阅读说明：本技术 冷却孔的自动化识别和工具路径生成 (Automated identification of cooling holes and tool path generation ) 是由 拉杰什·拉马穆尔蒂 凯文·乔治·哈丁 乔纳森·马修·洛马斯 瓦迪姆·布朗伯格 于 2018-09-28 设计创作，主要内容包括：本发明提供了一种处理零件的方法,该方法包括：使用零件(36)的计算机辅助设计(CAD)模型来识别(2502)设置在零件中的至少一个孔(62)的位置；在安装系统(56)中对准(2504)零件；3D扫描(2506)零件(36)；至少部分地基于得自3D扫描(2506)零件的至少一个基准来检测(2520)孔(36)的至少一个边界特征；以及至少部分地基于边界特征来生成(2536)第一工具路径(92)。(The invention provides a method of processing a part, the method comprising: identifying (2502) a location of at least one hole (62) disposed in the part using a computer-aided design (CAD) model of the part (36); aligning (2504) the part in a mounting system (56); 3D scanning (2506) the part (36); detecting (2520) at least one boundary feature of the hole (36) based at least in part on at least one fiducial from the 3D scanned (2506) part; and generating (2536) a first tool path (92) based at least in part on the boundary features.)

1. A method of processing a part, the method comprising:

identifying 2502 a location of at least one hole 62 disposed in the part using a computer-aided design (CAD) model of the part 36;

aligning 2504 the part in the mounting system 56;

3D scanning 2506 the part 36;

detecting 2520 at least one boundary feature of the at least one hole 36 based at least in part on at least one fiducial from the 3D scan 2506 of the part; and

a first tool path 92 is generated 2536 based at least in part on the at least one boundary feature.

2. The method of claim 1, further comprising repairing the part based at least in part on the first tool path,

wherein repairing the part further comprises at least one of drilling, milling, machining, recoating, resurfacing, and reshaping, and

wherein the at least one hole comprises a cooling hole.

3. The method of claim 1, further comprising:

defining a hole coordinate system,

wherein the hole coordinate system comprises a cylindrical coordinate system, wherein a center line of a cylinder of the cylindrical coordinate system represents a position and an orientation of a center line of the at least one hole, and

wherein the diameter of the cylinder represents the pore size of the at least one pore.

4. The method of claim 1, wherein aligning the part in a mounting system further comprises aligning the part in a mounting system via a multi-axis robotic arm.

5. The method of claim 1, further comprising:

selecting at least one well;

wherein the at least one selected hole satisfies at least one predetermined threshold, and

wherein a second 3D scan is performed on the selected at least one hole.

6. The method of claim 1, further comprising generating a structured 3D point cloud using data from a 3D scan of the part,

wherein the at least one hole comprises a cooling hole, and

wherein detecting at least one boundary feature of the at least one cooling hole further comprises detecting at least one of: a cooling hole downstream corner, a cooling hole ramp portion, a cooling hole sidewall, and a cooling hole free edge.

7. The method of claim 6, further comprising detecting a cooling hole ramp portion,

wherein the cooling hole ramp portion forms a transition between the metering portion of the cooling hole and the base of the part.

8. The method of claim 6, further comprising detecting a cooling hole free edge,

wherein the cooling hole free edge forms a transition between a non-normal surface of the part and a base of the part, and

wherein the base of the part has a normal surface orientation.

9. The method of claim 5, wherein detecting at least one boundary feature of the at least one hole further comprises detecting at least one boundary feature using surface normativity data obtained from the second 3D scan.

10. The method of claim 5, further comprising superimposing a first projection of a nominal hole boundary on a structured 3D point cloud from at least one of the initial 3D scan and the second 3D scan.

11. The method of claim 10, wherein the nominal aperture boundary is shell-shaped.

12. The method of claim 10, further comprising defining at least one offset between the first projection of nominal hole boundaries and the structured 3D point cloud;

wherein the at least one offset comprises at least one of translation and rotation.

13. The method of claim 12, further comprising:

refining and scaling the first projection using the at least one offset to generate a second projection, the second projection being a scaled version of the first projection; and

superimposing the second projection of a nominal hole boundary on the structured 3D point cloud from the second 3D scan.

14. The method of claim 13, further comprising:

at least one of the outlier data points is removed,

wherein the at least one outlier data point comprises at least one of: a first portion of the structured 3D point cloud disposed within the second projection having a normal surface orientation, and a second portion of the structured 3D point cloud disposed outside the second projection having a non-normal surface orientation.

15. The method of claim 14, further comprising rescaling the second projection after removing the at least one outlier data.

16. The method of claim 13, wherein generating a first tool path further comprises generating the first tool path based at least in part on the second projection.

