Masking system

Abstract

A masking system for selectively masking a component is provided. The component has a protrusion. The masking system includes a first mask having a recessed region. The recessed region is configured to receive the protrusion. The masking system has a second mask securable to the first mask. When the protrusion is received within the recessed area and the first mask is fixed to the second mask, the first portion of the component is masked and the second portion of the component is exposed.

Description

Technical Field

[0001] This disclosure generally relates to the field of masking systems. More specifically, this disclosure relates to multi-component masking systems configured to selectively mask components for coating and other processes. Background Technology

[0002] Gas turbine engines used in aerospace and power generation operate under extreme conditions of high temperature and corrosive environments. Compressor and turbine blades, typically made of superalloys such as nickel or cobalt-based materials, require protective coatings, such as diffused aluminides or thermal barrier coatings, to resist oxidation and corrosion. These coatings must be selectively applied to the airfoil, while the root (dovetail) remains uncoated to ensure proper fit and function. Inadvertent coating of the root can lead to assembly problems or require costly removal processes. Conventional masking methods, such as tape or paste, often struggle with complex blade geometries, including protrusions, resulting in coating leaks or incomplete masking. This invention addresses these challenges with a novel masking system designed for precise, reusable protection during the coating process, thereby improving efficiency and reducing defects. Summary of the Invention

[0003] To provide a basic understanding of certain aspects of the invention, an overview of the invention is given below. This overview is not a broad summary of the invention. It is not intended to identify key elements of the invention or to depict its scope. Its sole purpose is to present some concepts of the invention in a simplified form as a prelude to a more detailed description presented elsewhere herein.

[0004] On one hand, a masking system is provided for selectively masking a component. The component has a protrusion. The masking system includes a first masking member having a recessed region. The recessed region is configured to receive the protrusion. The masking system has a second masking member that can be fixed to the first masking member. When the protrusion is received within the recessed region and the first masking member is fixed to the second masking member, a first portion of the component is masked, and a second portion of the component is exposed.

[0005] On one hand, according to any of the foregoing aspects, the first masking member includes a first opening, and the second masking member includes a second opening, wherein when the first masking member is fixed to the second masking member, the second opening is aligned with the first opening.

[0006] On the one hand, according to any of the foregoing aspects, the first shield includes a receiving area for receiving the first portion.

[0007] On the one hand, according to any of the foregoing aspects, the shape of the receiving area corresponds to the shape of the first part.

[0008] On the one hand, according to either of the aforementioned aspects, both the first and second shielding components have an integral structure.

[0009] On the one hand, according to either of the foregoing, at least one of the first and second shielding components is additively manufactured.

[0010] On the one hand, according to either of the foregoing, the component is a gas turbine engine component.

[0011] On the one hand, according to either of the aforementioned aspects, the component is a blade.

[0012] On the one hand, according to either of the aforementioned aspects, the protrusion extends from the base of the leaf.

[0013] On the one hand, according to either of the foregoing, the first part includes the root of the leaf.

[0014] In one aspect of this disclosure, a masking system for selectively masking a blade is provided. The blade has a root and a protrusion extending from the root. The masking system includes a first masking member having a recessed region. The recessed region is configured to receive the protrusion. The masking system includes a second masking member that can be secured to the first masking member. When the protrusion is received within the recessed region and the first masking member is secured to the second masking member, the root is enclosed by the masking system.

[0015] On one hand, according to any of the foregoing aspects, the first masking member has a receiving area that supports the bottom surface of the root when the root is encapsulated by the masking system.

[0016] On one hand, according to any of the foregoing aspects, the shielding system includes fasteners passing through a first opening in the first shield and a second opening in the second shield.

[0017] On the one hand, according to either of the foregoing, when the root is enclosed by the masking system and the first mask is fixed to the second mask, the airfoil of the blade and the top edge of the platform are exposed.

[0018] On one hand, according to any of the foregoing aspects, the first shielding element includes a first portion and a second portion. The first portion extends perpendicular to the second portion.

[0019] On the one hand, according to either of the aforementioned aspects, both the first and second shielding components have an integral structure.

[0020] On the one hand, according to either of the foregoing, the shielding system can be reused to selectively shield the second blade.

[0021] On one hand, a method for selectively masking a component is provided. The component has a protrusion. The method includes positioning the protrusion in a recessed region of a first masking member and securing a second masking member to the first masking member. When the protrusion is located in the recessed region and the first masking member is secured to the second masking member, at least a first portion of the component is masked, and at least a second portion of the component is exposed.

[0022] On one hand, according to any of the foregoing aspects, the method includes passing a fastener through a first opening in a first shield and a second opening in a second shield.

[0023] On one hand, according to any of the foregoing, the method includes a portion of a sliding component in the receiving area of ​​the first shield. Attached Figure Description

[0024] The illustrative embodiments of this disclosure are described in detail below with reference to the accompanying drawings, in which:

[0025] Figure 1 This is a schematic diagram of a gas turbine engine based on some aspects of this disclosure.

[0026] Figure 2 This is a perspective view of a fan blade based on some aspects of this disclosure.

[0027] Figure 3A This is a front view of a compressor blade according to some aspects of this disclosure.

[0028] Figure 3B Based on some aspects of this disclosure Figure 3A Rear view of the compressor blades.

[0029] Figure 3C Based on some aspects of this disclosure Figure 3A End view of the compressor blades.

[0030] Figure 3D Based on some aspects of this disclosure Figure 3C A view of the compressor blades from opposite ends.

[0031] Figure 4 This is a perspective view of a shielding device according to some aspects of this disclosure.

[0032] Figure 5 Based on some aspects of this disclosure Figure 4 A perspective view of a concealment device, in which multiple Figures 3A to 3D The compressor blades are positioned in its insertion area.

[0033] Figure 6 An end-to-end configuration is shown. Figures 3A to 3D The two compressor blades.

[0034] Figure 7 This is a perspective view of a masking system based on some aspects of this disclosure.

[0035] Figures 8A to 8B Based on some aspects of this disclosure Figure 7 A perspective view of the first shielding element of the shielding system.

[0036] Figures 9A to 9B Based on some aspects of this disclosure Figure 7 A perspective view of the second shielding element of the shielding system.

[0037] Figure 9C Based on some aspects of this disclosure Figure 7 End view of the second masking element of the masking system.

[0038] Figure 10A This illustrates some aspects of maintaining in accordance with this disclosure. Figure 7 The receiving area of ​​the first shielding element of the shielding system Figures 3A to 3D A perspective view of the root of the compressor blades.

[0039] Figure 10B This illustrates some aspects of the arrangement according to this disclosure. Figure 7 The recessed area of ​​the first shielding element of the shielding system Figures 3A to 3D A side view of the protruding part of the compressor blade.

[0040] Figure 11 It shows Figure 7 The first and second shielding components of the shielding system are co-encapsulated. Figures 3A to 3D A perspective view of the root of the compressor blades.

[0041] Figure 12 It shows when Figures 3A to 3D When the roots of the compressor blades are encapsulated by a shielding system, they are fixed together. Figure 7 A perspective view of the first and second shielding elements of the shielding system.

[0042] Figure 13 This is a perspective view of another masking system based on some aspects of this disclosure.

[0043] Figures 14A to 14B Based on some aspects of this disclosure Figure 13 A perspective view of the first shielding element of the shielding system.

