Cleaning tool for a gas turbine engine and method for servicing a gas turbine engine

Abstract

A cleaning tool (100) for cleaning a component (50) positioned within a gas turbine engine (10) is disclosed. The cleaning tool (100) includes a tubular body (102) comprising: a first open end (104) and a second closed end (106); a connecting portion (108) adjacent to the second closed end (106) and configured to engage with a support (110) within the gas turbine engine (10); a nozzle orifice (112) disposed between the first open end (104) and the connecting portion (108); and a flow passage (114) extending from the first open end (104) and in fluid communication with the nozzle orifice (112). The flow passage (114) is configured to deliver cleaning fluid (115) from the first open end (104) to the nozzle orifice (112). The cleaning fluid (115) is delivered to the component (50) through the nozzle orifice (112). The tubular body (102) is configured to be inserted from the second closed end (106) through the first port (116) of the gas turbine engine (10), such that the engagement portion (108) engages with the support (110).

Description

[0001] Cross-reference to related applications This article presents the first application for this topic. Technical Field

[0002] This disclosure relates to cleaning tools for cleaning components located within a gas turbine engine and methods for maintaining a gas turbine engine. Background Technology

[0003] During the operation of a gas turbine engine, environmental contaminants (e.g., sand and gravel) can accumulate on the surfaces of various components located within the engine. This accumulation can reduce the engine's operating efficiency. Therefore, the gas turbine engine may require cleaning during its operational life. Such cleaning operations may necessitate removing the gas turbine engine from the aircraft's wing. For example, the gas turbine engine may need to be removed from the wing for cleaning sand-laden nozzle guide vanes (NGVs) to restore them to usable condition. Removing the gas turbine engine from the wing for cleaning can be costly and increase downtime.

[0004] Some gas turbine engines are equipped with clean fluid supply devices permanently fixed inside the engine, such as CN110064615 and US2017369174. These devices supply fluid at low pressure and flow rate, but are reinforced to withstand airflow passing through the engine during engine cycles through takeoff, cruise, and landing. Summary of the Invention

[0005] In a first aspect, a cleaning tool is provided for cleaning a component positioned within a gas turbine engine. The cleaning tool includes a tubular body. The tubular body includes a first open end and a second closed end. The tubular body further includes a engagement portion adjacent to the second closed end. The engagement portion is configured to engage with a support member within the gas turbine engine. The tubular body further includes at least one nozzle orifice disposed between the first open end and the engagement portion. The tubular body further includes a flow channel extending from the first open end and in fluid communication with the at least one nozzle orifice. The flow channel is configured to deliver cleaning fluid from the first open end to the at least one nozzle orifice. After the engagement portion engages with the support member, the at least one nozzle orifice is configured to face the component so as to deliver cleaning fluid to the component therethrough. The tubular body is configured to be inserted and removed from the second closed end through a first port of the gas turbine engine, such that the engagement portion engages with the support member.

[0006] The cleaning tool facilitates the cleaning of gas turbine engine components without removing the gas turbine engine from the aircraft's wing. The cleaning tool allows for cleaning of components while the gas turbine engine is being installed in the aircraft's wing. This can reduce costs associated with cleaning components (e.g., reducing costs associated with removing the gas turbine engine from the wing) and decrease gas turbine engine downtime. The cleaning tool can be removed from the gas turbine engine after the cleaning operation is complete.

[0007] The geometric constraints on the tubular body that allow it to be inserted through the first port may limit the rigidity provided solely by the tubular body without external supports. The engagement portion where the tubular body joins the support allows cleaning fluid to be delivered to the component at high pressure and velocity through at least one nozzle orifice. The tubular body resists deformation (e.g., bending) due to the engagement of the joint portion with the support. This also improves the accuracy of directing cleaning fluid to the component at high discharge velocities through at least one nozzle orifice and reduces the likelihood of damage to other components (e.g., thermal barriers or other coatings) adjacent to the component during cleaning operations.

[0008] In one embodiment, the flow channel has a maximum diameter between 4 mm and 6 mm.

[0009] In one embodiment, the tubular body further includes a curved portion extending partially from the second closed end toward the first open end. At least one nozzle orifice is disposed on the curved portion.

[0010] In one embodiment, the cleaning tool further includes a top plate that at least partially defines a first open end of the tubular body. The top plate extends outward from the tubular body.

[0011] In one embodiment, the cleaning tool further includes a mounting plate configured to be removably coupled to a gas turbine engine. A tubular body is configured to be inserted through a first port of the gas turbine engine after the mounting plate is removably coupled to the gas turbine engine. A top plate is configured to be removably coupled to the mounting plate after the tubular body is inserted through the first port of the gas turbine engine.

[0012] In one embodiment, the tubular body has a minimum wall thickness of greater than 1 mm and a maximum wall thickness of less than 5 mm along the flow channel.

[0013] In one embodiment, the tubular body has a minimum wall thickness of greater than 2 mm and a maximum wall thickness of less than 5 mm along the flow channel.

[0014] In one embodiment, the tubular body has a maximum outer diameter of less than 15 millimeters.

[0015] In one embodiment, the tubular body further includes a solid portion without flow channels. The joining portion is disposed on the solid portion.

[0016] In one embodiment, the tubular body further includes a first recessed portion near a second closed end of the tubular body. The cleaning tool further includes a first non-metallic component disposed around the first recessed portion. The first recessed portion may be provided by a localized thinning of the wall of the tubular body.

