Turbine assembly holder for imaging

Abstract

A holder configured to hold turbine assemblies in place for internal imaging includes a body configured to support one or more turbine assemblies and one or more holding spaces in the body. Each holding space is configured to hold a respective turbine assembly. Each of the one or more retention spaces is configured to automatically stabilize and orient a respective turbine assembly when the turbine assembly is inserted into the retention space.

Description

Technical Field

[0001] This technology relates to an arrangement for positioning one or more turbine components (including but not limited to turbine blades, turbine vanes, and other such turbine components) for imaging, and particularly to a system for positioning turbine components in multiple predetermined directions for imaging. Background Art

[0002] Turbine components in a gas turbine (such as turbine blades and turbine vanes) are affected by extreme temperatures, stresses, vibrations, and corrosive gases during operation in their exposed working environment. Due to their working environment, turbine components are periodically removed from the gas turbine to inspect for microcracks, corrosion, defects, wear, and other damages (collectively referred to as damages). The inspection includes looking for microcracks and internal defects that are not visible by external inspection in the turbine components.

[0003] X-ray imaging is used to inspect and analyze turbine components. An X-ray imaging system includes an X-ray source and a detector array. The turbine components are mounted between the X-ray source and the detector array in one or more predetermined directions. The turbine components are imaged in each direction. Each direction can image the turbine components to detect potential damages in the turbine components.

[0004] During the imaging process, when the turbine components are irradiated with X-rays, it is necessary to precisely hold the turbine components in each predetermined direction. These directions are selected to detect microcracks and other damages in the turbine components, especially in areas where the turbine components are prone to microcracks and other damages and / or areas where these damages may cause the failure of the turbine components. Precise orientation of the turbine components for inspection helps to detect microcracks and other defects and ensures uniform inspection of many turbine components.

[0005] The traditional practice is to use foam blocks that support the turbine components to orient the turbine components. Moving the turbine components on the foam blocks to a predetermined direction requires a lot of labor to ensure that the turbine components are in the correct direction and do not move during the X-ray imaging process. Summary of the Invention

[0006] The inventors have proposed a system and method to solve the above problems.

[0007] In one aspect of the technology, the retainer is configured to hold the turbine assembly in position for internal imaging. The retainer includes a body configured to support one or more turbine assemblies; and one or more retention spaces in the body, each retention space being configured to hold a corresponding turbine assembly. Each of the one or more retention spaces is configured to automatically secure and orient the corresponding turbine assembly by an interference fit when the turbine assembly is inserted into the retention space. The one or more retention spaces are configured to enable an imaging system to simultaneously capture images of multiple turbine assemblies in one or more directions.

[0008] Another aspect of the technology includes the foregoing aspect, wherein the retainer can be configured to hold the turbine assembly in multiple directions.

[0009] Another aspect of the technology includes any of the foregoing aspects, wherein each of the one or more retention spaces is in the form of a notch in the body, each notch opening at the top and opposite lateral sides.

[0010] Another aspect of the technology includes any of the foregoing aspects, wherein each notch is oriented at an angle relative to the horizontal plane so that the notch receives the corresponding turbine assembly along a plane intersecting the horizontal at an angle.

[0011] Another aspect of the technology includes any of the foregoing aspects, wherein the one or more retention spaces include two sets of retention spaces, each retention space in the first set of retention spaces being configured to hold the corresponding turbine assembly in a first direction, and each retention space in the second set of retention spaces being configured to hold the corresponding turbine assembly in a second direction.

[0012] Another aspect of the technology includes any of the foregoing aspects, wherein the one or more retention spaces are defined by opposing contoured surfaces.

[0013] Another aspect of the technology includes any of the foregoing aspects, wherein the retainer is formed by three-dimensional (3D) printing.

[0014] In yet another aspect of the technology, an X-ray imaging system for imaging multiple turbine assemblies includes: an X-ray source; a digital detector array; a retainer according to any of the foregoing aspects (the retainer being located between the X-ray source and the digital detector); and a control system configured to drive the X-ray source and receive data from the digital detector.