[0044] Figure 15 Based on some aspects of this disclosure Figure 13 A perspective view of the second shielding element of the shielding system.

[0045] Figure 16AThis illustrates some aspects of maintaining in accordance with this disclosure. Figure 13 The receiving area of ​​the first shielding element of the shielding system Figures 3A to 3D A perspective view of the root of the compressor blades.

[0046] Figure 16B This illustrates some aspects of the arrangement according to this disclosure. Figure 13 The recessed area of ​​the first shielding element of the shielding system Figures 3A to 3D A side view of the protruding part of the compressor blade.

[0047] Figure 17 This illustrates the common package. Figures 3A to 3D The root of the compressor blades Figure 13 A perspective view of the first and second shielding elements of the shielding system.

[0048] Figure 18 It shows when Figures 3A to 3D When the root of the compressor blades is encapsulated by a shielding system, Figure 13 A perspective view of the first and second shielding elements of a shielding system fixed to each other.

[0049] Figure 19 This is a perspective view of another masking system based on some aspects of this disclosure.

[0050] Figures 20A to 20B Based on some aspects of this disclosure Figure 19 A perspective view of the first shielding element of the shielding system.

[0051] Figures 21A to 21B Based on some aspects of this disclosure Figure 19 A perspective view of the second shielding element of the shielding system.

[0052] Figure 22 This illustrates some aspects according to this disclosure. Figure 19 A cross-sectional view of the interaction between the first and second shielding elements of the shielding system.

[0053] Figure 23A This illustrates some aspects of the disclosure, which are contained within Figure 19 The receiving area of ​​the first shielding element of the shielding system Figures 3A to 3D A perspective view of the root of the compressor blades.

[0054] Figure 23B This illustrates some aspects of the arrangement according to this disclosure. Figure 19 The recessed area of ​​the first shielding element of the shielding system Figures 3A to 3D A side view of the protruding part of the compressor blade.

[0055] Figure 24This illustrates some aspects of the common encapsulation according to this disclosure. Figures 3A to 3D The root of the compressor blades Figure 19 A perspective view of the first and second shielding elements of the shielding system.

[0056] Figure 25 This illustrates some aspects of the disclosure, when Figures 3A to 3D When the root of the compressor blades is encapsulated by a shielding system, Figure 19 A perspective view of the first and second shielding elements of a shielding system fixed to each other. Detailed Implementation

[0057] A gas turbine engine typically includes a multi-stage compressor coupled to a multi-stage turbine via an axial shaft. The multi-stage compressor may include a low-pressure compressor and a high-pressure compressor, and the multi-stage turbine may include a low-pressure turbine and a high-pressure turbine. Air enters the gas turbine engine through the low-pressure compressor, where its temperature and pressure increase as it passes through subsequent stages. The compressed air is then directed to one or more combustors, where it is mixed with a fuel source to produce a combustible mixture. This mixture is ignited in a combustion chamber, producing a hot combustion gas stream. These gases are then directed to the turbine, causing it to rotate and thus driving the compressor. The output of the gas turbine engine can be either mechanical thrust from the exhaust gas from the turbine or shaft power from the rotation of the axial shaft, which can drive a generator to produce electricity.

[0058] Compressors and turbines typically consist of multiple rotating blades and stationary impellers, with airfoils extending into the compressed air or hot combustion gas flow. Each blade or impeller has a specific set of design criteria that must be met to provide the necessary work to the airflow passing through the compressor and turbine. However, due to the harsh nature of the operating environment, especially in turbines, these blades and impellers often require cooling. Blades and impellers typically utilize complex internal cooling channels to maximize the efficiency of the cooling fluid passing through them.

[0059] Gas turbine engines typically also include a fan that can be positioned at the front of the engine. The fan may include a disk with multiple fan blades coupled to it. The fan can rotate to increase the amount of air flowing through the engine, thereby increasing the engine's thrust. The fan blades may be larger than the compressor blades and turbine blades.

[0060] Figure 1A gas turbine engine 1 is schematically shown. The gas turbine engine 1 typically 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 can flow into the gas turbine engine 1 in a direction A, which may be parallel to the longitudinal axis 22 of the gas turbine engine 1. The low-pressure compressor 12 and the low-pressure turbine 14 can be operatively connected via a low-pressure shaft 24 centered on the longitudinal axis 22. Similarly, the high-pressure compressor 16 and the high-pressure turbine 20 can be operatively connected via a high-pressure shaft 26 centered on the longitudinal axis 22. The high-pressure shaft 26 may be arranged around the low-pressure shaft 24. The gas turbine engine 1 may also include a fan 28, which may be housed in a fan shroud 30. The fan 28 may be positioned upstream of the low-pressure compressor 12 and may include a plurality of fan blades 40 rotating about the longitudinal axis 22. In some examples, the fan 28 is movably coupled to the low-pressure shaft 24 and driven by the low-pressure turbine 14.

[0061] Figure 2 Fan blade 40 is shown. Fan blade 40 can be... Figure 1 One of the multiple fan blades of fan 28, or one of the multiple fan blades of another gas turbine engine fan. Fan blade 40 includes an airfoil 42 having a pressure surface 44 (in...). Figure 2 (Not clearly visible in the middle) and suction surface 46. Pressure surface 44 and suction surface 46 each extend from the leading edge 48 of airfoil 42 to the trailing edge 50. Fan blade 40 may include dovetail tenon 52 at its lowest point. Dovetail tenon 52 may have a generally cedar shape.

[0062] Figures 3A to 3D An example compressor blade 60 is shown. Compressor blade 60 may be one of a plurality of blades in a low-pressure compressor 12, one of a plurality of blades in a high-pressure compressor 16, or (e.g., in another gas turbine engine) one of a plurality of blades in another low-pressure or high-pressure compressor. Compressor blade 60 may include an airfoil 62 having a suction surface 64 (see...). Figure 3A ) and the pressure surface 66 opposite to the suction surface 64 (see Figure 3B The suction surface 64 and the pressure surface 66 may each extend from the leading edge 68 to the trailing edge 70 of the airfoil 62.

[0063] The compressor blade 60 may include a root or dovetail (hereinafter referred to as "root 72") at its lowest part. The root 72 may have a first side 74 (see... Figure 3A ), second side 76 (see Figure 3B ), First end 78 (see Figure 3C ), second end 80 (see Figure 3D) and bottom side 82. Each of the first side 74, the second side 76, the first end 78 and the second end 80 may extend upward from the bottom side 82.

[0064] The first side 74 of the root 72 may extend generally laterally below the suction surface 64 of the airfoil 62. The second side 76 of the root 72 may be opposite the first side 74 and may extend generally laterally below the pressure surface 66 of the airfoil 62. The first end 78 of the root 72 may be below the leading edge 68 and extends generally longitudinally from the first side 74 of the root 72 to its second side 76. The second end 80 of the root 72 may be located below the trailing edge 70 and extends generally longitudinally from the first side 74 of the root 72 to its second side 76.

[0065] In some examples, the bottom side 82 may be generally flat, while each of the first side 74 and the second side 76 extending from it may be rounded (see [reference]). Figure 3C and Figure 3D For example, each of the first end 78 and the second end 80 of the root 72 may have a generally bulbous or truncated elliptical shape. In other examples, any one or more of the first side 74, the second side 76, the first end 78, the second end 80, and the bottom side 82 may be generally flat, round, or formed into other symmetrical or asymmetrical shapes.

