JP4822767B2 - Gas turbine hot parts repair and deformation correction method - Google Patents

Description

  The present invention relates to a gas turbine high-temperature component repair / deformation correction method that is effective when regenerating a gas turbine high-temperature component that has caused material deterioration or deformation as a result of operation over a long period of time.

  Gas turbines for power generation and aircraft are in a harsh state in which working gas having a temperature of 1000 ° C. or higher is subjected to expansion work, and as the cumulative operation time increases, material deterioration and deformation appear in the high-temperature parts. .

  For this reason, precipitation-strengthening alloys such as Ni-base superalloys are used for gas turbine high-temperature parts such as combustor liners, transition pieces (combustor tail cylinders), stationary blades, and moving blades.

  Further, since the precipitation-strengthened alloy to be used is expensive, the gas turbine high-temperature component is reused after repairing / correcting a deteriorated or deformed one without performing disposal or new production as much as possible.

  In this case, the material deterioration is repaired by material regeneration by HIP (Hot Isostatic Pressing), which has a considerable effect.

  For example, Patent Literature 1 and Patent Literature 2 are disclosed as techniques for repairing material deterioration such as blades using such a technique.

  On the other hand, for example, the blade deformation repair technique does not correct the target part, but modifies the arrangement of the blade rows arranged along the circumference of the turbine shaft, and contacts the shrouds provided on the tops of adjacent blades. The shroud gap is adjusted to an appropriate dimension so that the area does not become too small.

  Specifically, when manufacturing a blade by forging, correct the torsional distortion and bending distortion generated in the blade effective part (working fluid passage part) using the press machine etc. This is a method of applying a pressing force from

For example, Patent Literature 3 and Patent Literature 4 are disclosed as techniques for repairing deformation of a wing or the like using such a technique.
JP 11-335802 A JP 2001-74245 A JP-A-8-276216 JP 2004-84663 A

  By the way, although the material regeneration process using the HIP process disclosed in Patent Documents 1 and 2 has achieved good results, the HIP process applies isotropic pressurization with an inert gas, so the deformation is repaired. Not suitable for letting

  For this reason, in order to prevent the contact area between the shrouds of adjacent wings from becoming too small, the pressing force of the press machine is used and adjustments are made by hand during the placement of the wings.

  For this reason, time and cost are required for adjustment, and even if the contact area between adjacent blades can be ensured by adjustment, the overall balance adjustment becomes difficult.

  In addition, the contact area may not be ensured regardless of the arrangement.

  On the other hand, even if the technology for applying a pressing force to the blade to repair the deformation using the press machine disclosed in Patent Documents 3 and 4 is suitable for repairing the deformation, the pressing force is applied to the blade. It is difficult to repair material deterioration such as wings alone.

  In this way, it is called material deterioration repair technology, shape / dimension deformation repair technology, which is superior to individual technologies for repair and repair, but technology that satisfies both at the same time has not yet been realized. Absent.

  In particular, the above-mentioned repair technology and repair technology require a lot of work time, cost, and labor of workers, and therefore it is desired to realize a new technology that can be repaired and repaired at the same time more simply and quickly. It was.

  This invention is made | formed based on such a situation, and it aims at providing the repairing and deformation | transformation correction method of the gas turbine high temperature components which can perform the material deterioration repair construction and deformation | transformation repair construction of object product simultaneously. .

In order to achieve the above-mentioned object, the gas turbine high-temperature part repair / deformation correction method according to the present invention is a correction / deformation correction of a gas turbine high-temperature part used at high temperatures as described in claim 1. At the time of production, the acceptance inspection process to confirm and grasp the defect, the recovery process / deformation correction process to simultaneously recover the material deterioration due to HIP processing and the deformation correction using the weight of the heavy object, and the structure and shape dimensions of the parts a solution heat treatment step and the aging heat treatment process to restore the state, after the aging heat treatment process, possess a pre-shipment inspection step of inspecting the part, heavy utilized in the deformation correction is previously prepared The weight of the heavy object is set using a master curve indicating the correlation between the amount of deformation and the weight of the heavy object, and the heavy object having the set weight is attached to the deformed portion of the gas turbine high-temperature part. It is a method to do.

In addition, in order to achieve the above-mentioned object, the gas turbine high-temperature part repair / deformation correction method according to the present invention corrects / deforms a gas turbine high-temperature part used at high temperatures as described in claim 2. during modification, the acceptance inspection step of confirming grasp defect, and the recovery process and deformation correcting step of performing recovery and weight the deformation correction using the weight of the material degradation simultaneously by HIP treatment, after the recovery process, the deformation correction process, possess a pre-shipment inspection step of inspecting the part, heavy utilized in the deformation correction is prepared in advance which had been modified amount - the weight of the heavy using a master curve showing the correlation heavy weight A method is characterized in that a set weight is set and a heavy object having a set weight is attached to a deformed portion of the high-temperature component of the gas turbine .