[0015] In yet another aspect of the technology, the retainer is configured to hold a plurality of turbine components in place for internal imaging. The retainer includes a body configured to support the plurality of turbine components; a first set of notches on the body configured to hold the turbine components in a first direction; and a second set of notches on the body configured to hold the turbine components in a second direction. Each notch of the first set of notches and the second set of notches is configured to automatically secure and orient a corresponding turbine component when the turbine component is inserted into the retention space. The first set of notches and the second set of notches are configured to enable an imaging system to simultaneously capture images of the plurality of turbine components in one or more directions.

[0016] Another aspect of the technology includes the foregoing aspect, wherein each notch of the first set of notches and the second set of notches opens at the top and opposite lateral sides.

[0017] Another aspect of the technology includes any of the foregoing aspects, wherein each notch of the first set of notches and the second set of notches is oriented at an angle relative to a horizontal plane such that the notch receives a corresponding turbine component along a plane intersecting the horizontal at an angle.

[0018] Another aspect of the technology includes any of the foregoing aspects, wherein the notches of the first set of notches and the second set of notches are defined by opposing contoured surfaces.

[0019] Another aspect of the technology includes any of the foregoing aspects, wherein the notches of the first set of notches and the second set of notches are configured to hold the roots of the corresponding turbine components.

[0020] Another aspect of the technology includes any of the foregoing aspects, wherein the retainer is formed by three-dimensional (3D) printing.

[0021] In yet another aspect of the technology, an X-ray imaging system for imaging a plurality of turbine components includes: an X-ray source; a digital detector array; a retainer according to any of the foregoing aspects (the retainer being located between the X-ray source and the digital detector); and a control system configured to drive the X-ray source and receive data from the digital detector.

[0022] In yet another aspect of the technology, a method for positioning a turbine component for X-ray imaging includes sliding the turbine component into a receiving space in a turbine component retainer; and positioning the turbine component and the turbine component retainer between an X-ray source and a digital detector array. When the turbine component is slid into an opening in the turbine component retainer, the turbine component is automatically oriented in a target position for imaging the internal structure of the turbine component, and when the turbine component is slid into the opening in the turbine component retainer, the turbine component is automatically secured in the receiving space. One or more receiving spaces enable the imaging system to simultaneously capture images of a plurality of turbine components in one or more directions.

[0023] Another aspect of the technology includes the foregoing aspect, wherein the turbine component retainer includes a first set of receiving spaces and a second set of receiving spaces. The first set of receiving spaces can receive the turbine component only in a first direction. The second set of receiving spaces can receive the turbine component only in a second direction different from the first direction.

[0024] Another aspect of the technology includes any of the foregoing aspects, wherein the method further includes imaging a plurality of turbine components simultaneously. The plurality of turbine components are secured on the same turbine component retainer, and the turbine component retainer holds different turbine components in different directions.

[0025] Another aspect of the technology includes any of the foregoing aspects, wherein the turbine component is held in place within the receiving space by gravity.

[0026] Another aspect of the technology includes any of the foregoing aspects, wherein the turbine component is held in place by an interference fit.

[0027] In another aspect of the technology, the turbine component retainer can be used to present the turbine component for X-ray inspection without the need for additional components or only minimal additional components to support the turbine component. The turbine component retainer can also be used to support the turbine component during other types of non-destructive testing (NDT) or during destructive testing. Compared with the conventional technique using foam support, the turbine component retainer can orient the turbine component in a faster manner for inspection. The turbine component retainer can also quickly disassemble the turbine component that has been X-ray imaged and place it into the retainer of another turbine component. This speeds up the process of installing the turbine component to be inspected, X-ray imaging the turbine component, and removing the turbine component after imaging. By ensuring a uniform orientation of the turbine components, the turbine component retainer can also image each turbine component from the same direction, thereby improving the inspection of the turbine components. Since the turbine component retainer can quickly install the turbine component for X-ray imaging and hold the turbine component in a uniform orientation during the imaging process, the inspection of the turbine components is faster and more uniform compared with using foam blocks to support the turbine components.

