CN114752890A - Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade - Google Patents

Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade Download PDF

Info

Publication number
CN114752890A
CN114752890A CN202210412071.7A CN202210412071A CN114752890A CN 114752890 A CN114752890 A CN 114752890A CN 202210412071 A CN202210412071 A CN 202210412071A CN 114752890 A CN114752890 A CN 114752890A
Authority
CN
China
Prior art keywords
protection
thermal barrier
barrier coating
turbine working
working blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202210412071.7A
Other languages
Chinese (zh)
Inventor
杨岩
单建红
王玉锋
王瑞
过月娥
赵洁
陈勇
孙佳渭
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northwestern Polytechnical University
AECC Aviation Power Co Ltd
Original Assignee
Northwestern Polytechnical University
AECC Aviation Power Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northwestern Polytechnical University, AECC Aviation Power Co Ltd filed Critical Northwestern Polytechnical University
Priority to CN202210412071.7A priority Critical patent/CN114752890A/en
Publication of CN114752890A publication Critical patent/CN114752890A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/04—Coating on selected surface areas, e.g. using masks
    • C23C14/042—Coating on selected surface areas, e.g. using masks using masks
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/24—Vacuum evaporation
    • C23C14/28—Vacuum evaporation by wave energy or particle radiation
    • C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Toxicology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The device and the method for local protection of the thermal barrier coating at the trailing edge of the turbine working blade comprise a protection clamping plate, a protection box and a turbine working blade fixing device; the turbine working blade tenon is arranged in the protection box and is fixed in the protection box through a turbine working blade fixing device; the protection cardboard is fixed to be set up in the protection box outside, and the protection cardboard can be connected with turbine working vane tail edge exhaust side hole cooperation. The protection method adopted by the invention has no influence and damage on the base body and the bonding layer of the turbine working blade, and only protects the thermal barrier coating in the local area of the trailing edge of the turbine working blade; the protection method adopted by the invention is convenient for controlling the size of the local protection area of the thermal barrier coating, the interfaces of the thermal barrier coating in the coating area and the uncoated area are regular and smooth, and the appearance quality of the thermal barrier coating is good.

