CN110617114B - Ceramic-coated high-temperature alloy stator blade - Google Patents
Ceramic-coated high-temperature alloy stator blade Download PDFInfo
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- CN110617114B CN110617114B CN201910821113.0A CN201910821113A CN110617114B CN 110617114 B CN110617114 B CN 110617114B CN 201910821113 A CN201910821113 A CN 201910821113A CN 110617114 B CN110617114 B CN 110617114B
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- 239000000919 ceramic Substances 0.000 title claims abstract description 162
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 156
- 239000000956 alloy Substances 0.000 title claims abstract description 156
- 238000001816 cooling Methods 0.000 claims abstract description 154
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 86
- 239000002131 composite material Substances 0.000 claims abstract description 60
- 230000007704 transition Effects 0.000 claims abstract description 49
- 239000000463 material Substances 0.000 claims abstract description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 10
- 230000003068 static effect Effects 0.000 claims abstract description 6
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 5
- 239000010941 cobalt Substances 0.000 claims abstract description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 5
- 239000010410 layer Substances 0.000 claims description 116
- 238000009826 distribution Methods 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 9
- 239000002002 slurry Substances 0.000 claims description 8
- 230000003139 buffering effect Effects 0.000 claims description 7
- 238000010304 firing Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 6
- 239000002344 surface layer Substances 0.000 claims description 6
- 238000003466 welding Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000010146 3D printing Methods 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 4
- 238000004381 surface treatment Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 3
- 238000005266 casting Methods 0.000 claims description 2
- 230000008859 change Effects 0.000 claims description 2
- 239000000872 buffer Substances 0.000 claims 1
- 230000035939 shock Effects 0.000 abstract description 4
- 239000011248 coating agent Substances 0.000 description 13
- 238000000576 coating method Methods 0.000 description 13
- 239000012720 thermal barrier coating Substances 0.000 description 9
- 238000004519 manufacturing process Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000004080 punching Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 238000005507 spraying Methods 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 3
- 229910002110 ceramic alloy Inorganic materials 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
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- 238000010586 diagram Methods 0.000 description 1
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- 238000005495 investment casting Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
本发明公开了一种覆陶合金静叶片，包括高温合金坯体、高温合金冷却管网、陶瓷复合材料过渡层、陶瓷层。高温合金坯体是钴基或镍基高温合金铸造而成，合金坯体有冷却通道，通道的表面冷却孔处均铸造有凸起框架，冷却管网由同材质的高温合金冷却管编织成网状，凸起框架和网状结构连接形成悬浮在坯体外的一层结构。陶瓷过渡层喷涂在此坯体和网状结构上。陶瓷层、过渡层、网状结构和高温合金胚体形成静叶。网状结构可以增加陶瓷结合厚度，过渡层和网状结构抵消热冲击时的应力。本发明可提高涡轮入口温度和涡轮机械的效率，延长其使用寿命。
The invention discloses a ceramic-clad alloy static blade, which comprises a superalloy body, a superalloy cooling pipe network, a ceramic composite material transition layer and a ceramic layer. The superalloy body is cast from cobalt-based or nickel-based superalloy. The alloy body has cooling channels. The surface cooling holes of the channels are all cast with raised frames. The cooling pipe network is woven into a network of superalloy cooling pipes of the same material. shape, the raised frame and the mesh structure are connected to form a one-layer structure suspended outside the green body. A ceramic transition layer is sprayed on this green body and mesh structure. The ceramic layer, the transition layer, the network structure and the superalloy body form the stationary blade. The mesh structure can increase the thickness of the ceramic bond, and the transition layer and mesh structure offset the stress during thermal shock. The invention can improve the turbine inlet temperature and the efficiency of the turbomachine, and prolong its service life.
Description
Technical Field
The invention relates to a high-temperature alloy part of fluid power equipment, in particular to a ceramic-coated high-temperature alloy blade, which is applied to the technical field of gas turbine and engine turbine machinery.
