Tool and method for shading a turbine component, such as a

Abstract

A shielding tool for a turbine assembly configured to receive and cover a portion of the turbine assembly, the shielding tool including a first housing member and a second housing member configured to engage with the first housing member to form a chamber configured to receive a portion of the turbine assembly. The first and second housing components are configured to expose a portion of the turbine assembly to the atmosphere when the first and second housing components are secured together and receive the turbine assembly. The first housing part and the second housing part are configured to be mutually compressible when fixed together. Further, the first and second housing members are configured to seal a space containing the turbine assembly portion without the use of a resilient seal.

Description

Technical Field

[0001] This technology relates to tools used in the process of manufacturing or repairing turbine components, such as blades or vanes of a gas turbine. Specifically, this technology relates to a masking tool for securing a gas turbine component during the process of coating the component. Background Art

[0002] Turbine components in a gas turbine, such as turbine blades (also known as airfoils) or vanes, are typically stressed by centrifugal and fluid forces, which can cause fracture, yielding, or creep failures. In addition, turbine components typically withstand temperatures of around 2,500°F (1,370°C). Such high temperatures can weaken the turbine components, making them more susceptible to creep and corrosion failures. In addition, the vibrations of the turbine itself can also cause fatigue failures.

[0003] To improve the durability of turbine components and protect their safety, one solution is to apply a protective coating on the surface of the components. For example, thermal barrier coatings, such as high-temperature corrosion-resistant metal coatings.

[0004] Conventional coating processes can prepare turbine components by attaching casing parts of a metal plate to the turbine components so that a portion of the turbine components is shielded from the protective coating material. The metal plate is positioned to mask the parts of the turbine components that are not intended to be coated with the coating material. Since the shape of the metal plate does not conform to the shape of the turbine components, there may be gaps between the metal plate and the turbine components. There may also be gaps between different casing parts of the metal plate. The coating material may seep out from the gaps and coat the parts of the turbine components that do not need to be coated.

[0005] There is a need for a masking system that can better mask turbine components to prevent accidental leakage of the coating material during the coating process. Summary of the Invention

[0006] Systems and methods for solving the above problems are disclosed herein.

[0007] In one aspect of the technology, a masking tool for a turbine assembly, the masking tool being configured to receive and cover a portion of the turbine assembly, the masking tool including a first housing member; a second housing member configured to engage the first housing member to form a chamber configured to receive a portion of the turbine assembly; and an anchor configured to secure the masking tool to a mounting table, wherein when the first housing member and the second housing member are secured together and receive the turbine assembly, the masking tool is configured to expose a portion of the turbine assembly to the atmosphere; wherein when the first housing member and the second housing member are secured together, the first housing member and the second housing member are configured to press against each other; wherein the first housing member and the second housing member are configured to seal a space containing a portion of the turbine assembly without an elastomeric seal; and wherein the inner surfaces of the first housing member and the second housing member are contoured to match the contour of the turbine assembly.

[0008] Another aspect of the technology includes the foregoing aspect, wherein the first housing member and the second housing member have an opening that allows a portion of the turbine assembly to be exposed to the surrounding environment while the first housing member and the second housing member are secured together and receive the turbine assembly.

[0009] Another aspect of the technology includes any of the foregoing aspects, wherein a portion of the turbine assembly is a root pocket area.

[0010] Another aspect of the technology includes any of the foregoing aspects, wherein a portion of the turbine assembly is an airfoil portion.

[0011] Another aspect of the technology includes any of the foregoing aspects, wherein a portion of the turbine assembly is a plurality of vanes of a two-vane assembly.

[0012] Another aspect of the technology includes any of the foregoing aspects, wherein only the first housing member or the second housing member includes an opening configured to expose a portion of the turbine assembly such that when the turbine assembly is enclosed within the masking tool, only a portion on one side of the turbine assembly remains exposed to the atmosphere.

[0013] Another aspect of the technology includes any of the foregoing aspects, wherein a portion of the inner surface of the first housing member is convex and a portion of the inner surface of the second housing member is concave.

[0014] Another aspect of the technology includes any of the foregoing aspects, wherein the first housing member and the second housing member form a chamber that is open at the top when the first housing member and the second housing member are secured together.

[0015] Another aspect of the technology includes any of the foregoing aspects, wherein when the first housing component and the second housing component are fixed to each other and receive the turbine assembly, the first housing component and the second housing component are configured to form a rectangular parallelepiped shape with a part of the turbine assembly.

[0016] Another aspect of the technology includes any of the foregoing aspects, wherein the masking tool is formed by a three-dimensional (3D) printing method.

[0017] Another aspect of the technology includes any of the foregoing aspects, wherein the chamber is exposed to the atmosphere.

[0018] Another aspect of the technology includes a protective coating system for applying a protective coating to a turbine assembly, the system including a housing that encloses a chamber, an opening through a door of the housing providing access to the chamber; a mounting table within the chamber; and a masking tool of any of the foregoing aspects, wherein an anchor of the masking tool is configured to be fixed to the mounting table.

[0019] Another aspect of the technology includes any of the foregoing aspects, wherein the system is a physical vapor deposition (PVD) system utilizing a cathodic arc coating tool.

[0020] Another aspect of the technology includes any of the foregoing aspects, wherein the system is a low-pressure plasma spraying (LPPS) system.

[0021] Another aspect of the technology includes a method of loading a turbine assembly into a masking tool for a protective coating system, the method including separating or partially separating housing components of the masking tool to open access to a holding chamber of the masking tool; inserting the turbine assembly into the chamber; and securing the housing components of the masking tool together to form a tight fit between the housing components of the masking tool and the turbine assembly, the tight fit being substantially impermeable to the protective coating, wherein after the housing components of the masking tool are secured together, a portion of the turbine assembly remains uncovered and one or more inner surfaces of the housing components are contoured to match the contour of the turbine assembly such that at least a portion of the turbine assembly abuts the one or more contoured inner surfaces.

[0022] Another aspect of the technology includes the foregoing aspect, wherein the coating-impermeable tight fit between the housing components is formed without an elastomeric seal.

[0023] Another aspect of the technology includes any of the foregoing aspects, wherein the portion of the turbine assembly that remains uncovered is the root band region.

[0024] Another aspect of the technology includes any of the foregoing aspects, wherein the portion of the turbine assembly that remains uncovered is the airfoil portion.

[0025] Another aspect of the technology includes any of the preceding aspects, wherein the turbine assembly is a two-airfoil assembly and the portion of the turbine assembly that remains uncovered is an airfoil.