Description

Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade
Technical Field
The invention belongs to the technical field of thermal barrier coatings of turbine working blades of aeroengines, and particularly relates to a device and a method for locally protecting a thermal barrier coating at the tail edge of a turbine working blade.
Background
At present, electron beam physical vapor deposition (EB-PVD) is widely used for preparing thermal barrier coatings of various turbine working blades due to the advantages of high deposition rate, easiness in control, capability of obtaining a columnar crystal structure, high thermal efficiency and the like, so that the high-temperature oxidation resistance, the corrosion resistance and the heat insulation performance of the turbine working blades are remarkably improved, and the service life of an engine is prolonged.
Although the service life of the turbine working blade in a high-temperature, high-speed and high-corrosivity environment is greatly prolonged by the thermal barrier coating, the weight of the turbine working blade is increased and the cooling air film hole is reduced by the thermal barrier coating, the service life of the turbine working blade is greatly influenced by the weight increase of the turbine working blade, and the cooling efficiency and the surface aerodynamic performance of the turbine working blade are adversely influenced by the reduction of the cooling air film hole. Therefore, in order to reduce the weight of the turbine working blade, prevent the cooling air film hole from being reduced, improve the cooling efficiency and the surface aerodynamic performance of the turbine working blade and prolong the service life of an engine, the turbine working blade needs to be subjected to local protection treatment of a thermal barrier coating. However, when the thermal barrier coating on the trailing edge of the turbine rotor blade is locally protected, the trailing edge of the turbine rotor blade is in a twisted curved surface structure, and the thermal barrier coating is coated in a high-temperature processing process, so that technical risks such as untight protection, thermal deformation protection and falling off are easily caused, and the technical difficulty of locally protecting the thermal barrier coating is high.
At present, the technical means of local protection of the thermal barrier coating mainly comprises a protective adhesive tape, protective slurry and tool protection. The protective adhesive tape has general flexibility and is mainly designed for flat surface application; the protective slurry is mainly formed by matching a binder and powder, and after the thermal barrier coating is processed, the protective slurry is difficult to clean and is easy to cause the phenomenon of hole blocking of the powder.
Disclosure of Invention
The invention aims to provide a device and a method for local protection of a thermal barrier coating of a trailing edge of a turbine working blade, so as to solve the problems.
In order to realize the purpose, the invention adopts the following technical scheme:
the device for locally protecting the thermal barrier coating at the tail edge of the turbine working blade comprises a protection clamping plate, a protection box and a turbine working blade fixing device; the turbine working blade is arranged in the protective box and is fixed in the protective box through a turbine working blade fixing device; the protection cardboard is fixed to be set up in the protection box outside, and the protection cardboard can be connected with turbine working vane tail edge exhaust side hole cooperation.
Further, the protective clamping plate comprises a protective baffle and clamping teeth; the protective baffle comprises two sections, the joint of the two sections is an L-shaped corner, and the joint of the L-shaped corner can be bent and corrected in the direction of the blade body along the dotted line.
Furthermore, every latch both sides all are provided with the recess, and the latch can inject in turbine working vane tail edge exhaust edge hole.
Furthermore, the protective baffle is also provided with bolt holes.
Furthermore, the protective baffle is connected with the protective box through a baffle bolt on the bolt hole.
Further, the thickness of the plate of the protective baffle is 0.2-0.4 mm, the number of the clamping teeth is 2-4, the width of the clamping teeth is 1-2 mm, and the length of the clamping teeth is 5-7 mm; the width dimension of the groove is 0.1-0.2 mm; the diameter of the bolt hole is 7 mm-9 mm.
Furthermore, the dotted line part of the L-shaped corner joint of the protective baffle is of a groove-shaped structure, and the included angle is controlled to be 100-120 degrees.
Further, the turbine working blade fixing device comprises a pull rod, a bolt and a positioning pin; the tenon position of the turbine working blade is fixed by adopting a pull rod, the bolt penetrating through the side wall is arranged on the outer side of the protection box, the positioning pin is arranged on the inner side of the protection box, and the positioning pin and the bolt clamp and fix the tenon end face of the turbine working blade.
Furthermore, the pull rod and the protection box are fastened by nuts.
Further, the method for locally protecting the thermal barrier coating of the trailing edge of the turbine working blade comprises the following steps:
Step 1, determining the number and the size of clamping teeth, determining the thickness of a protective baffle plate and the bending angle of an L-shaped corner, and manufacturing a protective clamping plate;
step 2, fixing the tenon part of the turbine working blade by adopting a pull rod, installing the pull rod into a protective box, fixing the tenon end face of the turbine working blade by adopting a bolt and a positioning pin, and fixing a protective clamping plate on the protective box by adopting a baffle bolt;