Background
The utilization efficiency of the turbine machinery can be improved by improving the inlet temperature of the turbine according to the Brayton cycle, and how to improve the inlet temperature of the turbine machinery is related to the performance of the turbine machinery. The turbine inlet temperature of modern gas turbines and engines reaches 1650-1750 ℃, the third generation single crystal material can only bear 1100 ℃, the air film cooling can have a cooling effect of 400 ℃, the difference of about 100-200 ℃ exists, and the current is realized by a TBC thermal barrier coating. How to increase the thickness of the thermal barrier coating and increase the heat-resisting temperature can improve the inlet temperature of the turbine, and can improve the performance and efficiency of the combustion engine and the engine.
Reference is made to fig. 1 for a schematic view of the TBC coating structure of siemens patent US 2016/0369637 and fig. 2 for a schematic view of the TBC coating structure of Rolls-Royce patent US 2017/0096902. Both Siemens patent US 2016/0369637 and Rolls-Royce patent US 2017/0096902 propose TBC coating schemes that use the special structure of the blank to increase the adhesion of the coating, but the coating thickness of this type of TBC has certain limitations to only reach the tens of μm level.
Disclosure of Invention
In order to solve the problems in the prior art, the invention aims to overcome the defects in the prior art and provide a ceramic-coated superalloy stator blade, wherein a ceramic layer, a transition layer, a net structure and a superalloy blank form an integral structure of the stator blade. The net structure outside the high-temperature alloy blank can increase the ceramic bonding thickness and can improve the micron-grade coating to a mm-grade composite structure of ceramic and alloy; the transition layer and the network counteract the stress upon thermal shock. The invention can improve the turbine inlet temperature and the efficiency of the turbine machinery, and prolong the service life of the turbine machinery.
In order to achieve the purpose, the invention adopts the following technical scheme:
a ceramic-coated high-temperature alloy stator blade comprises a high-temperature alloy blank body, wherein a ceramic composite material transition layer and a ceramic layer are sequentially combined on the surface of the high-temperature alloy blank body, so that the ceramic composite material transition layer is positioned between the high-temperature alloy blank body and the ceramic layer to form an intermediate material layer with buffering, energy conduction and force transmission functions, the high-temperature alloy blank body, the ceramic composite material transition layer and the ceramic layer form an integrated composite material stator blade, a high-temperature alloy cooling pipe network is arranged in the integrated composite material stator blade, and the high-temperature alloy cooling pipe network penetrates through the high-temperature alloy blank body, the ceramic composite material transition layer and the ceramic layer to form a heat flow transmission channel; the hollow bulge is used as a fixed support pile foot of the high-temperature alloy cooling pipe network, so that the hollow bulge is connected with the high-temperature alloy cooling pipe network to form a bulge frame, and a pipe cavity of the hollow bulge is used as a part of a heat flow transmission channel and is communicated with the high-temperature alloy cooling pipe network; the outer surface of the high-temperature alloy blank and the outer surface of the high-temperature alloy cooling pipe network are both attached with ceramic composite material transition layers, ceramic layers are attached to the surfaces of the ceramic composite material transition layers, and the high-temperature alloy cooling pipe network also forms a three-dimensional reticular framework structure which is connected with the high-temperature alloy blank, the ceramic composite material transition layers and the ceramic layers. The invention relates to the structural form of ceramics and high-temperature alloy, and can improve the coating of micrometer level to the composite structure of ceramics and alloy of mm level. The invention comprises a high-temperature alloy blank, a high-temperature alloy frame cooling pipe network, a ceramic composite material transition layer and a ceramic layer part.
As the preferred technical scheme of the invention, cooling holes are distributed on the whole surface of the ceramic high-temperature alloy stationary blade according to thermodynamic distribution, the cooling holes are mainly arranged in the ceramic layer, and the cooling holes are communicated with a high-temperature alloy cooling pipe network to form a complete cooling channel. According to a further preferable technical scheme of the invention, hollow bulges are cast on the surface of the high-temperature alloy blank according to a structure staggered with the surface position of the high-temperature alloy blank corresponding to the cooling hole in the ceramic layer, so as to form a cooling channel of the main pipe rotor branch pipe structure. As another further preferable technical scheme, corresponding hollow bulges are cast at the positions, corresponding to the high-temperature alloy blank surface, of the cooling holes in the ceramic layer to form a cross-shaped cooling channel. The high-temperature alloy blank provided by the invention is internally provided with a cooling channel, and the internal cooling channel part is consistent with the design of a conventional turbine mechanical stationary blade. Compared with the conventional design, the cooling pipe network is different in that the surface of the cooling pipe network is provided with a bulge for supporting the alloy pipe network, and the bulge is hollow and then welded with the alloy pipe network to form a complete cooling pipe network. The bulge is of a hollow structure and is connected with a cooling channel in the blank.
