JP6101516B2 - Method for obtaining hole position of construction object and thermal barrier coating method using the same - Google Patents

Description

  The present invention relates to a hole position acquisition method for a construction object and a thermal barrier coating method using the method.

  In the gas turbine, in order to improve the efficiency, the temperature of the gas used is set high. Turbine blades exposed to such high-temperature gas (moving blades, stationary blades, etc.) are provided with a large number of cooling holes, and the cooling medium is circulated inside or discharged from the turbine blade surface. The turbine blades are cooled by providing a cooling layer. And the thermal barrier coating (Thermal Barrier Coating: TBC) is given to the surface of the gas turbine blade. TBC is a coating of a turbine blade, which is a sprayed material, coated with a thermal spray material having a low thermal conductivity (for example, a ceramic material having a low thermal conductivity) by thermal spraying. Improves sex.

  A thermal barrier coating is applied to the turbine blade by fixing the turbine blade on a table and spraying a spray material onto the entire surface of the turbine blade with a spray gun attached to a robot arm. Thereby, the thermal-insulation layer by the thermal spray material is formed on the surface of the turbine blade.

  However, since the thermal barrier layer is formed so as to coat the entire surface of the turbine blade by the spray gun, the cooling hole formed over the entire region of the turbine blade is blocked. Therefore, after spraying the thermal spray material on the surface, the operator removes the thermal spray material blocking the cooling hole with a tool while checking and searching for the cooling hole blocked by the thermal spray material by design data of the turbine blades. Drilling work needs to be done. This drilling operation requires a great deal of time until the operation is completed because the turbine blade has a large number of cooling holes, such as several hundred. Further, it is difficult to determine the position of the cooling hole that is thickly covered with the thermal spray material, and there is a possibility that a part without the cooling hole is accidentally shaved with a tool and a part of the heat shield layer is peeled off.

  As a method for improving such a problem, for example, in the thermal barrier coating construction apparatus described in Patent Document 1, a robot arm is a thermal spray gun that is a thermal spray apparatus, and a drill that removes the thermal spray material that closes the cooling holes. By having it, the thermal barrier coating and the subsequent drilling of the cooling holes can be performed without removing the turbine blades. Therefore, before the thermal barrier coating was applied, the operator taught the robot arm the position of the cooling hole by aligning the tip of the drill with the center position of the cooling hole, and the robot arm was taught after the thermal barrier coating was applied. The drilling of the cooling hole can be automatically performed by guiding the drill to the position. Thereby, workability is improved and work time is shortened.

  Moreover, in the thermal barrier coating construction apparatus described in Patent Document 2, a turbine blade is photographed using a camera, and the mark and the position of the cooling hole on the surface of the turbine blade are calculated by processing the photographed image. . And the position of the mark of a turbine blade is detected, the position of a cooling hole is estimated from the position data of a cooling hole on the basis of the position of this mark, and marking is performed by the marker device. As a result, the operator can perform a drilling operation with a drill at the marked position, and prevents a portion without a cooling hole from being accidentally cut with a tool.

  Furthermore, in the hole position specifying method described in Patent Document 3, the shape of the turbine blades installed on the stage is measured using a non-contact type three-dimensional measuring instrument combining a laser sensor and an orthogonal robot. Then, based on the point cloud data output from the three-dimensional measuring machine, the blade curved surface, which is the surface of the turbine blade, is calculated, and the points that are not on the surface are cut out as the shape of the cooling hole opening. The position of the cooling hole of the blade is estimated. Thereby, the position of the cooling hole can be calculated accurately.

JP 2012-102388 A JP 2012-122432 A JP 2007-0909908 A

  The methods of Patent Documents 1 to 3 all use the shape of the cooling hole on the surface of the turbine blade when acquiring the position of the cooling hole. Therefore, if the cooling hole has a complicated cross-sectional shape in which the opening shape on the surface and the hole shape on the inside are different, it is difficult to accurately obtain the position of the cooling hole.

  By the way, the cooling holes provided in the turbine blades include a circular cooling hole having a circular cross section for circulating a cooling medium therein, and a shape in which the shape of the frontage is widened to form a cooling layer on the surface of the turbine blade. Two types of holes are provided. In particular, the shape hole has a circular cross section inside, but the opening shape on the surface of the turbine blade has a shape in which the front opening is radially expanded, and has a complicated cross section shape. And since these cooling holes are very small, it is necessary to have a very high accuracy in order to grasp the position of the cooling holes and perform the drilling work. There is a risk of scraping and scratching.