[0066] Platform 83 (see) Figure 3C The airfoil 62 can be disposed between the airfoil 62 and the root 72. The airfoil 62 can extend above the platform 83, and the root 72 can extend below the platform 83. The platform 83 can have a first side 84 (see...). Figure 3A ), second side 86 (see Figure 3B ), first edge 88 (see Figure 3C ), second edge 90 (see Figure 3D ) and top edge 91 (see Figure 3A and Figure 5 The first side 84 of platform 83 may extend generally laterally above the first side 74 of root 72. The second side 86 of platform 83 may be opposite to its first side 84 and extend generally laterally above the second side 76 of root 72. The first edge 88 of platform 83 may extend generally longitudinally above the first end 78 of root 72, and the second edge 90 of platform 83 may extend generally longitudinally above the second end 80 of root 72. The top edge 91 of platform 83 may be opposite to the bottom side 82 of root 72. The airfoil 62 may extend from the top edge 91.

[0067] In some examples, the top edge 91 of platform 83 may have a width W1 (see...). Figure 5 Platform 83 may have a height H1 (see...) Figure 3BThe root 72 can have a height H2. The height H1 plus the height H2, that is, the combined height of the platform 83 and the root 72, can be equal to the height H3.

[0068] In some examples of the embodiments, the protrusion may protrude from one or more of the first side 74, the second side 76, the first end 78, and the second end 80 of the root 72 (and / or from other locations on the compressor blade 60). For example, the protrusion 92 may protrude from the second end 80 of the root 72 away from its first end 78. In some examples, such as Figure 3D As shown, the protrusion 92 may extend downward adjacent to the second edge 90 of the platform 83. In other examples, the protrusion 92 may extend from the platform 83 itself or from another portion of the compressor blade 60.

[0069] The protrusion 92 can be spherical, cylindrical, pyramidal, or other symmetrical or asymmetrical shapes. In the illustrated example, the protrusion 92 is asymmetrical and has a top surface 94T (see...). Figure 3A ), bottom surface 94B and outermost surface 94O (see Figure 3A and Figure 3D The outermost surface 94O may extend between the top surface 94T and the bottom surface 94B. In some examples, the top surface 94T may be curved.

[0070] In some examples, the first end 78 of the root 72 and the first edge 88 of the platform 83 may be planar. Similarly, in some examples, the second end 80 of the root 72 (ignoring the protrusion 92) and the second edge 90 of the platform 83 may be planar. In some examples, the first end 78 and / or the second end 80 may extend upward parallel to the vertical plane. In other examples, the first end 78 and / or the second end 80 may extend upward at an angle.

[0071] The hot gas path within a gas turbine engine, such as gas turbine engine 1, can be both thermally and chemically unfavorable. High-temperature performance of gas turbine components has been improved through the development of iron-based, nickel-based, and cobalt-based superalloys. The ability of gas turbine components to withstand the thermally and chemically unfavorable environment of the hot gas path within gas turbine engine 1 can also be improved by using anti-oxidation environmental coatings that protect these components from oxidation and corrosion. As an example, aluminum-containing coatings, such as diffused aluminate coatings, can be used as environmental coatings on gas turbine components. During high-temperature exposure in air, aluminum-containing coatings can form a protective alumina (alumina) scale or layer, inhibiting corrosion and oxidation of the coating and the underlying substrate. As another example, thermal barrier coatings, such as ceramic coatings, can be applied to gas turbine components to insulate these components within the hot gas path.

[0072] It may be desirable to selectively apply one or more coatings, such as environmental barrier coatings, thermal barrier coatings, etc., to gas turbine components, for example, only to those portions of the gas turbine components exposed to extremely high temperatures associated with the hot gas path of the gas turbine engine 1. For example, it may be desirable to apply a coating to the compressor blade 60 such that only the airfoil 62 and the top edge 91 of the platform 83 are coated; that is, it may be desirable to ensure that the coating does not affect the root 72 and does not affect each of the first side 84, the second side 86, the first edge 88, and the second edge 90 of the platform 83. If an environmental barrier coating, thermal barrier coating, and / or other coatings are unintentionally applied, for example, to the root 72, and / or to any of the first side 84, the second side 86, the first edge 88, and the second edge 90 of the platform 83, the coating will add unnecessary weight to the compressor blade 60 and adversely interfere with the coupling of the compressor blade 60 to the hub. Therefore, it may be necessary to remove any coatings unintentionally applied to these surfaces, for example, by laboriously using sanding, blasting, or other processes. In some cases, compressor blade 60 may need to be scrapped due to the unintentional application of a diffused aluminate coating to the root 72 and / or the first side 84, second side 86, first edge 88, or second edge 90 of platform 83. If the coating is applied to any of these surfaces, it adds unnecessary weight to the compressor blade 60 and adversely interferes with the connection between the compressor blade 60 and the hub. Therefore, it may be necessary to remove any coating unintentionally applied to these surfaces, for example, through laborious sanding, blasting, or other processes. In some cases, compressor blade 60 may need to be scrapped due to the unintentional application of a coating to the root 72 and / or the first side 84, second side 86, first edge 88, or second edge 90 of platform 83.

[0073] Figure 4 A masking device 100 is shown for selectively masking a component to be coated. For example, the masking device 100 can be used to selectively mask one or more surfaces of a gas turbine engine component, such as one or more surfaces of a compressor blade, fan blade, turbine blade, etc. For example, the masking device 100 can be used to coat the airfoil of a blade without affecting its root.

[0074] In some examples of embodiments, the masking device 100 includes a housing 102 for supportively holding a plurality of blades to be selectively coated. The housing 102 may include a first member 104 and a second member 106, each extending laterally along the length of the housing 102. The first member 104 may have a top side 104T, and the second member may have a top side 106T. The top sides 104T of the first member 104 and 106T of the second member 106 may be spaced apart from each other and define a cavity or insertion region (hereinafter referred to as "insertion region 108") therebetween. The insertion region 108 may have a width W2 (see...). Figure 4 The housing 102 may have a height H9, which in this example may also be the height of the insertion region 108. The insertion region 108 may be configured to insertably receive one or more portions of a component to be selectively coated. For example, in the case of a blade, the root of the blade may be inserted into the insertion region 108 such that the airfoil of the blade extends above the housing 102. The blade may then be selectively coated, for example, with a diffused aluminate coating and / or another coating, while the root of the blade is received within the insertion region 108. As an example, a masking device 100, in which the blade root is received within the insertion region 108, may be coated with a diffused aluminate coating. The masking device 100 may mask the blade root and prevent the deposition of diffused aluminate or other coatings on the root.

[0075] Using the masking device 100 to selectively apply diffused aluminate or other coatings to multiple components, such as multiple blades, simultaneously may be more cost-effective and efficient. Therefore, the insertion region 108 can be configured to insertably receive the roots of multiple blades. The masking device 100 allows the airfoil of these blades to be coated while the roots of the blades are masked and unaffected by the coating.