17. The method of claim 16, further comprising mapping the first tool path on the structured 3D point cloud.

18. The method of claim 17, further comprising:

combining the first tool path with at least one part geometry datum of the at least one hole to generate a second tool path,

wherein the second tool path is a refined version of the first tool path, and

wherein repairing the part at least partially according to the first tool path further comprises repairing based at least partially on the second tool path.

19. The method of claim 18, wherein the at least one part geometry datum of the at least one hole comprises:

a metering section;

a diffusion section downstream of the metering section; and

in the throat part of the water-jet engine,

wherein the throat portion transitions between the metering section and the diffusing section.

20. The method of claim 19, further comprising:

removing at least one outlier data point; and

rescaling the second projection after removing the at least one outlier data,

wherein the at least one outlier data point comprises at least one of: a first portion of the structured 3D point cloud disposed within the second projection having a normal surface orientation and a second portion of the structured 3D point cloud disposed outside the second projection having a non-normal surface orientation,

wherein the at least one hole comprises a cooling hole,

wherein detecting at least one boundary feature of the at least one cooling hole further comprises detecting at least one of: a cooling hole downstream corner, a cooling hole ramp portion, a cooling hole sidewall and a cooling hole free edge, and

wherein the nominal aperture boundary is shell-shaped.

Background

The present disclosure relates generally to cooling structures for gas turbines, and more particularly to systems and methods related to turbine airfoils.

In large frame heavy duty industrial gas turbine engines, a hot gas stream produced in a combustor is passed through a turbine to produce mechanical work. The turbine includes one or more rows or stages of stator vanes and rotor blades that react with a hot gas stream at progressively lower temperatures. The turbine and thus the efficiency of the engine can be increased by passing a higher temperature gas stream into the turbine. However, the turbine inlet temperature may be limited by the material properties of the turbine (particularly the first stage stator wheel and rotor blades) and the amount of cooling capacity of these first stage airfoils.

The first stage rotor and stator components are exposed to the highest gas flow temperatures, with the temperatures gradually decreasing as the gas flow passes through the turbine stages. The first and second stage airfoils (rotor blades and stator vanes) should be cooled by passing cooling air through internal cooling passages and exhausting the cooling air through film cooling holes to provide a blanket layer of cooling air to protect the cooling surfaces from the hot gas flow.

Turbine rotor blades, stationary impellers, and cooling passages therein typically require inspection, for example, to determine if the cooling passages have become blocked and/or to determine if the geometry of the part has deviated from the intended design. However, because of the large number of turbine airfoils (rotor blades and stator vanes) present in a gas turbine engine and the large number of cooling passages and holes typically present in each airfoil, manually inspecting each hole is a time consuming task.

Disclosure of Invention

Various aspects and advantages of the disclosure will be set forth in part in the following description, or may be learned by practice of the disclosure.

In one embodiment, a method of processing a part comprises: identifying 2502 a location of at least one hole 62 disposed in the part using a computer-aided design (CAD) model of the part 36; aligning 2504 the part in the mounting system 56; 3D scanning 2506 part 36; detecting 2520 at least one boundary feature of the aperture 36 based at least in part on at least one fiducial from the 3D scan 2506 part; and generating 2536 a first tool path 92 based at least in part on the boundary features.

These and other features, aspects, and advantages of the present disclosure will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.

Drawings

A full and enabling disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

FIG. 1 is a schematic illustration of an exemplary gas turbine that may incorporate embodiments of the present description;

FIG. 2 is an enlarged cross-sectional side view of a portion of an exemplary turbine rotor blade;

FIG. 3 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 4 is an exemplary view of an airfoil, an alignment system, and a mounting system;

FIG. 5 is an exemplary view of an airfoil;

FIG. 6 is an exemplary view of an airfoil;

FIG. 7 is an exemplary view of an airfoil;

FIG. 8 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 9 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 10 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 11 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 12 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 13 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 14 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 15 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 16 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 17 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 18 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 19 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 20 is an exemplary side view schematic of a cooling hole;

FIG. 21 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 22 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 23 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 24 is an enlarged view of a portion of a substrate including cooling holes;

FIG. 25 is a top view of the tool path;

FIG. 26 is a bottom view of the tool path;

FIG. 27 is a side view of the tool path; and

fig. 28 is a method of repairing a component according to various embodiments of the present disclosure.

Repeat use of reference characters in the present specification and drawings is intended to represent same or analogous features or elements of the present disclosure.