  Further, in order to achieve the above object, the gas turbine high-temperature part repair / deformation correction method according to the present invention is the HIP processing method as described in claim 3.

  Moreover, in order to achieve the above-described object, the gas turbine high-temperature part repair / deformation correction method according to the present invention includes a deformation correction step in which the deformation correction step is performed in advance. In this method, the weight of a heavy article is set using a master curve indicating the correlation of the weight of the heavy article, and the set weight of the heavy article is attached to a deformed portion of the gas turbine high-temperature component.

  Moreover, in order to achieve the above-mentioned object, the gas turbine high-temperature component repair / deformation correction method according to the present invention includes a combustor liner, a transition piece, This is a method of selecting either a stationary blade or a moving blade.

  The gas turbine high-temperature part repair / deformation correction method according to the present invention is a recovery process / deformation correction process in addition to an acceptance inspection process, a solution heat treatment, an aging heat treatment process, and a pre-shipment process when repairing and deforming a high-temperature part. In addition, because it is a process that allows material deterioration and deformation correction of high-temperature parts at the same time, the work time can be further shortened to reduce the labor of workers, and work efficiency can be further improved and maintenance measures taken. Can contribute.

  DESCRIPTION OF EMBODIMENTS Hereinafter, embodiments of a gas turbine high-temperature part repair / deformation correction method according to the present invention will be described with reference to the drawings and reference numerals attached to the drawings.

  FIG. 1 is a flowchart showing a first embodiment of a gas turbine high-temperature part repair / deformation correction method according to the present invention.

  The gas turbine high-temperature component according to the present invention is applied to, for example, a gas turbine blade and the like. Upon repair and modification of the gas turbine blade, etc., an acceptance inspection (step 1) for investigating and grasping the blade shape change and deformation. , Blade recovery treatment / deformation correction construction that simultaneously performs blade material deterioration and deformation correction (step 2), solution heat treatment (step 3) and aging heat treatment (step 4) for adjusting the blade structure to the original state, blade processing Each step of pre-shipment inspection after construction (step 5) is taken.

  First, in the acceptance inspection process of Step 1, for example, it is applied to a blade made of Inconel 738LC, which is a Ni-based superalloy that has reached the design life and is scheduled to be discarded. Fluorescent penetrant inspection is performed when defects such as dents and foreign objects cannot be confirmed visually, and the height from the blade root of the shroud provided on the blade top is measured using a height gauge or the like. Check for deformation at the beginning of the design.

  When it is confirmed in step 1 that the blade has deteriorated in material quality and deformation, in step 2, the blade recovery process and deformation correction are performed simultaneously.

  Wing recovery takes place over about 4 hours of HIP processing. In this HIP process, for example, a blade accommodated in an electric furnace is heated to about 1190 ° C. by a heater or the like, and a gas, for example, argon gas is sealed at 1000 atm.

  At that time, the deformation of the shroud of the wing is also corrected. As shown in FIG. 2, this deformation occurs when the shroud 2 provided at the top of the blade 1 was in the position indicated by the solid line at the beginning of production, but was exposed to high-temperature combustion gas during operation, causing creep deformation. , It may be deformed to the position indicated by the broken line.

  In this case, since the deformation amount is measured using a height gauge or the like as shown in step 1, the heavy object 3 corresponding to the deformation amount is attached to the shroud 2a that is deformed to the position indicated by the broken line. As shown in FIG. 3, the weight 3 is set by creating a relationship between the correction amount of the shroud 2a and the weight of the weight 3 in advance as a master curve and selecting the weight of the weight 3 from the master curve. Is done.

  Since many deformations of the shroud 2a can be seen in the direction of the ventral side of the wing, the deformation of the shroud 2a on the flank side of the wing is meticulously measured with a height gauge or the like.

  When the blade recovery process and the deformation correction process in Step 2 are completed, a solution heat treatment is performed in Step 3, and then an aging heat treatment is performed in Step 4.

  The solution heat treatment is performed, for example, in an electric furnace under a heating state at a temperature of about 1121 ° C. for about 2 hours, and in the aging heat treatment in Step 4, the heat treatment at a temperature of about 834 ° C. This is done over time to restore the wing structure and geometry to the original state.