[0017] In one embodiment, the tubular body further includes a second recessed portion near a first open end of the tubular body. The cleaning tool further includes a second non-metallic component disposed around the second recessed portion. The second recessed portion may be provided by a localized thinning of the wall of the tubular body.

[0018] In one embodiment, the flow channel and at least one nozzle orifice are configured to deliver cleaning fluid to the component at a flow rate greater than 10 liters per minute through the at least one nozzle orifice.

[0019] In one embodiment, the discharge velocity of the cleaning fluid delivered through at least one nozzle orifice is greater than 150 meters per second.

[0020] In one embodiment, the flow channel is configured to receive cleaning fluid at a pressure greater than 200 bar.

[0021] In one embodiment, at least one nozzle orifice is further configured to direct cleaning fluid to a target cleaning area of ​​the component.

[0022] In one embodiment, the cleaning tool further includes a nozzle removably connectable to at least one nozzle orifice. The nozzle is configured to direct cleaning fluid to a target cleaning area of ​​the component.

[0023] In one embodiment, the support includes a second port of the gas turbine engine. The engagement portion extends at least partially through the second port.

[0024] In a second aspect, a gas turbine engine is provided. The gas turbine engine includes an engine core. The gas turbine engine further includes a member positioned within the engine core. The gas turbine engine further includes a support member within the engine core. The gas turbine engine further includes a first port providing a passage to the member. The gas turbine engine further includes a cleaning tool for cleaning the member. The cleaning tool includes a tubular body. The tubular body includes a first open end and a second closed end. The tubular body further includes a engagement portion adjacent to the second closed end. The engagement portion is configured to engage with the support member. The tubular body further includes at least one nozzle orifice disposed between the first open end and the engagement portion. The tubular body further includes a flow channel extending from the first open end and in fluid communication with the at least one nozzle orifice. The flow channel is configured to deliver cleaning fluid from the first open end to the at least one nozzle orifice. After the engagement portion engages with the support member, the at least one nozzle orifice is configured to face the member so as to deliver cleaning fluid to the member therethrough. The tubular body is configured to be inserted from the second closed end through the first port such that the engagement portion engages with the support member.

[0025] Cleaning tools facilitate the cleaning of gas turbine engine components without removing the gas turbine engine from the aircraft's wing. These tools allow for cleaning of components while the gas turbine engine is being installed in the aircraft's wing. This can reduce costs associated with cleaning components (e.g., reducing costs associated with removing the gas turbine engine from the wing) and decrease gas turbine engine downtime.

[0026] The geometric constraints on the tubular body that allow it to be inserted through the first port may limit the rigidity provided solely by the tubular body without external supports. The engagement portion where the tubular body joins the support allows cleaning fluid to be delivered to the component at high pressure and velocity through at least one nozzle orifice. The tubular body resists deformation (e.g., bending) due to the engagement of the joint portion with the support. This also improves the accuracy of directing cleaning fluid to the component at high discharge velocities through at least one nozzle orifice and reduces the likelihood of damage to other components (e.g., thermal barriers or other coatings) adjacent to the component during cleaning operations.

[0027] In a third aspect, a method for maintaining a gas turbine engine is provided. The method includes providing a cleaning tool. The cleaning tool includes a tubular body. The tubular body includes a first open end and a second closed end. The tubular body further includes a joining portion adjacent to the second closed end. The joining portion is configured to engage with a support member within the gas turbine engine. The tubular body further includes at least one nozzle orifice disposed between the first open end and the joining portion. The tubular body further includes a flow channel extending from the first open end and in fluid communication with the at least one nozzle orifice. The flow channel is configured to deliver cleaning fluid from the first open end to the at least one nozzle orifice. After the joining portion engages with the support member, the at least one nozzle orifice is configured to face a component positioned within the gas turbine engine so as to deliver cleaning fluid to the component therethrough. The method further includes inserting the tubular body from the second closed end through a first port of the gas turbine engine, such that the joining portion engages with the support member. The method further includes supplying cleaning fluid to the flow channel, such that the cleaning fluid is delivered to the component through the at least one nozzle orifice. The method further includes removing the tubular body through the first port.

[0028] This method allows for the cleaning of gas turbine engine components using cleaning tools without removing the gas turbine engine from the aircraft's wing. Using this method, cleaning tools can be used to clean components while the gas turbine engine is being installed on the aircraft's wing. This method can therefore reduce the costs associated with cleaning components (e.g., reducing the costs associated with removing the gas turbine engine from the wing) and reduce gas turbine engine downtime.

[0029] The geometric constraints on the tubular body that allow it to be inserted through the first port may limit the rigidity provided solely by the tubular body without external supports. The engagement portion where the tubular body joins the support allows cleaning fluid to be delivered to the component at high pressure and velocity through at least one nozzle orifice. The tubular body resists deformation (e.g., bending) due to the engagement of the joint portion with the support. This also improves the accuracy of directing cleaning fluid to the component at high discharge velocities through at least one nozzle orifice and reduces the likelihood of damage to other components (e.g., thermal barriers or other coatings) adjacent to the component during cleaning operations.

[0030] In one embodiment, the method further includes removably attaching a mounting plate to a gas turbine engine. The method further includes removably attaching a top plate of a cleaning tool to the mounting plate after inserting a tubular body through a first port of the gas turbine engine.