  However, since the methods described in Patent Documents 1 to 3 are methods for obtaining the position of the cooling hole from the opening shape on the surface of the turbine blade, the opening shape on the surface of the turbine blade, such as a shape hole, has an internal cross section. In the case of a complicated hole shape that is different from the shape, the center position of the cooling hole cannot be obtained accurately only by the opening shape. Therefore, there is a problem that it is difficult to accurately obtain the position of the cooling hole.

  The present invention has been made to solve the above-described problems, and is a method for obtaining a hole position of a construction object capable of accurately obtaining the position of a hole provided in the construction object, and An object is to provide a thermal barrier coating method used.

In order to solve the above problems, the present invention proposes the following means.
Hole position acquiring method of the execution object in accordance with one embodiment of the present invention, the surface of the execution object that holes are formed on the surface so as to be inclined at a predetermined angle against the surface, scanning the laser beam An acquisition step of acquiring the surface shape of the construction object, a calculation step of calculating the center position of the hole from the reference position of the construction object based on the acquired surface shape, and the surface In contrast, the optical axis of the imaging unit is tilted by a predetermined angle according to the inclination angle of the hole, and the imaging unit is guided so that the optical axis of the imaging unit coincides with the center position. An imaging step of capturing an image of the hole, and a correction step of correcting the center position of the hole based on the image of the hole.

According to the hole position acquisition method of the construction object in such a process, the surface shape of the construction object can be obtained in the obtaining process, and the center position of the hole can be computed based on the surface shape obtained in the computation process. it can. Then, the imaging unit is guided so as to coincide with the center position of the cooling hole calculated by the imaging process, and an image of the hole is captured, and the center position is corrected in the correction process based on the captured image, thereby obtaining an accurate hole. The center position of can be obtained. Thereby, it becomes possible to acquire correctly the position of the hole provided in the construction object.
Moreover, the cross-sectional shape inside a hole part can also be imaged by inclining the optical axis of an imaging part only by the predetermined angle with respect to the surface of a construction target object, and imaging an image. As a result, the center position can be determined not only from the opening shape of the hole on the surface of the construction object but also from the cross-sectional shape inside the construction object, and the position of the hole provided in the construction object can be further determined. It becomes possible to acquire accurately.

  Further, in the hole position acquisition method for a construction object according to another aspect of the present invention, the calculation step calculates an opening shape of the hole portion based on the surface shape, and the opening shape and the design of the hole portion are calculated. The center position is calculated by comparing with data.

According to the hole position acquisition method of the construction object in such a process, the opening shape of the hole is obtained based on the surface shape acquired in the calculation process, and is compared with the design data so that the cooling hole can be changed from the opening shape. The rough center position can be easily calculated and obtained.

  Moreover, the hole position acquisition method of the construction target object according to another aspect of the present invention is based on the position of the plurality of holes acquired in the hole position acquisition method of the construction target object when the construction target object is produced. It has the design data comparison calculation process which calculates the position of another hole part from design data, It is characterized by the above-mentioned.

  According to the hole position acquisition method of the construction object in such a process, the positions of other holes can be obtained from the design data while reducing the number of holes to be acquired. As a result, the number of holes that must be acquired with the work can be minimized, and the work time can be greatly shortened.

  Moreover, the thermal barrier coating method according to one aspect of the present invention is a thermal barrier coating method using the hole position acquisition method of the construction object, and after the hole position acquisition method of the construction object, the construction A thermal spraying process for applying a thermal barrier coating to an object, and a drilling process for opening the hole blocked in the thermal spraying process based on the position of the hole obtained by the hole position acquisition method of the construction object. It is characterized by providing.

  According to the thermal barrier coating method of such a process, even if the hole portion is blocked by spraying the thermal spray material on the surface of the construction object by the thermal spraying process and the position cannot be confirmed, the hole position acquisition method Since the position of the hole is accurately acquired, the hole can be accurately opened in the drilling process. Accordingly, it is possible to reliably remove only the thermal spray material closing the hole without damaging the periphery of the hole blocked in the thermal spraying process and causing the heat shield layer to peel off.

  Furthermore, in the thermal barrier coating method according to another aspect of the present invention, the position of the construction object after the thermal spraying process is corrected to the position where the hole position acquisition method is being performed before the drilling process is performed. And a position correcting step.