[0076] Figure 5 The illustration shows the roots 72 of three compressor blades 60 insertably accommodated within an insertion region 108 of a masking device 100, such that each of the three compressor blades 60 can be selectively coated simultaneously, for example, with a diffused aluminide coating and / or another coating. In the illustrated example, it is desirable to selectively coat each compressor blade 60 such that only the airfoil 62 and the top edge 91 of the platform 83 of each compressor blade 60 are coated (e.g., because the airfoil 62 and the top edge 91 of the platform 83 of each compressor blade 60 are in the hot gas path of the gas turbine engine 1). That is, it may be desirable to mask the roots 72 of each compressor blade 60 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 to ensure that these portions of the compressor blade 60 are uncoated or minimally affected.

[0077] like Figure 5 As shown, the roots 72 of three compressor blades 60 are arranged side-by-side in the insertion area 108 of the shielding device 100. When the compressor blades 60 are arranged in this way, the second end 80 of the root 72 of one compressor blade 60 (see...) Figure 3A The first end 78 of the root 72 facing the adjacent compressor blade 60 (see) Figure 3A More specifically, such as Figure 6 As shown more clearly in the diagram, when the compressor blades 60 are arranged side by side, for example in the insertion region 108 (see... Figure 5 In the root 72, the protrusion 92 extends from the second end 80, and more specifically, the outermost surface 94O of the protrusion 92 (see...) Figure 3A The protrusion 92 contacts and abuts the first end 78 of the root 72 of the adjacent compressor blade 60. The protrusion 92 prevents the platforms 83 of the adjacent compressor blades 60 from contacting each other and results in the first edge 88 of the platform 83 of one compressor blade 60 (see also) Figure 3C ) and the second edge 90 of the platform 83 of the adjacent compressor blade 60 (see also Figure 3D A gap 110 is formed between them (see) Figure 5 The gap 110 may adversely interfere with the selective coating of the compressor blades 60. That is, if... Figure 5 If the three compressor blades 60 positioned in the shielding device 100 are coated, at least some of the coating (e.g., a diffused aluminate coating and / or another coating) may penetrate the gap 110, resulting in undesirable application of coating to one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the root 72 and / or platform 83 of each compressor blade 60. The coating on one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the root 72 and / or platform 83 of each compressor blade 60 must then be painstakingly removed, which may be undesirable. In some cases, one or more compressor blades 60 must be scrapped. It may be desirable to ensure that coating is excluded or at least minimized on one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the root 72 and / or platform 83 of each compressor blade 60.

[0078] Figure 7A masking system 200 according to one aspect of this disclosure is illustrated. The masking system 200 can be configured to retain and selectively mask a component, such as a compressor blade 60 or another component. In the illustrated example, the masking system 200 can be configured to retain and selectively mask the compressor blade 60 during coating, such that only the airfoil 62 and the top edge 91 of the platform 83 of the compressor blade 60 are coated. Only the airfoil 62 and the top edge 91 of the platform 83 may need to be coated because only the airfoil 62 and the top edge 91 of the platform 83 of each compressor blade 60 may be in the hot gas path of the gas turbine engine 1. That is, the masking system 200 can mask the root 72 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 of the compressor blade 60 to ensure that these portions of the compressor blade 60 are not coated, or are only minimally affected by the coating. The coating may be an environmental barrier coating, a thermal barrier coating, or another type of coating.

[0079] The masking system 200 may be a multi-component system. In some examples of embodiments, the masking system 200 may include a first mask 210 (see [link to embodiment]). Figures 8A to 8B ) and second shield 250 (see Figures 9A to 9B The first masking member 210 and the second masking member 250 may be fixed to each other or otherwise associated with each other. In some examples, the compressor blade 60, such as its root 72, may be insertably received by the first masking member 210. The first masking member 210 may partially or completely mask the root 72 of the compressor blade 60 and one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83. The second masking member 250 may then be fixed to the first masking member 210 while the compressor blade 60 remains within the first masking member 210. The second masking member 250 may cooperate with the first masking member 210 to selectively mask the compressor blade 60 such that the root 72 of the compressor blade 60 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 are substantially entirely masked. While the compressor blade 60 is held within the masking system 200, the compressor blade 60 may then be coated. The masking system 200 can exclude or at least minimize the application of coatings (e.g., an aluminide diffusion coating or another coating) on ​​one or more of the first side 84, second side 86, first edge 88 and second edge 90 of the root 72 and / or platform 83 of the compressor blade 60.

[0080] In some examples of the embodiments, the first mask 210 of the masking system 200 (see Figures 8A to 8BThe first mask 210 may include a first part 212 and a second part 230. The first mask 210 may have an integral structure (i.e., in some examples, the first part 212 and the second part 230 may have a single or monolithic structure).

[0081] The first portion 212 can typically be formed in the shape of a rectangular prism. In other examples, the first masking element 210 can be pyramidal, spherical, or formed in other symmetrical or asymmetrical shapes. In some examples, the first portion 212 can have a top wall 214, a bottom wall 216, a first side wall 218, a second side wall 220, a front wall 222, and a back wall 224 (the bottom wall 216 and the back wall 224 are in...). Figures 8A to 8B (Not clearly visible in the middle). The top wall 214 may be opposite the bottom wall 216, the first side wall 218 may be opposite the second side wall 220, and the front wall 222 may be opposite the back wall 224. The first side wall 218 and the second side wall 220 may have the same height H4, and the top wall 214 and the bottom wall 216 may have the same width W4.

[0082] In some examples, the front wall 222 may include a recessed region 226. The recessed region 226 may have a depth D5. The width W4 of the top wall 214 may be greater than the depth D5 of the recessed region 226. That is, the recessed region 226 may not extend all the way through the first portion 212. For example, the recessed region 226 may have a rear wall 228 that extends generally parallel to and is spaced apart from the front wall 222. The rear wall 228 may prevent access to the recessed region 226 from the back wall 224 of the first portion 212. In some examples, the recessed region 226 may be configured (e.g., sized) as part of a receiving component. For example, the recessed region 226 may be configured to receive a protrusion 92 of a compressor blade 60.

[0083] The second part 230 may include a first component 232, a second component 234, and a third component 236. In some examples, each of the first component 232, the second component 234, and the third component 236 may be generally cubic. In other examples, any one or more of the first component 232, the second component 234, and the third component 236 may be spherical, cylindrical, pyramidal, or formed into other symmetrical or asymmetrical shapes.

[0084] The first member 232 and the second member 234 may be spaced apart from each other. One end of each of the first member 232 and the second member 234 may extend laterally from the front wall 222 of the first part 212. The third member 236 may extend longitudinally between the first member 232 and the second member 234 from the other end of each of the first member 232 and the second member 234. Therefore, in some examples, the first member 232, the second member 234 and the third member 236 may together form a square U-shape.

[0085] The first component 232 may have a height H6. In some examples, the second component 234 and the third component 236 may have the same height H6. In other examples, one or more of the first component 232, the second component 234, and the third component 236 may have different heights. The height H6 may be less than the height H4 of the first sidewall 218 of the first portion 212. That is, the first portion 212 may extend above the second portion 230.

[0086] Each of the first component 232, the second component 234, and the third component 236 may have its own top surface 232T, 234T, and 236T. In some examples, because each of the first component 232, the second component 234, and the third component 236 has the same height H6, the top surfaces 232T, 234T, and 236T may each extend in the same or substantially the same horizontal plane.