step 3, inserting the clamping teeth into exhaust edge holes of the turbine working blades, and slowly pushing the clamping teeth along the direction of the blade body air inlet edge until the protective baffle is pushed immovably;
and 4, mounting the protection device on the special protection coating tool, processing the thermal barrier coating, disassembling the protection baffle and the special protection fixture after the thermal barrier coating is processed, taking out the part, and detecting the thickness of the thermal barrier coating after protection treatment.
Compared with the prior art, the invention has the following technical effects:
the protection method adopted by the invention has no influence and damage on the base body and the bonding layer of the turbine working blade, and only protects the thermal barrier coating of the local area of the trailing edge of the turbine working blade;
the protection method adopted by the invention is convenient for controlling the size of the local protection area of the thermal barrier coating, the interfaces of the thermal barrier coatings of the coating area and the uncoated area are regular and smooth, and the appearance quality of the thermal barrier coating is good;
The protection method adopted by the invention can effectively prevent the phenomenon of powder hole blocking caused by protection processes such as protection slurry and the like, and provides technical support for development of local protection of the thermal barrier coating;
the protection method adopted by the invention is simple, has low production cost and can realize batch engineering application.
Drawings
FIG. 1 is a front view of a guard barrier construction;
FIG. 2 is a front view of a partial protective tooling structure for a thermal barrier coating of a trailing edge of a turbine working blade;
FIG. 3 is a sectional right view of a partial protection tool A-A of the thermal barrier coating at the trailing edge of the turbine working blade
FIG. 4 is a partial view of the thickness of the thermal barrier coating along the profile of the turbine blade after partial protection;
FIG. 5 is the structural morphology of the cross section of the thermal barrier coating on the exhaust edge of the turbine working blade after the embodiment 1;
FIG. 6 is the cross-sectional texture of the thermal barrier coating on the exhaust edge of the turbine rotor blade after the treatment according to the embodiment 2;
FIG. 7 is the structure of the cross section of the thermal barrier coating on the exhaust edge of the turbine blade after the embodiment 3;
Detailed Description
The invention is further described below with reference to the accompanying drawings:
referring to fig. 1 to 7, the device and method for local protection of thermal barrier coating on the trailing edge of a turbine blade:
(1) and manufacturing a protective baffle.
Fig. 1 shows a front view of a guard barrier structure. The thickness of the plate of the protective baffle 1 is 0.2 mm-0.4 mm, the number of the latch 2 is 2-4, the width of the latch 2 is 1 mm-2 mm, the length is 5 mm-7 mm, the width of the groove 3 on two sides of each latch is 0.1-0.2 mm, the latch 2 can be inserted into an exhaust edge hole of the trailing edge of the turbine working blade, the diameter of the bolt hole 4 is 7 mm-9 mm, the L corner 5 joint is bent and corrected in the direction of the blade body along the dotted line, and the bending angle is 100-120 degrees.
(2) The trailing edge is locally protected.
Fig. 2 and 3 show a front view and a right side view of a-a section of the structure of the guard fixture, respectively. Operation is as follows: the tenon position of the turbine working blade 6 is fixed by a pull rod 7 and is arranged in a protective box 8, the pull rod 7 and the protective box 8 are fastened by a nut 9, and except for the fixation of the pull rod 7, the tenon end face of the part 6 to be processed is fixed by a bolt 10 and a positioning pin 11; operation II: the tail edge exhaust edge of the turbine working blade 6 is shielded and protected by the protective baffle 1, and the protective baffle 1 and the protective box 8 are connected by the baffle bolt 12 through the bolt hole 4. In order to effectively protect the exhaust edge of the tail edge of the turbine working blade, the dotted line part of the corner joint 5 of the protective baffle plate L is of a groove-shaped structure, the included angle is controlled to be 100-120 degrees, simultaneously, the latch of the protective baffle plate is inserted into the exhaust edge hole of the turbine working blade, the protective baffle plate is slowly pushed along the direction of the inlet edge of the blade body until the protective baffle plate is still pushed, the stability of the protective tool is realized by utilizing the snap-in force between the latch 2 and the exhaust hole of the tail edge of the blade body, and the size requirement of the local protection area of the thermal barrier coating of the tail edge of the blade is ensured by utilizing the plate width of the protective baffle plate 1.
(3) And (4) processing the thermal barrier coating.
And (3) installing the turbine working blade into the special protective coating tool, connecting the turbine working blade with the main shaft of the equipment, ensuring firm connection and processing the thermal barrier coating.
(4) And (5) disassembling the protective clamp.
After the thermal barrier coating is processed, the protective baffle and the special protective fixture are disassembled, and the part is taken out.
(5) Thermal barrier coating thickness detection after protection treatment
