Masking system

Abstract

A masking system for selectively masking components is provided that includes a first component, a second component, and a third component. The first assembly is provided with a groove. The second assembly is provided with a protrusion, a first channel and a second channel. The third assembly is provided with a first wall, a second wall, a first side wall and a second side wall. The first side wall is provided with a first notch. The groove is used for bearing the protrusion so as to connect the first assembly and the second assembly. The second wall of the third component is used for receiving the first channel and the second channel, so that a part of the component can be inserted through the first notch.

Description

TECHNICAL FIELD

[0001] The present invention relates to the field of masking systems. In particular, to an interlocking masking system for selectively masking components in high temperature processes. SUMMARY

[0002] The following summary of the invention is intended to help understand certain basic aspects of the invention. It is not intended to be a full description of the invention nor is it intended to define the scope of the invention. Its sole purpose is to present some concepts of the invention in a simplified form as a prelude to the more detailed description that is provided elsewhere in this document.

[0003] According to one embodiment of the present invention, a masking system for selectively masking components comprises a first component, a second component and a third component. The first component is provided with a recess. The second component is provided with a protrusion, a first channel and a second channel. The third component is provided with a first wall, a second wall, a first side wall and a second side wall. The first side wall is provided with a first notch. The recess is configured to receive the protrusion to connect the first and second components. The second wall of the third component is configured to receive the first and second channels such that a portion of the component can be inserted through the first notch.

[0004] In one embodiment, according to any of the above embodiments, the second component is provided with a top wall, the top wall being provided with a cutout.

[0005] In one embodiment, according to any of the above embodiments, the first and second channels are operable through the cutout.

[0006] In one embodiment, according to any of the above aspects, the recess is a truncated rectangular recess.

[0007] In one embodiment, according to any of the above embodiments, the protrusion is a truncated rectangular protrusion.

[0008] In one embodiment, according to any of the above embodiments, further comprising a fourth component, the fourth component being provided with a first wall and a second wall, the first wall and the second wall being connected by an angled wall.

[0009] In one embodiment, according to any of the above embodiments, the components are gas turbine components.

[0010] In one embodiment, according to any of the above embodiments, the components are fan disks.

[0011] In one embodiment, according to any of the above embodiments, the fan disk comprises a post provided with a wear plate.

[0012] In one embodiment, according to any of the above embodiments, the portion of the assembly is a wear plate.

[0013] In one embodiment, according to any of the above embodiments, the second wall has a height greater than a height of the first wall.

[0014] In one embodiment, according to any of the above embodiments, the masking system is tool-less.

[0015] In one embodiment, according to any of the above embodiments, a masking system for selectively masking a disk is disclosed. The disk has a stop including a post with a wear plate. The masking system includes a first assembly, a second assembly, and a third assembly. The second assembly has a first channel and a second channel. The first channel is opposite the second channel. The third assembly has a first wall, a second wall, a first side wall, and a second side wall. The first side wall has a first notch. The first assembly is configured to be connected to the second assembly in an end-to-end configuration. The second wall of the third assembly is configured to receive the first channel and the second channel, such that the first notch corresponds to the wear plate when the third assembly is on the post.

[0016] In one embodiment, according to any of the above embodiments, the post has a second wear plate opposite the wear plate. The second side wall has a second notch configured to correspond to the second wear plate when the second wall is inserted into the first channel and the second channel.

[0017] In one embodiment, according to any of the above embodiments, the masking system includes a fourth assembly having a notch configured to interface with an edge of the disk.

[0018] In one embodiment, according to any of the above embodiments, the disk is a fan disk of a gas turbine.

[0019] In one embodiment, according to any of the above embodiments, the masking system includes a first assembly, a second assembly having a first channel and a second channel, and a third assembly having a first wall, a second wall, a first side wall, and a second side wall. The first assembly is configured to be connected to the second assembly. The second wall of the third assembly is configured to receive the first channel and the second channel such that a portion of the assembly can be inserted through the first notch.

[0020] In one embodiment, according to any of the above embodiments, the first assembly has a truncated rectangular recess and the second assembly has a truncated rectangular protrusion.

[0021] In one embodiment, according to any of the above embodiments, the first assembly and the second assembly are connected in an end-to-end configuration.

[0022] In one embodiment, according to any of the above embodiments, the first component, the second component, and the third component are all manufactured using high-temperature materials additive manufacturing. Attached Figure Description

[0023] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings, wherein:

[0024] Figure 1 This is a schematic diagram of a gas turbine engine in some embodiments of the present invention;

[0025] Figure 2 This is a perspective view of fan blades in some embodiments of the present invention;

[0026] Figure 3 This is a front view of a fan disk with multiple fan blades in some embodiments of the present invention;

[0027] Figure 4A This is a perspective view of the fan disk of a gas turbine engine in some embodiments of the present invention;

[0028] Figure 4B for Figure 4A A partial detailed view of the fan disk shown;

[0029] Figure 5A for Figure 4A Another detailed view of a portion of the central fan disk shows a column with an undamaged wear-resistant plate in some embodiments of the invention;

[0030] Figure 5B for Figure 5A Another detailed view of a portion of the central fan disk shows a column with a damaged wear-resistant plate in some embodiments of the present invention;

[0031] Figure 6 for Figure 5B Another detailed view of a portion of the central fan disc shows the portion masked with masking tape in some embodiments of the invention;

[0032] Figure 7A This is a perspective view of a masking system in some embodiments of the present invention;

[0033] Figure 7B In some embodiments of the present invention Figure 7A An exploded view of the masking system;

[0034] Figure 8A In some embodiments of the present invention Figure 7A Perspective view of the first component of the masking system;

[0035] Figure 8B In some embodiments of the present invention Figure 8A Front view of the first component;

[0036] Figures 9A-9B for some embodiments of the present invention Figure 7A perspective view of a second component of the masking system;

[0037] Figures 10A-10D for some embodiments of the present invention Figure 7A perspective view of a third component of the masking system;

[0038] Figure 11A for some embodiments of the present invention Figure 7A perspective view of a fourth component of the masking system;

[0039] Figure 11B for some embodiments of the present invention Figure 7A side view of a fourth component of the masking system;

[0040] Figures 12A-12B perspective view of the first component and the second component connected for some embodiments of the present invention

[0041] Figures 12C-12D side view of the first component and the second component connected for some embodiments of the present invention