[0087] In some examples, one or more openings 238A may extend through one or more of the top surfaces 232T, 234T, and 236T. For example, opening 238A may extend through the top surface 232T of the first member 232 near the first portion 212, and another opening 238A may extend through the top surface 232T of the first member 232 near the third member 236. Similarly, opening 238A may extend through the top surface 234T of the second member 234 near the first portion 212, and another opening 238A may extend through the top surface 234T of the second member 234 near the third member 236. In some examples, opening 238A may not extend all the way through the respective first member 232, second member 234, or third member 236.

[0088] Each of the first member 232, the second member 234, and the third member 236 may have corresponding (internal) side surfaces 232S, 234S, and 236S. The side surface 232S of the first member 232 may face the side surface 234S of the second member 234, and the side surface 236S of the third member 236 may face the front wall 222 of the first portion 212. A lower wall 240 may extend continuously between the side surfaces 232S, 234S, 236S, and the front wall 222. The lower wall 240 may extend substantially parallel to and spaced apart from each of the top surfaces 232T of the first member 232, 234T of the second member 234, and 236T of the third member 236.

[0089] The front wall 222 of the first portion 212, the side surface 232S of the first member 232, the side surface 234S of the second member 234, the side surface 236S of the third member 236, and the lower wall 240 may collectively define a receiving region 242. As described herein, the receiving region 242 may be configured to receive part of an insertably received component, such as the root 72 of a compressor blade 60.

[0090] exist Figures 9A to 9B The second mask 250, shown in more detail, may include a first portion 252, a second portion 254, and a third portion 256. In some examples, the first portion 252, the second portion 254, and the third portion 256 may each be cubic or substantially cubic, and each may have a height H7. The first portion 252 and the second portion 254 may extend parallel to each other, and may have a gap 258 between them. The third portion 256 may extend longitudinally between the first portion 252 and the second portion 254, and close the gap 258 on one side. The gap 258 may be open at opposite ends. Thus, the second mask 250 may have a substantially square shape. In other examples, the second mask 250 may be formed as a sphere, a cylinder, or other symmetrical or asymmetrical shape.

[0091] In some examples, the first portion 252 of the second masking member 250 may have a cutout 252C extending along the length of the first portion 252 (see also...). Figure 9C The second portion 254 of the second shield 250 may also have a cutout 254C extending along the length of the second portion 254. Cutouts 252C and 254C may face each other. As described herein, cutouts 252C and 254C may facilitate correspondence between the first shield 210 and the second shield 250 when a component, such as a compressor blade 60, is held within the receiving area 242 of the first shield 210.

[0092] In some examples, one or more openings 238B may extend through one or more of the first portion 252, the second portion 254, and the third portion 256 of the second mask 250. For example, two openings 238B may extend through the first portion 252, and two openings 238B may extend through the second portion 254. The second mask 250 of the masking system 200 may be configured to be secured to its first mask 210. When the second mask 250 is aligned with the first mask 210 for securing, each opening 238B in the second mask 250 may correspond to one opening 238A in the first mask 210, as described herein. Fasteners or other means may then be passed through each set of openings 238A and 238B to secure the first mask 210 to the second mask 250.

[0093] Figure 10AThe receiving area 242, which is insertedably received or otherwise disposed in the first shield 210 at its root 72, is shown (see Figures 8A to 8B The component following the ) in this example is the compressor blade 60. The root 72 may be disposed within the receiving region 242, such that the second end 80 of the root 72 of the compressor blade 60 (see...) Figure 3D The first end 78 of the root 72 is spaced apart from the front wall 222 of the first shield 210. When configured in this way, the protrusion 92 of the compressor blade 60 is received within the recessed area 226 of the first shield 210 (see...). Figure 10B ).

[0094] Then, the second masking member 250 can slide on the first masking member 210 such that one end of each of the first portion 252 and the second portion 254 of the second masking member 250 abuts against the front wall 222 of the first masking member 210, and the third portion 256 of the second masking member 250 is spaced apart from the front wall 222 of the first masking member 210 (see...). Figure 11 The airfoil 62 is located on top of the third member 236 of the first shield 210 and generally corresponds to the third member 236 of the first shield 210. When arranged in this way, the airfoil 62 can extend through the gap 258 in the second shield 250. The cutout 252C in the second shield 250 (see...) Figure 9B The cutout 254C ensures that the root 72 and platform 83 do not interfere with the second mask 250 when it slides on the first mask 210. In some examples, the height H6 (see...) Figure 8A ) and height H7 (see Figure 9A The sum of ) can equal height H4 (see Figure 8A That is, the sum of the height H6 of the first member 232 of the first masking member 210 and the height H7 of the first portion 252 of the second masking member 250 can be equal to the height H4 of the first portion 212. Therefore, as described herein, when the second masking member 250 slides on the first masking member 210, the top wall 214 of the first masking member 210 and the uppermost surfaces of the first portion 252, the second portion 254 and the third portion 256 of the second masking member 250 can extend on the same or substantially the same horizontal plane.

[0095] Furthermore, when the second mask 250 slides over or is otherwise positioned on the first mask 210, each opening 238A in the first mask 210 can correspond to and align with one opening 238B in the second mask 250. Fastener 270 (see...) Figure 12The fastener 270 can pass through each set of openings 238A and 238B to securely fasten the first shield 210 to the second shield 250, while the root 72 of the compressor blade 60 remains within the receiving area 242 of the first shield 210. The fastener 270 can be a wing nut, cable tie, or any other suitable means for fastening the first shield 210 to the second shield 250.

[0096] In this configuration, each of the root 72 of the compressor blade 60 and the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 of the compressor blade 60 (see...) Figures 3A to 3D The first mask 210 and the second mask 250 can be co-encapsulated by the first mask 210 and the second mask 250. Therefore, the first mask 210 and the second mask 250 of the masking system 200 can jointly and selectively mask the compressor blade 60. Specifically, the first mask 210 and the second mask 250 can jointly mask each of the root 72 of the compressor blade 60 and the first side 84, the second side 86, the first edge 88, and the second edge 90 of the platform 83 (see...). Figures 3A to 3D This exposes only the airfoil 62 and top edge 91 of platform 83. The compressor blade 60 can then be coated while it remains within the masking system 200. The masking system 200 ensures that the coating does not affect any part of the compressor blade 60 other than the airfoil 62 and the top edge 91 of platform 83, or at least minimizes any impact on other parts of the compressor blade 60.

[0097] Once the coating process is complete, fastener 270 can be loosened to detach the first mask 210 from the second mask 250, and the second mask 250 can be slidably separated from the first mask 210 or otherwise detached. The selectively coated compressor blade 60 can then be removed from the receiving area 242. In some examples, the masking system 200 may be reusable and may be used to selectively mask another component (e.g., another compressor blade 60) for coating.

[0098] Figure 13A masking system 300 according to one aspect of this disclosure is shown. The masking system 300 can be configured to retain and selectively mask a component, such as a compressor blade 60 or another component. In the illustrated example, the masking system 300 can be configured to retain and selectively mask the compressor blade 60 during coating, such that only the airfoil 62 and the top edge 91 of the platform 83 of the compressor blade 60 are coated. Only the airfoil 62 and the top edge 91 of the platform 83 may need to be coated because only the airfoil 62 and the top edge 91 of the platform 83 of each compressor blade 60 may be in the hot gas path of the gas turbine engine 1. That is, the masking system 300 can mask the root 72 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 of the compressor blade 60 to ensure that these portions of the compressor blade 60 are not coated, or are only minimally affected by the coating. The coating may be an environmental barrier coating, a thermal barrier coating, or another type of coating.