According to the part section position in fig. 4, the thickness of the thermal barrier coating of the turbine working blade after protection is subjected to anatomical detection, and meanwhile, the part section position (tail edge exhaust edge part) in fig. 4 is subjected to metallographic structure observation so as to verify the feasibility of the tool protection method for the local area of the thermal barrier coating of the tail edge of the turbine working blade.
Embodiment 1:
(1) and manufacturing a protective baffle.
Fig. 1 shows a front view of a guard barrier structure. The thickness of the plate of the protective baffle 1 is 0.2mm, 2 numbers of the latch are 2, the width of the latch 2 is 1mm, the length of the latch 2 is 5mm, the width of the groove 3 on two sides of each latch is 0.1mm, the latch 2 can be inserted into the exhaust edge hole on the tail edge of the turbine working blade, the diameter of the bolt hole 4 is 7mm, the L corner joint 5 bends and corrects the shape of the blade body along the dotted line, and the bending angle is 100 degrees.
(2) The trailing edge is locally protected.
Fig. 2 and 3 show a front view and a right side view of a-a section of the structure of the guard fixture, respectively.
Operation is firstly: the tenon position of the turbine working blade 6 is fixed by a pull rod 7 and is arranged in a protective box 8, the pull rod 7 and the protective box 8 are fastened by a nut 9, and except for the fixation of the pull rod 7, the tenon end face of the part 6 to be processed is fixed by a bolt 10 and a positioning pin 11;
operation II: the tail edge exhaust edge of the turbine working blade 6 is shielded and protected by the protective baffle 1, and the protective baffle 1 and the protective box 8 are connected by the baffle bolt 12 through the bolt hole 4. In order to effectively protect the exhaust edge of the tail edge of the turbine working blade, the dotted line part of the corner joint 5 of the protective baffle plate L is of a groove-shaped structure, the included angle is controlled to be 100-120 degrees, meanwhile, the latch of the protective baffle plate is all inserted into the exhaust edge hole of the turbine working blade, the protective baffle plate is slowly pushed along the direction of the inlet edge of the blade body until the protective baffle plate is pushed immovably, the stability of a protective tool is realized by using the snap-in force between the latch 2 and the exhaust hole of the tail edge of the blade body, and the size requirement of the local protective area of the thermal barrier coating of the tail edge of the blade is ensured by using the plate width of the protective baffle plate 1.
(3) And (4) processing the thermal barrier coating.
The turbine working blade is arranged on the special protective coating tool and connected with the main shaft of the equipment, so that firm connection is ensured, and thermal barrier coating processing is carried out.
(4) And (5) disassembling the protective clamp.
After the thermal barrier coating is processed, the protective baffle and the special protective fixture are disassembled, and the part is taken out.
(5) Thermal barrier coating thickness detection after protection treatment
According to the part cross-section position in fig. 4, the thickness of the thermal barrier coating after the protection treatment is subjected to anatomical detection, and the result is shown in table 1, and it can be seen that after the protection is performed by adopting the local protection method of the thermal barrier coating at the trailing edge of the turbine working blade, the thickness of the coating at each part of the blade along the molded surface is 105-117 μm, and the thickness of the exhaust edge coating is 0 μm. Metallographic structure observation is carried out on the cross section position (tail edge exhaust edge position) of the part in the figure 4, as shown in figure 5, the exhaust edge of the part is coated without the thermal barrier coating, the problem of over-coating of the coating is avoided, the thermal barrier coating interface of the coating area and the non-coating area is regular and smooth, and the appearance quality of the thermal barrier coating is good.
Embodiment 2:
(1) and manufacturing a protective baffle.
Fig. 1 shows a front view of a guard barrier structure. The thickness of the plate of the protective baffle 1 is 0.3mm, 2 numbers of the latch are 3, the width of the latch 2 is 1.5mm, the length of the latch 2 is 6mm, the width of the groove 3 on two sides of each latch is 0.15mm, the latch 2 can be inserted into the exhaust edge hole on the tail edge of the turbine working blade, the diameter of the bolt hole 4 is 8mm, the L corner joint 5 bends and corrects the shape of the blade body along the dotted line, and the bending angle is 110 degrees.
(2) The trailing edge is locally protected.
Figures 2 and 3 show a front view and a right side view, in section a-a, respectively, of the structure of the guard clamp.
Operation is firstly: the tenon position of the turbine working blade 6 is fixed by a pull rod 7 and is arranged in a protective box 8, the pull rod 7 and the protective box 8 are fastened by a nut 9, and except for the fixation of the pull rod 7, a bolt 10 and a positioning pin 11 are adopted to fix the tenon end face of the part 6 to be processed;
operation II: the tail edge exhaust edge of the turbine working blade 6 is shielded and protected by the protective baffle 1, and the protective baffle 1 and the protective box 8 are connected by the baffle bolt 12 through the bolt hole 4. In order to effectively protect the exhaust edge of the tail edge of the turbine working blade, the dotted line part of the corner joint 5 of the protective baffle plate L is of a groove-shaped structure, the included angle is controlled to be 100-120 degrees, simultaneously, the latch of the protective baffle plate is inserted into the exhaust edge hole of the turbine working blade, the protective baffle plate is slowly pushed along the direction of the inlet edge of the blade body until the protective baffle plate is still pushed, the stability of the protective tool is realized by utilizing the snap-in force between the latch 2 and the exhaust hole of the tail edge of the blade body, and the size requirement of the local protection area of the thermal barrier coating of the tail edge of the blade is ensured by utilizing the plate width of the protective baffle plate 1.