  When the aging heat treatment process in step 4 is completed, a pre-shipment inspection process in step 5 is finally performed. In the pre-shipment inspection process of Step 5, the same as the acceptance inspection process of Step 1, visual inspection for cracks, thinning, etc., fluorescent penetration inspection when visual inspection is not possible, and shape dimension inspection using a height gauge are performed. It is shipped when it is confirmed that the wing has recovered at the beginning of production.

  As described above, in this embodiment, in the repair and deformation correction of the blade, since the deformation correction processing for correcting the blade deformation is performed at the same time as the recovery processing for recovering the material deterioration of the blade, the working time is further increased. It can be further shortened to reduce the labor of the operator.

  FIG. 4 is a flowchart showing a second embodiment of the gas turbine high-temperature part repair / deformation correction method according to the present invention.

  The gas turbine high-temperature component according to the present invention is applied to, for example, a moving blade of a gas turbine combustor liner and gas turbine blades. For repair and modification of these gas turbine high-temperature components, the first embodiment and Similarly, an acceptance inspection process (step A) for investigating and grasping the shape change and deformation of a high-temperature part, a high-temperature part recovery process and a deformation correction process (step B) for simultaneously performing material deterioration and deformation correction of the high-temperature part, and high-temperature part processing Each step of the pre-shipment inspection process (step C) after construction is taken.

  Here, the difference from the first embodiment is that solution heat treatment and aging heat treatment are not used.

  This is because, when using Hastelloy X material for the combustor liner, as shown in FIG. 5, the heavy object 3 is attached to the deformation region P of the gas turbine combustor 4 as shown in FIG. It is only necessary to correct the deformation during the HIP process, and it is based on the fact that no solution heat treatment or item heat treatment is required as in the first embodiment.

  The steps A, B, and C described above are the same steps as in the first embodiment.

  As described above, the present embodiment is a simple step of the acceptance inspection process in Step A, the high temperature part recovery process / deformation correction process in Step B, and the pre-shipment inspection process in Step C in repairing and modifying the gas turbine high temperature parts. Therefore, the work time can be further shortened and the labor of the operator can be reduced.

  In this embodiment, the combustor liner using the Hastelloy material is applied. However, the present invention is not limited to this example, and the U500 material, the U520 material, the IN989 material, the MarM247 material, and the IN792 material, which are Ni-based superalloys, are used. It is also applied to transition pieces of gas turbine rotor blades and gas turbine combustors, or gas turbine stationary blades.

The flowchart which shows 1st Embodiment of the repair and deformation | transformation correction method of the gas turbine high temperature components which concern on this invention. The conceptual diagram which shows the deformation correction of the shroud of a gas turbine blade among the repair and deformation correction methods of the gas turbine high temperature component which concerns on this invention. The mass-foo curve which shows the relationship between the correction amount used when the deformation | transformation correction of the shroud of a gas turbine blade is carried out among the repairing and deformation | transformation correction methods of the gas turbine high temperature component which concerns on this invention. The flowchart which shows 2nd Embodiment of the repair and deformation | transformation correction method of the gas turbine high temperature component which concerns on this invention. The conceptual diagram which shows deformation correction of a combustor liner among the repair and deformation correction methods of the gas turbine high temperature component which concerns on this invention.

Explanation of symbols

1 blade 2, 2a shroud 3 heavy load 4 gas turbine combustor

Claims (3)

Acceptance inspection process for confirming and grasping problems when correcting and correcting deformation of gas turbine hot parts used at high temperatures,
Recovery process / deformation correction process for simultaneously recovering material deterioration due to HIP processing and deformation correction using the weight of heavy objects,
A solution heat treatment step and an aging heat treatment step for restoring the structure and shape of the part to the state at the time of production; and
After aging heat treatment step, it possesses a pre-shipment inspection step of inspecting the part,
The heavy load used for the deformation correction is set in advance using a master curve indicating the correlation between the deformation amount and the heavy load weight prepared in advance. A method for repairing and deforming a gas turbine high-temperature part, characterized by being mounted on a deformed part of the gas turbine. Acceptance inspection process for confirming and grasping problems when correcting and correcting deformation of gas turbine hot parts used at high temperatures,
Recovery process / deformation correction process for simultaneously recovering material deterioration due to HIP processing and deformation correction using the weight of heavy objects,
After the recovery process, the deformation correction process, possess a pre-shipment inspection step of inspecting the part,
The heavy load used for the deformation correction is set in advance using a master curve indicating the correlation between the deformation amount and the heavy load weight prepared in advance. A method for repairing and deforming a gas turbine high-temperature part, characterized by being mounted on a deformed part of the gas turbine. 3. The gas turbine high-temperature part repair / deformation correcting method according to claim 1, wherein the gas turbine high-temperature part is selected from a combustor liner, a transition piece, a stationary blade, and a moving blade. .

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