[0031] In one embodiment, the step of supplying cleaning fluid to the flow channel includes delivering the cleaning fluid to the component at a flow rate greater than 10 liters per minute through at least one nozzle orifice.

[0032] In one embodiment, the discharge velocity of the cleaning fluid delivered through at least one nozzle orifice is greater than 150 meters per second.

[0033] In one embodiment, the step of supplying cleaning fluid to the flow channel further includes supplying the cleaning fluid to the flow channel at a pressure greater than 200 bar.

[0034] In one embodiment, the step of supplying cleaning fluid to the flow channel further includes guiding the cleaning fluid to a target cleaning area of ​​the component via at least one nozzle orifice.

[0035] In one embodiment, the method further includes removably attaching a nozzle to at least one nozzle orifice. The step of supplying cleaning fluid to the flow channel further includes directing the cleaning fluid via the nozzle to a target cleaning area of ​​the component.

[0036] In one embodiment, the step of inserting the tubular body through the first port further includes receiving, at least partially, a joining portion of the tubular body through a second port of the gas turbine engine, such that the joining portion extends at least partially through the second port.

[0037] In one embodiment, the method further includes inspecting the gas turbine engine to identify components.

[0038] As described elsewhere in this document, this disclosure relates to gas turbine engines. Such a gas turbine engine may include an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor. Such a gas turbine engine may include a fan (with fan blades) positioned upstream of the engine core. Those skilled in the art will recognize that, unless mutually exclusive, features or parameters described with respect to any of the foregoing aspects may be applied to any other aspect. Furthermore, unless mutually exclusive, any feature or parameter described herein may be applied to any aspect and / or combined with any other feature or parameter described herein. Attached Figure Description

[0039] Embodiments will now be described by way of example only with reference to the accompanying drawings, wherein: Figure 1 This is a cross-sectional side view of a gas turbine engine; Figure 2 The accompanying drawing illustrates a portion of a gas turbine engine including cleaning tools, according to an embodiment of the present disclosure; Figure 3A The accompanying drawings are of a cleaning tool according to an embodiment of the present disclosure; Figure 3BAnother drawing is of a cleaning tool according to an embodiment of the present disclosure; Figure 4 This is a separate top view of the mounting plate of a cleaning tool according to an embodiment of the present disclosure; and Figure 5 This is a flowchart depicting the steps of a method for maintaining a gas turbine engine according to an embodiment of the present disclosure. Detailed Implementation

[0040] Aspects and embodiments of this disclosure will now be discussed with reference to the accompanying drawings. Further aspects and embodiments will be apparent to those skilled in the art.

[0041] Figure 1 The diagram illustrates a gas turbine engine 10 with a main axis of rotation 9. The engine 10 includes an intake 12 and a propulsion fan 23 that generates two airflows (core airflow A and bypass airflow B). The gas turbine engine 10 includes a core 11 that receives core airflow A. The engine core 11 includes, in axial flow series, a low-pressure compressor 14, a high-pressure compressor 15, a combustion device 16, a high-pressure turbine 17, a low-pressure turbine 19, and a core exhaust nozzle 20. A nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18. Bypass airflow B flows through the bypass duct 22. The fan 23 is attached to and driven by the low-pressure turbine 19 via a shaft 26 and a planetary gearbox 30. The combustion device 16 may be interchangeably referred to as "burner 16".

[0042] In operation, the core airflow A is accelerated and compressed by the low-pressure compressor 14, and then directed to the high-pressure compressor 15, where it undergoes further compression. The compressed air discharged from the high-pressure compressor 15 is directed to the combustion device 16, where the compressed air is mixed with fuel and the mixture is burned. The resulting hot combustion products then expand through (and thereby drive) the high-pressure turbine 17 and the low-pressure turbine 19, and are then discharged through the core exhaust nozzle 20 to provide some propulsive thrust. The high-pressure turbine 17 drives the high-pressure compressor 15 via a suitable interconnecting shaft 27. The fan 23 provides roughly the majority of the propulsive thrust. The planetary gearbox 30 is a reduction gearbox.

[0043] Note that the terms "low-pressure turbine" and "low-pressure compressor" as used herein may be used to refer to the lowest-pressure turbine stage and the lowest-pressure compressor stage (i.e., excluding fan 23), and / or the turbine and compressor stages connected together by interconnecting shaft 26 at the lowest speed in engine 10 (i.e., excluding the gearbox output shaft driving fan 23). In some literature, "low-pressure turbine" and "low-pressure compressor" as used herein may alternatively be known as "intermediate-pressure turbine" and "intermediate-pressure compressor." When using such alternative terms, fan 23 may be referred to as the first (or lowest-pressure) compression stage.

[0044] Other gas turbine engines to which this disclosure is applied may have alternative configurations. For example, such an engine may have an alternative number of compressors and / or turbines, and / or an alternative number of interconnecting shafts. In another example, Figure 1 The gas turbine engine 10 shown has separate flow nozzles 18, 20, meaning that the flow through the bypass duct 22 has its own nozzle 18, independent of the core exhaust nozzle 20 and radially outside the core exhaust nozzle 20. However, this is not a limitation, and any aspect of this disclosure can also be applied to engines in which the flow through the bypass duct 22 and the flow through the core 11 are mixed or combined before a single nozzle (or upstream thereof), which may be referred to as a mixing flow nozzle. One or both nozzles (whether mixing or separating flows) may have fixed or variable areas. Although the described example relates to a turbofan engine, this disclosure can be applied, for example, to any type of gas turbine engine, such as an open rotor engine (where the fan stage is not surrounded by a nacelle), or, for example, a turboprop engine. In some arrangements, the gas turbine engine 10 may not include a gearbox 30.