[0028] In another aspect of the technology, the turbine component retainer can be 3D printed from any material (any rigid and inelastic material) having a hardness of about 80 or higher and a tensile strength of at least 750 megapascals. All retainer components can be printed and assembled together without fasteners and can hold the turbine component from two different angles so that an X-ray imaging machine can capture an internal view of the turbine component when inspecting it. A set of turbine components can be held in a first direction, where the base of the turbine component is held at a position of about +45 degrees, and another set of turbine components can be held in a second direction, opposite to the first direction, where the base of the turbine component is held at a position of about -45 degrees. The retainer can have a dovetail design with an interference fit to help stabilize the turbine component. The turbine component retainer can hold all turbine components in the same direction rather than multiple directions to leave more space between the turbine components. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 FIG. shows a schematic diagram of an X-ray imaging system.

[0030] Figure 2 FIG. shows a perspective view of an exemplary turbine component retainer.

[0031] Figure 3 FIG. shows Figure 2 a cross-sectional view of the turbine component retainer in

[0032] Figure 4 FIG. shows Figure 2 another perspective view of the turbine component retainer with the turbine component.

[0033] Figure 5 FIG. shows Figure 2 a top view of the turbine component retainer of

[0034] Figure 6 FIG. shows a perspective view of another turbine component retainer.

[0035] Figure 7 FIG. shows a top view of another turbine component retainer.

[0036] Figure 8 FIG. shows a flowchart of a method for taking images of turbine components in different directions. DETAILED DESCRIPTION

[0037] The embodiments described herein refer to turbine components, including but not limited to blades, vanes, and / 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.

[0038] Figure 1An exemplary X-ray imaging system 10 for capturing X-ray images of a turbine blade 12 is shown. The X-ray imaging system 10 can be used to detect microcracks or other signs of fatigue and wear. The X-ray imaging system 10 can include an X-ray source 14, a digital detector array 16 with an imaging region 18, a platform 20 for supporting the turbine blade 12, and a control system 22.

[0039] Figure 2 An exemplary blade holder 24 is shown, which can be positioned on the platform 20 and can be configured to hold one or more turbine blades 12 in a predetermined or preset orientation relative to the X-ray source 14 and the digital detector array 16. The blade holder 24 can include a body 26 and one or more stabilizing supports 28 (e.g., four) that provide support and stability to the body 26.

[0040] The body 26 can include one or more holding spaces 30, each holding space 30 being configured to hold one turbine blade 12 in a specific orientation. In Figures 2 - 6 the exemplary configuration shown, the body 26 is in the form of a substantially rectangular (or beam-shaped), and the holding spaces 30 are in the form of notches in the substantially rectangular.

[0041] Although the body 26 is shown as a beam with notches, the body 26 can have any shape that is configured to secure the root of the turbine blade 12 in a specific orientation relative to the X-ray source 14 and the digital detector array 16 having the imaging region 18. The notches can have opposing surfaces consisting of parallel ridges and grooves that mate with the fir-tree root of each turbine blade to be inserted into each notch. The gap between each notch can be narrowest at one end of the notch that receives the lower end of the fir-tree root or dovetail of the turbine blade, and widest at the other end of the notch, which wide end may be adjacent to the platform of the turbine blade. The platform is located between the fir-tree root and the airfoil of the turbine blade. Additionally, the stabilizing supports 28 can extend laterally from the body 26 to provide a stable base for the body 26.

[0042] The body 26 and the stabilizing supports 28 can be 3D printed, molded, welded, or a combination of both, and can be made of resin, other types of plastics, or other materials (such as metal) with a hardness of 80 MPa or higher and a tensile strength of at least 705 MPa. It is contemplated that the material can be rigid and inelastic.

[0043] The body 26 and the stabilizing supports 28 can be integrally formed and can include a single integrated continuum. Alternatively, the body 26 and the stabilizing supports 28 can be formed separately and assembled together. It is contemplated that when formed separately, the body 26 and the stabilizing supports can be formed in a manner that does not require fasteners to secure the components together. For example, the components can be assembled together by an interference fit, adhesion, and adhesives.