[0099] Like masking system 200, masking system 300 can be a multi-component system. In some examples of embodiments, masking system 300 may include a first masking element 310 (see...). Figures 14A to 14B ) and second shield 350 (see Figure 15 The first masking member 310 and the second masking member 350 may be fixed to each other or otherwise associated with each other. In some examples, the compressor blade 60, such as its root 72, is slidably accommodated within the first masking member 310. The first masking member 310 may partially or completely mask the root 72 of the compressor blade 60 and one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83. The second masking member 350 may then be fixed to the first masking member 310 while the compressor blade 60 (e.g., its root 72) remains within the first masking member 310. The second masking member 350 may cooperate with the first masking member 310 to selectively mask the compressor blade 60 such that the root 72 of the compressor blade 60 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 are substantially entirely masked. While the compressor blade 60 is held within the masking system 300, the compressor blade 60 may then be coated. The masking system 300 can exclude or at least minimize the application of coatings (e.g., an aluminide diffusion coating or another coating) on ​​one or more of the first side 84, second side 86, first edge 88 and second edge 90 of the root 72 and / or platform 83 of the compressor blade 60.

[0100] The first shielding element 310 of the shielding system 300 Figures 14A to 14BThe first mask 310 may include a first portion 312, a second portion 314, and a third portion 316. In some examples, the first mask 310 may be a single piece. The first portion 312 and the second portion 314 may extend generally laterally parallel and spaced apart from each other. The third portion 316 may extend longitudinally between the first portion 312 and the second portion 314 at one end of its respective end.

[0101] The first shield 310 may have a receiving region 320. In some examples, the receiving region 320 may be formed at least partially by a second portion 314 and a third portion 316, specifically by their inner surfaces. The receiving region 320 may have a generally spherical bottom region 322 and a generally cubic top region 324, each region being open from at least one end. The spherical shape of the bottom region 322 may generally correspond to the shape of the root 72 of the compressor blade 60. The generally cubic shape of the top region 324 may generally correspond to the shape of the platform 83 of the compressor blade 60. As described herein, the receiving region 320 may be configured to slidably receive the root 72 of the compressor blade 60.

[0102] A recessed region 330 may be formed within the third portion 316. The recessed region 330 can be accessed through and adjacent to the receiving region 320. In some examples, the recessed region 330 may be configured to receive a protrusion 92 of the compressor blade 60. The rear portion of the recessed region 330 may be closed by a rear wall 331 that extends substantially vertically and is spaced apart from the receiving region 320.

[0103] A first portion 312 of the first masking member 310 may include a front surface 312F, and a second portion 314 of the first masking member 310 may include a front surface 314F. These front surfaces 312F and 314F may extend substantially perpendicularly to and parallel to the rear wall 331. One or more openings 332A may be provided in each of the front surfaces 312F and 314F. The length of the openings 332A may be less than the length of the receiving area 320; that is, the openings 332A and 332B may not extend continuously through the first masking member 310.

[0104] Second cover element 350 (see Figure 15The first mask 310 can typically be formed in a cuboid shape and can have an integral structure. In some examples, the height of the second mask 350 can be the same as the height of the first mask 310. The second mask 350 can have one or more openings 332B extending through it. When the second mask 350 is disposed adjacent to and in contact with the first mask 310, each opening 332A in the first mask 310 can correspond to one opening 332B in the second mask 350. Fasteners or other devices can then pass through each set of openings 332A and 332B to secure the first mask 310 to the second mask 350.

[0105] focus on Figures 16A to 16B This illustrates a compressor blade 60 after its root 72 has been slidably inserted into the receiving area 320 of the first shield 310. Specifically, the root 72 of the compressor blade 60 can be positioned adjacent to the receiving area 320, such that the second end 80 of the root 72 (see...) Figure 3B The rear wall 331 faces the recessed region 330. Then, the root 72 can slide generally laterally into the receiving region 320, such that the second end 80 of the root 72 approaches (e.g., abuts) the recessed region 330. Figure 16B As shown, when constructed in this manner, the protrusion 92 of the compressor blade 60 can enter and be accommodated in the recessed region 330. The airfoil 62 can extend above the top region 324 of the receiving region 320.

[0106] like Figure 17 As shown, the second masking member 350 of the masking system 300 can be configured adjacent to and in contact with the first masking member 310, such that each opening 332A in the first masking member 310 is aligned with one opening 332B in the second masking member 350. The second masking member 350 can effectively close the receiving area 320, such that the first end 78 of the root 72 and the first edge 88 of the platform 83 are covered. The first masking member 310 and the second masking member 350 can now jointly and selectively mask the compressor blade 60, such that only the airfoil 62 of the compressor blade 60 and the top edge 91 of the platform 83 are exposed. That is, the masking system 300 can mask the root 72 and each of the first side 84, the second side 86, the first edge 88, and the second edge 90 of the platform 83 of the compressor blade 60.

[0107] like Figure 18As shown, the second mask 350 can be fastened to the first mask 310 by fasteners 370, while the root 72 is held within the receiving area 320 and the protrusion 92 is received within the recessed area 330. Specifically, the fasteners 370 can pass through each set of openings 332A and 332B to secure the first mask 310 to the second mask 350. Like the fasteners 270 of the masking system 200, each fastener 370 of the masking system 300 can be a wing nut, cable tie, or any other suitable means for fastening the first mask 310 to the second mask 350.

[0108] The compressor blade 60 can now be selectively coated, with the root 72 positioned within the receiving area 320 and the protrusion 92 retained within the recessed area 330. The masking system 300 can exclude or at least minimize coating of the root 72 of the compressor blade 60, as well as any of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83. Once coating is complete, the fastener 370 can be released to detach the first mask 310 from the second mask 350, and the root 72 can slide out of the receiving area 320 to detach the compressor blade 60 from the first mask 310. In some examples, the masking system 300 can be reusable and can be used to selectively mask another component (e.g., another compressor blade 60) for coating.

[0109] focus on Figure 19 The illustration shows a masking system 400 according to one aspect of this disclosure. The masking system 400 can be configured to retain and selectively mask a component, such as a compressor blade 60 or another component. In the illustrated example, the masking system 400 can be configured to retain and selectively mask the compressor blade 60 during coating, such that only the airfoil 62 of the compressor blade 60 and the top edge 91 of the platform 83 are coated. That is, the masking system 400 can mask the root 72 of the compressor blade 60 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 to ensure that these portions of the compressor blade 60 are not coated, or are only minimally affected by the coating. The coating can be an environmental barrier coating, a thermal barrier coating, or another type of coating.