(3) And (4) processing the thermal barrier coating.
And (3) installing the turbine working blade into the special protective coating tool, connecting the turbine working blade with the main shaft of the equipment, ensuring firm connection and processing the thermal barrier coating.
(4) And (5) disassembling the protective clamp.
After the thermal barrier coating is processed, the protective baffle and the special protective fixture are disassembled, and the part is taken out.
(5) Thermal barrier coating thickness detection after protection treatment
According to the cross-sectional position of the part in fig. 4, the thickness of the thermal barrier coating after the protection treatment is subjected to anatomical detection, and the result is shown in table 1, and it can be seen that after the protection is performed by adopting the local protection method for the thermal barrier coating at the trailing edge of the turbine working blade, the thickness of the coating at each part of the blade along the molded surface is 104-115 μm, and the thickness of the coating at the exhaust edge is 0 μm. Metallographic structure observation is carried out on the section position (tail edge exhaust edge position) of the part in the figure 4, as shown in figure 6, the exhaust edge of the part is coated without the thermal barrier coating, the problem of over-coating of the coating is avoided, the thermal barrier coating interface of the coating area and the thermal barrier coating interface of the non-coating area are regular and smooth, and the appearance quality of the thermal barrier coating is good.
Embodiment 3:
(1) and manufacturing a protective baffle.
Fig. 1 is a front view of a guard structure. The thickness of the plate of the protective baffle 1 is 0.4mm, the number of the latch 2 is 4, the width of the latch 2 is 2mm, the length of the latch 2 is 7mm, the width of the groove 3 on the two sides of each latch is 0.2mm, the latch 2 can be inserted into an exhaust edge hole on the tail edge of a turbine working blade, the diameter of the bolt hole 4 is 9mm, the L-shaped corner joint 5 bends and corrects the shape of the blade body along the dotted line, and the bending angle is 120 degrees.
(2) The trailing edge is locally protected.
Figures 2 and 3 show a front view and a right side view, in section a-a, respectively, of the structure of the guard clamp.
Operation is firstly: the tenon position of the turbine working blade 6 is fixed by a pull rod 7 and is arranged in a protective box 8, the pull rod 7 and the protective box 8 are fastened by a nut 9, and except for the fixation of the pull rod 7, the tenon end face of the part 6 to be processed is fixed by a bolt 10 and a positioning pin 11;
operation II: the tail edge exhaust edge of the turbine working blade 6 is shielded and protected by the protective baffle 1, and the protective baffle 1 and the protective box 8 are connected by the baffle bolt 12 through the bolt hole 4. In order to effectively protect the exhaust edge of the tail edge of the turbine working blade, the dotted line part of the corner joint 5 of the protective baffle plate L is of a groove-shaped structure, the included angle is controlled to be 100-120 degrees, simultaneously, the latch of the protective baffle plate is inserted into the exhaust edge hole of the turbine working blade, the protective baffle plate is slowly pushed along the direction of the inlet edge of the blade body until the protective baffle plate is still pushed, the stability of the protective tool is realized by utilizing the snap-in force between the latch 2 and the exhaust hole of the tail edge of the blade body, and the size requirement of the local protection area of the thermal barrier coating of the tail edge of the blade is ensured by utilizing the plate width of the protective baffle plate 1.
(3) And (4) processing the thermal barrier coating.
And (3) installing the turbine working blade into the special protective coating tool, connecting the turbine working blade with the main shaft of the equipment, ensuring firm connection and processing the thermal barrier coating.
(4) And (5) disassembling the protective clamp.
After the thermal barrier coating is processed, the protective baffle and the special protective fixture are disassembled, and the part is taken out.
(5) Thermal barrier coating thickness detection after protection treatment
According to the part cross-section position in fig. 4, the thickness of the thermal barrier coating after the protection treatment is subjected to anatomical detection, and the result is shown in table 1, and it can be seen that after the protection is performed by adopting the local protection method for the thermal barrier coating at the trailing edge of the turbine working blade, the thickness of the coating at each part of the blade along the profile is 105-118 μm, and the thickness of the exhaust edge coating is 0 μm. Metallographic structure observation is carried out on the cross section position (tail edge exhaust edge position) of the part in the figure 4, as shown in figure 7, the exhaust edge of the part is coated without the thermal barrier coating, the problem of over-coating of the coating is avoided, the thermal barrier coating interface of the coating area and the non-coating area is regular and smooth, and the appearance quality of the thermal barrier coating is good.
TABLE 1
Figure BDA0003604388250000081