[0044] It can also be considered that the body 26 can have a shape that can stably support itself without the stabilizing support 28. In this configuration, the stabilizing support 28 can be omitted. In addition, the body 26 and / or the stabilizing support 28 can include fasteners such as clamps, clips, and bolts, which can be releasably engaged with the platform 20. It can also be considered to integrate the blade holder 24 into the platform 20 so that the platform 20 and the blade holder 24 form a single unit.

[0045] As Figure 2 shown, the holding spaces 30 can be linearly arranged along the length of the body 26. In addition, the holding spaces 30 can be open at the top and on the lateral sides so that the turbine blades 12 can be inserted into the holding spaces 30 from above. The open lateral sides of the holding spaces 30 allow the turbine blades 12 to hang on the sides of the body 26 (see Figure 4 ).

[0046] Figure 3 More details of the holding spaces 30 are shown. It can be seen that each holding space 30 can be formed by a bottom wall 32, a rear surface 34, and a front surface 36 opposite the rear surface 34. Each rear surface 34 and front surface 36 can extend from the bottom wall 32 to the upper side of the body 26. In addition, the distance from the bottom wall 32 to the top of the body 26 (i.e., the depth of the holding space 30) is about 2 to 10 centimeters (e.g., about 3 to about 5 centimeters). It can be considered that the depth of the holding space 30 is about 5 centimeters.

[0047] In addition, each holding space 30 (e.g., a notch) can be angled with respect to the horizontal plane. For example, the orientation of the bottom wall 32 can be such that a plane 38 perpendicular to the bottom wall 32 forms an angle α with the horizontal plane. The angle α can be between about 20 degrees and about 90 degrees. For example, the angle α can be between about 30 degrees and about 80 degrees. It can be considered that the angle α can be about 30 degrees, about 45 degrees, or about 60 degrees. In addition, the angle α of each holding space 30 can be the same throughout the body 26. In this way, X-ray analysis and the positioning of multiple turbine blades 12 on the body 26 can be kept consistent. In addition, the turbine blades 12 can be inserted into the holding spaces 30 along the direction of the plane 38. In other words, the turbine blades 12 can be inserted into or removed from the holding spaces 30 at an angle α.

[0048] In one configuration, the size and shape of the holding spaces 30 can be used to hold a fir tree root or a dovetail or root (hereinafter referred to as the root 40) (see Figure 4 ). For example, the rear surface 34 and the front surface 36 of each receiving space 30 can be contoured, and this contour 42 (see Figure 3 and Figure 5 ) can match the contour of the root 40 of the turbine blade 12. AsFigure 4 As shown, the profiles of the rear surface 34 and the front surface 36 are interlocked with the profile of the root 40 of the turbine blade 12 to limit or prevent lateral movement of the turbine blade 12 through the retention space 30. It is contemplated that the rear surface 34 and the front surface 36 may not be profiled.

[0049] Figure 5 is a top view of a cross-section of the body 26. It can be seen that the body 26 may have a first lateral side 44 and a second lateral side 46. Additionally, each retention space 30 may be separated from each other by a dividing wall 48. One side of each dividing wall 48 may be the rear surface 34 and the other side of the dividing wall 48 may be the front surface 36. Additionally, each retention space 30 may be in the form of a lateral dovetail. For example, for a particular retention space 30, the distance between the dividing walls 48 defining the retention space 30 may be greater on the first lateral side 44 than on the second lateral side 46. The directions of the two defining dividing walls 48 may form an angle θ, which may be between about 20 degrees and about 80 degrees. For example, between about 35 degrees and about 65 degrees. It is contemplated that the angle θ may be about 30 degrees, about 45 degrees, about 50 degrees, or about 60 degrees. The angle θ may match the angle formed by the two sides of the root 40 of the turbine blade 12.