[0045] The geometry of the gas turbine engine 10 and its components is defined by a conventional coordinate system, which includes the axial direction (aligned with the axis of rotation 9) and the radial direction (in...). Figure 1 The middle direction is from bottom to top), and the circumferential direction (in the middle). Figure 1 (Perpendicular to the page in the view). The axial, radial, and circumferential directions are mutually perpendicular.

[0046] Figure 2 A portion of a gas turbine engine 10 within an engine core 11 according to an embodiment of the present disclosure is shown. Specifically, Figure 2 A portion of the burner 16 of the gas turbine engine 10 is shown.

[0047] Reference Figure 1 and Figure 2The gas turbine engine 10 further includes a component 50 positioned within the engine core 11. The component 50 can be any component positioned within the engine core 11, on which contaminants (such as dust, sand, etc.) can accumulate due to the operation of the gas turbine engine 10. The component 50 may include, for example, airfoils (e.g., rotor blades, stator blades, guide vanes, etc.). In some embodiments, the component 50 may be a nozzle guide vane (NGV).

[0048] The gas turbine engine 10 further includes a first port 116 providing access to the component 50. The first port 116 may include, for example, a borescope port or a mixing port. The gas turbine engine 10 further includes a support member 110. The support member 110 may be positioned within the engine core 11. Furthermore, the support member 110 may be positioned close to the component 50. The support member 110 may include a component, port, or any suitable structure of the gas turbine engine 10 having sufficient structural integrity and positioned within the engine core 11. In one embodiment, the support member 110 may include a second port 117 of the gas turbine engine 10. The second port 117 may be different from the first port 116. The second port 117 may include, for example, a borescope port or a mixing port.

[0049] The gas turbine engine 10 further includes a cleaning tool 100 for cleaning components 50 located within the gas turbine engine 10. Figure 3A and Figure 3B The cleaning tool 100 is also shown in the picture.

[0050] Reference Figure 2 , Figure 3A and Figure 3B The cleaning tool 100 includes a tubular body 102. The tubular body 102 includes a first open end 104 and a second closed end 106. The second closed end 106 is located away from the first open end 104. The tubular body 102 extends between the first open end 104 and the second closed end 106. The tubular body 102 may have a circular or non-circular cross-section. In some embodiments, the tubular body 102 may be substantially cylindrical. The tubular body 102 may be made of any suitable rigid material, such as metal (e.g., stainless steel).

[0051] The tubular body 102 further includes an engagement portion 108 near the second closed end 106. In some embodiments, the engagement portion 108 may extend partially from the second closed end 106 toward the first open end 104. Alternatively, as Figure 2 As shown, the engagement portion 108 may be spaced apart from (but close to) the second closed end 106 and extend partially toward the first open end 104.

[0052] The engagement portion 108 is configured to engage with a support member 110 within the gas turbine engine 10. The engagement portion 108 can engage with the support member 110 in any suitable manner, such that the engagement portion 108 is structurally supported by the support member 110. Figure 2 In the illustrated embodiment, the engagement portion 108 extends at least partially through the second port 117.

[0053] The tubular body 102 further includes at least one nozzle orifice 112 disposed between the first open end 104 and the engagement portion 108. The tubular body 102 further includes a flow channel 114 extending from the first open end 104 and in fluid communication with at least one nozzle orifice 112 (shown in…). Figure 3A (Middle). The flow channel 114 is configured to deliver cleaning fluid 115 from the first open end 104 to at least one nozzle orifice 112.

[0054] Cleaning fluid 115 may include any suitable fluid for cleaning component 50. As an example, cleaning fluid 115 may include water, or a combination of water and detergent, soap, and / or other additives (e.g., abrasive media, such as sodium bicarbonate). The composition of cleaning fluid 115 may be selected such that cleaning fluid 115 does not damage one or more metallic portions and / or thermal barrier coatings (TBCs) of component 50 or other components adjacent to component 50. Any suitable technology may be implemented for supplying or providing cleaning fluid 115 to flow channel 114. For example, a pump (not shown) may be used to supply cleaning fluid 115 from a storage container (not shown) to flow channel 114 at a desired pressure.

[0055] After the engagement portion 108 engages with the support member 110, at least one nozzle orifice 112 is configured to face the member 50 to deliver cleaning fluid 115 to the member 50. In one embodiment, at least one nozzle orifice 112 may be further configured to direct the cleaning fluid 115 to a target cleaning area 51 of the member 50. Specifically, in some embodiments, after the engagement portion 108 engages with the support member 110, at least one nozzle orifice 112 may direct the cleaning fluid 115 to a target cleaning area 51 of the member 50.

[0056] The tubular body 102 is configured to be inserted from the second closed end 106 through the first port 116 of the gas turbine engine 10, such that the engaging portion 108 engages with the support member 110. As discussed above, in Figure 2 In the illustrated embodiment, the engagement portion 108 extends at least partially through the second port 117.