  According to the thermal barrier coating method of such a process, the position of the construction object after the spraying process is corrected to the position where the hole position obtaining method is being performed, so that the position of the construction object after the hole position obtaining method is corrected. The position of the construction object when the hole position acquisition method is carried out and the position of the construction object performing the drilling process can be in the same positional relationship even when the hole position is shifted, and the acquired position is used. be able to. That is, even if the position of the construction object is shifted in a state where the position of the hole of the construction object cannot be confirmed by the thermal spraying process, the position of the hole can be accurately grasped. Thereby, only the thermal spraying material which has plugged up the hole can be reliably removed without damaging the heat shield layer applied to the construction object.

  Furthermore, the thermal barrier coating method according to another aspect of the present invention is characterized in that the position correction step corrects the position of the construction object to a position before the spraying step based on the reference position.

  According to the thermal barrier coating method of such a process, by using the reference position acquired in the acquisition process in which the position correction process acquires the position of the hole, by comparing with the rear reference position of the same position, The position can be easily adjusted regardless of the shape of the construction object. This makes it possible to shorten the work time.

  According to the hole position acquisition step of the construction object of the present invention, the center of the hole part can be obtained by acquiring the center position of the hole part of the construction object not only from the opening shape but also from the image of the cross-sectional shape inside the hole part. The position can be accurately acquired, and the position of the hole provided in the construction object can be accurately acquired.

It is process drawing of the thermal barrier coating method which concerns on 1st embodiment of this invention. It is a schematic diagram explaining the acquisition process of the hole position acquisition method which concerns on 1st embodiment of this invention. The schematic diagram explaining the calculation process of the hole position acquisition method which concerns on 1st embodiment of this invention, The figure (a) is the schematic diagram explaining the state which is acquiring the point cloud data with a laser sensor, the figure ( b) is a schematic diagram for explaining a state in which the opening shape of the circular cooling hole is acquired, and FIG. 10 (c) is a schematic diagram for explaining a state in which the opening shape of the shape hole is acquired and compared with the hole portion template. It is a schematic diagram explaining the imaging process of the hole position acquisition method which concerns on 1st embodiment of this invention. It is a schematic diagram explaining the correction | amendment process of the hole position acquisition method which concerns on 1st embodiment of this invention. It is process drawing of the thermal barrier coating method which concerns on 2nd embodiment of this invention.

Hereinafter, a first embodiment according to the present invention will be described with reference to FIGS. 1 to 5.
As shown in FIG. 1, the thermal barrier coating method S <b> 1 according to the first embodiment performs thermal barrier coating on the turbine blade 1, which is a construction target, and forms a thermal barrier layer on the surface of the turbine blade 1. The construction object used in this embodiment is a turbine blade 1, and as shown in FIG. 2, a large number of cooling holes 10 are provided as holes on the surface.
The cooling hole 10 which is a hole has a circular cooling hole 11 having a circular cross section, and a shape hole 12 in which the opening shape on the surface of the construction object is radially expanded.
The circular cooling hole 11 is formed so as to be inclined at a certain angle with respect to the surface of the turbine blade 1 which is a construction object, and has the same circular cross section from the surface to the inside of the turbine blade 1.
Like the circular cooling hole 11, the shape hole 12 is formed so as to be inclined at a constant angle with respect to the surface of the turbine blade 1, and has a circular cross section inside the turbine blade 1. Then, it has a shape that spreads radially. That is, the shape hole 12 is formed in a shape in which the opening shape and the cross-sectional shape are different such that the opening shape on the surface of the turbine blade 1 is radial and the cross-sectional shape inside the turbine blade 1 is circular.

The thermal barrier coating method S1 of the first embodiment includes a thermal barrier coating application device that performs thermal barrier coating on the turbine blade 1, a cooling hole measuring device that acquires the center position 101 of the cooling hole 10 of the turbine blade 1, and cooling. Three devices (not shown) including a cooling hole drilling device that removes the thermal spray material that closes the holes 10 are used.
The thermal barrier coating construction apparatus includes a thermal spray arm having a thermal spray gun for spraying a thermal spray material, a thermal spray robot that adjusts the position of the thermal spray arm, and a thermal spray fixing base that fixes the turbine blade 1 that is a construction target. ing. In the thermal barrier coating construction apparatus, the thermal spray robot guides the thermal spray arm to the surface of the turbine blade 1 fixed to the thermal spray fixing base, adjusts the position of the tip of the thermal spray arm, and sprays the thermal spray material with the thermal spray gun, Thermal barrier coating is performed to form a thermal barrier layer on the surface of the turbine blade 1.