Detailed Description

Reference will now be made in detail to the various aspects of embodiments of the invention, one or more examples of which are illustrated in the figures. Detailed description the detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of embodiments of the invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one element from another and are not intended to denote the position or importance of the various elements. The terms "upstream" (or "rearward") and "downstream" (or "forward") refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" or "rearward" refers to the direction from which fluid flow comes, sometimes referred to as "rearward". "downstream" or "forward" refers to the direction of fluid flow, sometimes referred to as "forward". The term "radially" refers to relative directions substantially perpendicular to the axial centerline of a particular component, and the term "axially" refers to relative directions substantially parallel to the axial centerline of a particular component. The terms "circumferential" and "tangential" may refer to directions aligned with the circumference of a rotating turbine or compressor rotor.

Approximating language, as used herein throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms (such as "about", "about" and "substantially") is not to be limited to the precise value specified. In at least some cases, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be combined and/or interchanged. Unless context or language indicates otherwise, such ranges are identified and include all sub-ranges subsumed therein.

Each example is provided by way of explanation of embodiments of the invention, not limitation of embodiments of the invention. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments of the present invention without departing from the scope or spirit of the embodiments of the invention. For instance, features illustrated or described as part of one embodiment, can be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present embodiments cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents. While exemplary aspects of embodiments of the invention will generally be described in the context of a gas turbine for illustrative purposes, one of ordinary skill in the art will readily appreciate that various aspects of embodiments of the invention may be applied to any turbo-machine and are not limited to industrial gas turbines, unless expressly recited in the claims. Although an industrial, marine, or land-based gas turbine is shown and described herein, the present disclosure as shown and described herein is not limited to land-based and/or industrial and/or marine gas turbines unless otherwise specified in the claims. For example, the disclosure as described herein may be used with any type of turbine, including but not limited to aeroderivative or marine gas turbines, as well as aeronautical and/or aircraft engines.

Referring now to the drawings, in which like reference numerals refer to like parts, FIG. 1 illustrates an example of a gas turbine 10 that may incorporate various aspects of embodiments of the present invention. As shown, the gas turbine 10 generally includes a compressor section 12 having an inlet 14 disposed at an upstream end of the gas turbine 10, and a casing 16 at least partially surrounding the compressor section 12. The gas turbine 10 also includes a combustion section 18 downstream of the compressor section 12 having at least one combustor 20, and a turbine section 22 downstream of the combustion section 18. As shown, the combustion section 18 may include a plurality of combustors 20. A shaft 24 extends axially through the gas turbine 10. Fig. 1 shows a radial direction 94, an axial direction 92, and a circumferential direction 90.

In operation, air 26 is drawn into inlet 14 of compressor section 12 and gradually compressed to provide compressed air 28 to combustion section 18. The compressed air 28 flows into the combustion section 18 and mixes with fuel in the combustor 20 to form a combustible mixture. The combustible mixture is combusted in the combustor 20, thereby producing hot gases 30 that flow from the combustor 20 through a first stage 32 of a turbine nozzle 34 and into the turbine section 22. The turbine section generally includes one or more rows of rotor blades 36 axially separated by an adjacent row of turbine nozzles 34. Rotor blades 36 are coupled to rotor shaft 24 via a rotor disk. The rotor shaft 24 rotates about the engine centerline CL. A turbine casing 38 at least partially surrounds the rotor blades 36 and the turbine nozzle 34. Each or some of the rows of rotor blades 36 may be concentrically surrounded by a shroud block assembly 40 disposed within the turbine casing 38. As the hot gas 30 flows through the turbine section 22, it expands rapidly. Thermal and/or kinetic energy is transferred from the hot gas 30 to each stage of the rotor blades 36, thereby causing the shaft 24 to rotate and produce mechanical work. The shaft 24 may be coupled to a load, such as a generator (not shown), to generate electrical power. Additionally or alternatively, the shaft 24 may be used to drive the compressor section 12 of the gas turbine.

FIG. 2 provides an enlarged cross-sectional side view of an exemplary turbine rotor blade or airfoil 36 extending from an axially forward leading edge 44 to an axially aft trailing edge 46, and from a radially inward root 48 to a radially outward tip 42. The airfoil 36 includes a platform 50 that defines a radially inner boundary of the hot gas path. The airfoil 36 also includes at least one substrate 52 in which cooling holes, such as film cooling holes (not shown), may be disposed. The substrate including the cooling holes may be located on any portion of the airfoil, including the leading edge 44, the trailing edge 46, the tip 42, as well as on the airfoil pressure side and/or the airfoil suction side. The airfoil 36 of FIG. 2 serves as an exemplary component illustrating the systems and methods described herein, which are also applicable to turbine stator wheels, turbine nozzles, combustor liners, shrouds, and other components including substrates and/or surfaces having cooling holes disposed therein.

FIG. 3 illustrates a portion of a base 52 of an airfoil 36 including cooling holes 54. A Computer Aided Design (CAD) model may be used to identify the location of the cooling holes 54. Each cooling hole 54 may be represented in CAD by a cylinder 60, where the center line of the z-axis of the cylinder 60 is aligned with the location and orientation of the center of the cooling hole 54. The diameter of the cylinder 60 may be sized to match the bore diameter of the cooling holes 54. Thus, many aspects of the geometry of the cooling holes 54 may be represented in CAD using a cylinder. In other embodiments, elliptical, trapezoidal, triangular, rectangular, and/or other shaped prisms may be used to represent the geometry of the cooling holes 54, and the shape used may depend on the cross-sectional shape of the cooling holes 54. FIG. 3 also shows an x-y-z coordinate system, where the z-axis may be aligned to be orthogonal to the local surface or substrate 52 near the cooling hole 54. The zero or origin of the z-axis (and typically the zero of the x-y-z coordinate system) may be selected as the inner center of the cooling hole 54.

FIG. 4 illustrates an exemplary airfoil 36 including a leading edge 44, a trailing edge 46, an airfoil tip 42, an airfoil root 46, and an airfoil platform 50. In the embodiment of FIG. 4, a number of cooling holes 54 are provided in the base 52 of the airfoil 36. FIG. 4 illustrates the alignment of the airfoil 36 relative to an x-y-z coordinate system and the mounting system 56. For example, the x-axis may be defined along a circumferential edge of the airfoil platform, the y-axis may be defined along an axial edge of the platform, and the z-axis may be aligned along a leading edge and/or other radially extending portion of the airfoil 36. Other coordinate systems may also be defined. A6-axis robotic arm 58 and/or other alignment tool may be used to align the airfoil 36 relative to the mounting system 56 such that the x-y-z coordinate system is precisely aligned on the airfoil. Robotic alignment of the airfoil 36, mounting system 56, and x-y-z coordinate system may be performed using camera views provided by an on-board camera of the 6-axis robotic arm 58, as well as other instrumented items including calipers, depth gauges, proximity gauges, gyroscopes, markers, positioning features, and/or alignment features on the airfoil 36. Other types of meters or probes that may be used include structured light probes, point confocal probes, conoscopic probes, or interferometric probes that are combined with a robot in a fixed arrangement to establish alignment. Further, from the part model, known data points can be used to align the part using a precision mechanical fixture. After aligning the airfoil 36, the mounting system 56, and the x-y-z coordinate system, an initial 3D scan of the airfoil 36 may be performed using a 3D scanner. The 3D scanner may consist of: a laser stripe system, a triangulated structured light system, a phase shift based white light scanner, a point scanning confocal system, a lidar system, a stereo photography system, a depth of focus based camera system, a mechanical touch based system, or any combination thereof. The alignment and scanning systems may be combined into a single system, or may be two or more separate systems. The use of separate alignment and scanning systems and/or machines may allow each system to achieve only a single purpose, which may allow for improved accuracy of each system. Furthermore, the use of separate alignment and scanning systems and/or machines may allow for improvements in the overall process, as the systems may be operated independently and/or simultaneously.

Fig. 5 shows airfoil 36 skewed relative to measurement data received via the 3D scanner of fig. 4. In other words, the 3D measurement data acquired by the 3D scanner is transformed such that it is aligned with the hole x-y-z coordinate system established in FIG. 4. The 3D measurement data acquired by the scanner may be converted from unstructured 3D point cloud to structured 3D point cloud data with regional neighborhood information (such as local normalcy and connectivity), such as, for example, 3D triangulation by points. Such a structured data cloud may be referred to as a 3D mesh, a data mesh, a 3D data mesh, and/or a 3D measurement data mesh, and may be transmitted from the scanner to other processing systems using various file formats, including stereolithography (. stl), VRML, or wavefront data formats, to preserve the data structure.

FIG. 6 illustrates an airfoil 36 including a number of cooling holes 54 disposed in an airfoil base 52, and a cylinder 60 disposed within the number of cooling holes. The 3D measurement data acquired by the 3D scanner is transposed into the cylindrical coordinate system such that each reference derived from the 3D measurement data is located within or outside the volume of the cylinder 60 of the cooling hole 54 associated with that reference. The conversion of the 3D measurement data to cylindrical coordinates may be performed via various methods, including a matrix conversion that associates an inspection coordinate system with a hole coordinate system.

FIG. 7 illustrates an airfoil 36 including cooling holes 62 that have been selected for further processing. Various criteria may be used to select the cooling holes 62, including 3D measurement data within the volume of the cylinder 60 (not shown) that exceeds one or more particular criteria. For example, if the 3D measurement data indicates that foreign matter such as residual and/or worn Thermal Barrier Coating (TBC) and other foreign matter is present within the volume of the cylinder (and thus within the cooling hole 62), the cooling hole 62 may be selected. In other words, if the volume of the foreign matter exceeds a predetermined threshold volume (e.g., a percentage of the cylinder volume), the cooling holes 62 may be selected for further processing. Similarly, if the 3D measurement data indicates the presence of a foreign object at a range of cooling hole depths (i.e., z-axis relative to the cylindrical coordinate system), the cooling holes 62 may also be selected for further processing. At least one additional 3D scan may be performed for any cooling holes 62 selected for further processing. Other foreign matter may include abraded bond coats, Environmental Barrier Coatings (EBC), deposits, contaminants, dirt, oxides, and other materials. The holes may also be selected for possible damage, missing material, or significant mis-positioning.

FIG. 8 illustrates an enlarged view of the cooling holes 62 disposed within the base 52 of the airfoil 36 (not shown). The cooling hole 62 may include one or more sidewalls 64 and one or more downstream corners 68 at a cooling hole exit portion where the cooling hole intersects the plane of the substrate 52. The cooling hole 62 may also include a ramp portion 66 defining a transition between the cooling hole metering section and the cooling hole outlet. The ramp portion 66 may be substantially planar or have an aerodynamic shape. The cooling holes 62 may also include a central bore portion 70.

FIG. 9 shows an enlarged view of the cooling hole 62 of FIG. 8 with the point cloud data mapped on top thereof. A point cloud is a series of measured data points for which there are no connections or ordered associations between points with respect to adjacency, surface fit, or other mathematical model connections. The only information known about each point is the X-Y-Z coordinates of the point. Only this point data will be used to evaluate local trends or changes rather than the conventional approach of placing individual points on mathematical surfaces of a curve or small surface area based on the nominal model geometry and then using these surfaces to determine geometric features. Using a fitted mathematical surface is both time consuming and may lose or bias very local features present within the point cloud data due to the shape or location of other non-hole features in the mathematical surface model. The point cloud data may be collected during a second or subsequent 3D scan on cooling holes 62 selected for further processing, as well as via other processes. The point cloud data may represent the orientation of the direction orthogonal to the surface in each location. Similarly, the point cloud data may represent varying normal surface orientations. Thus, the point cloud data can be used to identify regions (such as planar portions, e.g., base 52 and ramp portion 66) where the surface normal orientation is constant relative to other points in close proximity. The point cloud data may be used to identify areas of rapid change in surface normal orientation, such as downstream corners 68 and sidewalls 64. The point cloud data may be used to identify areas where there is no surface normal orientation, such as areas located at the cooling hole center hole portion 70. The point cloud data may be used to identify regions, such as the substrate 52, where the surface normal orientation is orthogonal with respect to the 3D scan direction (e.g., z-axis). Using the point cloud data described allows for identifying multiple attributes of the geometry of the cooling hole 62 without bias or averaging effects that may affect other features on the part to which the surface is mathematically fit, which in turn allows for multiple methods of identifying the boundaries of the cooling hole 62 even if the cooling hole geometry as measured deviates from the nominal cooling hole geometry or expected location.

FIG. 10 shows an enlarged view of the cooling hole 62 of FIGS. 8 and 9, including a first pass to identify the substrate 52 and a coarse hole boundary 72 using the point cloud data and substrate surface normal.

FIG. 11 illustrates an enlarged view of the cooling hole 62 of FIGS. 8-10, including a refined mapping of the hole boundary 72 using downstream corner and/or ramp portion cloud point data, the substrate 52, and the coarse hole boundary 72 using the point cloud data and substrate surface normal.

FIG. 12 shows an enlarged view of a representation of a cooling hole 62, including a portion having a normal surface orientation, such as the substrate 52, and a first non-normal surface portion 74 and a second non-normal surface portion 76.

Fig. 13 shows an enlarged view of a representation of a cooling hole 62, including a portion having a normal surface orientation, such as the substrate 52, and a first non-normal surface portion 74 and a second non-normal surface portion 76. In the illustration of fig. 13, a portion of the cooling hole free edge 73 is identified at a transition or edge between a portion having a normal surface orientation, such as the base 52, and at least one of the first non-normal surface portion 74 and the second non-normal surface portion 76. The cooling hole free edge 73 may have a shape that matches the geometry of the nominal part shape according to a cylindrical coordinate system. In the illustration of fig. 13, a cooling hole free edge 73 is identified at the transition between the base 52 and the first non-normal surface 74. The cooling hole free edge 73 is not identified at the transition between the base 52 and the second non-normal surface 76 because the transition does not match the geometry or orientation of the nominal part datum. The third non-normal surface 77 is also identified and also does not include a matching standard cooling hole free edge 73. In other words, the shape and orientation of the transition between the normal portion and the non-normal portion may both be used to identify the cooling hole boundary. The cooling hole free edge 73 may or may not coincide with the cooling hole boundary 72 (not shown). For example, the cooling hole free edge 73 defining the transition between the portion having the normal surface orientation and the portion having the non-normal surface orientation may be within the cooling hole 62, and thus may not define the cooling hole boundaries. This may occur when the cooling hole boundaries 72 are covered with one or more layers of chips, coatings, and/or dirt, and thus may appear to have a normal surface orientation, with at least one cooling hole free edge 73 (i.e., a transition between the normal surface orientation and a non-normal surface orientation) disposed at a depth within the cooling hole 62. Thus, the cooling hole free edge 73 may be an approximation of the cooling hole boundary 72 that may require scaling (since the free edge occurs at a depth within the cooling hole 62 or at a height above the cooling hole) and/or translation (since the cooling hole free edge 73 includes only a portion, e.g., one side, of the characteristic hole shape of the cooling hole boundary 72).

Still referring to fig. 13, the second non-normal surface portion 76 (i.e., at a location of the substrate where "expected" to have a normal surface orientation) may be attributable to erosion, damage, deposition of foreign matter, foreign matter damage, and other forms of deterioration and/or degradation of the substrate. The representation of the cooling hole 62 may include an embedded normal portion 80 that appears to have a normal orientation, and thus appears to be the portion of the substrate 52 surrounding the cooling hole 62, but is located in a portion of the representation of the cooling hole 62 that would be expected to be occupied by the cooling hole 62 itself. Because the portion within the cooling hole 62 may "look" like the surrounding substrate 52, it may not be possible to precisely match the geometry of the cooling hole free edge 73 to the geometry of the nominal part datum. Fig. 8-11 and 12 and 13 illustrate methods of using measured surface normal data, nominal part datum geometry, and its orientation relative to a predetermined coordinate system for the purpose of identifying initial or rough boundaries of the cooling holes 62, among other possible purposes.

FIG. 14 illustrates an approximate refinement of the cooling hole boundary 72 (not shown) of FIGS. 12 and 13 that maps a projection 82 of the expected cooling hole boundary feature shell shape onto measured 3D data including the cooling hole free edge 73. The characteristic housing shape can be described as a symmetrical trapezoid with rounded edges. The projection 82 may be scaled up or down in size to best match the cooling hole free edge 73. For example, if deposits are present in the cooling hole 62, the cooling hole free edge 73 may appear to be a different size than the cooling hole boundary 72 (i.e., the cooling hole 62 intersects the substrate 52, e.g., at zero depth or in a plane coplanar with the substrate 52). The profile of the cooling hole 62 may include the same feature shape at various depths, scaled up or down in size only (as the cross-sectional area and/or flow area of, for example, the diffusion portion of the film cooling hole continues to increase as the hole transitions to the substrate 52). Additionally, it may also be desirable to scale based on the orientation of the projection relative to the cylindrical coordinate system within a predetermined tolerance. Therefore, the projection 82 may have to be scaled to match the cooling hole free edge 73. Due to the characteristic shape, the projection 82 may also be described as a shell, as shown in FIG. 14.

FIG. 15 includes another refinement showing only the cooling hole free edge 73 and the projection 82 of the characteristic shell shape superimposed on one another. This superposition allows defining at least one offset 84. The offset 84 may be defined as the spatial displacement between the nominal location of the cooling hole feature and the location of the corresponding measurement data. The offset may include translation relative to any axis (lateral, longitudinal, axial) and/or rotation for matching orientation relative to a cylindrical coordinate system. Further, multiple offsets may be defined.

Fig. 16 shows a projection 80 of the characteristic shell shape and an offset shell 86 that applies the offset 84 from fig. 15 to the projection 80 of the characteristic shell shape. FIG. 16 also illustrates a second projection 88 that approximates the cooling hole boundary 72 at the plane defined by the substrate 52. In other words, the projection 80 of the characteristic shell shape and the shell offset 86 may occur at a different depth and/or height than the plane defined by the base 52, and the difference may be approximated and accounted for by the second projection 88.