[0057] The cleaning tool 100 facilitates cleaning of the components 50 of the gas turbine engine 10 without removing it from the wing of the aircraft. The cleaning tool 100 allows cleaning of the components 50 while the gas turbine engine 10 is mounted to the wing of the aircraft. The cleaning tool 100 can therefore reduce costs associated with cleaning the components 50 (e.g., reduce costs associated with removing the gas turbine engine from the wing) and reduce downtime of the gas turbine engine 10.

[0058] The geometric constraints on the tubular body 102 that allow it to be inserted through the first port 116 may limit the rigidity provided solely by the tubular body 102 without external supports. The engagement portion 108 where the tubular body 102 engages with the support 110 allows the cleaning fluid 115 to be delivered to the component 50 at high pressure and velocity through at least one nozzle orifice 112. The tubular body 102 resists deformation (e.g., bending) due to the engagement of the engagement portion 108 with the support 110. This also improves the accuracy of directing the cleaning fluid 115 to the component 50 at high discharge velocity through at least one nozzle orifice 112 and reduces the likelihood of damage to other components (e.g., thermal barriers or other coatings) adjacent to the component 50 during cleaning operations.

[0059] In one embodiment, the tubular body 102 may further include a solid portion 120 without the flow channel 114. A connecting portion 108 may be disposed on the solid portion 120. The solid portion 120 may provide additional rigidity to the tubular body 102. Furthermore, the tubular body 102 may include a curved portion 130 extending partially from the second closed end 106 toward the first open end 104. At least one nozzle orifice 112 may be disposed on the curved portion 130. The curved portion 130 may include at least one nozzle orifice 112, a portion of the flow channel 114, and a portion of the solid portion 120. The curved portion 130 may (in some cases) allow the tubular body 102 to be inserted through the first port 116, such that the connecting portion 108 extends at least partially through the second port 117. However, it is noteworthy that the design of the tubular body 102 may vary depending on the relative positioning of the first port 116 and the support member 110 (e.g., the second port 117).

[0060] The tubular body 102 has a maximum outer diameter 132. The maximum outer diameter 132 may be smaller than the diameter of the first port 116, allowing the tubular body 102 to be inserted through the first port 116. In some embodiments, the maximum outer diameter 132 may be smaller than the diameter of the second port 117, such that the engaging portion 108 extends at least partially through the second port 117. In some embodiments, the maximum outer diameter 132 of the tubular body 102 may be less than 15 mm. In some embodiments, the maximum outer diameter 132 may be less than 13 mm. In some embodiments, the maximum outer diameter 132 may be approximately 12 mm.

[0061] In one embodiment, the flow channel 114 may have a maximum diameter 114D between 4 mm and 6 mm. In some embodiments, the flow channel 114 may have a maximum diameter 114D of 5 mm. Furthermore, the tubular body 102 may define a wall thickness 131 along the flow channel 114. The wall thickness 131 may vary or remain constant along the flow channel 114. In one embodiment, the tubular body 102 may have a minimum wall thickness greater than 1 mm and a maximum wall thickness less than 5 mm along the flow channel 114. The minimum wall thickness may be greater than 2 mm.

[0062] In one embodiment, the flow channel 114 may be configured to receive cleaning fluid 115 at a pressure greater than 200 bar. In some embodiments, the flow channel 114 may be configured to receive cleaning fluid 115 at a pressure greater than 300 bar or greater than 350 bar. The engagement of the engagement portion 108 with the support member 110 allows the cleaning fluid 115 to be supplied at high pressure to the flow channel 114 of the tubular body 102.

[0063] In some embodiments, the flow channel 114 and at least one nozzle orifice 112 may be configured to deliver cleaning fluid 115 to the component 50 at a flow rate greater than 10 liters per minute through the at least one nozzle orifice 112. In some embodiments, the flow channel 114 and at least one nozzle orifice 112 may be configured to deliver cleaning fluid 115 to the component 50 at a flow rate greater than 20 liters per minute through the at least one nozzle orifice 112.

[0064] In some embodiments, the discharge velocity of the cleaning fluid 115 through at least one nozzle orifice 112 may be greater than 150 meters per second. In some embodiments, the discharge velocity of the cleaning fluid 115 through at least one nozzle orifice 112 may be greater than 250 meters per second.

[0065] It should be noted that the pressure, flow rate, and discharge velocity of the cleaning fluid 115 may vary depending on the desired application properties.

[0066] In some embodiments, the cleaning tool 100 may further include a top plate 118 that at least partially defines a first open end 104 of the tubular body 102. The top plate 118 may extend beyond the tubular body 102. In some examples, the top plate 118 may extend radially beyond the tubular body 102. The top plate 118 may include a plurality of holes 119 for connecting the cleaning tool 100 to other components, such as a mounting plate.

[0067] The cleaning tool 100 may further include a mounting plate 136 (shown in...) Figure 1 And shown separately in Figure 4 (In the middle), mounting plate 136 is configured to be removably coupled to gas turbine engine 10. For example, mounting plate 136 may be configured to be removably coupled to combustor housing 60 of gas turbine engine 10.

[0068] Reference Figure 1 , Figure 3A and Figure 4 The mounting plate 136 may include a plurality of first holes 137 for removably mounting the mounting plate 136 to the gas turbine engine 10. The mounting plate 136 may be removably coupled to the gas turbine engine 10 via a plurality of coupling elements (e.g., fasteners) extending through the plurality of first holes 137.

[0069] Mounting plate 136 may further include a plurality of second holes 138. The plurality of second holes 138 may correspond to a plurality of holes 119 of top plate 118. Mounting plate 136 may further include a main hole 139. Tubular body 102 may be inserted through the main hole 139 from second closed end 106 such that the plurality of holes 119 of top plate 118 are aligned with the plurality of second holes 138. Top plate 118 may be removably coupled to mounting plate 136 using a plurality of coupling elements (e.g., fasteners) extending through the plurality of holes 119 of top plate 118 and the plurality of second holes 138 of mounting plate 136.

[0070] The tubular body 102 may be configured to be inserted through the first port 116 of the gas turbine engine 10 after the mounting plate 136 is removably coupled to the gas turbine engine 10. The top plate 118 may be configured to be removably coupled to the mounting plate 136 after the tubular body 102 is inserted through the first port 116 of the gas turbine engine 10.

[0071] In one embodiment, the tubular body 102 may further include a first recessed portion 122 adjacent to a second closed end 106 of the tubular body 102. The cleaning tool 100 may further include a first non-metallic component 124 disposed around the first recessed portion 122. The first recessed portion 122 may have a diameter smaller than the maximum outer diameter 132 of the tubular body 102. In some embodiments, the first recessed portion 122 may at least partially define an engagement portion 108.

[0072] In one embodiment, the tubular body 102 may further include a second recessed portion 126 adjacent to a first open end 104 of the tubular body 102. The cleaning tool 100 may further include a second non-metallic component 128 disposed around the second recessed portion 126. The second recessed portion 126 may have a diameter smaller than the maximum outer diameter 132 of the tubular body 102.

[0073] The first non-metallic component 124 and the second non-metallic component 128 prevent direct contact between the tubular body 102 and components of the gas turbine engine 10 (which may be metallic in some cases). For example, the first non-metallic component 124 prevents direct contact between the first recess 122 and the support member 110. The second non-metallic component 128 prevents direct contact between the second recess 126 and the burner bushing 61. In some examples, each of the first non-metallic component 124 and the second non-metallic component 128 may be a nylon pad.

[0074] As discussed above, the wall thickness 131 can vary along the flow channel 114. The wall thickness 131 in the second recessed portion 126 can be smaller than that in other parts of the tubular body 102.

[0075] The cleaning tool 100 may further include a nozzle 134 connected to at least one nozzle orifice 112 (shown only in...). Figure 3A (For illustrative purposes only). Nozzle 134 may be configured to direct cleaning fluid 115 to a target cleaning area 51 of component 50 (shown in... Figure 2 (In some embodiments, the nozzle 134 may be non-removably connected to at least one nozzle orifice 112. In some other embodiments, the nozzle 134 may be removably connected to at least one nozzle orifice 112.)

[0076] The cleaning tool 100 may include any suitable device for connecting the nozzle 134 to at least one nozzle orifice 112. For example, depending on the desired application properties, the tubular body 102 may include a threaded portion (not shown) positioned at at least one nozzle orifice 112 to allow connection of various types of nozzles 134.

[0077] In some embodiments, at least one nozzle orifice 112 may include a plurality of nozzle orifices 112. Each nozzle orifice 112 of the plurality of nozzle orifices 112 may be configured to deliver cleaning fluid 115 to a corresponding component located within the gas turbine engine 10 (or more specifically, within the engine core 11). In this way, the cleaning tool 100 can be used to clean multiple components (e.g., multiple NGVs) located within the gas turbine engine 10. Alternatively, in some embodiments, multiple units of the cleaning tool 100 (with different designs) may be developed for multiple components (e.g., multiple NGVs). Based on the component that needs to be cleaned, a corresponding unit from the plurality of units of the cleaning tool 100 may be selected and used.

[0078] Figure 5 A flowchart illustrating an embodiment of the present disclosure is shown, depicting a method for maintaining a gas turbine engine (e.g., Figure 1 The various steps of method 200 for the gas turbine engine 10) will be further referred to. Figures 2 to 4 Let's discuss method 200.

[0079] At step 202, method 200 includes providing a cleaning tool. The cleaning tool includes a tubular body. The tubular body includes a first open end and a second closed end. The tubular body further includes a joining portion adjacent to the second closed end. The joining portion is configured to engage with a support member within a gas turbine engine. The tubular body further includes at least one nozzle orifice disposed between the first open end and the joining portion. The tubular body further includes a flow channel extending from the first open end and in fluid communication with the at least one nozzle orifice. The flow channel is configured to deliver cleaning fluid from the first open end to the at least one nozzle orifice. After the joining portion engages with the support member, the at least one nozzle orifice is configured to face a component positioned within the gas turbine engine to deliver cleaning fluid to the component therethrough. The method further includes inserting the tubular body from the second closed end through a first port of the gas turbine engine such that the joining portion engages with the support member. The method further includes supplying cleaning fluid to the flow channel such that the cleaning fluid is delivered to the component through the at least one nozzle orifice. (Refer to...) Figure 2 For example, method 200 may include providing cleaning tool 100.

[0080] At step 204, method 200 further includes inserting the tubular body from the second closed end through the first port of the gas turbine engine, such that the engagement portion engages with the support. (See reference...) Figure 2 For example, method 200 may include inserting a tubular body 102 from a second closed end 106 through a first port 116 of the gas turbine engine 10, such that the engagement portion 108 engages with the support member 110.