The cooling hole measuring device includes an arm having a laser sensor 2 and a camera 3 at the tip, a controller that adjusts the position of the arm, and a swivel table that fixes the turbine blade 1 that is a construction object via a fixed mount. ing. The cooling hole measuring device guides the arm to a specified position on the surface of the turbine blade 1 fixed to the swivel table, and measures the laser sensor 2 and the camera 3 at the tip of the arm toward the surface of the turbine blade 1. ing.
The cooling hole drilling device includes an arm having a drill driven by an air motor at a tip thereof, a controller that adjusts the position of the arm, and an air supply source that supplies air to the air motor that drives the drill. The cooling hole drilling device guides the arm with a controller to a specified position on the surface of the turbine blade 1 fixed to the swivel table of the cooling hole measuring device, and applies a drill to the cooling hole 10 on the surface of the turbine blade 1 to make a hole. Processing is carried out.

  As shown in FIG. 1, the thermal barrier coating method S <b> 1 of the first embodiment forms a thermal barrier layer by spraying a thermal spray material on the surface of the turbine blade 1, which is a construction target, after performing the hole position acquisition method S <b> 2. The thermal spraying process S11, the position correction process S12 for correcting and matching the positions of the turbine blades 1 before and after the thermal spraying process S11, and the thermal spray material blocking the cooling holes 10 of the turbine blades 1 in the thermal spraying process S11 are removed. Drilling step S13.

  The hole position acquisition method S2 of the construction object is performed using the laser sensor 2 and the camera 3 of the cooling hole measuring device. As shown in FIG. 1, the hole position acquisition method S <b> 2 includes an acquisition step S <b> 21 that acquires the surface shape of the turbine blade 1 that is a construction target by scanning with the laser light of the laser sensor 2, and the acquired surface of the turbine blade 1. The calculation step S22 for calculating the provisional center position 100 of the cooling hole 10 that is the hole from the shape, and the cooling hole 10 is imaged so that the calculated provisional center position 100 and the optical axis of the camera 3 that is the imaging unit coincide. An imaging step S23 and a correction step S24 for correcting the provisional center position 100 based on the captured image of the cooling hole 10 to obtain position data of the center position 101 are provided. In the hole position acquisition method S2, the acquisition process S21 to the correction process S24 are repeatedly performed by the number of cooling holes 10 that are holes formed on the surface of the turbine blade 1 that is a construction target, so that all cooling is performed. The position data of the center position 101 of the hole 10 is acquired.

In the acquisition step S21, as shown in FIG. 2, the turbine blade 1 as a construction object is fixed to a turning table (not shown), and the arm having the laser sensor 2 is a surface on which the cooling holes 10 of the turbine blade 1 are formed. Guiding perpendicular to The laser sensor 2 guided to the surface of the turbine blade 1 scans the surface of the turbine blade 1 with laser light, and acquires the surface shape of the turbine blade 1 as a construction object as point cloud data. Moreover, acquisition process S21 also acquires the positional data of the point used as the reference position 50 defined beforehand.
The reference position 50 is an arbitrary point on the surface of the turbine blade 1, which is a predetermined construction object, and is preferably easily distinguishable visually. For example, a shroud portion or a corner portion of the blade root portion of the turbine blade 1 that does not have the cooling hole 10 may be set, or an arbitrary cooling hole 10 may be set. The reference position 50 may be only one arbitrary point, but is preferably a plurality of points, and even if it is the turbine blade 1 that is a construction object having a complicated three-dimensional shape by using a plurality of points, the cooling hole 10 The accuracy of the position data of the center position 101 can be improved.

In the calculation step S22, as shown in FIG. 3A, the reference blade surface 51 of the turbine blade 1 is calculated by plane approximation of the point shape data of the surface shape acquired in the acquisition step S21 by the least square method. The magnitude of the distance between the reference blade surface 51 of the turbine blade 1 that is the calculated plane and each point of the point cloud data is calculated, and the point cloud data in which the calculated distance is equal to or greater than a predetermined threshold is set as the opening. 52 is extracted from the point cloud data, and the opening shape of the cooling hole 10 on the surface of the turbine blade 1 is calculated and acquired as point cloud data.
The threshold value is calculated based on design data at the time of manufacturing the turbine blade that is the construction object, and is previously determined based on the reference blade surface 51 of the turbine blade 1 and the depth from the surface of the cooling hole 10 formed in the turbine blade 1 in the design data. Set it up.
The opening 52 is point cloud data in which the distance from the reference blade surface 51 exceeds the threshold in the point cloud data acquired in the acquisition step S21. This is point cloud data in a region that is recessed by more than a threshold value from the surface. By collecting the point cloud data of the opening 52, the point cloud data indicating the opening shape of the cooling hole 10 on the surface of the turbine blade 1 is obtained.