[0042] Figures 13A-13D perspective view of the third component and the second component connected for some embodiments of the present invention

[0043] Figure 14 perspective view of the second component operating on a damaged fan disk for some embodiments of the present invention

[0044] Figures 15A-15B perspective view of the first component and the second component operating on a damaged fan disk for some embodiments of the present invention

[0045] Figures 16A-16B perspective view of the first component, the second component, and the third component operating on a damaged fan disk for some embodiments of the present invention

[0046] Figure 17 perspective view of the first component, the second component, the third component, and the fourth component operating on a damaged fan disk for some embodiments of the present invention

[0047] Figure 18 a plurality of Figure 7A perspective view of the masking system selectively masking a damaged fan disk

[0048] Figure 19A a plurality of Figure 7A another perspective view of the masking system selectively masking a damaged fan disk

[0049] Figure 19B FIG. 1 is a perspective view of a fan disk having a damaged portion; Figure 19A FIG. 2 is a detailed view of a portion of the damaged fan disk of FIG. 1;

[0050] Figure 20A FIG. 3 is a perspective view of the masking system of FIG. 1 in use on the damaged fan disk of FIG. 1; Figure 7A FIG. 4 is another perspective view of the masking system selectively masking the damaged fan disk while repairing the wear plate in some embodiments of the present invention;

[0051] Figure 20B FIG. 5 is a detailed view of a portion of the damaged fan disk of FIG. 3; Figure 20A FIG. 6 is a detailed view of a portion of the damaged fan disk of FIG. 4;

[0052] Figures 21A-21B FIG. 7 is a perspective view of the masking system selectively masking the damaged fan disk while repairing the wear plate in some embodiments of the present invention. Figure 7A FIG. 8 is a perspective view of the masking system selectively masking the damaged fan disk while repairing the wear plate in some embodiments of the present invention. DETAILED DESCRIPTION

[0053] Gas turbine engines generally include a multi-stage compressor connected by an axial shaft to a multi-stage turbine. The multi-stage compressor includes a low pressure compressor and a high pressure compressor, and the multi-stage turbine includes a low pressure turbine and a high pressure turbine. Air enters the gas turbine engine through the low pressure compressor, where the temperature and pressure of the air increases as the air passes through successive stages of the compressor. The compressed air is then directed to one or more combustion chambers where it is mixed with a fuel source to form a fuel mixture. The mixture is ignited in the combustion chamber to produce a hot combustion gas stream. These gases are directed into the turbine to cause the turbine to rotate, thereby driving the compressor. The output of the gas turbine engine is either the mechanical thrust of the turbine exhaust or the shaft power of the axial shaft rotation, where the axial shaft drives an electrical generator to produce electricity.

[0054] The compressor and turbine each include a plurality of rotating blades and stationary vanes, the airfoils of which extend into the flow of compressed air or hot combustion gases. Each blade or vane has a specific set of design criteria that must be met in order to provide the necessary work on the flow of air through the compressor and turbine. However, due to the severity of the operating environment, particularly in the turbine, it is often necessary to cool these blades and vanes. The blades and vanes are typically provided with complex internal cooling passages to maximize the cooling efficiency of the fluid flowing therethrough.

[0055] Gas turbine engines also include a fan placed at the front of the engine. The fan includes a disk to which a plurality of fan blades are attached. The fan, when rotated, increases the amount of air flowing through the engine, thereby increasing the engine's thrust. The fan blades are larger in size than the compressor and turbine blades.

[0056] Figure 1This is a schematic diagram of a gas turbine engine 1. The gas turbine engine 1 includes a generator 10, a low-pressure compressor 12, a low-pressure turbine 14, a high-pressure compressor 16, a combustion chamber 18, and a high-pressure turbine 20. Gas flows into the gas turbine engine 1 in direction A, which is parallel to the longitudinal axis 22 of the gas turbine engine 1. The low-pressure compressor 12 and the low-pressure turbine 14 are connected by a low-pressure shaft 24 centered on the longitudinal axis 22. Similarly, the high-pressure compressor 16 and the high-pressure turbine 20 are connected by a high-pressure shaft 26 centered on the longitudinal axis 22. The high-pressure shaft 26 is fitted around the low-pressure shaft 24. The gas turbine engine 1 also includes a fan 28, which is housed in a fan shroud 30 and positioned upstream of the low-pressure compressor 12. The fan 28 includes a plurality of fan blades 40 that rotate about the longitudinal axis 22. In some examples, the fan 28 is movably connected to the low-pressure shaft 24 and driven by the low-pressure turbine 14.

[0057] Figure 2 The fan blade is 40. The fan blade 40 is... Figure 1 One of the multiple fan blades of the intermediate fan 28, or one of the multiple fan blades of another gas turbine engine fan. Fan blade 40 includes an airfoil 42, which has a pressure surface 44 (in... Figure 2 (Not clearly shown in the text) and suction surface 46. Pressure surface 44 and suction surface 46 extend from the leading edge 48 and trailing edge 50 of airfoil 42, respectively. Fan blade 40 includes a root or dovetail (hereinafter referred to as "root 52") at its lowest part. Root 52 is fir-shaped. As described herein, root 52 is located in a corresponding slot in the fan disk to attach fan blade 40 to the fan disk.

[0058] Figure 3 As an example, a fan disk 60 has multiple radially connected fan blades 40. The fan disk 60 is movably (e.g., rotatably) connected to the low-pressure shaft 24 of the gas turbine engine 1 (see...). Figure 1 The fan disk 60 is mounted on a gas turbine engine and driven by a low-pressure turbine 14. In other examples, the fan disk 60 is connected to one or more components of another gas turbine engine for operation.

[0059] Figure 4A and Figure 4B This is a perspective view of the fan disc 60 (without fan blades 40 installed). In some examples, the fan disc 60 includes a flange 62 and a mounting portion 64 adjacent to the flange 62. The flange 62 and the mounting portion 64 are an integral structure, and the flange 62 is connected to the mounting portion 64 using fasteners, welded joints, or one or more other suitable fastening techniques. When the fan disc 60 is connected to the low-pressure shaft 24 of the gas turbine engine 1 (see...), Figure 1 When the mounting part 64 is located upstream of the flange part 62, the mounting part 64 is positioned upstream of the flange part 62.