[0050] In addition, as Figure 5 shown, the direction of the "lateral dovetail" may alternate between adjacent retention spaces 30. For example, for one retention space 30, the wider side of the dovetail may be located on the first lateral side 44 of the body 26 and the narrower side of the dovetail may be located on the second lateral side 46 of the body 26. For a second adjacent retention space 30, the narrower side of the dovetail may be located on the first lateral side 44 of the body 26 and the wider side of the dovetail may be located on the second lateral side 46 of the body 26.

[0051] The distance between the first lateral side 44 and the second lateral side 46 (i.e., the width of the retention space 30 and the width of the body 26) may be in the range of about 2 to about 10 centimeters (e.g., about 3 to about 5 centimeters). It is contemplated that the width of the retention space 30 (and the body 26) is about 5 centimeters. Additionally, the distance between the dividing walls 48 may be in the range of about 1 centimeter to about 3 centimeters (e.g., about 3 centimeters). As embodied in the present disclosure, the width size of the retention space 30 corresponds to the respective blade root, and thus the above width ranges are merely exemplary and are not intended to limit the present embodiment in any way.

[0052] Due to the alternating dovetail configuration, adjacent turbine blades 12 will be oriented in opposite directions. For example, in a first set of receiving spaces 30, the airfoil portions 50 of the turbine blades 12 will be positioned near the first lateral side 44 of the body 26, while in a second set of receiving spaces 30, the airfoil portions 50 of the turbine blades 12 will be positioned near the second lateral side 46 of the body 26. Since adjacent turbine blades 12 are oriented in opposite directions, the distance between the turbine blades 12 can be reduced, and more turbine blades 12 can be held on the blade holder 24 simultaneously, such that more turbine blades 12 can be analyzed at the same time.

[0053] Figure 6 Another arrangement of the receiving spaces 30 is shown. In particular, the dividing wall 48 is arranged such that all the receiving spaces 30 are wider on the same lateral side and narrower on the same lateral side. For example, as Figure 6 shown, the first lateral side 44 of all the receiving spaces 30 is wider than the second lateral side 46. It goes without saying that there may be arrangements where the opposite is the case. In this arrangement, all the turbine blades 12 can be oriented such that the airfoil portions 50 are located near the first lateral side 44, and vice versa. Although the capacity of the blade holder 24 in this arrangement may be less than Figures 2 - 5 the capacity of the "alternating" arrangement shown in

[0054] Figure 7 Another arrangement of the receiving spaces 30 is shown. In particular, Figure 7 the receiving spaces 30 in Figures 2 - 6 can be arranged laterally instead of longitudinally. It can be seen that the receiving spaces 30 can take the form of back-to-back dovetails, with one dovetail located on the first lateral side 44 of the body 26 and the other dovetail located on the second lateral side 46 of the body 26. The dividing wall 48 can extend longitudinally instead of extending laterally as in the arrangement shown in

[0055] In all arrangements of the turbine blade retainer 24, the turbine blade 12 can be inserted into the corresponding retaining space 30 from above (e.g., dropped or lowered into the retaining space 30). Additionally, due to the special shape of the retaining space 30, the turbine blade 12 can only be inserted into the retaining space 30 in a specific orientation. Further, inserting the turbine blade 12 into the retaining space 30 automatically secures the turbine blade 12 and automatically positions the turbine blade 12 in the desired location. In other words, the retaining space 30 is designed to hold and retain the turbine blade 12 in place using gravity during the analysis process. Additionally, the dimensions of the retaining space 30 can hold the turbine blade 12 in place with an interference fit without the need for any additional components such as clamps or latches to hold the turbine blade 12 in place.

[0056] Further, while the configurations shown in the figures include four or eight retaining spaces 30, it is contemplated that the blade retainer 24 can include any number of retaining spaces 30, e.g., from one retaining space 30 to twenty or more retaining spaces 30. Additionally, the body 26 can be modular, with each module containing one or more retaining spaces 30. These modules can be combined with other modules to obtain the desired number of retaining spaces 30. Further, different modules can be mixed and matched so that turbine blades 12 of different sizes or different shapes can be analyzed simultaneously. The modules can be held together by dovetails, interference fits, snap fits, fasteners, and magnets, among other means.