And as shown in FIG.3 (b), when the opening 52 which is the point cloud data of the acquired opening shape of the cooling hole 10 has an elliptical shape, the cooling hole 10 is a circular cooling hole 11, The center of the elliptical shape is acquired as the center position 101.
On the other hand, as shown in FIG. 3C, when the opening 52 that is the point cloud data of the acquired opening shape of the cooling hole 10 has a trapezoidal shape, the cooling hole 10 is the shape hole 12, and the opening 52 does not have an elliptical shape, and the center position 101 cannot be obtained from the trapezoidal shape. Therefore, the provisional center position 100 of the cooling hole 10 which is a hole is obtained by comparing with the predetermined hole template A from the design data of the shape hole 12. Then, the position data from the reference position 50 to the provisional center position 100 is calculated by calculating from the reference position 50 to the provisional center position 100 of the cooling hole 10.
The hole template A is calculated based on the design data of the shape hole 12 and is determined in advance from the opening shape of the shape hole 12 which is one of the cooling holes 10 on the surface of the turbine blade 1 in the design data.

As shown in FIG. 4, the imaging step S <b> 23 guides the arm having the camera 3 as an imaging unit to the surface of the turbine blade 1 where the shape hole 12 of the cooling hole 10 is formed. In the imaging step S23, the optical axis of the camera 3 that is the imaging unit guided to the surface of the turbine blade 1 is tilted by a predetermined inclination angle α that is a predetermined angle with respect to the surface of the turbine blade 1, and the calculation is performed. The camera 3 is guided and imaged to a position that coincides with the provisional center position 100 obtained in step S22 and that the opening shape of all the shape holes 12 is accommodated. The camera 3 captures the cross-sectional shape inside the shape hole 12 by capturing an image of the shape hole 12 that is a hole so that the entire opening shape can be accommodated in an inclined state.
The specified inclination angle α is calculated based on the design data, and is determined in advance from the inclination angle of the cooling hole 10 formed in the turbine blade 1 in the design data.

  As shown in FIG. 5, the correction step S <b> 24 is a hole portion that performs image processing based on an image of a cross-sectional shape of the shape hole 12 that is one of the cooling holes 10 that are the hole portions imaged in the imaging step S <b> 23. By calculating the center position 101 of the cooling hole 10, the temporary center position 100 calculated in the calculation step S22 is corrected. That is, the correction step S24 detects the end of the cross-sectional shape inside the shape hole 12 from the image of the cross-sectional shape inside the shape hole 12 imaged in the imaging step S23. In the correction step S24, the outer shape of the cross-sectional shape of the shape hole 12 is obtained from the detected end portion by least square approximation, and the center position 101 of the cross-sectional shape is calculated from the outer shape. Thereafter, the correction step S24 corrects the temporary center position 100 calculated in the calculation step S22 to match the calculated center position 101 of the cross-sectional shape of the shape hole 12, and is one of the cooling holes 10 that are holes. The position data of the center position 101 of the shape hole 12 is acquired.

  Thermal spraying process S11 is implemented after completion | finish of hole position acquisition method S2, removes turbine blade 1 which is a construction object from an acquisition fixed stand of a hole position measuring device, and fixes and attaches to a thermal spray fixation stand of a thermal barrier coating construction device. The thermal spraying arm is guided to the surface of the turbine blade 1 attached to the thermal spray fixing base, and the thermal spray layer is sprayed by the thermal spray gun, thereby forming a heat shield layer on the surface of the turbine blade 1. Moreover, the cooling hole 10 of the turbine blade 1 which is the construction object on which the thermal spraying step S11 is performed is blocked by the thermal spray material.