[0060] Flange portion 62 is generally stepped or Z-shaped, including a first wall 68, a second wall 70, and a connecting wall 71. First wall 68 and second wall 70 of flange portion 62 are both vertically extending (see Figure 4A ), and connecting wall 71 extends upwardly at an angle (e.g., acute) from first wall 68 to second wall 70. In some examples, first wall 68 of flange portion 62 of fan disk 60 is adjacent mounting portion 64 of fan disk 60. Second wall 70 is closer to low pressure turbine 14 relative to first wall 68 when fan disk 60 is connected to low pressure shaft 24 (see Figure 1 ) as part of fan 28 of gas turbine engine 1. In some examples, flange portion 62 includes an edge 73 (see Figure 4A ) that is adjacent second wall 70 and distal from mounting portion 64.

[0061] Mounting portion 64 of fan disk 60 is for mounting a plurality of fan blades 40, such as roots 52 thereof, or other roots or dovetail fan blades. In one example, mounting portion 64 of fan disk 60 includes slots 72 and blocks 74 alternating circumferentially along mounting portion 64. Each slot 72 is substantially the same size, and each block 74 is substantially the same size. Each slot 72 and block 74 extends axially along a width of mounting portion 64 (see Figure 4B ). Each slot 72 is bounded by an axially extending block 74 adjacent the slot 72 in a counterclockwise direction and an axially extending block 74 adjacent the slot 72 in a clockwise direction.

[0062] In some examples, each block 74 includes a first side wall 76, a second side wall 78, a top wall 80, a proximal end 82P, and a distal end 84D (see Figure 4B ). First side wall 76 is opposite second side wall 78, and proximal end 82P is opposite distal end 84D. In some examples, proximal end 82P of each block 74 is opposite and proximal to flange portion 62. First side wall 76 and second side wall 78 of each block 74 are spaced apart from each other and each extends axially along the width of mounting portion 64 from proximal end 82P to distal end 84D of block 74. In some examples, first side wall 76 of each block 74 is counterclockwise of second side wall 78 of the block 74, and each of first side wall 76 and second side wall 78 extends axially and is substantially parallel to each other. Top wall 80 is at a top of first side wall 76 and second side wall 78 and extends axially from distal end 84D to proximal end 82P. In some examples, top wall 80 is provided with an overhang 81 (see Figure 4B ) that extends outwardly beyond first side wall 76 and second side wall 78 from distal end 84D.

[0063] Each slot 72 is bounded by a second sidewall 78 of one block 74 and a first sidewall 76 of another block 74. More specifically, the bounds of each slot 72 include the second sidewall 78 of the block 74 adjacent the slot 72 in the counterclockwise direction and the first sidewall 76 of the block 74 adjacent the slot 72 in the clockwise direction. The first sidewall 76 and the second sidewall 78 of each block 74 are fir-tree shaped, matching the root 52 of the corresponding fan blade 40 (see Figure 2 ). Thus, each slot 72 is used to secure a fan blade 40, and more specifically, the root 52 of the fan blade 40. For example, the root 52 of each fan blade 40 is axially slid into and mounted to one of the slots 72, such that each slot 72 receives and secures one fan blade 40. Although not clearly shown in the figures, when the root 52 of each fan blade 40 is inserted into the corresponding slot 72, the leading edge 48 (see Figure 2 ) of the fan blade 40 is positioned proximate and between the distal end 84D of the block 74 adjacent the slot 72 in the counterclockwise direction and the distal end 84D of the block 74 adjacent the slot 72 in the clockwise direction. Similarly, the trailing edge 50 of the fan blade 40 secured in the slot 72 is positioned proximate and between the proximal end 82P of the block 74 adjacent the slot 72 in the counterclockwise direction and the proximal end of the block 74 adjacent the slot 72 in the clockwise direction.

[0064] A post 86 (see Figure 4B ) extends at or near the proximal end 82P of each block 74. Each post 86 extends radially outward from the top wall 80 of the corresponding block 74. Each post 86 includes a first sidewall 88, a second sidewall 90, and a top wall 92. In some examples, each post 86 is generally frusto-triangular in shape. In other examples, the post 86 can be square, rectangular, triangular, or other regular or irregular shape.

[0065] The first sidewall 88 and the second sidewall 90 of each post 86 extend radially outward from the top wall 80 of the corresponding block 74. In some examples, the first sidewall 88 of each post 86 extends radially outward from the top wall 80 of the corresponding block 74 at or near the first sidewall 76 of the block 74, and the second sidewall 90 of the post 86 extends radially outward from the top wall 80 of the block 74 at or near the second sidewall 78 of the block 74. Each post 86 includes a hole 93. Each hole 93 is used for a fastener (not shown) to pass therethrough, allowing the fan disk 60 to be rotatably secured to one or more other components of the gas turbine engine 1.

[0066] In some examples, each stud 86 includes two wear plates, tabs, or fins (hereinafter referred to as "first wear plate 94" and "second wear plate 96"). The first wear plate 94 of each stud 86 extends outwardly opposite and away from the second wear plate 96. In one example of the present application, the first wear plate 94 of each stud 86 extends laterally from the first side wall 88 of the respective stud 86, and the second wear plate 96 of each stud 86 extends laterally from the second side wall 90 of the respective stud 86. More specifically, the first wear plate 94 of each stud 86 extends laterally counterclockwise over the nearest slot 72 to the stud 86, and the second wear plate 96 of each stud 86 extends laterally clockwise over the nearest slot 72 to the stud 86.

[0067] Once the root 52 of one fan blade 40 is secured within each slot 72, the first wear plate 94 and the second wear plate 96 of each stud 86 will contact the airfoil 42 of one fan blade 40. In some aspects of the embodiment, when the root 52 of one fan blade 40 is inserted counterclockwise into the nearest slot 72 to the stud 86, the first wear plate 94 of the stud 86 contacts and pushes against the suction side 46 and the pressure side 44 of the fan blade 40, and when the root 52 of another fan blade 40 is inserted clockwise into the nearest slot 72 to the stud 86, the second wear plate 96 of the stud 86 contacts and pushes against the suction side 46 and the pressure side 44 of the other fan blade 40. For example, when the root 52 of one fan blade 40 is inserted counterclockwise into the nearest slot 72 to the stud 86, the first wear plate 94 of the stud 86 contacts and pushes against the suction side 46 of the fan blade 40, and when the root 52 of another fan blade 40 is inserted clockwise into the nearest slot 72 to the stud 86, the second wear plate 96 of the stud 86 contacts and pushes against the pressure side 44 of the other fan blade 40. In one aspect of the embodiment, the suction side 46 of a particular fan blade 40 is engaged by the first wear plate 94 of a particular stud 86, while the pressure side 44 of the particular fan blade 40 is engaged by the second wear plate 96 of an adjacent stud 86 in the counterclockwise direction. The engagement, such as frictional engagement, between the first wear plate 94 and the second wear plate 96 of the stud 86 and the pressure side 44 and the suction side 46 of the fan blade 40 can cause the fan blade 40 to be securely mounted to the fan disk 60. Specifically, the airfoil 42 of each fan blade 40 is in contact with and sandwiched between the first wear plate 94 of an adjacent stud 86 and the second wear plate 96 of an adjacent stud 86, thereby preventing or minimizing relative movement between the fan blade 40 and the slot 72 in which the root 52 of the fan blade 40 is mounted.

[0068] During operation of the gas turbine engine 1, the fan disk 60 rotates, for example, driven by the low pressure turbine 14. Rotation of the fan disk 60 can cause the fan blades 40 fixed thereto to rotate as well. During operation of the gas turbine engine 1, the angular velocity of the fan disk 60 (and thus the angular velocity of the fan blades 40 fixed thereto) can be non-uniformly increased or decreased (e.g., by adjusting the increase or decrease in the angular velocity of the fan disk 60, an aircraft powered by one or more gas turbine engines 1 can be accelerated or decelerated, respectively). Angular acceleration and deceleration of the fan blades 40 can cause the airfoils 42 thereof to exert varying loads on the first wear plate 94 and / or the second wear plate 96 with which they come into contact. These loads exerted by the airfoils 42 on the first wear plate 94 and the second wear plate 96 can cause damage or erosion to the first wear plate 94 and / or the second wear plate 96 of one or more of the struts 86 over time.

[0069] For example, comparing Figure 5A and Figure 5B . Figure 5A is a portion of the mounting portion 64 of the fan disk 60, Figure 5B is a portion of the mounting portion 64’ of the damaged fan disk 60’. The fan disk 60 and the damaged fan disk 60’ are identical except that the struts 86 of the mounting portion 64 of the fan disk 60 have the first wear plate 94 and the second wear plate 96 that are not eroded, while the struts 86’ of the mounting portion 64’ of the damaged fan disk 60’ have the first wear plate 94’ and the second wear plate 96’ that are eroded over time due to interaction with the fan blades 40. Erosion of the first wear plate 94 and the second wear plate 9 of one or more of the struts 86 can weaken the connection of the fan blades 40 to the fan disk 60, thereby reducing the operational speed of the fan 28. Therefore, it is necessary to repair the damaged fan disk 60’, particularly the damaged first wear plate 94’ and / or the damaged second wear plate 96’ on the struts 86’ thereof, to facilitate normal operation of the fan 28.

[0070] In Figure 5B the example shown, the damaged portion of the fan disk 60’ is the first wear plate 94’ and the second wear plate 96’ of the struts 86’. In some examples, to repair the first wear plate 94’ and / or the second wear plate 96’, the remainder of the fan disk 60’ is selectively masked, exposing only the area of the fan disk 60’ that needs to be repaired. That is, the first wear plate 94’ and the second wear plate 96’ of the mounting portion 64’ remain exposed, while the remainder of the fan disk 60’ is generally masked. The first wear plate 94’ and the second wear plate 96’ are exposed for repair of the first wear plate 94’ and the second wear plate 96’. For example, the surface of the exposed first wear plate 94’ and the second wear plate 96’ can be blasted with an abrasive medium, and then repaired using a thermal spray process and / or one or more other suitable repair processes.

[0071] Adhesive tape, such as heat-resistant adhesive tape, is used to selectively mask the damaged fan disc 60’. For example, the areas of the damaged fan disc 60’ near the first wear plate 94’ and the second wear plate 96’, as well as other areas that can be affected during the process of repairing the first wear plate 94’ and the second wear plate 96’, can be masked with heat-resistant adhesive tape. In some examples, most of the components of the damaged fan disc 60’ can be masked with heat-resistant adhesive tape in addition to the first wear plate 94’ and the second wear plate 96’, so that damage to these components is minimized when repairing the first wear plate 94’ and the second wear plate 96’.

[0072] Figure 6 A portion of the damaged fan disc 60’ is selectively masked with heat-resistant adhesive tape 99 for use in repairing the first wear plate 94’ and the second wear plate 96’ (the shaded area in FIG. 9 represents the area of the damaged fan disc 60’ that is masked with heat-resistant adhesive tape 99). In the example shown in FIG. 9, the first wear plate 94’ and the second wear plate 96’ are exposed, while the rest of the damaged fan disc 60’ is masked with heat-resistant adhesive tape 99. Selectively wrapping the damaged fan disc 60’ with heat-resistant adhesive tape 99 ensures that those parts that do not need to be repaired (e.g., the flange portion 62, the first side wall 76, the second side wall 78, and the top wall 80 of each block 74, etc.) are not affected during the repair process (e.g., the sandblasting and thermal spraying processes). Figure 6 Figure 6 In the example shown in FIG. 9, the first wear plate 94’ and the second wear plate 96’ are exposed, while the rest of the damaged fan disc 60’ is masked with heat-resistant adhesive tape 99. Selectively wrapping the damaged fan disc 60’ with heat-resistant adhesive tape 99 ensures that those parts that do not need to be repaired (e.g., the flange portion 62, the first side wall 76, the second side wall 78, and the top wall 80 of each block 74, etc.) are not affected during the repair process (e.g., the sandblasting and thermal spraying processes).

[0073] The damaged area of the fan disc 60’ can be relatively large, for example, 5 feet or more in diameter. Taping up most of the area of the damaged fan disc 60’ is time-consuming, labor-intensive, and expensive. Heat-resistant adhesive tape 99 is only available in specific standard sizes, and an operator is required to cut the heat-resistant adhesive tape 99 into specific shapes to ensure that the heat-resistant adhesive tape 99 selectively masks the damaged area of the fan disc 60’, or else those areas can be inadvertently damaged during the process of repairing the first wear plate 94’ and the second wear plate 96’. Furthermore, the heat-resistant adhesive tape 99 needs to be cut into a custom shape before it is applied to the damaged fan disc 60’, because cutting the heat-resistant adhesive tape 99 after it is applied to the damaged fan disc 60’ can scratch or damage one or more surfaces of the fan disc 60’. Given these factors, it can take several hours to selectively tape up a relatively large fan disc 60’ to expose its first wear plate 94’ and second wear plate 96’. After the repair is complete, the heat-resistant adhesive tape 99 can need to be laboriously removed from the fan disc 60’ as well. Furthermore, heat-resistant adhesive tape 99 is typically expensive and is a consumable item that must be discarded after a single use. It is not uncommon for a facility that repairs fan discs to spend hundreds of thousands of dollars on heat-resistant adhesive tape.

[0074] Figures 7A-7B ​A masking system 200 for one embodiment of the present application. The masking system 200 is also referred to in the present application as an interlocking masking system (hereinafter simply "masking system 200"). In some embodiments of the example, the masking system 200 includes a first assembly 202 (see Figures 8A-8B ), a second assembly 220 (see Figures 9A-9B ), a third assembly 250 (see Figures 10A-10D ), and a fourth assembly 270 (see Figures 11A-11B ). In some examples, the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 are separate from each other, each being a unitary construction. As described herein, multiple masking systems 200 can be used collectively to selectively mask a damaged fan disk 60', exposing the first wear plate 94' and the second wear plate 96' of each stanchion 86' for repair. In some examples of the example, the fourth assembly 270 can be omitted, i.e., the masking system 200 includes the first assembly 202, the second assembly 220, and the third assembly 250.

[0075] Figure 8A is a perspective view of the first assembly 202, Figure 8B is an elevation view of the first assembly 202. The first assembly 202 extends from a proximal end 204P to a distal end 206D. In some examples, the first assembly 202 includes a main body 208. In one aspect of the example, the main body 208 is generally U-shaped. In other aspects of the example, the main body 208 can be rectangular, triangular, cylindrical, or other symmetrical or asymmetrical shape.

[0076] The main body 208 has a first wall 210, a second wall 212, and a top wall 214. The first wall 210 is opposite the second wall 212, each of the first wall 210 and the second wall 212 extending perpendicularly from opposite ends of the top wall 214. The first wall 210 and the second wall 212 are the same height and width. At the distal end 206D, a back wall 218 extends from the top wall 214. The back wall 218 is the same width as the top wall 214, and the back wall 218 is taller than the first wall 210 and the second wall 212. The back wall 218 is thus provided with an extension 219 that extends below the first wall 210 and the second wall 212.

[0077] In some examples, each of the first wall 210, the second wall 212, and the top wall 214 includes a respective cutout 210C, 212C, and 214C at the proximal end 204P of the first assembly 202. The cutouts 210C, 212C, and 214C collectively form a continuous three-sided or truncated rectangular recess 216.

[0078] Figure 9A and 9BThe second assembly 220 of the masking system 200 is shown in greater detail. The second assembly 220 has a body 224 that extends from a proximal end 226P to a distal end 228D of the second assembly 220. In some examples, the body 224 of the second assembly 220 is generally U-shaped, although in other examples the body 224 can be rectangular, cylindrical, or other symmetrical or asymmetrical shape. The body 224 includes a first wall 230, a second wall 232, and a top wall 234. The first wall 230 and the second wall 232 are opposite one another and extend perpendicularly from opposite ends of the top wall 234.

[0079] The body 224 of the second assembly 220 includes a protrusion 236 at the distal end 228D. The protrusion 236 is continuous and is tri-faceted or truncated rectangular. For example, the protrusion 236 is formed by a protrusion 230P of the first wall 230, a protrusion 232P of the second wall 232, and a protrusion 234P of the top wall 234.

[0080] The inner surface of the first wall 230 includes a first channel 240 Figures 9A-9B that extends generally perpendicularly. The second wall 232 likewise includes a second channel 242 on its inner surface that extends perpendicularly and faces the first channel 240. In some examples, the first channel 240 and the second channel 242 are closer to the proximal end 226P than the distal end 228D. A cutout 238 is formed at the proximal end 226P of the top wall 234. The first channel 240 and the second channel 242 enter through the cutout 238 in the top wall 234.

[0081] Figures 10A-10D The third assembly 250 of the masking system 200 is shown in greater detail. The third assembly 250 has a body 252. In some examples, the body 252 is generally square hook-shaped. In other embodiments, the body 252 can be rectangular, triangular, cylindrical, or other symmetrical or asymmetrical shape.

[0082] In some examples, the body 252 of the third assembly 250 includes a first wall 254, a second wall 256, a first side wall 258, a second side wall 260, and a top wall 261. The first wall 254 is opposite the second wall 256, and the first side wall 258 is opposite the second side wall 260. The first wall 254 has a bottom end 254E. The second wall 256 has a bottom end 257C, a first edge 257A, and a second, opposite edge 257B. In some examples, the second wall 256 is taller than the first wall 254, i.e., the bottom end 257C of the second wall 256 extends below the bottom end 254E of the first wall 254.

[0083] The first side wall 258 and the second side wall 260 are spaced apart and extend from the first wall 254 to the second wall 256. In one example of an embodiment, the first side wall 258 is provided with a first notch 262 and the second side wall 260 is provided with a second notch 264. The first notch 262 is opposite the second notch 264. In some examples, each of the first notch 262 and the second notch 264 is a truncated rectangle. In other examples, the first notch 262 and / or the second notch 264 can be rectangular, spherical, or other symmetrical or asymmetrical shape.

[0084] Figures 11A-11B A fourth assembly 270 of the masking system 200 is shown in greater detail. As noted above, the fourth assembly 270 is optional and can be omitted from the masking system 200 in some examples. The fourth assembly 270 is generally stepped or Z-shaped. In one example, the fourth assembly 270 is provided with a first wall 272, a second wall 274, and a connecting wall 276. The first wall 272 and the second wall 274 of the fourth assembly 270 each extend vertically, and the connecting wall 276 extends upwardly from the first wall 272 to the second wall 274 at an acute angle. The second wall 274 has a bottom end 278. In some examples, the bottom end 278 has a notch 279 and is generally L-shaped. In other examples, the bottom end 278 can be rectangular, square, or other symmetrical or asymmetrical shape.

[0085] One or more of the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 of the masking system 200 (but not necessarily) are configured to mate or otherwise connect with one or more of the other first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270. In one example, each of the first assembly 202 and the third assembly 250 can be connected with the second assembly 220, as described herein.