Fig. 17 shows a projection 80 of the characteristic shell shape, an offset shell 86, and a second projection 88 superimposed on a 3D grid of measured data, which also shows the substrate 52 depicted as having portions with normal surface orientations. FIG. 17 shows that after superimposing a second projection 88 (which is a refined approximation of the cooling hole boundary 72) onto the 3D point of the measured data, the normal surface orientation is partially within the projected hole boundary. In other words, the portion of the measurement data that was previously identified as a likely portion of the substrate 52 due to its surface normal (and thus outside the cooling hole boundary 72) is actually determined to be within the cooling hole boundary 72 after the refinement approximation. Thus, those that were originally identified as part of the substrate 52 are re-identified as stray material or foreign matter in the cooling holes 62 upon refinement. Thus, using the cooling hole free edge 73, the projection 80 of the characteristic shell shape, the offset shell 86, and the second projection 88 superimposed on the 3D grid of measured data, as shown in fig. 13-17, the cooling hole boundary 72 may be refined more accurately than methods that rely only on surface normativity data to identify the cooling hole boundary.

FIG. 18 illustrates a refined approximation of the cooling hole 62 after the portion of the surface normal (i.e., the approximation of the cooling hole boundary 72) within the second projection 88 is removed. The second non-normal surface 76 and the third non-normal surface 77 are also identified as being outside the refined cooling hole boundary 72, and therefore do not form part of the cooling hole 62.

FIG. 19 shows a refined approximation of the cooling hole 62 using a higher order fit or approximation after the portion of the normal surface (or cooling hole boundary approximation) within the second projection 88 and the second non-normal surface 76 and the third non-normal surface 77 (not shown) outside the second projection 88 are removed. Removing these outlier surfaces allows for an even more refined approximation of the cooling hole boundaries. Thus, after discarding outlier data, additional refinement can be achieved by iteratively and/or incrementally increasing the fitting order.

FIG. 20 illustrates a side view of an exemplary cooling hole 62 including a metering section 96, a throat 100 defining a transition to a diffusion section 98, and a base 52. The cooling hole 62 includes a centerline 102 and a pierce point 104. A pierce point 104 is defined at the intersection of the cooling hole centerline 102 and the plane of the substrate 52. The pierce point 104 can serve as the origin or zero point of the hole coordinate system. The pierce point 104 may also be used to anchor the cooling hole boundary approximation (e.g., the second projection 88) to the plane (i.e., the substrate 52) in which the cooling hole boundary is defined.

FIG. 21 shows the cooling hole 62, the substrate 52, and the second projection 88 before the second projection 88 is transformed into the actual cooling hole boundary.

FIG. 22 shows the cooling hole 62, the substrate 52, and the second projection 88 after the second projection 88 is transformed into the actual cooling hole boundary. The second projection 88 may be translated and rotated within the plane of the drawing so that it may be converted to a best fit to match the actual cooling hole boundary. In addition, the second projection 88 may be anchored to the correct height or plane using the puncture points 104 shown in FIG. 20.

Fig. 23 shows a tool path 90 constructed from a plurality of curves 92, which in turn are constructed from a second projection 88. The second projection 88 provides a refined approximation of the entire perimeter of the cooling hole boundary 72, which is then applied at multiple depths. Each depth at which the second projection 88 is applied is represented by one of a plurality of curves 92, each of which may include a characteristic shell shape and may be concentric with the second projection 88 at the center of the cooling hole 62.

FIG. 24 shows a tool path 90 resulting from a second projection 88 superimposed at multiple depths (as shown in FIG. 23) on the surface of the airfoil 36 including the 3D scan measurement data, which includes the cooling hole 62 and the substrate 52. The tool path 90 is translated and/or rotated within the normal surface plane using the offset data such that it is aligned with a corresponding portion of the cooling hole 62 using a cylindrical coordinate system.

Fig. 25-27 show top, bottom, and side views, respectively, of an detailing tool path 94 that includes the second projection 88 (i.e., a detailing approximation of the cooling hole boundary 72) and a plurality of curves 92 at various depths. The refined tool path 94 of fig. 25-27 also includes portions constructed by intersecting and/or combining the tool path 90 of fig. 23 and 24 with cooling hole part geometry data. For example, the cooling hole part geometry data may include a metering section 96 that transitions to a diffusion section 98 at a cooling hole throat 100.