  Position correction process S12 correct | amends so that the position of turbine blade 1 which is a construction target object after thermal spraying process S11 may be in the position which is performing acquisition process S21 of hole position acquisition method S2. That is, in the position correction step S12, first, the turbine blade 1 after the thermal spraying step S11 is removed from the thermal spray fixing base of the thermal barrier coating application device, and is again mounted on the turning table of the cooling hole acquisition device and fixed. In the position correction step S12, the arm is guided to the same position as the reference position 50 on the surface of the turbine blade 1 acquired in the acquisition step S21, and the position data of the reference position 50 is acquired again by the laser sensor 2. Here, the acquired position data of the reference position 50 is set as a rear reference position. The acquired position data of the reference position and the reference position 50 are compared, and the rotation amount and the parallel movement amount are corrected by performing coordinate conversion using a homogeneous conversion matrix, and the position data of the reference position 50 and the reference position 50 are corrected. Correct so that it matches the position data. Then, the coordinate data when the position data of the reference position 50 is matched with the position data of the rear reference position is also applied to the position data of the center position 101 of the other cooling holes 10 to thereby change the center position 101 of the other cooling holes 10. The position data is also corrected, and the position data of the center positions 101 of all the cooling holes 10 after the turbine blades 1 are replaced are acquired.

  The drilling step S13 is performed based on the position data of the center position 101 of the cooling hole 10 obtained by correcting the center position 101 of the hole obtained by the hole position acquisition method S2 of the construction object in the position correction step S12. The drill is guided to the center position 101 of the cooling hole 10 to open the cooling hole 10 closed in the spraying step S11.

Next, operations of the thermal barrier coating method S1 and the hole position acquisition method S2 of the first embodiment having the above-described configuration will be described.
According to the hole position acquisition method S2 of the first embodiment as described above, the surface shape of the turbine blade 1 that is the construction object is acquired in the acquisition step S21, and the hole portion is based on the surface shape acquired in the calculation step S22. The position data of the temporary center position 100 that is the rough center position 101 of the cooling hole 10 can be calculated and obtained. Then, the camera 3 as the imaging unit is guided so as to coincide with the temporary center position 100 of the shape hole 12 which is one of the cooling holes 10 calculated in the imaging step S23, and an image of the cross-sectional shape of the cooling hole 10 as the hole is obtained. The center position 101 of the shape hole 12 that is a very accurate hole can be obtained by correcting the temporary center position 100 in the correction step S24 based on the image obtained by capturing the cross-sectional shape. Thereby, the position of the shape hole 12 which is a hole provided in the turbine blade 1 which is a construction object can be accurately acquired.

  Further, the opening shape of the cooling hole 10 that is the hole is obtained based on the surface shape acquired in the calculation step S22, and is compared with the hole template A that is the design data. The provisional center position 100, which is the rough center position 101 of the shape hole 12, which is the same, can be easily calculated and obtained.

  Furthermore, the optical axis of the camera 3 that is the imaging unit is inclined by a specified inclination angle α that is a predetermined angle with respect to the surface of the turbine blade 1 that is the construction target, and the shape of the shape hole 12 that is the hole is formed. By capturing an image so as to fit all, the cross-sectional shape inside the shape hole 12 can also be captured. Accordingly, the center position 101 can be obtained not only from the shape of the shape hole 12 which is one of the cooling holes 10 on the surface of the turbine blade 1 but also from the sectional shape inside the turbine blade 1. Thus, the position of the shape hole 12 which is a hole provided in the turbine blade 1 can be obtained more accurately.

  Further, even if the cooling hole 10 that is a hole is formed in a shape having a different opening shape and cross-sectional shape as the shape hole 12, after calculating the temporary center position 100 with the opening shape on the surface, the cross-sectional shape By calculating and correcting the center position 101, the position of the shape hole 12, which is a hole, can be accurately obtained. That is, even if the cooling hole 10 has a complicated shape, the center position 101 of the hole can be accurately specified, and the position can be accurately acquired regardless of the shape of the opening 52 of the cooling hole 10.

  Then, according to the thermal barrier coating method S1 of the first embodiment as described above, the cooling hole 10 which is a hole is blocked by the thermal barrier layer by spraying the thermal spray material on the surface of the turbine blade 1 by the thermal spraying step S11. Even if the position cannot be confirmed due to peeling, since the position of the cooling hole 10 is accurately acquired by the hole position acquisition method S2, the drill is accurately guided to the position of the cooling hole in the drilling step S13. It is possible to remove only the thermal spray material that is blocking. Thus, only the thermal spray material that closes the cooling hole 10 is surely removed without damaging the periphery of the cooling hole 10 that is the hole blocked in the thermal spraying step S11 and causing the thermal barrier layer to peel off. Can do.