[0110] Like masking systems 200 and 300, masking system 400 can be a multi-component masking system. In some examples of embodiments, masking system 400 may include a first masking element 410 (see...). Figures 20A to 20B ) and second shield 450 (see Figures 21A to 21BThe first masking member 410 and the second masking member 450 may be fixed to each other, or may be coupled or cooperate with each other. In some examples, the compressor blade 60, such as its root 72, may be received within the receiving area of ​​the first masking member 410. The first masking member 410 may partially or completely mask the root 72 of the compressor blade 60 and one or more of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83. The second masking member 450 may then be fixed to the first masking member 410 while the compressor blade 60 remains within the receiving area 444 of the first masking member 410. The second masking member 450 may cooperate with the first masking member 410 to selectively mask the compressor blade 60 such that the root 72 of the compressor blade 60 and each of the first side 84, second side 86, first edge 88, and second edge 90 of the platform 83 are substantially entirely masked. While the compressor blade 60 is held within the masking system 400, the compressor blade 60 may then be coated. The masking system 400 can exclude or at least minimize the application of coatings (e.g., an aluminide diffusion coating or another coating) on ​​one or more of the root 72 and / or platform 83 of the compressor blade 60 and / or platform 83, including the first side 84, the second side 86, the first edge 88 and the second edge 90.

[0111] Notice Figures 20A to 20B The first masking element 410 may include a first portion 412 and a second portion 414. In some examples, the first masking element 410 may be a monolithic structure.

[0112] In some examples, the first portion 412 may be formed as a cuboid. In other examples, the first portion 412 may be spherical, cylindrical, pyramidal, or formed as other symmetrical or asymmetrical shapes. The first portion 412 may have a front wall 415 and a top wall 416. In some examples, the first portion 412 may include a recessed region 418. The recessed region 418 may extend from the front wall 415 to a rear wall 420, which is spaced apart from and extends parallel to the front wall 415. The recessed region 418 may be configured to receive a protrusion 92 of the compressor blade 60.

[0113] The second portion 414 may extend substantially perpendicularly from the front wall 415 of the first portion 412. The second portion 414 may include a rear wall 417 (see...). Figure 20BThe second portion 414 may include a first step structure 422 and a second step structure 432, each step structure extending vertically from the front wall 415 of the first portion 412. The first step structure 422 may include a vertical plate 424 and a lower support member 426. The vertical plate 424 may extend generally vertically, and the lower support member 426 may extend generally vertically from the vertical plate 424 to give the first step structure 422 a generally stepped shape. In some examples, the vertical plate 424 may include one or more openings 428A extending through or partially through the second portion 414.

[0114] The second-step structure 432 may have a vertical plate 434 and an upper support member 436. The vertical plate 434 may extend substantially vertically from the lower support member 426, and the upper support member 436 may extend substantially vertically from the vertical plate 434. Therefore, the lower support member 426 and the upper support member 436 may be spaced apart and may extend parallel to each other, and the vertical plate 424 and the vertical plate 434 may be spaced apart and may extend parallel to each other and parallel to the rear wall 417.

[0115] The second portion 414 may have a top wall 438. The top wall 438 of the second portion 414 and the top wall 416 of the first portion 412 may extend in the same horizontal plane. A side wall 442 may extend substantially vertically from the upper support 436 to the top wall 438. The top wall 438, the side wall 442, and the upper support 436 may together define a receiving region 444. As described herein, the receiving region 444 may be configured to receive a compressor blade 60, specifically its root 72.

[0116] In some examples, the second mask 450 may have an integral structure. The second mask 450 (see...) Figures 21A to 21B It may have a first part 452 and a second part 454. In some examples, the first part 452 may be formed as a cuboid. In other examples, the first part 452 may be spherical, cylindrical, pyramidal, or formed as other symmetrical or asymmetrical shapes. The first part 452 may have a front wall 455 and a top wall 456.

[0117] The second portion 454 may extend substantially vertically from the front wall 455 of the first portion 452. The second portion 454 may include a substantially vertically extending rear wall 457 (see...). Figure 21B ) and the top wall 458, which extends generally vertically from the rear wall 457.

[0118] The second part 454 may have a first sidewall 460 and a second sidewall 462, each of which may extend generally vertically and may be spaced apart from each other. The first sidewall 460 may have one or more openings 428B extending from the first sidewall 460 to the rear wall 457. That is, the openings 428B may extend through the second shield 450. A shelf 464 may be disposed above the first sidewall 460. The shelf 464 may extend generally horizontally from the second sidewall 462 beyond the first sidewall 460.

[0119] The first shield 410 and the second shield 450 can be complementary and can be configured to be fixed to each other. Specifically, as shown in the figure... Figure 22 As shown, the first masking member 410 and the second masking member 450 can be configured such that the upright plate 424 of the first masking member 410 faces and contacts the first sidewall 460 of the second masking member 450. When configured in this way, the surface of the shelf 464 of the second masking member 450 can rest on top of the lower support 426 of the first masking member 410 and abut against the upright plate 434, and each of the upper support 436 of the first masking member 410 and the uppermost surface of the shelf 464 of the second masking member 450 generally extends continuously in the same horizontal plane. When the first masking member 410 and the second masking member 450 are arranged in this way, each opening 428A in the first masking member 410 can correspond to and align with one opening 428B in the second masking member 450.

[0120] Gap 466 (see) Figure 22 The gap 466 can be defined by both the first mask 410 and the second mask 450. Specifically, the top wall 438 of the second portion 414 of the first mask 410 and the top wall 458 of the second portion 454 of the second mask 450 can define the lateral boundary of the gap 466 (see [link]). Figure 22 The longitudinal boundary of the gap 466 can be defined by the top wall 416 of the first portion 412 of the first mask 410 and the top wall 456 of the first portion 452 of the second mask 450. The gap 466 is sized to accommodate the platform 83 such that only its top edge 91 is exposed (see...). Figure 24 ).

[0121] The shielding system 400, namely the first shielding element 410 and the second shielding element 450, can be used together to retain and selectively shield the compressor blades 60. For example, as Figure 23AAs shown, the compressor blade 60, especially its root 72, can be disposed in the receiving area 444 such that the bottom side 82 of the root 72 of the compressor blade 60 rests on top of the upper support 436 of the first shield 410. In this configuration, the top edge 91 of the platform 83 of the compressor blade 60 can be aligned with the top wall 438 of the first shield 410 and extend in the same horizontal plane, and the bottom side 82 of the root 72 can be spaced apart from the lower support 426 and extend above the lower support 426.

[0122] like Figure 23B As shown, when the base 72 of the compressor blade 60 is positioned on the upper support 436 in this manner (see...) Figure 21A The protrusion 92 of the compressor blade 60 can extend into and be located within the recessed region 418 of the first shield 410. Therefore, despite the protrusion 92, the second end 80 of the root 72 (see...) Figure 3D It can abut against the front wall 415 of the first shield 410. The width of the bottom side 82 of the root 72 can be greater than the width of the upper support 436, so that a part of the root 72 can extend out of the upper support 436.

[0123] Although the root 72 of the compressor blade 60 is located within the receiving area 444 of the first shield 410, such as Figure 23A As shown, the second mask 450 can be aligned with the first mask 410. Specifically, as referenced above... Figure 22 As discussed, the second shield 450 can be arranged such that the shelf 464 of the second shield 450 is located on top of the lower support 426 of the first shield 410. Therefore, the bottom side 82 of the root 72 of the compressor blade 60 can be supported by each of the upper support 436 of the first shield 410 and the shelf 464 of the second shield 450. The top edge 91 of the platform 83 can close (e.g., completely or partially) the gap 466 (see...). Figure 22 The top edge 91 of platform 83 can typically extend on the same horizontal plane as each of the top wall 416 of the first portion 412 of the first shield 410, the top wall 438 of the second portion 414 of the first shield 410, the top wall 456 of the first portion 412 of the second shield 450, and the top wall 458 of the second portion 454 of the second shield 450. The airfoil 62 can extend above the gap 466.