[0026] Another aspect of the technology includes any of the previous aspects, further comprising attaching an anchor to a first housing component of the housing components, wherein the anchor secures the masking tool to the chamber floor, wherein the coating material is deposited on the masking tool and the exposed portion of the turbine airfoil.

[0027] Another aspect of the technology includes any of the previous aspects, wherein the first housing member and the second housing member are connected by a hinge. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1A The first protective coating system is demonstrated.

[0029] Figure 1B A second protective coating system was demonstrated.

[0030] Figure 2A and Figure 2B is a perspective view of an exemplary turbine assembly.

[0031] Figure 3A is a perspective view of the masking tool without the turbine assembly.

[0032] Figure 3B and Figure 3C yes Figure 3A A perspective view of a masking tool with a turbine assembly mounted therein.

[0033] Figure 4A This is a perspective view of the masking tool section.

[0034] Figure 4B yes Figure 4A A perspective view of the masking tool portion of FIG. 1 with the turbine assembly mounted therein.

[0035] Figure 4C - 4G yes Figure 4A A perspective view of a masking tool with a turbine assembly mounted therein.

[0036] Figure 5A - 5F is a perspective view of another masking tool.

[0037] Figure 6A - 6C is a perspective view of another masking tool.

[0038] Figure 6D - 6I Schematic diagram of the method for installing the turbine assembly into the masking tool. DETAILED DESCRIPTION

[0039] Figure 1ADisclosed is an exemplary turbine component coating system 10. The coating system 10 can be in the form of a physical vapor deposition (PVD) system, utilize a cathodic arc coating tool, and can include a housing 12 that encloses a chamber 14. The chamber 14 can be accessed by opening a door 16. The coating system 10 can also include a mounting table 17 for supporting a turbine component, such as a turbine blade or vane, enclosed within a masking tool 18. The mounting table 17 with the masking tool 18 can be mounted between an anode 19 and a cathode 20. The chamber 14 can include an outlet 21 that communicates with a vacuum pump (not shown).

[0040] Figure 1B Disclosed is another exemplary turbine component coating system 150 in the form of a low pressure plasma spray (LPPS) system. The coating system 150 can include a chamber 14, and a mounting table 17 is located within the chamber 14 for supporting a masking tool 18 that carries a turbine component enclosed therein, such as a turbine blade. A plasma torch 23 can direct a plasma stream 25 towards the masking tool 18, and an infrared pyrometer 27 can irradiate the plasma stream 25. It should be understood that although two types of coating systems are shown in the figures, any type of system capable of applying a protective coating to the turbine component can be used.

[0041] It is also contemplated that the turbine coating system can also be an electron beam physical vapor deposition system (EB-PVD system).

[0042] During the operation of a conventional turbine, different regions of each turbine component are affected by different conditions. That is, different regions of each turbine component are subjected to different temperatures and stresses. Therefore, for each turbine component, different types of protective coatings are applied to different regions of the turbine component. To prevent a particular coating type from being deposited on unwanted portions of the turbine component, the turbine component can be encapsulated within a masking tool to cover the portions of the turbine component that do not need to be coated.

[0043] To ensure that the coating deposit does not penetrate into unwanted regions of the turbine component, the masking tool can be manufactured to conform to the shape of the turbine component and can be shaped to expose certain portions of the turbine component.

[0044] The embodiments described herein refer to turbine components, including but not limited to blades, vanes, or other turbine components. For ease of description, unless otherwise specified, the turbine component will be referred to as an exemplary "turbine blade". However, this description is not intended to limit the embodiments in any way.

[0045] Figure 2A and Figure 2BShows an exemplary turbine blade 22 having a root pocket region 24, a root region 26, an airfoil region 28, and a platform 30. The root pocket region 24 and the platform 30 may be located between the root region 26 and the airfoil region 28, where the root pocket region 24 is adjacent to the root region 26 and the platform 30 is located between the airfoil region 28 and the root pocket region 24. In Figure 2A the convex surface of the airfoil region 28 is clearly visible, extending from the wider leading edge 32 to the narrower trailing edge 34. In Figure 2B the concave surface of the airfoil region 28 is clearly visible, extending from the narrower trailing edge 34 to the wider leading edge 32. Additionally, the root region 26 includes a plurality of ridges and an end 36 that extends laterally beyond the remainder of the root region 26. Further, the surface of the platform 30 facing the airfoil region 28 is convex.

[0046] Figure 3A - 3C Shows an exemplary masking tool 38 for masking Figure 2A and Figure 2B the turbine blade 22. The masking tool 38 is intended for use in a cathodic arc deposition system. However, it is contemplated that the masking tool 38 may be used in other coating systems. The masking tool 38 is configured to mask all parts of the turbine blade 22 except the root pocket region 24 so that only the root pocket region 24 receives a protective coating during the coating process.

[0047] The masking tool 38 may include a first housing member 40 and a second housing member 42, the second housing member 42 being configured to be secured to the first housing member 40 to form an outer shroud around the turbine blade 22, leaving a portion of the turbine blade 22 exposed to the atmosphere. In Figure 3A - 3C the configuration shown, the opening portion of the masking tool 38 is located at the root pocket region 24 of the turbine blade 22 so that the root pocket region 24 is exposed to the atmosphere. However, the masking tool 38 can be designed to expose any part of the turbine blade 22 to the atmosphere, depending on which part of the turbine blade 22 needs to be coated.

[0048] The first housing member 40 may be configured to cover the side of the turbine blade 22 having the concave airfoil surface, while the second housing member 42 may be configured to cover the side of the turbine blade 22 having the convex airfoil surface without engaging or contacting the root pocket region 24. Each of the first housing member 40 and the second housing member 42 may include a root region covering portion 44, an airfoil covering portion 46, and a platform covering portion 48 located between the root region covering portion 44 and the airfoil covering portion 46.

[0049] Each covering portion of the first housing member 40 and the second housing member 42 can be manufactured to have a profile that closely conforms to the turbine blade 22. For example, the root region covering portion 44 can be configured to cover the root region 26. Additionally, the inner surface of the root region covering portion 44 can include ridges similar to those on the root region 26. For a close fit, the ridges on the root region covering portion 44 can be positioned to engage with the valleys on the root region 26. The root region covering portion 44 can also include valleys located between the ridges, and the valleys of the root region covering portion 44 can be positioned to engage with the ridges of the root region 26. It is contemplated that the root region covering portion 44 can also include a laterally projecting portion 50 that accommodates the tip 36.