Fig. 28 illustrates a method 2500 of repairing a part according to embodiments disclosed herein. At step 2502, the method 2500 includes identifying a cooling hole and defining a cooling hole coordinate system in the CAD. The cooling hole coordinate system may include a cylinder 60 defining a cooling hole central axis location and axis orientation and a cooling hole bore diameter. At step 2504, method 2500 includes aligning the part with mounting system 56 using an alignment tool, such as 6-axis robot 28. The part coordinate system may include any implementation based on part geometry. For example, the part coordinate system may map the x-axis, y-axis, and z-axis to circumferential, axial, and radial directions of parts used in the turbomachine (such as turbine rotor blades or turbine nozzles). Other coordinate systems are also possible. At step 2506, method 2500 includes 3D scanning the part. At step 2508, method 2500 includes aligning 3D measurement data from the scan of step 2506 with the part geometry data and constructing 3D structured point cloud data, such as a triangular mesh from an unstructured measurement point cloud. At step 2510, method 2500 includes transforming 3D measurement data (i.e., data derived from the scan) from the part coordinate system to the hole coordinate system. At step 2512, the method 2500 includes identifying cooling holes 62 that pass a predetermined threshold for further processing. The predetermined threshold may include identifying cooling holes that include significant material (i.e., above a certain volume percentage, for example) within the volume of the cylinder 60.

Still referring to FIG. 28, at step 2514, the method 2500 may include performing a second 3D scan only on cooling holes selected for further processing in step 2512. Alternatively, at step 2514, the method 2500 may include reprocessing the data corresponding to the selected cooling hole using the data from the initial scan (i.e., at step 2506). At step 2516, the method includes overlaying the surface normalcy data from the second scan and/or the 3D measurement data from the first scan onto the part geometry data. At step 2518, the method 2500 includes filtering the point cloud data to identify normal and non-normal surfaces of the cooling holes 62 and the surrounding substrate 52. At step 2520, method 2500 may include determining a coarse aperture boundary using surface normativity data. Determining the coarse hole boundaries may include matching the 3D scan data to nominal cooling hole features such as downstream corners 68, ramp portions 66, and at least one cooling hole free edge 73. At step 2522, the method 2500 includes mapping the approximated cooling hole boundaries onto a 3D measurement data grid using the cooling hole shape features. At step 2524, the method 2500 may include projecting nominal cooling hole boundaries onto a 3D measurement data grid. At step 2526, the method 2500 may include determining an offset between the nominal cooling hole boundaries and the measured cooling hole boundaries. The offset may include rotation and/or translation within the plate defined by the base 52 and parallel planes (to account for measurement data at various heights within the hole or above the base 52).

Still referring to fig. 28, at step 2528, the method may include scaling the projections based on the offset and/or the hold depth data (i.e., the depth to which the measured data corresponds). At step 2530, the method may include projecting the scaled projection 88 onto a 3D measurement data mesh or structured point cloud using the puncture points to transform the scaled projection 88 to match the actual detected boundary in each of the X, Y, and Z directions. At step 2532, the method may include removing outlier data. The outlier data may include normal surface data identified within the scaled projection 88 (i.e., cooling hole boundary approximation), and non-normal surface data outside of the scaled (or second) projection 88 (i.e., data that "looks like" but is actually located on a portion of the substrate). At step 2534, the method 2500 may include refining the cooling hole boundaries using a high order fit. At step 2536, the method 2500 may include generating a tool path using the offset data and the scaled projection 88. At 2538, method 2500 may include projecting the tool path onto a 3D measurement data grid. At step 2540, the method may include intersecting and/or combining the tool path with the part geometry data to generate a refined tool path. At step 2542, the method may include repairing the part using the refined tool path. The repaired part may include cooling holes, cooling hole boundaries, drilling, milling, other forms of machining, recoating, resurfacing, and/or reshaping of portions of the cooling hole walls and/or substrate. In other words, the repair process may include an additive and/or subtractive cooling hole repair process. Other repair methods may also be used. Further, the reshaping of the airfoil, the part, and/or the cooling hole may be performed via additive manufacturing as well as via other processes. Method 2500 may also include other steps and sub-steps. In some embodiments, all of the steps of method 2500 will not be performed. Further, the various steps of method 2500 may be performed in a different order than shown in FIG. 28.

The methods, systems, and embodiments described herein enable a fast and automated process of cleaning or masking various cooling hole geometries, and they may completely eliminate the labor intensive process of manual cooling hole clearance and repair. Calculating cooling hole feature information directly from the scan information may also establish a digital dominant line and digital twin for each part, which enables statistical studies of cooling hole geometry information in several parts in the series, thereby generating a more accurate part lifting model based on actual hole location and boundary data. By automatically identifying the location and boundary geometry of cooling holes on a part and generating a tool path instruction set that allows a multi-axis robot to accurately and adaptively deposit or remove material in or around each cooling hole, the methods and systems described herein may be used to simplify a component repair process while improving the quality of the repair process and the resulting repaired part. The process described herein utilizes the nominal design geometry of an engine component (e.g., a turbine rotor blade or nozzle) in conjunction with three-dimensional scan data derived from a physical instance of the component.

This written description uses examples to disclose embodiments of the invention, including the best mode, and also to enable any person skilled in the art to practice embodiments of the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.