As a preferred technical scheme of the invention, a part pipeline of the high-temperature alloy cooling pipe network forms a cooling channel arranged in the high-temperature alloy blank, the high-temperature alloy cooling pipe network adopts high-temperature alloy cooling pipes which are made of the same material as the high-temperature alloy blank to weave a spatial reticular structure, and the raised frame and the reticular structure are connected to form a layer of frame structure which is arranged outside the high-temperature alloy blank in a hanging manner. The ceramic layer is attached to the high-temperature alloy blank and the alloy pipe network and can resist higher temperature, the ceramic layer is positioned between the alloy blank and the pipe network structure and different ceramics on the pipe network structure to form a whole, and the whole is attached to the special structure of the invention, and the thickness of the ceramic of the invention can reach mm level.
The high-temperature alloy blank is preferably cast by cobalt-based high-temperature alloy or nickel-based high-temperature alloy.
As a preferred technical scheme of the invention, the ceramic composite material transition layer is prepared by adopting a component gradient material, and the composite material components of the ceramic composite material transition layer are subjected to gradient change from a high-temperature alloy surface layer combined with the high-temperature alloy blank to a ceramic surface layer combined with the ceramic layer to form a functional material layer for buffering the internal stress of the cold and hot material difference. The ceramic composite layer is sprayed on the high-temperature alloy blank and the alloy pipe network and is used for buffering the physical difference of the cold and hot thermal expansion and heat conduction of the alloy and the ceramic. The composition of the composite material from the high temperature aggregate layer to the ceramic layer has a gradient.
The high-temperature alloy blank and the high-temperature alloy cooling pipe network are preferably formed by welding, 3D printing or direct casting.
As the preferred technical scheme of the invention, after the high-temperature alloy cooling pipe network is prepared, heat treatment is carried out to eliminate forming stress; and carrying out surface treatment and external dimension control on the surface of the high-temperature alloy blank and the surface of the high-temperature alloy cooling pipe network.
As a preferred technical scheme, when the ceramic layer is prepared, an alloy blank completing a preparation procedure of the ceramic composite material transition layer is fixed on a tool and arranged in a stationary blade die, then ceramic liquid slurry of the ceramic layer is poured into the stationary blade die, and the ceramic slurry is fully and tightly combined with a high-temperature alloy net structure outside a high-temperature alloy blank and the surface of the high-temperature alloy blank through centrifugal vibration; and then after the stationary blade is formed and fixed, removing the mold, transferring the formed stationary blade to a blade firing furnace, performing firing forming, and then performing punching treatment on the surface of the ceramic layer to manufacture the cooling hole. And arranging cooling holes on the whole surface of the high-temperature alloy stator blade attached to the ceramic layer according to thermodynamic distribution, punching holes on the surfaces of all the composite stator blades and uniformly arranging the composite stator blades, wherein the cooling holes are connected with a high-temperature alloy pipe network to form a complete cooling channel. The cooling system formed in this way is complete and has excellent cooling effect.
As a preferred technical scheme, the high-temperature alloy pipe network is formed by welding an alloy pipe with the inner diameter larger than a certain size and a high-temperature alloy blank in a protruding mode. Forming a complete cooling pipe network. Wherein, the pipe network has a certain distance from the surface of the high-temperature alloy blank body, which is convenient for the attachment of the ceramic layer. In addition, the distribution of blade cooling is fully considered in the arrangement of the pipe network, and all the pipe distribution positions are the positions of the outermost ceramic layer with cooling holes.