[0057] Figure 8 A method 100 for taking images of the turbine blade 12 during inspection is shown. The method 100 can first mount the turbine blade 12 onto the blade retainer 24 (step 102). The turbine blade 12 can be inserted into the retaining space 30 from above. Additionally, when the turbine blade 12 is inserted into the retaining space 30, the orientation of the dovetail shape of each retaining space 30 determines the orientation of the turbine blade 12. For Figures 2 - 5 the blade retainer 24 shown, the first set of turbine blades can be oriented such that the airfoil portions extend laterally in a first direction, while the second set of turbine blades can be oriented such that the airfoil portions extend laterally in a second direction opposite the first direction.

[0058] It is also contemplated that all of the turbine blades 12 can be positioned in the same orientation (see Figure 6the configuration shown). Additionally, the turbine blades 12 can be positioned such that adjacent turbine blades 12 have different orientations. Further, the blade retainer 24 can have a first portion that holds the turbine blade 12 in a first orientation and a second portion that holds the turbine blade 12 in a second orientation. It can also be contemplated that the turbine retainer 24 can hold the turbine 12 in three or more different orientations. Additionally, turbines can be loaded on multiple blade retainers 24. The multiple blade retainers 24 can hold the turbine blades 12 in the same orientation. Alternatively, each blade retainer 24 can hold the turbine blade 12 in an orientation different from that of the other blade retainers 24.

[0059] Once the turbine blade 12 is loaded onto one or more blade retainers 24, the blade retainer 24 can be placed between the X-ray source 14 and the digital detector array 16. The X-ray source 14 can be activated to emit a beam of X-ray radiation that passes through the turbine blade 12 and reaches the digital detector array 16 to take an image of the turbine blade 12 (step 104).

[0060] Once the image is taken, the orientation of the turbine blade 12 can be changed (step 106). One way to change the orientation of the turbine blade 12 is to rotate the blade retainer 24 by approximately 180 degrees. In this way, the turbine blade 12 that was originally in the first orientation will now be in the second orientation. Additionally, the blade that was originally in the second orientation will now be in the first orientation.

[0061] Another way to change the orientation of the turbine blade 12 is to move the turbine blade 12 to a different holding space 30 such that the turbine blade 12 that was originally in the first holding space 30 oriented in the first direction can be moved to the second holding space 30 oriented in the second direction. It can be contemplated that for a configuration using multiple blade retainers 24, the turbine blades 12 can be interchanged between different blade retainers 24.

[0062] Once the orientation of the turbine blade 12 is changed, another image of the turbine blade 12 can be taken (step 108). This can be achieved in the same manner as taking the image in step 104. Additionally, once the second image is taken, it can be determined whether the turbine blade 12 has been imaged in all the desired orientations (step 110). If there are more orientations that need to be imaged, step 106 can be repeated. Conversely, the turbine blade 12 can be removed from the blade retainer 24 (step 112) and method 100 can end.

[0063] 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 may 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. Further, in the present disclosure, the terms "comprising" or "including" do not exclude other elements or steps, the term "a" or "an" does not exclude a plurality, the term "or" means either one or both, unless otherwise stated in the present application. Further, the terms "about", "approximately", and "substantially" encompass a range of plus or minus 15%. Further, the features or steps that have been described may also be used in combination with other features or steps and may be used in any order, unless the disclosure or context otherwise implies. The present disclosure hereby incorporates by reference the entire disclosure of any patent or application from which it claims benefit or priority.

Claims

1. A retainer configured to hold a turbine assembly in place for internal imaging, the retainer comprising: A body configured to support one or more turbine assemblies; And One or more retention spaces in the body, each retention space configured to hold a corresponding turbine assembly, Wherein each of the one or more retention spaces is configured to automatically secure and orient the corresponding turbine assembly by an interference fit when the turbine assembly is inserted into the retention space, and Wherein the one or more retention spaces are configured to enable an imaging system to simultaneously capture images of multiple turbine assemblies in one or more directions.