Claims (10)

1. The device for locally protecting the thermal barrier coating at the tail edge of the turbine working blade is characterized by comprising a protection clamping plate, a protection box (8) and a turbine working blade fixing device; the tenon of the turbine working blade is arranged in the protective box (8), and the tenon of the turbine working blade (6) is fixed in the protective box (8) through a turbine working blade fixing device; the protection cardboard is fixed to be set up in protection box (8) outside, and the protection cardboard can be connected with turbine working blade tail edge exhaust edge hole cooperation.
2. The device for the local protection of the thermal barrier coating of the tail edge of a turbine working blade according to claim 1, characterized in that the protection catch plate comprises a protection baffle (1) and a latch (2); the plurality of clamping teeth (2) are arranged on the protective baffle (1), the protective baffle (1) comprises two sections, the joint of the two sections is an L-shaped corner (5), and the joint of the L-shaped corner (5) can be bent and corrected towards the blade body direction.
3. Device for the local protection of the thermal barrier coating of the trailing edge of a turbine rotor blade according to claim 2, characterized in that each latch (2) is provided with a recess (3) on both sides, the latch (2) being insertable into the exhaust-edge hole of the trailing edge of a turbine rotor blade.
4. Device for the local protection of the thermal barrier coating of the trailing edge of a turbine working blade according to claim 3, characterized in that the protective shield (1) is also provided with bolt holes (4).
5. Device for the local protection of the thermal barrier coating of the trailing edge of a turbine working blade according to claim 4, characterized in that the protective screen (1) is connected with the protective box (8) by means of screen bolts (12) on the bolt holes (4).
6. The device for the local protection of the thermal barrier coating at the tail edge of the turbine working blade as claimed in claim 2, characterized in that the thickness of the plate of the protective baffle (1) is 0.2 mm-0.4 mm, the number of the latches (2) is 2-4, the width of the latches (2) is 1 mm-2 mm, and the length is 5 mm-7 mm; the width dimension of the groove (3) is 0.1-0.2 mm; the diameter of the bolt hole (4) is 7-9 mm.
7. The device for the local protection of the thermal barrier coating at the tail edge of the turbine working blade as claimed in claim 2, characterized in that the L-shaped corner junction of the protective baffle (1) is in a "groove" shaped structure, and the included angle is controlled to be 100-120 °.
8. Device for the local protection of the turbine rotor blade trailing edge thermal barrier coating according to claim 1, characterized in that the turbine rotor blade fixing means comprise tie rods (7), bolts (10) and dowel pins (11); the tenon position of the turbine working blade (6) is fixed by adopting a pull rod (7), a bolt (10) penetrating through the side wall is arranged on the outer side of the protection box (8), a positioning pin (11) is arranged on the inner side of the protection box, and the positioning pin (11) and the bolt (10) clamp and fix the tenon end face of the turbine working blade (6).
9. Device for the local protection of the thermal barrier coating of the trailing edge of a turbine working blade according to claim 1, characterized in that the tie rod (7) is fastened with the protective box (8) with a nut (9).
10. Method for the local protection of the thermal barrier coating of the trailing edge of a turbine rotor blade, characterized in that the device for the local protection of the thermal barrier coating of the trailing edge of a turbine rotor blade, based on any of claims 1 to 9, comprises the following steps:
Step 1, determining the number and the size of clamping teeth, determining the thickness of a protective baffle plate and the bending angle of an L-shaped corner part, and manufacturing a protective clamping plate;
step 2, fixing the tenon part of the turbine working blade by adopting a pull rod, installing the pull rod into a protection box, fixing the tenon end face of the turbine working blade by adopting a bolt and a positioning pin, and fixing a protection clamping plate on the protection box by adopting a baffle bolt;
step 3, inserting the clamping teeth into exhaust side holes of the turbine working blades, and slowly pushing the clamping teeth along the direction of the air inlet side of the blade body until the protective baffle is pushed immovably;
and 4, mounting the protection device on the special protection coating tool, processing the thermal barrier coating, disassembling the protection baffle and the special protection fixture after the thermal barrier coating is processed, taking out the part, and detecting the thickness of the thermal barrier coating after protection treatment.
CN202210412071.7A 2022-04-19 2022-04-19 Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade Pending CN114752890A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210412071.7A CN114752890A (en) 2022-04-19 2022-04-19 Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210412071.7A CN114752890A (en) 2022-04-19 2022-04-19 Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade

Publications (1)

Publication Number Publication Date
CN114752890A true CN114752890A (en) 2022-07-15

Family

ID=82330405

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210412071.7A Pending CN114752890A (en) 2022-04-19 2022-04-19 Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade

Country Status (1)

Country Link
CN (1) CN114752890A (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2339443A1 (en) * 2000-03-08 2001-09-08 Mitsubishi Heavy Industries, Ltd. Gas turbine cooled stationary blade
CN104404454A (en) * 2014-11-04 2015-03-11 西安航空动力股份有限公司 Tool for depositing coating on multi-arc ion plating equipment and usage method thereof
CN106521428A (en) * 2016-08-26 2017-03-22 中航动力股份有限公司 Device for local coating painting of turbine guide vane and painting technique of device
EP3347200A1 (en) * 2015-11-27 2018-07-18 Siemens Aktiengesellschaft Local two-layer thermal barrier coating
CN113001339A (en) * 2021-03-17 2021-06-22 中国航发动力股份有限公司 Turbine blade thermal barrier coating finishing protection device and method
CN215209602U (en) * 2020-12-22 2021-12-17 中船重工龙江广瀚燃气轮机有限公司 Thermal barrier coating protection device for preparing turbine working blade

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2339443A1 (en) * 2000-03-08 2001-09-08 Mitsubishi Heavy Industries, Ltd. Gas turbine cooled stationary blade
US20010021343A1 (en) * 2000-03-08 2001-09-13 Masamitsu Kuwabara Gas turbine cooled stationary blade
CN104404454A (en) * 2014-11-04 2015-03-11 西安航空动力股份有限公司 Tool for depositing coating on multi-arc ion plating equipment and usage method thereof
EP3347200A1 (en) * 2015-11-27 2018-07-18 Siemens Aktiengesellschaft Local two-layer thermal barrier coating
CN106521428A (en) * 2016-08-26 2017-03-22 中航动力股份有限公司 Device for local coating painting of turbine guide vane and painting technique of device
CN215209602U (en) * 2020-12-22 2021-12-17 中船重工龙江广瀚燃气轮机有限公司 Thermal barrier coating protection device for preparing turbine working blade
CN113001339A (en) * 2021-03-17 2021-06-22 中国航发动力股份有限公司 Turbine blade thermal barrier coating finishing protection device and method

Similar Documents

Publication Publication Date Title
JP5394004B2 (en) Method for protecting airfoils and leading edges of airfoils
EP2823085B1 (en) Method of making leading edge protection
EP2154333B1 (en) Airfoil and corresponding turbine assembly
US7393183B2 (en) Trailing edge attachment for composite airfoil
JP6034860B2 (en) Turbomachine element
KR20080037586A (en) Airfoil shape for a turbine nozzle
JP2007285296A (en) Method for repairing/replacing vane and turbine engine component
CN114752890A (en) Device and method for local protection of thermal barrier coating of trailing edge of turbine working blade
CN113357010A (en) Forward radar stealth structure of aircraft engine
US20170335699A1 (en) Inter-turbine ducts
CN112901278B (en) Turbine blade adopting buckle fixed ceramic armor
US10309237B2 (en) Shield
CN115161578B (en) Thermal barrier coating spraying method for blade with air film Kong Guolun
US20240003265A1 (en) Blade comprising a shield having a defrosting air passage duct
US11346242B1 (en) Retaining ejected gas turbine blades
JP2007270833A (en) Stator blade having locally reworked shape, stator section with such stator blade, compression stage, compressor, and turbomachine
CN219993750U (en) Rotor structure with long service life
CN112901279B (en) Turbine blade adopting bolt-fixed ceramic armor
US20240068438A1 (en) Protective cap for a leading edge of a wind turbine blade
CN211914264U (en) Gas turbine movable vane clamp
CN116085062A (en) Turbine guide vane in aeroengine
CN113891835A (en) Air inlet pipe lip of a turbojet engine nacelle comprising acoustic means and method for manufacturing such a lip
WO2023062578A1 (en) Blade for a low-noise industrial axial fan, industrial axial fan and process for manufacturing a blade of an industrial axial fan

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination