the inflatable bladder 350 by a fluid supply system 390. The fluid supply system 390 includes a fluid supply device 392 containing inflation fluid. The fluid supply system 390 also includes one or more fluid supply lines 394 that fluidly connect the fluid supply device 392 to the inflatable bladder 350. In this respect, the inflatable bladder 350 can be fluidly coupled or connected to the fluid supply device 392. A fitting 360, coupled or connected to the inflatable bladder 350 at a second end 354 of the inflatable bladder 350, can be connected to a complementary connector 396 of one of the fluid supply lines 394. The fitting 360 provides an inlet and an outlet for inflation fluid to enter or leave the inflatable bladder 350. Figure 3 and Figure 9In this configuration, the inflatable bladder 350 is shown as deflated or in a deflated state. During the installation of the inflatable device 300 into the annular chamber, the inflatable bladder 350 is typically deflated. Thus, the inflatable device 300 can be inserted through an access port (e.g., an igniter port) with a diameter equal to or less than twenty millimeters (20 mm; 0.8 inches). Then, when the inflatable bladder 350 of the inflatable device 300 is positioned in place (e.g., annularly positioned within the combustion chamber), the inflatable bladder 350 can be inflated with inflation fluid supplied by the fluid supply system 390, ultimately forming an annular seal, for example, as... Figure 10 As shown.

[0055] In some embodiments, the inflatable bladder 350 is formed of a fluid-impermeable material (e.g., a liquid-impermeable material and / or a gas-impermeable material). This allows the inflatable fluid to be retained within the inflatable bladder 350 when it is introduced. In some embodiments, the longitudinally inflatable bladder 350 is formed of an expandable material having a strain capacity greater than fifty percent (50%) when the inflatable bladder 350 is inflated. Furthermore, in some embodiments, the inflatable bladder 350 is formed of a material capable of radially (e.g., radially outward) inflating to at least three times its initial diameter or shape in its deflated state. In other embodiments, the inflatable bladder 350 is formed of a material capable of radially (e.g., radially outward) inflating to at least five times its initial diameter or shape in its deflated state. In other embodiments, the inflatable bladder 350 is formed of a foldable material that allows the inflatable bladder 350 to be folded up so that the inflatable bladder 350 and the frame 310 of the inflatable device 300 can pass through an access port, such as the ignition port of an aviation gas turbine engine.

[0056] Figure 5 A schematic diagram of another example inflatable device 300 according to an example embodiment of this subject is provided. Figure 5 The construction method of the inflatable device and Figure 3 and Figure 4 The inflatable device is constructed in the same way, except as noted below. For Figure 5 As described in the embodiments, the skeleton 310 is formed in segments, rather than as... Figure 3 The inflatable device in this embodiment is formed from a single continuous piece, just like the frame of the inflatable device. In particular, Figure 5 The frame 310 of the inflatable device 300 includes a first segment 330 and a second segment 332. The first segment 332 and the second segment 334 may each have a non-circular cross-section, such as a rectangular cross-section. The first segment 330 and the second segment 332 are connected together by a connecting member 334, which in this embodiment is a line. In other embodiments, the connecting member 334 may be other suitable components, such as a chain, one or more links, a rope, etc.

[0057] The first segment 330 is the "free end" of the frame 310 and is not attached to or connected to the inflatable bladder 350. The first segment 330 can be used to "catch" or guide the inflatable device 300 circumferentially through the annular chamber. In some embodiments, the length of the first segment 330 in the longitudinal or longitudinal direction is equal to or greater than the length of the second segment 332 of the frame 310 in the longitudinal or longitudinal direction. The second segment 332 of the frame 310 extends longitudinally between the connecting member 334 and the second end 314. The inflatable bladder 350 is longitudinally connected to or attached to a portion of the second segment 332. The inflatable bladder 350 can be connected to or attached to a portion of the second segment 332 in any suitable manner described herein. The second segment 332 also includes a portion of the inflatable bladder 350 to which it is not connected or attached. This portion, or extension of the second segment 332, is also the "free end" and can be used by an operator or machine to push or move the inflatable device 300 through the access port and into the appropriate position within the chamber of the gas turbine engine. Specifically, the operator or machine can grasp the free portion of the second segment 332 and push the inflatable device 300 into the appropriate position.

[0058] In this embodiment, a connecting member 334 is connected to the second segment 332 of the frame 310 at or near (within 30 cm; 1 inch) the longitudinal position where the first end 352 of the inflatable bladder 350 connects to the second segment 332. The connecting member 334 extends longitudinally and connects to the first segment 330. In some embodiments, the longitudinal length of the connecting member 334 is one-quarter or less than the longitudinal length of the first segment 330 of the frame 310. Advantageously, the connecting member 334, extending longitudinally between the first segment 330 and the second segment 332 of the frame 310, facilitates the movement of the inflatable device 300 into place.

[0059] Now for reference Figures 6 to 10 , Figure 6 A flowchart is provided for a method (400) of forming an in-situ temporary barrier within a gas turbine engine using an inflatable device, according to an example embodiment of this subject matter. For example, Figure 3 Inflatable device or Figure 5 The inflatable device can be inflated using method (400) to form an in-situ temporary barrier within the gas turbine engine. Figure 7 , 8 9 and 10 will be referenced to provide the context for method (400). Figures 7 to 10 The various stages of installing an inflatable device inside a gas turbine engine and inflating it to form a temporary in-situ barrier are described.

[0060] In (402), the method (400) includes installing an inflatable device within the gas turbine engine. For example, the inflatable device could be... Figure 3 or Figure 5 An inflatable device. The gas turbine engine can be any suitable type of gas turbine engine, such as a turbofan, turboprop, turboshaft engine, etc. For example, the inflatable device can be installed inside the gas turbine engine when the engine is online or on the wing of the aircraft. The inflatable device can also be installed inside a gas turbine engine that is offline or off the wing.

[0061] It is noteworthy that the inflatable device has an inflatable bladder attached to the frame. The inflatable bladder can be formed of an inflatable material so that when inflated with an inflation fluid, the inflatable bladder fills a cavity or chamber, thereby forming a seal along the fluid path of the gas turbine engine. For example, the seal formed by the inflation of the inflatable bladder can be an annular seal. The frame can be formed of a flexible and non-stretchable material and serve as a guide mechanism for directing the inflatable bladder to its proper position within the gas turbine engine. In some embodiments, the frame is formed of a material having a flexural modulus in the range of 100-1000 ksi. Additionally, or alternatively, in some embodiments, the frame is formed of a material having a tensile strength greater than 46 MPa (6672 psi). Thus, in some embodiments, the frame is formed of acrylonitrile-butadiene-styrene (ABS) material. In other embodiments, the frame is formed of nylon material. Furthermore, in some embodiments, the frame can be prefabricated, for example, having a circular or substantially circular shape. For example, a prefabricated circular frame can advantageously facilitate the movement of the inflatable device through the annular chamber. The following describes an example of how an inflatable device can be installed in a gas turbine engine, with reference to (402A) to (402D).

[0062] In (402A), installing the inflatable device within the gas turbine engine may include inserting a free section of the frame through a first access port of the gas turbine engine. The free section of the frame is a segment or portion of the frame along which the inflatable bladder is not attached. In this respect, the free section is "free". The free section 316 of the frame 318 may be inserted through the first access port 222A, in Figure 7 The diagram is schematically shown. Specifically, to insert the free section 316 of the skeleton 310 via the first access port 222A, an operator or machine can insert the first end 312 of the skeleton 310 and push the free section 316 inward along the radial direction R toward the longitudinal centerline 102 (the longitudinal centerline 102 is located at...). Figure 7 (Extending in the direction of entering and exiting the page). In this way, the free section 316 of the skeleton 310 enters the combustion chamber 198 through the first access port 222A. In this example, the first access port 222A is an igniter port, which provides internal access to the combustion chamber 198 of the burner 176.

[0063] In some embodiments, the free section 316 of the frame 310 is oriented in a preselected direction before or during the insertion of the first end 312 of the frame 310 into the first access port 222A. Thus, when the first end 312 of the frame 310 enters the combustion chamber 198 and engages with the inner liner 186, as the free section 316 of the frame 310 moves in the circumferential direction C, the second surface 324 of the frame 310 ( Figure 4 It engages with and remains engaged with the inner liner 186, as will be explained below. This facilitates the movement of the free section 316 through the annular combustion chamber 198 and prevents the frame 310 from twisting.

[0064] In (402B), installing the inflatable device within the gas turbine engine in (402) may further include moving the free section of the frame circumferentially through the annular chamber. For example, refer to Figure 7 The free segment 316 of the skeleton 310 is shown to be moved, indicated by arrow M, along the circumferential direction C through the annular combustion chamber 198. In this example, from Figure 7 From this angle, the free segment 316 of the frame 310 is shown moving in a counterclockwise direction. It is understood that in other embodiments, the free segment 316 of the frame 310 may move in a clockwise direction. To allow the free segment 316 to move circumferentially C through the annular combustion chamber 198, an operator or machine can further push the free segment 316 in the radial direction R through the first access port 222A. This pushing of the free segment 316 causes it to move circumferentially through the combustion chamber 198. Ultimately, the first end 312 of the frame 310 traverses the entire annular combustion chamber 198, as... Figure 8 As depicted in [the text]. In particular, as [the text] describes. Figure 8 As shown, the free section 316 of the frame 310 is moved such that the first end 312 passes through the annular combustion chamber 198 by more than 360 degrees. The flexible and non-stretchable material of the frame 310 allows the frame 310 to move efficiently and effectively through the annular combustion chamber 198 with repeatable reliability.

[0065] In (402C), installing the inflatable device within the gas turbine engine in (402) may further include retracting a free section of the frame via a second access port of the gas turbine engine. For example, refer to Figure 8 The free section 316 of the skeleton 310 can be retrieved or moved through the annular combustion chamber 198 at (402B) so that the first end 312 is close to the second access port 222B (in Figure 8(Schematably shown in the diagram), the second access port 222B is spaced apart from the first access port 222A in the circumferential direction C. In this way, the first end 312 of the frame 310 can be retracted and pulled outward in the radial direction R through the second access port 222B. In this example, the second access port 222B is an igniter port that provides internal access to the combustion chamber 198 of the burner 176.

[0066] The free section 316 of the skeleton 310 at or near the first end 312 can be accessed by a tool 380 (e.g., Figure 8 The spring-loaded claw (described herein) is retracted through the second access port 222B. The tool 380 can be inserted radially inward through the second access port 222B. The claw or gripping mechanism of the tool 380 can grip the free section 316 of the skeleton 310, such as... Figure 8 As shown. Then, tool 380, together with the held free section 316 of frame 310, can be pulled out of combustion chamber 198 through second access port 222B. In this respect, at this stage of the installation process, the first end 312 of frame 310 is positioned outside combustion chamber 198 and second access port 222B, while the second end 314 ( Figure 9 The frame 310 is positioned outside the combustion chamber 198 and the first access port 222A. It is noteworthy that when the free section 316 of the frame 310 is retracted through the second access port 222B, the frame 310 extends substantially annularly through the combustion chamber 198, and at least a portion of the frame 310 engages or wraps around the inner liner 186, as shown. Figure 8 As shown. As used herein, “substantially annular” means that the object (such as skeleton 310) extends through or around the annular chamber at least 270 degrees.

[0067] In (402D), installing an inflatable device within a gas turbine engine may further include moving the inflatable device so that the inflatable bladder extends annularly or substantially annularly within the annular combustion chamber. For example, as... Figure 9 As shown, the inflatable device 300 is moved so that the inflatable airbag 350 extends annularly or substantially annularly within the annular combustion chamber 198. The second surface 324 of the frame 310 ( Figure 4 ) engage the inner liner 186, and when the inflatable bladder 350 is attached or connected to the first surface 322 of the skeleton 310 ( Figure 4 When inflated, the inflatable bladder 350 is positioned radially R on the outside of the frame 310. Advantageously, this allows the inflatable bladder 350 to expand outwards radially R without obstruction when inflated.

[0068] In some embodiments, the inflatable airbag 350 can be moved into position within the combustion chamber 198 by pushing the inflatable device 300 through the first access port 222A and pulling the inflatable device 300 out from the second access port 222B. More specifically, an operator or machine can grasp the free extension section 320 of the frame 310 and push the inflatable device 300 further into the first access port 222A, which ultimately moves the frame 310 and the inflatable airbag 350 connected thereto through the annular combustion chamber 198 in the circumferential direction C. This pushing action... Figure 9 The arrow P1 indicates this. The operator or machine can also grasp the retracted free section 316 of the externally extending frame 310 of the oriented gas turbine engine and further pull the inflatable device 300 out of the second access port 222B, which ultimately allows the frame 310 and the connected inflatable bladder 350 to move circumferentially C through the annular combustion chamber 198. This pulling action... Figure 9 The arrow P2 indicates this. It is worth noting that the free section 316 and the free extension section 320 of the frame 310 are "free" sections or portions of the frame 310, therefore the inflatable bladder 350 can be moved into position without being grasped or touched. This protects the inflatable bladder 350 from accidental puncture or other damage during installation. A push-pull technique can be used to effectively move the inflatable bladder 350 into position within the annular combustion chamber 198. However, it is understood that in other embodiments, the inflatable device 300 may be moved into position within the annular combustion chamber 198 using only a pushing or pulling motion.

[0069] In (404), the method (400) includes connecting an inflatable bladder to a fluid supply. For example, as... Figure 10 The accessory 360, which is depicted as being coupled or connected to the inflatable bladder 350 at its second end 354, can be connected to a connector 396 of one of the fluid supply lines 394, which in turn is connected to the fluid supply device 392 of the fluid supply system 390. In this way, the inflatable bladder 350 is fluidly connected to the fluid supply device 392. Therefore, when needed, inflation fluid can be delivered from the fluid supply device 392 to the inflatable bladder 350.

[0070] In (406), with an inflatable device installed and the inflatable bladder connected to a fluid supply, the method (400) includes inflating the inflatable bladder with an inflation fluid so that the inflatable bladder forms a seal along the fluid path of the gas turbine engine. For example, as Figure 10As shown, the inflatable bladder 350 is depicted as being inflated with an inflation fluid. The inflatable bladder 350 can be inflated with an inflation fluid, such as compressed air or liquid. The inflation fluid can be passively or actively delivered to the inflatable bladder 350. As an example, a valve (not shown) can be opened, and inflation fluid can be passively filled into the inflatable bladder 350. As another example, a pump (not shown) can be driven to actively move inflation fluid into the inflatable bladder 350.

[0071] As shown in the figure, when inflated, the inflatable bladder 350 forms an annular seal within the combustion chamber 198. In this way, the inflatable bladder 350 prevents fluid flow. Specifically, when the inflatable bladder 350 inflates within the combustion chamber 198, the annular seal formed by the inflatable bladder 350 extends along the fluid path of the gas turbine engine (in this example, the core airflow path 132). Figure 2 This formed a temporary barrier on site.

[0072] To inflate the inflatable bladder 350, inflation fluid (e.g., compressed air stored in a fluid supply) can be supplied to the inflatable bladder 350. The inflation fluid can flow into the inflatable bladder 350 and cause it to expand outward in the radial direction R so that the inflatable bladder 350 engages with the outer bushing 192. The inflatable bladder 350 can also expand in the axial direction A. For example, as... Figure 2 As shown, the inflatable bladder 350 can expand in the axial direction A, such that the inflatable bladder 350 expands to the entire axial length of the combustion chamber 198, for example, from the front radial wall 200 to the leading edge of the nozzle 164 of the first stage 212.

[0073] In some embodiments, accessory 360 may be fluidly connected directly to inflatable airbag 350, for example, as Figure 10 As shown. Therefore, inflation fluid can flow through fitting 360 and into inflatable airbag 350. When inflating inflatable airbag 350, fitting 360 is positioned outside combustion chamber 198 and first inlet 222A. Inflatable airbag 350 may include a supply portion 356 that extends longitudinally across a distance from a second end 354 of inflatable airbag 350 to an end end. This distance can be selected to be approximately the radial distance from the inlet port (e.g., the first inlet port 222A). Notably, the supply portion 356 may be made of a thicker material than the non-supply portion of inflatable airbag 250. This allows inflation fluid to inflate this portion of inflatable airbag 350 less easily than the non-supply portion.

[0074] In other embodiments, fitting 360 may be fluidly connected to inflatable bladder 350 via a supply tube extending longitudinally between fitting 360 and the inlet of inflatable bladder 350. The supply tube may be formed of a non-inflatable material. The supply tube may be sized to receive within an access port (e.g., first access port 222A) and may extend longitudinally at least in the radial length of the access port so that the supply tube can extend between fitting 360, located outside the gas turbine engine, and the inlet of inflatable bladder 350, located within combustion chamber 198. In such embodiments, inflatable device 300 is moved such that inflatable bladder 350 extends annularly or substantially annularly within the chamber, and the first end 352 of inflatable bladder 350 ( Figure 3 The second end 354 is located in the annular combustion chamber 198.

[0075] In (408), in some embodiments, the method (400) includes performing a servicing operation while the inflatable bladder is inflated to form a seal along the fluid path of the gas turbine engine. For example, the servicing operation may be at least one of a foam cleaning operation, a water washing operation, a general engine cleaning operation, and a coating operation on airfoils positioned along the core airflow path. Other servicing operations are also conceivable.

[0076] For example, in foam cleaning operations, foam solution or foam can be introduced into a gas turbine engine, as described above. The foam can exit the compressor section and flow into the combustion section. Figure 2 and Figure 10 As shown, with the inflatable bladder 350 forming an annular seal, foam is prevented from flowing into the combustion chamber 198. Therefore, the foam is guided to the inner and outer air chambers located inside and outside the combustion chamber 198, respectively. The foam can bypass the combustion chamber and axially penetrate into the turbine section. Advantageously, the foam can flow into the cavities of components in the turbine section (such as stator blades, turbine blades, shrouds, etc.). Therefore, the cavities of these components can be effectively cleaned with foam. By preventing foam from flowing into the combustion chamber 198, foam accumulation in the combustion chamber 198 can be prevented; thus, a larger amount of foam can be guided into the turbine section to clean its components.

[0077] After or during the service operation (408), the method (400) may further include deflating the inflatable bladder 350 and removing the inflatable device 300 from the gas turbine engine. To deflate the inflatable bladder 350, inflation fluid is released through fitting 360. The inflatable device 300 can then be pulled outward from the first access port 222A. Alternatively, the inflatable device 300 can be pushed inward through the second access port 222B. In this way, the inflatable device 300 can be removed from the combustion chamber 198 of the gas turbine engine.

[0078] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that would occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not different from the literal language of the claims, or include equivalent structural elements that are not substantially different from the literal language of the claims.

[0079] Further details of this invention are provided by the subject matter of the following provisions:

[0080] 1. A method for forming an in-situ temporary barrier within a gas turbine engine, the method comprising: installing an inflatable device within the gas turbine engine, the inflatable device having a frame and an inflatable bladder connected to the frame; and inflating the inflatable bladder with an inflation fluid to form a seal along the fluid path of the gas turbine engine.

[0081] 2. The method according to any of the preceding clauses, wherein the skeleton is formed of a material that is not extensible under tension and allows for conformal bending of the skeleton.

[0082] 3. The method according to any of the preceding clauses, wherein the inflatable bladder is inflated in an annular chamber, the annular chamber forming at least a portion of the fluid path, and wherein the seal formed by the inflation of the inflatable bladder is an annular seal.

[0083] 4. The method according to any of the preceding clauses, wherein installing the inflatable device within the gas turbine engine comprises: inserting a free section of the frame through a first access port of the gas turbine engine, the first access port providing access to the annular chamber, the free section of the frame being a section of the frame along which the inflatable bladder is not connected; and moving the free section of the frame around the annular chamber in a circumferential direction defined by the gas turbine engine.

[0084] 5. The method according to any of the preceding clauses, wherein the free segment of the skeleton moves more than 360 degrees around the annular chamber along the circumferential direction.

[0085] 6. The method according to any of the preceding clauses, wherein installing the inflatable device within the gas turbine engine further comprises: retracting the free section of the frame through a second access port of the gas turbine engine, the second access port providing access to the annular chamber; and further moving the inflatable device along the circumferential direction such that the inflatable bladder extends annularly or substantially annularly within the annular chamber.

[0086] 7. The method according to any of the preceding clauses, wherein further moving the inflatable device along the circumferential direction to extend the inflatable bladder circumferentially or substantially circumferentially within the annular chamber comprises: pushing a portion of the inflatable device extending outward from the annular chamber and the first access port to further move the inflatable device into the first access port; and further pulling a portion of the free section extending outward from the annular chamber and the second access port outward from the second access port.

[0087] 8. The method according to any of the preceding clauses, wherein the skeleton has a bladder support section and a free extension section, the bladder support section being a section of the skeleton connecting the inflatable bladder, the free extension section being a section of the skeleton along which it is not connected to the inflatable bladder, the bladder support section being positioned between the free section and the free extension section, and wherein the pushed portion of the inflatable device extending outward from the annular chamber and from the first access port is the free extension section.

[0088] 9. The method according to any of the preceding clauses, wherein after inflating the inflatable bladder with the inflation fluid to form the seal along the fluid path of the gas turbine engine, the method further comprises: foam cleaning the gas turbine engine.

[0089] 10. The method according to any of the preceding clauses, wherein the skeleton comprises a first segment and a second segment joined together by a connecting member, wherein the inflatable bladder is connected to the second segment but not to the first segment.

[0090] 11. An inflatable device for forming an in-situ temporary barrier within a gas turbine engine, the inflatable device comprising: a frame; and an inflatable bladder longitudinally connected to the frame and operable to receive inflation fluid, the inflatable bladder being formed of an inflatable or foldable material.

[0091] 12. The inflatable device according to any of the preceding clauses, wherein the frame has a free section, a bladder support section, and a free extension section, the bladder support section being a section of the frame connecting the inflatable bladder, the free section and the free extension section being sections of the frame along which they are not connected to the inflatable bladder, and the bladder support section being positioned between the free section and the free extension section.

[0092] 13. The inflatable device according to any of the preceding clauses, wherein the inflatable bladder has a longitudinal length, and wherein the free section of the skeleton extends longitudinally at least along the longitudinal length of the inflatable bladder.

[0093] 14. The inflatable device according to any of the preceding clauses, wherein the frame has at least one flat surface, and wherein the inflatable bladder is not connected to the at least one flat surface.

[0094] 15. The inflatable device according to any of the preceding clauses, wherein the at least one flat surface is a second surface opposite to a first surface of the frame, wherein the inflatable bladder is connected to the first surface of the frame.

[0095] 16. The inflatable device according to any of the preceding clauses, wherein the skeleton forms a single continuous piece.

[0096] 17. The inflatable device according to any of the preceding clauses, wherein the frame comprises a first segment and a second segment joined together by connecting members.

[0097] 18. The inflatable device according to any of the preceding clauses, wherein the frame is formed of a material having a flexural modulus in the range of 100-1000 ksi.

[0098] 19. The inflatable device according to any of the preceding clauses, wherein the frame is formed of a material having a tensile strength greater than 46 MPa.

[0099] 20. A method for forming an in-situ temporary barrier within a gas turbine engine, the method comprising: installing an inflatable device within an annular chamber defined by the gas turbine engine, the inflatable device having a frame and an inflatable bladder connected to the frame, the inflatable bladder being formed of an inflatable or foldable material, wherein installing the inflatable device within the annular chamber comprises: guiding a free section of the frame through a first access port of the gas turbine engine and circumferentially through the annular chamber, the free section of the frame being a section along which it is not connected to the inflatable bladder; through a second access port of the gas turbine engine The inlet port retracts a portion of the free section of the skeleton, positioning that portion of the free section outside the annular chamber; and the inflatable device is moved such that the inflatable bladder extends annularly or substantially annularly within the annular chamber by performing at least one of the following: pulling the portion of the free section extending from the second inlet port to the outside of the annular chamber; and pushing the portion of the inflatable device extending from the first inlet port to the outside of the annular chamber; and inflating the inflatable bladder with inflation fluid, thereby forming an annular seal within the annular chamber.

Claims

1. A method for forming an in-situ temporary barrier within a gas turbine engine, characterized in that, The method includes: An inflatable device is installed within the gas turbine engine. The inflatable device has a frame and an inflatable bladder. The inflatable bladder has an elongated connection to the frame, extending between a first end point and a second end point on the frame, wherein the second end point is spaced apart from the first end point along the length of the frame. The elongated connection of the inflatable bladder extends along at least one-quarter of the total longitudinal length of the frame. The inflatable airbag is inflated with an inflation fluid, causing the inflatable airbag to form a seal along the fluid path of the gas turbine engine.

2. The method according to claim 1, characterized in that, The skeleton is formed of a material that is non-extensible under tension and allows for conformal bending of the skeleton.

3. The method according to claim 1, characterized in that, The inflatable bladder is inflated in an annular chamber that forms at least a portion of the fluid path, and the seal formed by the inflation of the inflatable bladder is an annular seal.

4. The method according to claim 3, characterized in that, The installation of the inflatable device within the gas turbine engine includes: A free section of the frame is inserted through a first access port of the gas turbine engine, the first access port providing access to the annular chamber, the free section of the frame being a section of the frame along which the inflatable bladder is not connected; and The free section of the frame is moved around the annular chamber in a circumferential direction defined by the gas turbine engine.

5. The method according to claim 4, characterized in that, The free segment of the skeleton moves more than 360 degrees around the annular chamber along the circumferential direction.