[0124] As described above, when the first mask 410 and the second mask 450 are aligned with each other, each opening 428A in the first mask 410 can correspond to and align with one opening 428B in the second mask 450. Fastener 470 (see...) Figure 25The fastener 470 can pass through each set of openings 428A and 428B to securely fasten the first shield 410 to the second shield 450, while the root 72 of the compressor blade 60 remains within the shielding system 400. The fastener 470 can be a wing nut, cable tie, or any other suitable means for fastening the first shield 410 to the second shield 450.

[0125] After the first masking member 410 and the second masking member 450 are secured to each other, the compressor blade 60 can be coated while it is held within the masking system 400. The top edge 91 and airfoil 62 of the platform 83 can be exposed and receive the coating as needed. The root 72 of the compressor blade 60 and each of the first side 84, second side 86, first edge 88 and second edge 90 of the platform 83 can be masked by the masking system 400 and can be unaffected by the coating or only minimally affected by the coating.

[0126] Once coating is complete, fastener 470 can be loosened to detach the first mask 410 from the second mask 450. The compressor blade 60, particularly its root 72, can be separated from the masking system 400. In some examples, the masking system 400 can be reusable and can be used to selectively mask another component (e.g., another compressor blade 60) for coating.

[0127] The masking systems disclosed herein, such as each of masking system 200, masking system 300, and masking system 400, can be manufactured using a variety of processes and from a variety of materials (e.g., metals, polymers, etc.). In some examples of the embodiments, one or more components of masking system 200, masking system 300, and / or masking system 400 can be manufactured using conventional processing and assembly techniques. In other examples of the embodiments, one or more components of masking system 200, masking system 300, and / or masking system 400 can be constructed using suitable additive manufacturing or additive printing techniques. Several known additive printing methods exist, such as material extrusion, material jetting, binder jetting, sheet lamination, cell polymerization, powder bed melting, directional energy deposition (DED), etc. Any one or more of these methods, or any other additive manufacturing method now known or developed hereafter, can be used to manufacture one or more components of masking system 200, masking system 300, and / or masking system 400. In some examples, the first mask 210 of the masking system 200 may be additionally manufactured as a single piece, and the second mask 250 of the masking system 200 may be additionally manufactured as a single piece. Similarly, each of the first mask 310 and the second mask 350 of the masking system 300 may be additionally manufactured as a single piece; and each of the first mask 410 and the second mask 450 of the masking system 400 may be additionally manufactured as a single piece.

[0128] In some examples, one or more components of masking system 200, masking system 300, and / or masking system 400 may be manufactured using the same or a variety of materials (e.g., metals or metal alloys) used to manufacture compressor blades 60. For example, where compressor blades 60 are primarily made of stainless steel (e.g., grade 316 or another grade), masking system 200, masking system 300, and / or masking system 400 may also be manufactured using stainless steel (e.g., additive manufacturing). In other examples, one or more components of masking system 200, masking system 300, and masking system 400 may be made using another one or more suitable materials, such as metals, metal alloys, plastics, thermoplastics, composites, or any other suitable material (e.g., any suitable material that can be attached for printing). In high-temperature coating applications, masking system 200, masking system 300, and masking system 400 may be made using materials capable of withstanding the temperatures encountered during the coating process.

[0129] While the above disclosures have generally referred to the use of masking systems 200, 300, and 400 in coating applications, these masking systems can also be used to selectively mask compressor blades 60 in other applications where it is desirable to selectively impact only a portion of the compressor blades 60 during processes such as shot peening, sandblasting, media blasting, etc. Furthermore, while the above disclosures have generally referred to compressor blades 60 in masking systems 200, 300, and 400, the masking systems disclosed herein can also be used to selectively mask other components, such as other components of a gas turbine engine 1 (e.g., fan blades 40 or turbine blades), components for the automotive industry, components for the shipping industry, etc. The dimensions, shapes, and configurations of the various components of masking systems 200, 300, and 400 can be reconfigured as needed for specific applications.

[0130] In some examples, one or more surfaces of the compressor blade 60 may be angled. For example, the first end 78 and / or the second end 80 of the platform 83 of the compressor blade 60 ( Figures 3C to 3D The shielding system 60 can extend at an angle from the bottom side 82 of the platform 83. One or more components of the shielding system 200, shielding system 300 and / or shielding system 400 can be angled accordingly to ensure that only the airfoil 62 of the compressor blade 60 and the top edge 91 of the platform 83 are exposed when the compressor blade 60 is held therein.

[0131] Therefore, as already described, each of the shielding systems 200, 300 and 400 can be used to selectively shield the compressor blades 60 and can allow the root 72 to be enclosed and shielded, regardless of the protrusion 92.

[0132] As used herein, the terms “first,” “second,” “third,” and “fourth” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components. The terms “coupled,” “fixed,” “attached,” etc., refer to direct coupling, fixing, or attachment, as well as indirect coupling, fixing, or attachment via one or more intermediate components or features, unless otherwise stated herein. The singular forms “a,” “an,” and “the” include plural references unless the context clearly specifies otherwise.

[0133] Many different arrangements of the various components depicted, as well as those not shown, are possible without departing from the spirit and scope of this disclosure. 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. Alternative means for achieving the above improvements can be developed by those skilled in the art without departing from the scope of this disclosure.

[0134] It should be understood that certain features and sub-combinations are useful and can be used without reference to other features and sub-combinations, and are considered to be within the scope of the claims.

Claims

1. A masking system (200) for selectively masking a component (60) having a protrusion (92), the masking system (200) comprising: A first masking element (210) having a recessed region (226) configured to accommodate the protrusion (92); as well as A second shielding element (250) is fixed to the first shielding element (210); When the protrusion (92) is accommodated in the recessed area (226) and the first masking member (210) is fixed to the second masking member (250), at least a first portion (72) of the component (60) is masked and at least a second portion (62, 91) of the component (60) is exposed.

2. The shielding system (200) according to claim 1, wherein, The first mask (210) includes a first opening (238A), and the second mask (250) includes a second opening (238B), wherein when the first mask (210) is fixed to the second mask (250), the second opening (238B) is aligned with the first opening (238A).

3. The shielding system (200) according to claim 1, wherein, The first shield (210) includes a receiving area (242) for receiving the first portion (72).

4. The shielding system (200) according to claim 3, wherein, The shape of the receiving area (242) generally corresponds to the shape of the first part (72).

5. The shielding system (200) according to claim 1, wherein, The first mask (210) has an integral structure, and the second mask (250) has an integral structure.

6. The shielding system (200) according to claim 1, wherein, At least one of the first mask (210) and the second mask (250) is additively manufactured.

7. The shielding system (200) according to claim 1, wherein, The component (60) is a gas turbine engine component (60).

8. The shielding system (200) according to claim 7, wherein, The component (60) is a blade (60).

9. The shielding system (200) according to claim 8, wherein, The protrusion (92) extends from the root (72) of the blade (60).

10. The shielding system (200) according to claim 9, wherein, The first portion (72) includes the root (72) of the leaf (60).

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