[0081] In one embodiment, the step of inserting the tubular body through the first port may further include receiving, at least partially, a joining portion of the tubular body through a second port of the gas turbine engine, such that the joining portion extends at least partially through the second port. (See also...) Figure 2 For example, method 200 may include receiving at least a portion 108 of the tubular body 102 through a second port 117 of the gas turbine engine 10, such that the portion 108 extends at least partially through the second port 117.

[0082] At step 206, method 200 further includes supplying cleaning fluid to a flow channel such that the cleaning fluid is delivered to the component through at least one nozzle orifice. (Refer to...) Figure 2 For example, method 200 may include supplying cleaning fluid 115 to flow channel 114 such that cleaning fluid 115 is delivered to component 50 through at least one nozzle orifice 112.

[0083] Method 200 can be used to clean the components of the gas turbine engine using a cleaning tool without removing the gas turbine engine from the wing of the aircraft. Using method 200, the cleaning tool can be used to clean the components while the gas turbine engine is being installed on the wing of the aircraft. Method 200 can thus reduce the costs associated with cleaning the components (e.g., reducing the costs associated with removing the gas turbine engine from the wing) and reduce the downtime of the gas turbine engine.

[0084] The geometric constraints on the tubular body that allow it to be inserted through the first port may limit the rigidity provided solely by the tubular body without external supports. The engagement portion where the tubular body joins the support allows cleaning fluid to be delivered to the component at high pressure and velocity through at least one nozzle orifice. The tubular body resists deformation (e.g., bending) due to the engagement of the joint portion with the support. This also improves the accuracy of directing cleaning fluid to the component at high discharge velocities through at least one nozzle orifice and reduces the likelihood of damage to other components (e.g., thermal barriers or other coatings) adjacent to the component during cleaning operations.

[0085] In one embodiment, the step of supplying cleaning fluid to the flow channel may include delivering the cleaning fluid to the component at a flow rate greater than 10 liters per minute through at least one nozzle orifice. (See also...) Figure 2 For example, cleaning fluid 115 can be delivered to component 50 at a flow rate greater than 10 liters per minute through at least one nozzle hole 112.

[0086] In one embodiment, the discharge velocity of the cleaning fluid delivered through at least one nozzle orifice can be greater than 150 meters per second.

[0087] In one embodiment, the step of supplying cleaning fluid to the flow channel may include supplying the cleaning fluid to the flow channel at a pressure greater than 200 bar. (See also...) Figure 2 For example, cleaning fluid 115 can be supplied to flow channel 114 at a pressure greater than 200 bar.

[0088] In one embodiment, the step of supplying cleaning fluid to the flow channel may further include guiding the cleaning fluid to a target cleaning area of ​​the component via at least one nozzle orifice. (See also...) Figure 2 For example, cleaning fluid 115 can be directed to the target cleaning area 51 of component 50 via at least one nozzle hole 112.

[0089] In one embodiment, method 200 may further include removably connecting the nozzle to at least one nozzle orifice. (Refer to...) Figure 3A For example, method 200 may include removably connecting nozzle 134 to at least one nozzle orifice 112.

[0090] In one embodiment, the step of supplying cleaning fluid to the flow channel may further include directing the cleaning fluid to a target cleaning area of ​​the component via a nozzle. (See also...) Figure 2 and Figure 3A For example, the cleaning fluid 115 can be directed to the target cleaning area 51 of the component 50 via the nozzle 134.

[0091] In one embodiment, method 200 may further include inspecting the gas turbine engine to identify components. (See also...) Figure 1 and Figure 2 For example, method 200 may include inspecting the gas turbine engine 10 to identify component 50. In some examples, method 200 may further include identifying a target clean area of ​​the component.

[0092] In one embodiment, method 200 may further include removably attaching a mounting plate to a gas turbine engine. Method 200 may further include removably attaching a top plate of a cleaning tool to the mounting plate after inserting a tubular body through a first port of the gas turbine engine. See also... Figure 2 For example, method 200 may include removably attaching mounting plate 136 to gas turbine engine 10 and removably attaching top plate 118 to mounting plate 136 after inserting tubular body 102 through first port 116 of gas turbine engine 10.

[0093] Various examples have been described, each including various combinations of features. It will be appreciated by those skilled in the art that any feature may be used alone or in combination with any other feature unless there is obvious mutual exclusion, and the invention extends to and includes all combinations and sub-combinations of one or more features described herein.

Claims

1. A cleaning tool (100) for cleaning components (50) positioned within a gas turbine engine (10), the cleaning tool (100) comprising: The tubular body (102) includes: First open end (104) and second closed end (106); A joining portion (108) near the second closed end (106), wherein the joining portion (108) is configured to engage with a support (110) within the gas turbine engine (10); At least one nozzle orifice (112) is disposed between the first open end (104) and the engagement portion (108); and A flow channel (114) extending from the first open end (104) and in fluid communication with the at least one nozzle orifice (112), wherein the flow channel (114) is configured to deliver cleaning fluid (115) from the first open end (104) to the at least one nozzle orifice (112), and wherein, after the engagement portion (108) engages with the support member (110), the at least one nozzle orifice (112) is configured to face the member (50) so as to pass the cleaning fluid (115) to the member (50) therethrough; and The tubular body (102) is configured to be inserted from the second closed end (106) through the first port (116) of the gas turbine engine (10), such that the engagement portion (108) engages with the support (110).