6. The method according to claim 4, characterized in that, The installation of the inflatable device within the gas turbine engine further includes: The free section of the frame is retracted via a second access port of the gas turbine engine, the second access port providing access to the annular chamber; and The inflatable device is further moved along the circumferential direction, so that the inflatable bladder extends circumferentially or substantially circumferentially within the annular chamber.

7. The method according to claim 6, characterized in that, Further moving the inflatable device along the circumferential direction, causing the inflatable bladder to extend circumferentially or substantially circumferentially within the annular chamber, includes: Pushing the inflatable device from the annular chamber and a portion extending outward from the first access port, causing the inflatable device to move further into the first access port; and A portion of the free section extending outward from the annular chamber and the second access port is further pulled out of the second access port.

8. The method according to claim 7, characterized in that, The frame has a bladder support section and a free extension section, the bladder support section being the section of the frame that connects to the inflatable bladder, and the free extension section being the section of the frame along which it does not connect to the inflatable bladder, the bladder support section being positioned between the free section and the free extension section, and wherein the pushed portion of the inflatable device extending outward from the annular chamber and from the first access port is the free extension section.

9. The method according to claim 1, characterized in that, The method further includes, after inflating the inflatable bladder with the inflation fluid to form a seal along the fluid path of the gas turbine engine, the method further includes: The gas turbine engine was foam-cleaned.

10. The method according to claim 1, characterized in that, The frame includes a first segment and a second segment connected together by a connecting member, wherein the inflatable bladder is connected to the second segment but not to the first segment.

11. An inflatable device for forming an in-situ temporary barrier within a gas turbine engine, characterized in that, The inflatable device includes: Skeleton; and An inflatable bladder, longitudinally connected to the frame and operable to receive inflation fluid, the inflatable bladder being formed of an inflatable or foldable material, the inflatable bladder having an elongated connection to the frame extending between a first end point and a second end point on the frame, wherein the second end point is spaced apart from the first end point along the length of the frame, the elongated connection of the inflatable bladder extending for at least one-quarter of the total longitudinal length of the frame.

12. The inflatable device according to claim 11, characterized in that, The skeleton has a free section, a bladder support section, and a free extension section. The bladder support section is the section of the skeleton that connects to the inflatable bladder. The free section and the free extension section are sections of the skeleton along which they do not connect to the inflatable bladder. The bladder support section is located between the free section and the free extension section.

13. The inflatable device according to claim 12, characterized in that, The inflatable bladder has a longitudinal length, and the free section of the skeleton extends longitudinally at least along the longitudinal length of the inflatable bladder.

14. The inflatable device according to claim 11, characterized in that, The frame has at least one flat surface, and the inflatable bladder is not connected to the at least one flat surface.

15. The inflatable device according to claim 14, characterized in that, The at least one flat surface is a second surface opposite to the first surface of the skeleton, wherein the inflatable bladder is connected to the first surface of the skeleton.

16. The inflatable device according to claim 11, characterized in that, The skeleton forms a single continuous piece.

17. The inflatable device according to claim 11, characterized in that, The skeleton comprises a first segment and a second segment connected together by connecting members.

18. The inflatable device according to claim 11, characterized in that, The skeleton is formed of a material having a flexural modulus in the range of 100-1000 ksi.

19. The inflatable device according to claim 11, characterized in that, The skeleton is formed of a material with a tensile strength greater than 46 MPa.

20. A method for forming an in-situ temporary barrier within a gas turbine engine, characterized in that, The method includes: An inflatable device is installed within an annular chamber defined by the gas turbine engine. The inflatable device has a frame and an inflatable bladder connected to the frame. The inflatable bladder is formed of an inflatable or foldable material. Installing the inflatable device within the annular chamber includes: The free section of the frame is guided through the first access port of the gas turbine engine and circumferentially through the annular chamber, wherein the free section of the frame is the section along which it is not connected to the inflatable bladder; A portion of the free section of the frame is retracted through the second access port of the gas turbine engine, positioning that portion of the free section outside the annular chamber; and The inflatable device is moved such that the inflatable bladder extends circumferentially or at least 270° through or around the annular chamber by performing at least one of the following: pulling the portion of the free section extending from the second access port to the outside of the annular chamber; and pushing the portion of the inflatable device extending from the first access port to the outside of the annular chamber; and The inflatable bladder is inflated with an inflation fluid, causing the inflatable bladder to form an annular seal within the annular chamber.

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