[0050] Furthermore, the airfoil covering portions 46 of the first housing member 40 and the second housing member 42 can be configured to cover the airfoil region 28. Thus, the airfoil covering portion 46 can be manufactured to have a profile complementary to the shape of the airfoil region 28. For example, the inward surface of the airfoil covering portion 46 of the first housing member 40 can be convex to interface (or contact) with the concave surface of the airfoil region 28. Conversely, the inward surface of the airfoil covering portion 46 of the second housing member 42 can be concave to interface (or contact) with the concave surface of the airfoil region 28.

[0051] The platform covering portion 48 can be configured to cover the platform 30. Thus, the platform covering portion 48 can extend laterally beyond the root region covering portion 44 and the airfoil covering portion 46.

[0052] Both the first housing member 40 and the second housing member 42 can include an opening 52 sized and shaped to keep a portion or all of the root pocket region 24 unobscured by the masking tool 38. The opening 52 can be entirely defined by the platform covering portion 48 or defined by a combination of the platform covering portion 48 and the root region covering portion 44. Additionally, the first housing member 40 and the second housing member 42 can be configured such that the openings 52 in the first housing member 40 and the second housing member 42 form a chamber 54 that receives the root pocket region 24 and seals with the other portions inside the masking tool 38.

[0053] It is contemplated that only the first housing member 40 or the second housing member 42 includes the opening 52. In this configuration, only one side of the root pocket region 24 will be exposed to the atmosphere. The other side will be masked like the other parts of the turbine blade 22.

[0054] The chamber 54 can be sealed from the rest of the interior of the masking tool 38 by compressing the first housing member 40 and the second housing member 42 together. Additionally, the manufacturing tolerances of the first housing member 40 and the second housing member 42 can be small enough such that the seam between the two members is small enough to effectively act as a seal to prevent the coating material from infiltrating or leaking into any part outside the root pocket region 24 of the turbine blade 22. In other words, the tolerances of the first housing member 40 and the second housing member 42 can be small enough to form a seal between the first housing member 40 and the second housing member 42 without the use of an elastomeric seal. This may increase the service life of the masking tool 38 as the absence of an elastomeric seal component eliminates one component that could potentially fail under the operating conditions of the masking tool 38. Nevertheless, it is contemplated that one or both of the first housing member 40 and the second housing member 42 can include one or more elastomeric seals to seal the chamber 54 from the rest of the interior of the masking tool 38 and to seal the interior of the masking tool 38 from the exterior of the periphery of the masking tool 38.

[0055] It is contemplated that the entire inner surface of each of the first housing member 40 and the second housing member 42 can be manufactured to a specific profile such that when the first housing member 40 and the second housing member 42 are secured together and enclose the turbine blade 22, the entire inner surface of each of the first housing member 40 and the second housing member 42 abuts (or contacts) the turbine blade 22. Such a configuration can prevent particulate infiltration to the surface covered by the first housing member 40 and the second housing member 42.

[0056] Alternatively, only a portion of the inner surfaces of the first housing member 40 and the second housing member 42 can be manufactured to a specific profile to abut (or contact) the turbine blade 22. For example, only the perimeters of the first housing member 40 and the second housing member 42 and the perimeter of the opening 52 will abut (or contact) the turbine blade 22. In another embodiment, the inner surfaces of the first housing member 40 and the second housing member 42 will intermittently abut (or contact) the turbine blade 22 (i.e., in addition to the perimeters of the first housing member 40 and the second housing member 42, other portions of the inner surfaces of the first housing member 40 and the second housing member 42 will also abut (or contact) the turbine blade 22). Only partial engagement of the inner surfaces of the first housing member 40 and the second housing member 42 with the turbine blade 2 provides for manufacturing tolerances and prevents leakage due to minor inconsistencies in the shape of different turbine blades 22, such that one masking tool 38 can be used for multiple turbine blades 22 of a particular shape and size.

[0057] As Figure 3BAs shown, the first housing member 40 and the second housing member 42 can be fixed together by a fastening device 56. The fastening device 56 can be a simple wire looped around the shielding tool 38. The loop can be tightened to provide a compressive force on the first housing member 40 and the second housing member 42. Alternatively, the first housing member 40 and the second housing member 42 can also be fixed together by snap connections, one or more clips, one or more bolts, or any other fastening device known currently or developed in the future that can press the first housing member 40 and the second housing member 42 against each other. It is also conceivable that the first housing member 40 and the second housing member 42 can be completely separated. Alternatively, the first housing member 40 and the second housing member 42 can be interconnected by a hinge and can rotate between an open position and a closed position.

[0058] The length L of the shielding tool 38 (the total length of the root region covering portion 44, the airfoil covering portion 46, and the platform covering portion 48) can range from about 5 cm to about 15 cm (e.g., about 11 cm). The maximum width W of the root region covering portion 44 can range from about 3 cm to about 7 cm (e.g., about 4.5 cm). In addition, the minimum width w of the airfoil covering portion 46 can be from about 3 cm to about 7 cm (e.g., about 5 cm).

[0059] As described above, the shielding tool 38 can be designed such that other parts of the turbine blade 22 except the root pocket region 24 are kept exposed to the atmosphere. For example, the opening 52 can be near the airfoil region 28, the platform 30, and / or the root region 26. The size of the opening 52 can expose the entire airfoil region 28, the platform 30, or the root region 26; or only a part of the airfoil region 28, the platform 30, or the root region 26; or a combination of the airfoil region 28, the platform 30, and the root region 26 can be exposed.

[0060] In some cases where the airfoil region 28 is exposed to the atmosphere, the length L of the shielding tool 38 can be shortened, and the shielding tool 38 can terminate at the platform 30 (while surrounding the platform 30). In addition, the length L of the shielding tool 38 can be shortened, and the shielding tool 38 can terminate at the root pocket region 24 or the platform 30 (surrounding the platform 30 or surrounding the platform 30 and the root pocket region 24).

[0061] In addition, as described above, the shielding tool 38 may only expose one side of the turbine blade. In this configuration, the first housing member 40 or the second housing member 42 can extend to the length of the turbine blade, while the other of the first housing member 40 or the second housing member 42 can terminate before the airfoil region 28 or the root region 26. In this configuration, the lengths L of the first housing member 40 and the second housing member 42 can be different.

[0062] The masking tool 38 may also include an anchor 57 configured to anchor the masking tool 38 to the mounting table 17. The anchor 57 may be in the form of any device capable of removably anchoring the masking tool 38 to the mounting table 17. For example, the anchor 57 may include a bayonet system, bolts, threaded fasteners, etc.

[0063] By securing the masking tool 38 to the mounting table 17, the turbine blade 22 can be held stable during the coating process so that a substantially uniform coating can be applied to all of the predetermined surfaces of the turbine blade 22. It is contemplated that the anchor 57 may lock or secure the masking tool 38 to the mounting table 17 in a manner that allows the masking tool 38 to rotate relative to the coating applicator or allows the masking tool 38 to remain fixed in place and maintain a particular orientation as the coating applicator moves around the masking tool 38.

[0064] It is also contemplated that the mounting table 17 may include a receiver (not shown) dedicated to the anchor 57 such that all masking tools 38 can be positioned in a specific location on the mounting table 17. In other words, a specific location on the mounting table 17 can be selected to secure the masking tools 38 that are designed to be used only for coating the root pocket region 24. The specific location on the mounting table 17 for mounting the masking tool 38 can result in a substantially uniform coating of the root pocket region 24 of all turbine blades 22.

[0065] It is also contemplated that there may be multiple receivers on the mounting table 17 configured to receive the anchor 57. In other words, the anchor 57 and the mounting table 17 may be configured such that the masking tool 38 is secured to the mounting table 17 only at one or more discreet locations.

[0066] In addition, it is contemplated that the first housing member 40 and the second housing member 42 may be formed by a 3D printing process. Alternatively, the first housing member 40 and the second housing member 42 may be formed by a molding process. It is also contemplated that the first housing member 40 and the second housing member 42 may be formed by welding together metal sheets. Further, each of the first housing member 40 and the second housing member 42 may be a continuous monolith. However, it is contemplated that one or more of the root region covering portion 44, the airfoil covering portion 46, and the platform covering portion 48 may be formed separately and assembled to the other parts of the first housing member 40 and / or the second housing member 42. Additionally, the masking tool 38 may be made of any material that remains stable at a temperature of about {2000°F (1093°C)}. For example, the masking tool 38 may be made of a material containing about 40% to about 70% nickel (such as a nickel-chromium alloy). It is contemplated that the material forming the masking tool 38 may also be a cobalt-based alloy.

[0067] Figure 4A - 4GShows another exemplary masking tool 58 for masking Figure 2A and Figure 2B of the turbine blade 22. The masking tool 58 is intended for use in an LPPS system. However, it is contemplated that the masking tool 58 can be used in other coating systems. In Figure 4A - 4G the configuration shown, the masking tool 58 is shown masking all parts of the turbine blade 22 except for the airfoil region 28 and the portion of the platform 30 facing the airfoil region 28, such that during the coating process, only the airfoil region 28 and the portion of the platform 30 facing the airfoil region 28 receive the protective coating. However, the masking tool 58 can be designed to expose any part of the turbine blade 22 to the atmosphere, depending on which part of the turbine blade 22 needs to be coated.

[0068] Figure 4A - 4G The shown masking tool 28 can be similar to existing masking tools formed from welded metal sheets. However, the individual components of the masking tool 58 can be customized according to the specific turbine assembly being masked in order to seal the parts of the turbine assembly intended to remain uncoated from the parts intended to be coated to prevent seepage and / or leakage to the parts intended to remain uncoated. This can be done by attaching tightly and conformably and / or sealing (e.g., elastomeric or foam seals) to individual components (e.g., at the edges contacting the turbine assembly or other components of the masking tool 58). Additionally, the masking tool 58 can be formed by a 3D printing process. Alternatively, the masking tool 58 can be formed by a molding process. The masking tool 58 can be made of any material that remains stable at a temperature of about 2000°F (1093°C). For example, the masking tool 58 can be made of a material containing about 40% to about 70% nickel (such as a nickel-chromium alloy). It is contemplated that the material forming the masking tool 58 can be a cobalt-based alloy.

[0069] The masking tool 58 may include a first housing member 60 and a second housing member 62, wherein the second housing member 62 is configured to be secured to the first housing member 60 without contacting or engaging the airfoil region 28 or the surface of the platform 30 facing the airfoil region 28. The first housing member 60 may include a horizontal bottom wall 64 and two adjacent vertical walls 66, 68. The second housing member 62 may include two additional adjacent vertical walls 70, 72. When the first and second housing members 60, 62 are secured together, they may form a rectangular parallelepiped shape. It should be understood that while shown as a rectangular parallelepiped shape, the chamber formed by the first and second housing members 60, 62 may be any three-dimensional shape with a top surface that matches the perimeter shape of the platform 30. Furthermore, the angle θ between the vertical walls 66, 68 (similar to the angle between the vertical walls 70, 72) may be in the range of 90-150 degrees (e.g., approximately 125 degrees). Additionally, the included angle α between the vertical walls 66 , 70 (which is the same as the included angle between the vertical walls 68 , 72 ) may be between 30 and 90 degrees (eg, 55°).

[0070] Furthermore, similar to the masking tool 38, some or all of the inner surface of the masking tool 58 may also be contoured to match the contour of the turbine blade 22. In this configuration, the walls 66, 68, 70, and 72 may be formed into a shape that generally reflects the shape of the turbine blade 22 (e.g., the root region 26). It is also contemplated that the inner surfaces of the walls 66, 68, 70, or 72 may include ridges and valleys that match the ridges and valleys of the root region 26, such that the valleys of the masking tool 58 receive the ridges of the root region 26, and the valleys of the root region 26 receive the ridges of the masking tool 58. Furthermore, it is contemplated that the first and second shell components 60, 62 may only peripherally interface (or contact) with the turbine blade 22.

[0071] In addition, if Figure 4G As shown, one end of each wall 68 and 70 can be bent laterally at an angle (e.g., approximately 90°) so that when the first housing component 60 and the second housing component 62 are secured together, the bent end of wall 68 overlaps the outer surface of wall 72, and the bent end of wall 70 overlaps the outer surface of wall 66. The overlapping of the walls ensures a tight fit and provides an interface that facilitates separation of the first housing component 60 and the second housing component 62 after use.

[0072] The chamber formed by the first and second shell members 60, 62 may be open at the top so that the platform 30 may enclose the chamber when the turbine blade 22 is inserted into the masking tool 58. The chamber may receive the root pocket 24 and the root region 26 so that these portions of the turbine blade 22 are isolated and sealed from the outside by the walls of the first and second shell members 60, 62 and the platform 30.

[0073] The masking tool 58 may include an external masking member 74. The external masking member 74 may include a base 76 and a projecting element 78. The base 76 may be configured to attach the external masking member 74 to the outer surface of the first housing member 60. It is contemplated that the base 76 may be attached to the vertical wall 66 of the first housing member 60. The projecting element may extend vertically from the base 76 at a location near the trailing edge 34 of the airfoil region 28 of the turbine blade 22. At this location, the projecting element 78 may prevent the coating material from accumulating on the trailing edge 34. It should be understood that the external masking member 74 is located near the trailing edge 34 regardless of the position of the trailing edge relative to the first housing member 60 and the second housing member 62. In other words, the external masking member 74 may be disposed at any position that facilitates the projecting element 78 being close to the trailing edge 34.

[0074] The root region 26 and the root pocket region 24 may be sealed from the outside of the masking tool 58 by compressing the first housing member 60 and the second housing member 62 together. Additionally, the manufacturing tolerances of the first housing member 60 and the second housing member 62 may be small enough such that the seam between the first housing member 60 and the second housing member 62 and the platform 30 is small enough to effectively act as a seal to prevent the coating material from infiltrating or leaking into any part of the turbine blade 22 other than the airfoil region 28 and the surface of the platform 30 facing the airfoil region 28. In other words, the tolerances of the first housing member 60 and the second housing member 62 may be small enough to form a seal between the first housing member 60 and the second housing member 62 and the platform 30 without the use of an elastomeric seal. This may increase the service life of the masking tool 58 because the absence of an elastomeric seal component eliminates one component that could potentially be damaged under the operating conditions of the masking tool 58. Nevertheless, it is contemplated that one or both of the first housing member 60 and the second housing member 62 may include one or more elastomeric seals for sealing the root region 26 and the root pocket region 24 from the outside of the masking tool 58.

[0075] The first housing member 60 and the second housing member 62 can be fixed together by fastening means 80. In addition, the external shielding member 74 can be fixed to the first housing member 60 or the second housing member 62 by fastening means 82. The fastening means 80, 82 can be one or more bolts, which can provide a pressing force on the first housing member 60 and the second housing member 62 after being tightened. Alternatively, the first housing member 60, the second housing member 62 and the external shielding member 74 can be fixed together by snap connections, one or more clips, wires wound around the shielding tool 58, or any other fastening means known currently or developed later that can press the first housing member 60 and the second housing member 62 against each other. It is also conceivable that the first housing member 60, the second housing member 62 and the external shielding member 74 can be completely separated. Alternatively, the first housing member 60 and the second housing member 62 can be interconnected by a hinge and can be rotated between an open position and a closed position.

[0076] The shielding tool 58 can also include an anchor 84 configured to anchor the shielding tool 58 to the mounting table 17. The anchor 84 can be in the form of any device capable of removably anchoring the shielding tool 58 to the mounting table 17. For example, the anchor 84 can include a bayonet system, bolts, threaded fasteners, etc.

[0077] By fixing the shielding tool 58 to the mounting table 17, the turbine blade 22 can be kept stable during the coating process so that a substantially uniform coating can be applied to all the predetermined surfaces of the turbine blade 22. It is conceivable that the anchor 84 can lock or fix the shielding tool 58 to the mounting table 17 in a manner that allows the shielding tool 58 to rotate relative to the coating applicator, or allows the shielding tool 58 to be fixed in place and maintain a specific orientation when the coating applicator moves around the shielding tool 58.

[0078] It is also conceivable that the mounting table 17 can include a receiver (not shown) dedicated to the anchor 84, so that all the shielding tools 58 can be positioned at specific locations on the mounting table 17. In other words, specific locations on the mounting table 17 can be selected to fix the shielding tools 58, which are designed to coat only one surface of the airfoil region 28 and the platform 30. The specific locations for mounting the shielding tools 58 on the mounting table 17 can make the coatings on the root pocket regions 24 of all the turbine blades 22 substantially uniform.

[0079] It is also conceivable that there are multiple receivers configured to receive the anchor 84 on the mounting table 17. In other words, the anchor 84 and the mounting table 17 can be configured to fix the shielding tool 58 to the mounting table 17 only at one or more concealed locations.

[0080] In addition, the anchors 57 and 84 can be configured such that they cannot be fixed to the mounting table 17 at the same location. In other words, the location where the masking tool can be fixed to the mounting table can depend on the type of masking tool used. Alternatively, the mounting table 17 can include a universal receiver for receiving the anchors of any type of masking tool.

[0081] The shapes and sizes of the vertical walls 66 and 70 can be such that the distance D1 between the inner surfaces of the walls 66 and 72 is between about 5 cm and about 10 cm (e.g., about 8 cm). In addition, the shapes and sizes of the vertical walls 68 and 72 can be such that the distance D2 between the walls 68 and 70 is between about 5 cm and about 10 cm (e.g., about 4.5 cm). The height H1 of the masking tool 58, which is the maximum height of the vertical walls 66, 68, 70, 72, can be in the range of about 3 cm to about 7 cm (e.g., about 4.5 cm). The masking tool 58 has a second height H2, which is the distance that the protruding element 78 extends beyond the adjacent vertical wall, and can be about 3 cm to about 10 cm (e.g., about 7 cm).

[0082] Although the first housing member 60, the second housing member 62, and the external masking member 74 are illustrated as separate components, each of the first housing member 60, the second housing member 62, and the external masking member 74 can be a continuous integral body.

[0083] Figure 5A - 5F Another exemplary masking tool 88 is shown for masking Figure 2A and Figure 2B the turbine blade 22. The masking tool 88 is similar to the masking tool 58, except that the masking tool 88 does not include an external masking member with a protruding element. Thus, the masking tool 88 is intended for use in an LPPS system, but can also be used in other coating systems. In the Figure 5A - 5F configuration shown, the masking tool 88 is configured to mask all parts of the turbine blade 22 except for the airfoil region 28 and the portion of the platform 30 facing the airfoil region 28, such that during the coating process, only the airfoil region 28 and the portion of the platform 30 facing the airfoil region 28 receive the protective coating. However, the masking tool 58 can be designed such that any part of the turbine blade 22 is exposed to the atmosphere, depending on which part of the turbine blade 22 needs to be coated.

[0084] Figure 5A - 5F The shown masking tool 88 is similar to existing masking tools made of welded metal sheets. However, the masking tool 88 is formed by a 3D printing process. Alternatively, the masking tool 88 can be formed by a molding process. The masking tool 88 can be made of any material that remains stable at a temperature of about 2000°F (1093°C). For example, the masking tool 88 can be made of a material containing about 40% to about 70% nickel (such as a nickel-chromium alloy). It is contemplated that the material forming the masking tool 88 can be a cobalt-based alloy.

[0085] The masking tool 88 may include a first housing member 90 and a second housing member 92, and the second housing member 92 is configured to be fixed to the first housing member 90. The first housing member 90 may include a horizontal bottom wall 94 and three adjacent vertical walls 96, 98, 100. The second housing member 92 may include an additional vertical wall 102. When the first housing member 90 and the second housing member 92 are fixed together, they may form a rectangular parallelepiped shape. It should be understood that although illustrated as a rectangular parallelepiped shape, the cavity formed by the first housing member 90 and the second housing member 92 may be any three-dimensional shape, and the top surface may match the peripheral shape of the platform 30. Additionally, the angle θ (the same as the angle between the vertical walls 98 and 100) between the vertical walls 96 and 102 may be in the range of about 90 degrees to about 150 degrees (such as about 125°). Further, the angle α (the same as the angle between the vertical walls 100 and 102) between the vertical walls 96 and 98 may be between about 30 degrees and about 90 degrees (such as about 55°).

[0086] In addition, similar to the masking tool 38, part or all of the inner surface of the masking tool 88 may be manufactured to match the profile of the turbine blade 22. In such a configuration, the walls 96, 98, 100, and 102 may form a shape that substantially reflects the shape of the turbine blade 22 (such as the root region 26). It is also contemplated that the inner surfaces of the walls 96, 98, 100, and 102 may include ridges and valleys that match the ridges and valleys of the root region 26, so that the valleys of the masking tool 88 receive the ridges of the root region 26, while the valleys of the root region 26 receive the ridges of the masking tool 88. Additionally, it is contemplated that only the peripheries of the first housing member 90 and the second housing member 92 are in contact (or touch) with the turbine blade 22.

[0087] In addition, as Figure 5F shown, both ends of the wall 96 may be laterally bent at an angle (such as about 90°) so that when the first housing member 90 and the second housing member 92 are fixed together, the bent ends of the wall 96 overlap the outer surfaces of the wall 98 and the wall 102. The overlap of the walls may ensure a tight fit and provide an interface that facilitates separating the first housing member 90 and the second housing member 92 after use.

[0088] The chamber formed by the first housing member 90 and the second housing member 92 may be open at the top so that when the turbine blade 22 is inserted into the masking tool 88, the platform 30 may surround the chamber. The chamber may receive the root pocket region 24 and the root region 26 so that these portions of the turbine blade 22 are isolated and sealed from the outside by the walls of the first housing member 90 and the second housing member 92 and the platform 30.

[0089] The root region 26 and the root pocket region 24 can be sealed from the outside of the masking tool 88 by compressing the first housing member 90 and the second housing member 92 together. Additionally, the manufacturing tolerances of the first housing member 90 and the second housing member 92 can be small enough such that the seam between the two members and the platform 30 is small enough to effectively act as a seal to prevent the coating material from infiltrating or leaking into any part of the turbine blade 22 other than the airfoil region 28 and the surface of the platform 30 facing the airfoil region 28. In other words, the tolerances of the first housing member 90 and the second housing member 92 can be small enough to form a seal between the first housing member 90 and the second housing member 92 and the platform 30 without the use of an elastomeric seal. This may increase the service life of the masking tool 88 because the absence of an elastomeric seal component reduces the number of components that could potentially fail under the operating conditions of the masking tool 88. Nevertheless, it is contemplated that one or both of the first housing member 90 and the second housing member 92 can include one or more elastomeric seals for sealing the root region 26 and the root pocket region 24 from the outside of the masking tool 88.

[0090] The first housing member 90 and the second housing member 92 can be secured together by fastening means 104. The fastening means 104 can be one or more bolts that, when tightened, provide a clamping force to the first housing member 90 and the second housing member 92. Additionally, the first housing member 90 and the second housing member 92 can also be secured together by snap connections, one or more clips, a wire looped around the masking tool 88, or any other fastening means known currently or developed in the future that can clamp the first housing member 90 and the second housing member 92 against each other. It is also contemplated that the first housing member 90 and the second housing member 92 can be completely separated. Alternatively, the first housing member 90 and the second housing member 92 can be interconnected by a hinge and be rotatable between an open position and a closed position.

[0091] The masking tool 88 can further include an anchor 106 configured to anchor the masking tool 88 to the mounting table 17. The anchor 106 can be in the form of any device capable of removably anchoring the masking tool 88 to the mounting table 17. For example, the anchor 106 can include a bayonet system, bolts, threaded fasteners, etc.

[0092] By securing the masking tool 88 to the mounting table 17, the turbine blade 22 can be held stable during the coating process so that a substantially uniform coating can be applied to all the predetermined surfaces of the turbine blade 22. It is contemplated that the anchor 106 can lock or secure the masking tool 88 to the mounting table 17 in a manner that allows the masking tool 88 to rotate relative to the coating applicator or allows the masking tool 88 to remain fixed in place and maintain a specific orientation as the coating applicator moves around the masking tool 88.

[0093] It is also contemplated that the mounting table 17 may include a receiver (not shown) dedicated to the anchor 106 such that all of the masking tools 88 can be positioned at specific locations on the mounting table 17. In other words, specific locations on the mounting table 17 can be selected to secure the masking tools 88 which are designed to coat only one surface of the airfoil region 28 and the platform 30. Mounting the masking tools 88 at specific locations on the mounting table 17 can result in a substantially uniform coating on one surface of the airfoil region 28 and the platform 30 for all of the turbine blades 22.

[0094] It is also contemplated that the mounting table 17 has a plurality of receivers configured to receive the anchor 106. In other words, the anchor 106 and the mounting table 17 can be configured such that the masking tools 88 are secured to the mounting table 17 only at one or more discrete locations.

[0095] In addition, the anchors 57 and 84 can be configured such that they cannot be secured to the mounting table 17 at the same location as the anchor 106. In other words, the location at which the masking tool can be secured to the mounting table can depend on the type of masking tool used. Alternatively, the mounting table 17 can include a universal receiver for receiving the anchors of any type of masking tool.

[0096] The vertical walls 96 and 100 can be sized and shaped such that the distance D3 between the inner surfaces of the walls 98 and 102 is between about 10 cm and about 20 cm (e.g., about 15 cm). In addition, the vertical walls 98 and 102 can be sized and shaped such that the distance D3 between the inner surfaces of the walls 96 and 100 is between about 5 cm and about 15 cm (e.g., about 9 cm). The maximum height H3 of the vertical walls 96, 98, 100, 102 can range from about 5 cm to about 15 cm (e.g., about 8 cm).

[0097] Although the first housing member 90 and the second housing member 92 are illustrated as separate members, the first housing member 90 and the second housing member 92 can be a continuous unitary body.

[0098] Figure 6A - 6I Another exemplary masking tool 108 is shown for masking a turbine double airfoil assembly 110 (see Figure 6D ). The masking tool 108 is intended for use in an EB - PVD system but can also be used in other coating systems. In the Figure 6A - 6I configuration shown, the masking tool 108 is configured to receive the entire double airfoil assembly 110 and mask all parts of the double airfoil assembly 110 except for the airfoils 112 such that only the airfoils 112 receive a protective coating during the coating process. However, the masking tool 108 can be designed to expose any part of the turbine double airfoil assembly 110 to the atmosphere depending on the parts of the turbine double airfoil assembly 110 that need to be coated.

[0099] Figure 6A - 6IThe shown masking tool 108 is similar to existing masking tools made of welded metal sheets. However, the masking tool 108 is formed by a 3D printing process. Alternatively, the masking tool 108 can be formed by a molding process. The masking tool 108 can be made of any material that remains stable at a temperature of about 2000°F (1093°C). For example, the masking tool 108 can be made of a material containing about 40% to about 70% nickel (such as a nickel-chromium alloy). Additionally, it is also contemplated to use a cobalt-based alloy as the material for the masking tool 108.

[0100] The masking tool 108 can include a first housing member 114 and a second housing member 116 configured to be fixed to the first housing member 114, and a base 118 configured to be fixed to the bottom surface of the first housing member 114.

[0101] The first housing member 114 can be generally in the shape of a trapezoidal prism and can include a horizontal bottom wall 120, a horizontal top wall 122, and two side walls 124, 126 that extend upward from the bottom wall 120 toward each other to the top wall 122. A third side wall 128 can extend from the first side wall 124 to the second side wall and can extend upward from the bottom wall 120 to the top wall 122. The third side wall 128 can also include an inwardly projecting support 130 configured to support the double-flap assembly 110 inside the masking tool 108. The support 130 can include one or more openings 132 sized and shaped to allow at least a portion of the flap 112 to pass through the opening 132, thereby exposing the flap 112 to the outside of the masking tool 108. The support 130 can be configured such that when the double-flap assembly 110 is mounted on the support 130, the flap 112 can press against the third side wall 128 to form a barrier that is substantially impervious to the coating material, so that during operation of the coating system 10, only the exposed portion of the flap 112 will receive the protective coating. It is contemplated that the edges of the opening 132 can include one or more elastic seals for sealing a portion of the double-flap assembly 110 from the outside of the masking tool 108. It should be understood that each flap 112 can be associated with a corresponding opening 132, and the number of openings 132 is equal to the number of flaps 112.

[0102] The first housing member 114 can be open on a side opposite the third side wall 128, giving the first housing member 114 a trapezoidal opening. The second housing member 116 can include a trapezoidal wall 133 shaped and sized to cover the opening in the first housing member 114 opposite the third side wall 128 and enclose the chamber formed by the first housing member 114.

[0103] In addition, part or all of the inner surface of the masking tool 108 can be formed with a contour to match the contour of the turbine vane assembly 110. In this configuration, the walls 120, 122, 124, 126, 128 can form a shape that substantially reflects the shape of the turbine vane assembly 110.

[0104] The base 118 can be used to secure the masking tool 108 to the mounting table 17 and can include a substantially planar base 134 and an anchor 136. The base 134 can be configured to attach to the bottom wall 120 of the first housing component 114. The anchor 136 can extend downward from the base 134 and can attach to the mounting table 17.

[0105] By securing the masking tool 108 to the mounting table 17, the vane assembly 110 can be stabilized during the coating process so that a substantially uniform coating can be applied to all of the predetermined surfaces of the vane assembly 110. It is contemplated that the anchor 136 can lock or secure the masking tool 108 to the mounting table 17 in a manner that allows the masking tool 108 to rotate relative to the coating applicator or allows the masking tool 108 to remain fixed in place and maintain a specific orientation as the coating applicator moves around the masking tool 108.

[0106] It is also contemplated that the mounting table 17 can include a receiver (not shown) dedicated to the anchor 136 so that all masking tools 108 can be positioned at a specific location on the mounting table 17. In other words, a specific location on the mounting table 17 can be selected to secure the masking tools 108 that are only used to coat the vanes 112 of the vane assembly 110. Mounting the masking tools 108 at a specific location on the mounting table 17 can result in a substantially uniform coating of the vanes 112 for all vane assemblies 110.

[0107] It is also contemplated that the mounting table 17 can have a plurality of receivers configured to receive the anchor 136. In other words, the anchor 136 and the mounting table 17 can be configured to secure the masking tool 108 to the mounting table 17 only at one or more discrete locations.

[0108] In addition, the anchors 57, 84, and 106 can be configured to not be securable to the same location on the mounting table 17 as the anchor 136. In other words, the location on the mounting table to which the masking tool can be secured can depend on the type of masking tool used. Alternatively, the mounting table 17 can include a universal receiver for receiving the anchors of any type of masking tool.

[0109] The first housing component 114 and the second housing component 116 can be fixed together by fastening means 138. Figure 6EThe fastening device 138 shown in [Figure 0] can be a wire that is wound around a ring attached to the shielding tool 108. The base 118 can be attached to the first housing component 114 by a similar fastening device 138. However, it should be understood that the fastening device 138 can be any type of device capable of securing the first housing component 114, the second housing component 116, and the base 118 together. For example, it can be a snap connection, one or more clips, one or more bolts, or any other fastening device known currently or developed later that can press the first housing component 114 and the second housing component 116 against each other. It is also conceivable that the first housing component 114, the second housing component 116, and the base 118 can be completely separated. Alternatively, the first housing component 114 and the second housing component 116 can be interconnected by a hinge and can rotate between an open position and a closed position.

[0110] The length L2 of the side walls 124, 126 can be between approximately 5 cm and approximately 10 cm (e.g., approximately 8 cm). The maximum height H4 of the combination of the first housing component 114 and the second housing component 116 can be in the range of approximately 5 cm to approximately 15 cm (e.g., approximately 8 cm).

[0111] It is conceivable that each of the first housing component 114, the second housing component 116, and the base 118 can be a continuous integral body.

[0112] Figure 6D - 6I A method for loading the double - flap assembly 110 into the shielding tool 108 is shown. As Figure 6D shown, the second housing component 116 (acting as a "door" or removable lid) is opened. The second housing component 116 can remain attached to the first housing component 114 by the fastening device 138. Alternatively, the first housing component 114 and the second housing component 116 can be attached to each other in a hinged manner or can be completely separated from each other.