2. The retainer according to claim 1, wherein the retainer is configured to hold the turbine assembly in multiple directions.

3. The retainer according to claim 1, wherein each of the one or more retention spaces is in the form of a notch in the body, each notch opening at the top and opposite lateral sides.

4. The retainer according to claim 3, wherein each notch is oriented at an angle with respect to the horizontal plane such that the notch receives the corresponding turbine assembly along a plane intersecting the horizontal at the angle.

5. The retainer according to claim 1, wherein the one or more retention spaces include two sets of retention spaces, each retention space in the first set of retention spaces being configured to hold the corresponding turbine assembly in a first direction, and each retention space in the second set of retention spaces being configured to hold the corresponding turbine assembly in a second direction.

6. The retainer according to claim 1, wherein the one or more retention spaces are defined by opposing contour surfaces.

7. The retainer according to claim 1, wherein the retainer is formed by three-dimensional printing.

8. The retainer according to claim 1, wherein the retainer is configured to hold turbine blades.

9. An X-ray imaging system for imaging multiple turbine blades, the system comprising: An X-ray source; A digital detector array; The retainer according to any one of claims 1 to 8, the retainer being located between the X-ray source and the digital detector; And A control system configured to drive the X-ray source and receive data from the digital detector.

10. A retainer configured to hold multiple turbine blades in place for internal imaging, the retainer comprising: A body configured to support the multiple turbine blades; A first set of notches on the body configured to hold the turbine blades in a first direction; A second set of notches on the body configured to hold the turbine blades in a second direction; Wherein each notch in the first set of notches and the second set of notches is configured to automatically secure and orient the corresponding turbine blade when the turbine blade is inserted into the retention space, and Wherein the first set of notches and the second set of notches are configured to enable an imaging system to simultaneously capture images of multiple turbine blades in one or more directions.

11. The retainer according to claim 10, wherein each notch of the first set of notches and the second set of notches opens at the top and opposite lateral sides.

12. The retainer according to claim 10, wherein each notch of the first set of notches and the second set of notches is oriented at an angle with respect to a horizontal plane so that the notch receives a corresponding turbine blade along a plane intersecting the horizontal at the angle.

13. The retainer according to claim 10, wherein the notches of the first set of notches and the second set of notches are defined by opposing contoured surfaces.

14. The retainer according to claim 13, wherein the notches of the first set of notches and the second set of notches are configured to hold the roots of corresponding turbine blades.

15. The retainer according to claim 10, wherein the retainer is formed by three-dimensional printing.

16. An X-ray imaging system for imaging a plurality of turbine blades, the system comprising: an X-ray source; a digital detector array; a retainer according to any one of claims 10 to 15, the retainer being located between the X-ray source and the digital detector; and a control system configured to drive the X-ray source and receive data from the digital detector.

17. A method for positioning a turbine blade for X-ray imaging, the method comprising: sliding the turbine blade into a receiving space in a blade retainer; and positioning the turbine blade and the blade retainer between an X-ray source and a digital detector array, wherein sliding the turbine blade into an opening in the blade retainer automatically orients the turbine blade to a target position for imaging the internal structure of the turbine blade, wherein sliding the turbine blade into the opening in the blade retainer automatically secures the turbine blade in the receiving space, and wherein the one or more receiving spaces enable an imaging system to simultaneously capture images of a plurality of turbine blades in one or more directions.

18. The method according to claim 17, wherein the blade retainer includes a first set of receiving spaces and a second set of receiving spaces, Among them, the first set of receiving spaces being configured to receive the turbine blade only in a first direction, wherein the second set of receiving spaces is configured to receive the turbine blade only in a second direction different from the first direction.

19. The method according to claim 17, further comprising simultaneously imaging a plurality of turbine assemblies, wherein the plurality of turbine assemblies are secured to the same turbine assembly retainer, the turbine assembly retainer holding different turbine assemblies in different orientations.

20. The method according to claim 17, wherein the turbine blade is held in place within the receiving space by gravity.

21. The method according to claim 17, wherein the turbine blade is held in place by an interference fit.

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