2. The cleaning tool (100) according to claim 1 or claim 2, wherein the tubular body (102) further includes a curved portion (130) extending partially from the second closed end (106) toward the first open end (104), and wherein at least one nozzle hole (112) is disposed on the curved portion (130).

3. The cleaning tool (100) according to any one of the preceding claims, further comprising a top plate (118) that at least partially defines the first open end (104) of the tubular body (102), and a mounting plate (136) configured to be removably coupled to the gas turbine engine (10), wherein the tubular body (102) is configured to be inserted through the first port (116) of the gas turbine engine (10) after the mounting plate (136) is removably coupled to the gas turbine engine (10), and wherein the top plate (118) extends outward from the tubular body (102) and is configured to be removably coupled to the mounting plate (136) after the tubular body (102) is inserted through the first port (116) of the gas turbine engine (10).

4. The cleaning tool (100) according to any one of the preceding claims, wherein the tubular body (102) has a maximum outer diameter (132) of less than 15 mm.

5. The cleaning tool (100) according to any one of the preceding claims, wherein the tubular body (102) further includes a solid portion (120) without the flow channel (114), and wherein the engagement portion (108) is disposed on the solid portion (120).

6. The cleaning tool (100) according to any one of the preceding claims, wherein the tubular body (102) further includes a first recessed portion (122) near the second closed end (106) of the tubular body (102), and wherein the cleaning tool (100) further includes a first non-metallic component (124) disposed around the first recessed portion (122).

7. The cleaning tool (100) according to any one of the preceding claims, wherein the tubular body (102) further includes a second recessed portion (126) near the first open end (104) of the tubular body (102), and wherein the cleaning tool (100) further includes a second non-metallic component (128) disposed around the second recessed portion (126).

8. The cleaning tool (100) according to any one of the preceding claims, wherein the flow channel (114) and the at least one nozzle (112) are configured to deliver the cleaning fluid (115) to the component (50) at a flow rate greater than 10 liters per minute through the at least one nozzle (112).

9. The cleaning tool (100) according to any one of the preceding claims, wherein the flow channel (114) is configured to receive the cleaning fluid (115) at a pressure greater than 200 bar.

10. The cleaning tool (100) according to any one of the preceding claims, wherein the support (110) includes a second port (117) of the gas turbine engine (10), and wherein the engagement portion (108) extends at least partially through the second port (117).

11. A gas turbine engine (10) comprising: Engine core (11); Component (50), which is positioned within the engine core (11); Support member (110) is located within the engine core (11); The first port (116) provides a pathway to the component (50); as well as Cleaning tool (100) for cleaning the component (50), the cleaning tool (100) comprising: The tubular body (102) includes: First open end (104) and second closed end (106); A joining portion (108) is located near the second closed end (106), wherein the joining portion (108) is configured to engage with the support member (110); At least one nozzle orifice (112) is disposed between the first open end (104) and the engagement portion (108); and A flow channel (114) extending from the first open end (104) and in fluid communication with the at least one nozzle orifice (112), wherein the flow channel (114) is configured to deliver cleaning fluid (115) from the first open end (104) to the at least one nozzle orifice (112), and wherein, after the engagement portion (108) engages with the support member (110), the at least one nozzle orifice (112) is configured to face the member (50) so as to pass the cleaning fluid (115) to the member (50) therethrough; and The tubular body (102) is configured to be inserted from the second closed end (106) through the first port (116) such that the engagement portion (108) engages with the support (110).

12. A method (200) for maintaining a gas turbine engine (10), the method (200) comprising: A cleaning tool (100) is provided, the cleaning tool (100) comprising: The tubular body (102) includes: First open end (104) and second closed end (106); A joining portion (108) near the second closed end (106), wherein the joining portion (108) is configured to engage with a support (110) within the gas turbine engine (10); At least one nozzle orifice (112) is disposed between the first open end (104) and the engagement portion (108); and A flow passage (114) extending from the first open end (104) and in fluid communication with the at least one nozzle orifice (112), wherein the flow passage (114) is configured to deliver cleaning fluid (115) from the first open end (104) to the at least one nozzle orifice (112), and wherein, after the engagement portion (108) engages with the support member (110), the at least one nozzle orifice (112) is configured to face a member (50) positioned within the gas turbine engine (10) so as to deliver the cleaning fluid (115) to the member (50) therethrough. The tubular body (102) is inserted into the second closed end (106) through the first port (116) of the gas turbine engine (10), such that the joining portion (108) engages with the support member (110); and The cleaning fluid (115) is supplied to the flow channel (114) such that the cleaning fluid (115) is delivered to the component (50) through the at least one nozzle hole (112).

13. The method (200) according to claim 12, further comprising: The mounting plate (136) is removably attached to the gas turbine engine (10). as well as After the tubular body (102) is inserted through the first port (116) of the gas turbine engine (10), the top plate (118) of the cleaning tool (100) is removably attached to the mounting plate (136).

14. The method (200) according to any one of claims 12 or 13, wherein the step of supplying the cleaning fluid (115) to the flow channel (114) comprises supplying the cleaning fluid (115) to the flow channel (114) at a pressure greater than 200 bar.

15. The method (200) according to any one of claims 12 to 14, wherein the step of inserting the tubular body (102) through the first port (116) further comprises receiving the engagement portion (108) of the tubular body (102) at least partially through the second port (117) of the gas turbine engine (10), such that the engagement portion (108) extends at least partially through the second port (117).

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