[0113] As Figure 6E shown, the double - flap assembly 110 can be loaded into the chamber in the first housing component 114 and mounted on the support 130. As described above, the double - flap assembly 110 can be positioned such that the double - flap assembly 110 is pressed against the side wall 128 and the flaps 112 are at least partially pushed through the opening 132 so that the flaps 112 can prevent the protective coating from seeping into the chamber in the first housing component 114 through the opening 132.

[0114] In Figure 6F [Figure 22], the second housing component 116 is moved to the closed position, where the second housing component 116 covers the open end of the first housing component 114. In Figure 6GIn [the above], the first housing member 114 and the second housing member 116 are fixed together by a fastening device 138. The fastening device 138 can be a wire tied around a loop. Alternatively, the first housing member 114 and the second housing member 116 can also be fixed together by snap connections, one or more clips, one or more bolts, or any other fastening device known currently or developed later that can press the first housing member 114 and the second housing member 116 against each other. Alternatively, the first housing member 114 and the second housing member 116 can be interconnected by a hinge and can rotate between an open position and a closed position.

[0115] In Figure 6H and 6I [the above], the remaining fastening devices 138 also fix the first housing member 114 to the second housing member 116. The masking tool 108 can include any number of fastening devices 138 as long as there are enough fastening devices 138 to form a tight connection between the first housing member 114 and the second housing member 116 to prevent the protective coating from penetrating into the inner cavity of the masking tool 108.

[0116] Once the first housing member 114 and the second housing member 116 are fixed together, the first housing member 114 can be fixed to the third base 118 by additional fastening devices 138.

[0117] Although at least one exemplary embodiment of the present invention is disclosed herein, it should be understood that modifications, substitutions, and alternatives may be apparent to those of ordinary skill in the art and can be made without departing from the scope of the present disclosure. The present disclosure is intended to cover any adaptations or variations of the exemplary embodiments. Additionally, in the present disclosure, the terms "comprise" or "include" do not exclude other elements or steps, the term "a" or "an" does not exclude a plurality, the term "or" means one or both, unless otherwise stated in this application. Further, the terms "about", "approximately", and "substantially" encompass a range of plus or minus 15%. Additionally, the described features or steps can also be used in combination with other features or steps and can be used in any order, unless the disclosed content or context otherwise implies.

Claims

1. A masking tool for a turbine assembly, configured to receive and cover a portion of the turbine assembly, the masking tool comprising: A first housing member; A second housing member configured to engage with the first housing member to form a chamber configured to receive a portion of the turbine assembly; And An anchor configured to secure the masking tool to a mounting table, Wherein, when the first housing member and the second housing member are secured together and receive the turbine assembly, the masking tool is configured to expose a portion of the turbine assembly to the atmosphere, Wherein the first housing member and the second housing member are configured to press against each other when secured together, Wherein the first housing member and the second housing member are configured to seal a space containing a portion of the turbine assembly without an elastic seal, and Wherein the inner surfaces of the first housing member and the second housing member are contoured to match the contour of the turbine assembly.

2. The masking tool according to claim 1, wherein the first housing member and the second housing member have an opening that allows a portion of the turbine assembly to be exposed to the surrounding environment while the first housing member and the second housing member are secured together and receive the turbine assembly.

3. The masking tool according to claim 2, wherein the turbine assembly includes turbine blades, and wherein, The portion of the turbine blade is the root pocket region.

4. The masking tool according to claim 2, wherein the turbine assembly includes turbine blades, and wherein, The portion of the turbine blade is the airfoil portion.

5. The masking tool according to claim 2, wherein the turbine assembly includes turbine blades, and wherein, The portion of the turbine blade is the plurality of vanes of a double vane assembly.

6. The masking tool according to claim 1, wherein only the first housing member or the second housing member includes an opening configured to expose a portion of the turbine assembly so that when the turbine assembly is enclosed within the masking tool, only a portion on one side of the turbine assembly remains exposed to the atmosphere.

7. The masking tool according to claim 1, wherein a portion of the inner surface of the first housing member is convex and a portion of the inner surface of the second housing member is concave.

8. The masking tool according to claim 1, wherein the first housing member and the second housing member form a chamber, and when the first housing member and the second housing member are secured together, the top surface of the chamber is open.

9. The masking tool according to claim 8, wherein the first housing member and the second housing member are configured to form a rectangular parallelepiped shape with a portion of the turbine assembly when the first housing member and the second housing member are secured to each other and receive the turbine assembly.

10. The masking tool according to claim 1, formed by a 3D printing method, wherein the chamber is exposed to the atmosphere.

11. A protective coating system for applying a protective coating to a turbine assembly, the system comprising: A housing that encloses a chamber, and the chamber can be accessed through an opening in the door of the housing; A mounting table within the chamber; And The masking tool according to any one of claims 1 to 10, Wherein the anchor of the masking tool is configured to be fixed to the mounting table.

12. The system according to claim 11, wherein the system is a physical vapor deposition (PVD) system that utilizes a cathodic arc coating tool.

13. The system according to claim 11, wherein the system is a low pressure plasma spray (LPPS) system.

14. A method of loading a turbine assembly into a masking tool for protecting a coating system, the method comprising: Separating or partially separating a housing member of the masking tool to open access to a holding chamber of the masking tool; Inserting the turbine assembly into the chamber; And Securing the housing members of the masking tool together to create a tight fit between the housing members of the masking tool and the turbine assembly, the tight fit being substantially impermeable to the protective coating, Wherein, after the housing members of the masking tool are secured together, a portion of the turbine assembly remains uncovered, and Wherein one or more inner surfaces of the housing members are contoured to match the contour of the turbine assembly such that at least a portion of the turbine assembly abuts one or more of the contoured inner surfaces.

15. The method according to claim 14, wherein, The coating-impermeable tight fit between the housing members is formed without an elastomeric seal.

16. The method according to claim 14, wherein the portion of the turbine assembly that remains uncovered is a root pocket region.

17. The method according to claim 14, wherein the portion of the turbine assembly that remains uncovered is an airfoil portion.

18. The method according to claim 14, wherein the turbine assembly is a two-vane assembly, and the portion of the turbine assembly that remains uncovered is a vane.

19. The method according to claim 14, further comprising attaching an anchor to a first housing member of the housing members, wherein the anchor secures the masking tool to a chamber floor, and wherein coating material is deposited on the masking tool and exposed portions of the turbine vanes.

20. The method according to claim 14, wherein the first housing member and the second housing member are connected by a hinge.

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