  In addition, the position correction step S12 corrects the position of the turbine blade 1 that is the construction target after the thermal spraying step S11 to the position where the acquisition step S21 of the hole position acquisition method S2 is being performed, whereby the hole position acquisition method. Even if the position of the turbine blade 1 which is a construction target after S2 is shifted due to attachment / detachment from a fixed base or the like, the position and drilling of the turbine blade 1 when the acquisition step S21 of the hole position acquisition method S2 is performed. The position of the turbine blade 1 that performs step S13 can be set to the same positional relationship, and the acquired position can be used. That is, even if the position of the turbine blade 1 is shifted in a state where the cooling hole 10 of the turbine blade 1 which is a construction object is blocked by the spraying step S11 and the position of the cooling hole cannot be confirmed, the cooling hole 10 is accurately detected. The position of can be grasped. Thereby, only the thermal spray material which has plugged the cooling hole 10 can be surely removed without damaging the heat shield layer applied to the turbine blade 1.

  Furthermore, by using the reference position 50 acquired in the acquisition step S21 in which the position correction step S12 acquires the position of the cooling hole 10 that is a hole, the subsequent reference position and the position data of the same position are compared and corrected. The position can be easily adjusted regardless of the shape of the turbine blade 1 as the construction object. Thereby, workability can be improved and work time can be shortened.

Next, the thermal barrier coating method S1 of the second embodiment will be described with reference to FIG.
In the second embodiment, the same components as those in the first embodiment are given the same reference numerals, and detailed description thereof is omitted. The thermal barrier coating method S1 of the second embodiment is different from the first embodiment in that the position of the entire cooling hole 10 is calculated from the positions of several cooling holes 10.

  That is, the thermal barrier coating method S1 of the second embodiment is acquired after the acquisition step S21 to the correction step S24, which is the same hole position acquisition method S2 as that of the first embodiment, is performed on any number of cooling holes 10. There is a design data comparison / calculation step S30 for obtaining position data of other cooling holes 10 by comparing the position data of the cooling holes 10 and the design data of the cooling holes 10 together.

  In the design data comparison calculation step S30, the acquisition step S21 to the correction step S24 are performed for an arbitrary number of cooling holes 10 determined in advance, and position data of the central positions 101 of the cooling holes 10 which are several holes are obtained. Acquired and set as the hole reference position. The design data comparison and calculation step S30 is shifted by obtaining the position data of the hole reference position, comparing the position data of the hole reference position with the design data, and performing coordinate conversion by the homogeneous transformation matrix. The rotation amount and the parallel movement amount are corrected, and the position data of the hole reference position and the design data of the cooling hole 10 set as the hole reference position are matched. Then, after combining the position data of the hole reference position and the design data, the design data of the cooling holes other than the cooling hole 10 set as the hole reference position is calculated as the position data of the other cooling holes.

According to the hole position acquisition method S2 as described above, all other cooling holes using the position data and design data of the cooling holes 10 that are the hole reference positions acquired until the design data comparison calculation step S30 is performed. Ten positions can be calculated. That is, it is possible to calculate the positions of all the cooling holes 10 by matching the relative positions of the cooling holes 10 in the design data with the position data of the cooling holes 10 which are the hole reference positions provided in the turbine blade 1. it can. Usually, the design data of the cooling hole 10 which is a hole and the position of the cooling hole 10 actually provided in the turbine blade 1 are shifted when the cooling hole 10 is processed in the turbine blade 1. However, this occurs because the installation positions of the turbine blades 1 are shifted during processing, and the relative positions of the cooling holes 10 are almost automatically opened by the machine based on the design data. It is not shifted. Therefore, the position of the plurality of cooling holes 10 is set as the hole reference position, and the actual position on the turbine blade 1 and the position on the design data are compared and corrected, and then the design data is collated to obtain other It is possible to calculate the position of the cooling hole 10 which is a hole portion of the first hole.
Therefore, the acquisition process S21 to the correction process S24 are performed while the number of cooling holes 10 that are holes acquired by repeating the acquisition process S21 to the correction process S24 is reduced to a necessary number as the hole reference position. The position of the cooling hole 10 that is not another hole can be calculated from the design data. Thereby, the number of the cooling holes 10 acquired with the operation | work from acquisition process S21 to correction | amendment process S24 can be made into the minimum required, and the frequency | count of implementing the acquisition process S21 to correction | amendment process S24 can be reduced, and work time can be reduced. Can be greatly shortened.

  It should be noted that the number of cooling holes 10 that are hole reference positions acquired by performing the acquisition process S21 to the correction process S24 before the design data comparison calculation process S30 is performed is the turbine blade that is the construction object. What is necessary is just to select suitably according to the shape of 1. That is, when the shape of the turbine blade 1 is complicated, the accuracy of the position of the other cooling hole 10 to be calculated can be improved by increasing the position of the cooling hole 10 that is the hole reference position to be acquired. On the contrary, when the shape of the turbine blade 1 is simple and high accuracy is not required, the working time can be further shortened by reducing the position of the cooling hole 10 which is the hole reference position to be acquired.

  Although the embodiments of the present invention have been described in detail with reference to the drawings, the configurations and combinations of the embodiments in the embodiments are examples, and the addition and omission of configurations are within the scope not departing from the gist of the present invention. , Substitutions, and other changes are possible. Further, the present invention is not limited by the embodiments, and is limited only by the scope of the claims.

In addition, the construction object for which the hole position acquisition method S2 of the present embodiment is used is not limited to the turbine blade 1, and may be a structure having a hole on the surface.
Further, the position correction step S12 is not limited to only correcting the position of the turbine blade 1 on the data, and for example, the position of the turbine blade 1 may be corrected by moving the thermal spray fixing base directly.
Furthermore, the thermal barrier coating method S1 of the present embodiment is not limited to being performed by another apparatus such as a thermal barrier coating construction apparatus, a cooling hole acquisition apparatus, and a cooling hole drilling apparatus, It may be implemented by a device, and conversely, may be implemented by a larger number of devices.
In addition, the cooling hole 10 that is a hole in which the imaging step S23 and the correction step S24 are performed in the present embodiment is not limited to the shape hole 12, and may be performed on the circular cooling hole 11.

DESCRIPTION OF SYMBOLS 1 ... Turbine blade 10 ... Cooling hole 11 ... Circular cooling hole 12 ... Shape hole 2 ... Laser sensor 50 ... Reference position 51 ... Reference blade surface 52 ... Opening part A ... Hole part template 100 ... Temporary center position 3 ... Camera alpha ... Specification Inclination angle 101 ... Center position S1 ... Thermal barrier coating method S2 ... Hole position acquisition method S21 ... Acquisition step S22 ... Calculation step S23 ... Imaging step S24 ... Correction step S11 ... Thermal spraying step S12 ... Position correction step S13 ... Drilling step S30 ... Design Data comparison calculation process

Claims (6)

The surface of the execution object that holes are formed on the surface so as to be inclined at a predetermined angle against the surface, the acquisition step by scanning by a laser beam to obtain the surface shape of the execution object,
Based on the acquired surface shape, a calculation step of calculating the center position of the hole from the reference position of the construction object,
Inclining the optical axis of the imaging unit by a predetermined angle with respect to the surface by the inclination angle of the hole, guiding the imaging unit so that the optical axis of the imaging unit coincides with the center position, An imaging step of capturing an image of the hole by an imaging unit;
A correction step for correcting the center position of the hole based on the image of the hole;
The hole position acquisition method of the construction target object characterized by comprising.   The calculation step calculates an opening shape of the hole based on the surface shape, and calculates the center position by comparing the opening shape with design data of the hole. The hole position acquisition method of the construction target object according to 1. Based on the position of the plurality of holes acquired in the hole position acquisition method of the construction object,
Execution object of hole positions acquisition method according to claim 1 or 2, characterized in that it has a design data comparison calculation step of calculating the position of the other hole from the design data at the time of making the execution object. A thermal barrier coating method using the hole position acquisition method for a construction object according to any one of claims 1 to 3 ,
After the hole position acquisition method of the construction object, a thermal spraying process for applying a thermal barrier coating to the construction object,
A thermal barrier coating method comprising: a hole making step of opening the hole portion blocked in the thermal spraying step based on the position of the hole portion obtained by the hole position obtaining method of the construction object. The method according to claim 1, further comprising a step of correcting the position of the construction object after the spraying step so as to be a position where the hole position acquisition method is being performed before the drilling step. thermal coating methods barrier according to 4. The thermal barrier coating method according to claim 5 , wherein the position correction step corrects the position of the construction object to a position before the spraying step based on the reference position.

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