[0086] Figure 7A The first assembly 202 connected to the second assembly 220 is shown. Figures 12A-12D The manner in which the first assembly 202 and the second assembly 220 are connected is shown in greater detail. As noted above, with reference to Figures 8A-8B , the first assembly 202 includes a recess 216 (e.g., a truncated rectangular recess) at the proximal end 204P. With reference to Figures 9A-9B , the second assembly 220 includes a protrusion 236 (e.g., a truncated rectangular protrusion) at the distal end 228D. In some examples, the recess 216 of the first assembly 202 is configured to receive the protrusion 236 of the second assembly 220, thereby connecting the first assembly 202 to the second assembly 220 (see Figures 12A-12D). For example, one of the first assembly 202 and the second assembly 220 pushes against the other such that the protrusion 236 of the second assembly 220 is received by the recess 216 of the first assembly 202. In one aspect of the embodiment, at least one of the first assembly 202 and the second assembly 220 is pushed in the lateral direction 280 toward the other of the first assembly 202 and the second assembly 220 (see Figure 12C ) to connect the first assembly 202 and the second assembly 220 in an end-to-end configuration. Figure 12D The first assembly 202 and the second assembly 220 are shown connected to one another. In some examples, the recess 216 is relatively smaller in size than the protrusion 236 such that an interference fit exists between the first assembly 202 and the second assembly 220.

[0087] Figure 7A A third assembly 250 is also shown connected to the second assembly 220, as well as the connection of the first assembly 202 and the second assembly 220. Figures 13A-13D The connection between the second assembly 220 and the third assembly 250 is shown in greater detail. As noted above with reference to Figures 9A-9B , the second assembly 220 is provided with the first channel 240 and the second channel 242, which enter through the cutout 238 in the top wall 234. With reference to Figures 10A-10D As noted above, the first side wall 258 and the second side wall 260 of the third assembly 250 include the first notch 262 and the second notch 264, respectively. In some examples, as shown in Figure 13A and 13B , the third assembly 250 is positioned adjacent to the second assembly 220 such that the second wall 256 of the third assembly 250 is adjacent to the cutout 238 in the top wall 234 of the second assembly 220. For example, the second wall 256 of the third assembly 250 can be insertably received by the first channel 240 and the second channel 242 of the second assembly 220. For example, the second wall 256 of the third assembly 250 is pushed downwardly in the vertical direction 282 Figure 13B ) through the cutout 238 such that the first edge 257A of the second wall 256 of the third assembly 250 is received by the first channel 240 of the second assembly 220 and the second edge 257B of the second wall 256 of the third assembly 250 is received by the second channel 242 of the second assembly 220. The third assembly 250 is thus lockingly connected to the second assembly 220.

[0088] As noted above, the second wall 256 of the third assembly 250 has a height that is greater than the height of the first wall 254. In one example of the embodiment, when the third assembly 250 is lockingly connected to the second assembly 220 (see Figure 13C and 13DThe bottom end 254E of the first wall 254 of the third component 250 rests on the top wall 234 of the second component 220, such that the first notch 262 of the first side wall 258 of the third component 250 (see...) Figure 13C ) and the second recess 264 of the second sidewall 260 of the third component 250 (see Figure 13D All of them are upward adjacent to the top wall 234 of the second component. Therefore, the first window 284 (see Figure 13C The third component 250 is formed by the first notch 262 of the first sidewall 258 and the top wall 234 of the second component 220. Similarly, the second window 286 (see...) Figure 13D The first window 284 and the second window 286 are formed by the second recess 264 of the second sidewall 260 of the third component 250 and the top wall 234 of the second component 220. The function and masking of the first window 284 and the second window 286 will be described below.

[0089] Refer again Figure 7A The masking system 200 includes a fourth component 270. As described herein, each of the first component 202 and the third component 250 may be mated with or otherwise connected to the second component 220. In one example of the embodiment, the fourth component 270 is not connected to any of the first component 202, the second component 220, and the third component 250. However, in other respects, the fourth component 270 may be connected to one or more of the first component 202, the second component 220, and the third component 250.

[0090] As described herein, one or more masking systems 200 may be used to selectively mask or cover one or more surfaces of a damaged fan disk 60', i.e., a fan disk 60 with a first wear plate 94 and / or a second wear plate 96 that has worn over time (e.g., ...). Figure 5B The first wear-resistant plate 94' and the second wear-resistant plate 96' of the damaged fan disk 60' are shown. In some examples, multiple masking systems 200 selectively mask the flange 62 of the damaged fan disk 60' (see...). Figure 4A The first wear plate 94' and the second wear plate 96' of each column 86' are exposed. This allows the first wear plate 94' and the second wear plate 96' of the damaged fan disc 60' to be repaired, for example, by allowing the first wear plate 94' and the second wear plate 96' of each column 86' (or a subset of columns 86') to be repaired by abrasive blasting and thermal spraying, while simultaneously eliminating or reducing the impact on the performance of other parts of the damaged fan disc 60' during the abrasive blasting and / or thermal spraying processes.

[0091] Now refer to Figures 14 to 17 Description of the use of the shielding system 200 to selectively shield the damaged fan disk 60'. AlthoughFigures 14-17 The components of a masking system 200 arranged in a specific order on the damaged fan plate 60' are shown, but the depicted order is not a limitation. As described herein, multiple masking systems 200 may be required to selectively mask the damaged fan plate 60' so that the first wear plate 94' and the second wear plate 96' can be repaired.

[0092] In some examples, such as Figure 14 As shown, a second component 220 of a shielding system 200 is disposed on a stop 74 of a damaged fan disk 60', such that a post 86' in contact with the stop 74 extends through a cut 238 in the top wall 234 of the second component 220 (see...). Figure 9A With this configuration, the first wear-resistant plate 94' of the column 86' can be adjacent to the first channel 240 of the second component 220, and the second wear-resistant plate 96' of the column 86' can be adjacent to the second channel 242 of the second component 220, and both the first wear-resistant plate 94' and the second wear-resistant plate 96' are above the top wall 234 of the second component 220.

[0093] The connection method of the first component 202 and the second component 220 is referenced. Figures 12A-12D This has already been discussed above. For example... Figure 14 As shown, once the second component 220 is configured on the damaged fan plate 60', then, as Figures 15A-15B As shown, the first component 202 of the shielding system 200 can be placed above the corresponding block 74 (see Figure 1). Figure 14 ), and connected to the second component 22, see reference Figures 12A-12D As described above. When the first component 202 and the second component 220 are connected above the respective stop 74, the extension 219 of the rear wall 218 of the first component 202 (see Figures 8A-8B The cantilevered portion 81 that abuts against the top wall 80 of the corresponding stop 74 (see...) Figure 4B ).

[0094] The connection method between the third component 250 and the second component 220 was discussed above. (Refer to...) Figures 13A-13D Once the second component 220 is as described above... Figure 14 As discussed, it is configured on top of the stop, in the first component 202 as above. Figures 15A-15B As discussed, before or after connecting to the second component 220, the third component 250 can be connected to the second component 220, such as... Figures 16A-16B As shown. When the third component 250 is connected to the second component 220 in this manner, the third component 250 can selectively mask the corresponding post 86'. More specifically, the third component 250 selectively masks the corresponding post 86', such that the first window 284 (see...) Figure 13C ) corresponds to the first wear-resistant plate 94' (seeFigure 4B and 16A ), the second window 286 corresponds to the second wear plate 96' (see Figure 4B and 16B ). Thus, the first window 284 and the second window 286 can be repaired by accessing the first wear plate 94' and the second wear plate 96', respectively, while the rest of the block 74 and the stud 86' is masked by the first assembly 202, the second assembly 220, and the third assembly 250 of the masking system 200 (completely or at least partially).

[0095] The first assembly 202, the second assembly 220, and the third assembly 250 of the masking system 200 are each configured to mask one or more surfaces of the damaged fan disc 60' mounting portion 64' (see Figure 5B ). In some examples of the embodiments, as shown in Figure 17 , a fourth assembly 270 can be configured to mask the flange portion 62 of the damaged fan disc 60'. Specifically, the fourth assembly 270 is configured to the flange portion 62 of the damaged fan disc 60' such that the first wall 272 of the fourth assembly 270 is adjacent to and can mask at least a portion of the first wall 68 of the flange portion 62, the second wall 274 of the fourth assembly 270 is adjacent to and can mask at least a portion of the second wall 70 of the flange portion 62, and the connecting wall 276 of the fourth assembly 270 is adjacent to and can mask at least a portion of the connecting wall 71 of the flange portion 62. The gap 279 at the bottom end 278 of the second wall 274 (see Figure 11B ) can be snapped onto the edge 73 of the damaged fan disc 60' to secure the fourth assembly 270 to the damaged fan disc 60'.

[0096] As shown in Figure 17 , one masking system 200 is configured to selectively mask one of the blocks 74 (see Figure 4B ) and the studs 86' (see Figure 5B ) of the damaged fan disc 60'. The damaged fan disc 60' is provided with a plurality of blocks 74 and studs 86'. In some examples of the embodiments, a plurality of masking systems 200 can be used to selectively mask the fan disc 60' such that the first wear plate 94' and the second wear plate 96' of all of the studs 86' are exposed and can be repaired.

[0097] Figure 18 A damaged fan disc 60' (i.e., the first wear plate 94' and the second wear plate 96' of the studs 86' of the fan disc 60' have been damaged) is shown as being selectively masked by a plurality of masking systems 200 such that all of the first wear plates 94' and the second wear plates 96' of all of the studs 86' are exposed (e.g., for repair). The fourth assembly 270 of the masking system 200 is not shown in Figure 18 . As shown in Figure 5BAs shown, the damaged fan disk 60' has multiple pillars 86' (e.g., between ten (10) and fifty (50)). Therefore, multiple masking systems 200 can be used to selectively mask the damaged fan disk 60'.

[0098] Figure 19A This is another perspective view showing multiple shielding systems 200 selectively providing overall shielding to the damaged fan disk 60'. As mentioned above, shielding system 200 does not necessarily include a fourth component 270. For example, in Figure 19A In the example shown, the damaged fan plate 60' has thirty (30) columns 86'. Therefore, Figure 19A The image shows thirty (30) groups, each group consisting of a first component 202, a second component 220, and a third component 250, with each group corresponding to a column 86'. However, in Figure 19A In the example shown, only eighteen (18) require the fourth component 270 to mask the flange 62 (see Figure 4A Therefore, in some examples, the fourth component 270 is omitted from the masking system 200.

[0099] Figure 19B for Figure 19A A detailed view of a portion of the damaged fan plate 60'. It can be seen that each third component 250 selectively masks the corresponding column 86', such that a first window 284 formed by the third component 250 and the second component 220 in contact with it exposes the first wear plate 94' of the column 86' (see...). Figure 4B and 16A ).

[0100] Figure 20A yes Figure 19A Another perspective view of the damaged fan disc 60'. Figure 20B yes Figure 20A A detailed view of a portion of the damaged fan plate. (See attached image.) Figure 20B As shown, each third component 250 selectively masks the corresponding post 86', such that the second window 286 formed by the third component 250 and the second component 220 in contact with it exposes the second wear plate 96' of the post 86' (see Figure 4B and 16A In this way, each shielding system 200, including the first component 202, the second component 220, and the third component 250, selectively shields the pillar 86' and the stop 74, such that the first wear plate 94' and the second wear plate 96' of each pillar 86' of the damaged fan disc 60' are exposed and can be repaired.

[0101] Once the damaged fan disc 60' is masked using the masking system 200 described herein, all (or part) of the first wear plate 94' and the second wear plate 96' can be repaired. In some examples, the repair process involves coating the first wear plate 94' and the second wear plate 96' using thermal spraying techniques, such as air plasma spraying (APS), vacuum plasma spraying (VPS), low-pressure plasma spraying (LPPS), high-velocity oxygen fuel spraying (HVOF), etc. For example, the first wear plate 94' and the second wear plate 96' are coated with HVOF. When using an HVOF spraying assembly, a mixture of fluid fuel and oxygen is fed into a combustion chamber and ignited. The resulting gas has extremely high temperature and pressure, allowing it to be ejected at supersonic speeds through a nozzle. Powder is injected into the high-velocity gas stream, which causes the powder to partially melt. The hot gas and powder stream are directed to the surface to be coated. The resulting coating is dense, has low porosity, high bonding strength, and other advantages such as corrosion resistance.

[0102] Figure 21A and 21B Examples of thermal spraying systems with nozzles 302 and 304 are shown. Figure 21A As shown, the thermal spray nozzle 302 coats the first wear-resistant plate 94' of the damaged fan disc 60' through the first window 284 (see...). Figure 5B );like Figure 21B As shown, the thermal spray nozzle 304 coats the second wear plate 96' of the damaged fan disc 60' through the second window 286. The damaged fan disc 60' and / or the spraying system can be moved relative to each other to allow each of the first wear plate 94' and the second wear plate 96' to be repaired. In some examples, the first wear plate 94' and the second wear plate 96' are sandblasted with abrasive media (after the damaged fan disc 60' has been masked as described herein) to prepare for the thermal spraying process. In some examples, the first wear plate 94' and the second wear plate 96' are also machined after the thermal spraying process to complete the repair process. In this way, the masking system 200 allows the damaged fan disc 60' to be selectively masked, for example for repair, without the need for laboriously covering the damaged fan disc 60' with heat-resistant tape.

[0103] In certain aspects of the invention, all or part of the masking system 200 may be additively manufactured. For example, one or more of the first component 202, the second component 220, the third component 250, and the fourth component 270 may be additively manufactured using a high-temperature, low-elongation material capable of repeated thermal spraying processes. The phrase "high-temperature material" herein refers to a material with a heat distortion temperature of at least about 300°C. "High-temperature process" herein refers to a process associated with at least about 300°C, such as a thermal coating (e.g., an HVOF coating) or other high-temperature processes.

[0104] In some examples of the present disclosure, one or more of the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 are manufactured using Loctite's 3D 3955 additive manufacturing, which is a halogen-free high-temperature high-modulus material having a Shore hardness between about 80D and about 85D. In some examples, one or more of the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 are manufactured using a resin, a granule, a filament, a powder, and / or other suitable material having a Shore hardness between about 60D and 105D, in some examples, between about 70D and 95D. The material used to manufacture the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 is a high-temperature material and is capable of withstanding the extreme temperatures encountered during the thermal spray process. For example, the material used to manufacture one or more of the first assembly 202, the second assembly 220, the third assembly 250, and the fourth assembly 270 is capable of withstanding temperatures above about 300°C, above about 400°C, and / or above about 500°C

[0105] The masking system 200 is unidirectionally mountable on the damaged fan disk 60'. For example, the first assembly 202 is unidirectionally mountable on the dam 74 to allow the extension 219 (see Figures 8A-8B ) of the back wall 218 of the first assembly 202 to abut the overhang 81 (see Figure 4B ) of the top wall 80 of the corresponding dam 74. This minimizes or eliminates the possibility of misassembling the masking system 200.

[0106] The masking system 200 is reusable. The masking system 200 can thus be used to selectively mask a plurality of damaged fan disks 60', reducing the cost of repairing the plurality of damaged fan disks 60'. In some examples, the masking system 200 is installed without the need for tools; that is, the masking system 200 is manually configured on the damaged fan disk 60' to selectively mask the damaged fan disk 60' without the need for any tools. Similarly, once the repair process is complete, the masking system 200 can be manually separated from the fan disk 60' without the use of any tools. For example, any of the first assembly 202, the second assembly 220, and the third assembly 250 placed on top of the dam 74 can be separated from the dam 74 manually without the use of any tools after the repair process is complete.

[0107] As described herein, the shielding system 200 is a multi-component system. Sometimes, one or more components of the shielding system 200 (e.g., any one of the first component 202, the second component 220, the third component 250, and the fourth component 270) may be damaged. The segmented nature of the shielding system 200 allows for the replacement and / or repair of only that component, without having to manufacture the entire new shielding system 200. This further reduces the costs associated with manufacturing and using the shielding system 200.

[0108] Although the shielding system 200 has been described herein with reference to the fan disc 60, the shielding system 200 can also be used to selectively shield other gas turbine components, such as turbine discs, compressor discs, etc. The shielding system 200 is also suitable for selectively shielding other components in other industries (e.g., wheel rims used in the automotive industry).

[0109] As used herein, the terms “first,” “second,” “third,” and “fourth” are used interchangeably to distinguish one component from another, but do not indicate the location or importance of a single component. The terms “coupled,” “fixed,” “connected to,” etc., refer to direct coupling, fixing, or connection, as well as indirect coupling, fixing, or connection through one or more intermediate components or features, unless otherwise specified herein. The singular forms “a,” “an,” and “the” include plural references unless the context clearly specifies otherwise.

[0110] Many different arrangements of the various components, as well as those not shown, are possible without departing from the spirit and scope of the invention. Embodiments of this disclosure have been described in an illustrative rather than restrictive manner. Alternative embodiments will become apparent to those skilled in the art without departing from their scope. Those skilled in the art can develop alternative means to achieve the above-described improvements without departing from the scope of this disclosure.

[0111] It should be understood that certain features and sub-combinations are practical and can be used without reference to other features and sub-combinations, and are considered to be within the scope of the claims. Not all steps listed in the various figures need to be performed in the specific order described.

Claims

1. A masking system (200) for a selective masking assembly (60), characterized by, Comprising: a first component (202) provided with a recess (216); a second component (220) provided with a protrusion (236), a first channel (240) and a second channel (242); a third component (250) provided with a first wall (254), a second wall (256), a first side wall (258) provided with a first notch (262) and a second side wall (260); wherein: the recess (216) is configured to receive the protrusion (236) to connect the first component (202) and the second component (220); the second wall (256) of the third component (250) is configured to receive the first channel (240) and the second channel (242) such that a portion of the component (60) can be inserted through the first notch (262).

2. The masking system (200) according to claim 1, characterized in that the second component (220) is provided with a top wall (234) provided with a cutout (238).

3. The masking system (200) according to claim 2, characterized in that the first channel (240) and the second channel (242) are operable through the cutout (238).

4. The masking system (200) of claim 1, wherein, the recess (216) is a truncated rectangular recess.

5. The masking system (200) according to claim 4, characterized in that the protrusion (236) is a truncated rectangular protrusion.

6. The masking system (200) of claim 1, wherein, further comprising a fourth component (270) provided with a first wall (272) and a second wall (274) connected by an angled wall (276).

7. The masking system (200) of claim 1, wherein, the component (60) is a gas turbine (1) component.

8. The masking system (200) of claim 1, wherein, the component is a fan disc (60).

9. The masking system (200) of claim 1, wherein, the fan disc (60) comprises a post (86) provided with a wear plate (94).

10. The masking system (200) of claim 1, wherein, the portion of the component (60) is a wear plate (94).

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