Compared with the prior art, the invention has the following obvious and prominent substantive characteristics and remarkable advantages:
1. the alloy blank body is provided with a cooling channel, raised frames are cast at cooling holes on the surface of the channel, a cooling pipe network is woven into a net shape by high-temperature alloy cooling pipes made of the same material, and the raised frames and the net structure are connected to form a layer of structure suspended outside the blank body; the ceramic transition layer is sprayed on the green body and the reticular structure; the ceramic layer, the transition layer, the net structure and the high-temperature alloy blank form a static blade; the net structure can increase the thickness of the ceramic combination, and the transition layer and the net structure counteract the stress during thermal shock. The invention can improve the turbine inlet temperature and the efficiency of the turbine machinery, and prolong the service life of the turbine machinery;
2. the structural form of the ceramic and the high-temperature alloy is redesigned, a cooling channel is arranged in the high-temperature alloy blank, and the part of the internal cooling channel is consistent with the design of the conventional turbine mechanical stationary blade; the difference from the conventional design is that the surface of the high-temperature alloy blank body is provided with a bulge for supporting an alloy pipe network, and the bulge is hollow and then welded with the alloy pipe to form a complete cooling pipe network; the bulge is of a hollow structure and is connected with a cooling channel in the blank; the composite structure of ceramic and alloy can improve the micron-grade coating to the mm-grade;
3. the cooling holes are distributed according to the thermodynamic distribution on the whole surface of the high-temperature alloy static blade attached by ceramics, the holes are uniformly distributed on the surfaces of all the composite static blades, and the cooling holes are connected with a high-temperature alloy pipe network to form a complete cooling channel, so that the formed cooling system is complete and has excellent cooling effect; the ceramic-coated high-temperature alloy stator blade has a simple structure, so that the tolerance of the ceramic-coated high-temperature alloy stator blade to complex working conditions is obviously improved, and the performance and efficiency of a combustion engine and an engine using the ceramic-coated high-temperature alloy stator blade are obviously improved.
Drawings
FIG. 1 is a schematic representation of a prior art TBC coating structure.
FIG. 2 is a schematic representation of a prior art TBC coating structure.
FIG. 3 is a schematic structural diagram of a ceramic-coated superalloy stationary blade according to an embodiment of the present invention.
FIG. 4 is a schematic view of a cooling hole structure and a local portion of an alloy cooling pipe network of a ceramic-coated superalloy stationary blade according to an embodiment of the present invention.
FIG. 5 is a schematic view of the arrangement of cooling holes at the trailing edge of a ceramic-coated superalloy stator blade according to an embodiment of the present invention.
FIG. 6 is a schematic view of a cylinder structure on the surface of a superalloy blank according to an embodiment of the present invention.
FIG. 7 is a schematic view of a superalloy blank and an alloy cooling pipe network according to an embodiment of the present invention.
Detailed Description
The above-described scheme is further illustrated below with reference to specific embodiments, which are detailed below:
the first embodiment is as follows:
in this embodiment, referring to fig. 3 to 7, a ceramic-coated superalloy stator blade includes a superalloy blank 1, a ceramic composite transition layer 3 and a ceramic layer 4 are sequentially bonded to a surface of the superalloy blank 1, so that the ceramic composite transition layer 3 is located between the superalloy blank 1 and the ceramic layer 4 to form an intermediate material layer with buffering, energy conduction and force transmission functions, the superalloy blank 1, the ceramic composite transition layer 3 and the ceramic layer 4 form an integrated composite stator blade, a superalloy cooling pipe network 2 is disposed in the integrated composite stator blade, and the superalloy cooling pipe network 2 passes through the superalloy blank 1, the ceramic composite transition layer 3 and the ceramic layer 4 to form a heat flow transmission channel; the cast hollow bulge 6 on the high-temperature alloy blank 1 is connected with the high-temperature alloy cooling pipe network 2, the hollow bulge 6 is used as a fixed supporting pile foot of the high-temperature alloy cooling pipe network 2, the hollow bulge 6 is connected with the high-temperature alloy cooling pipe network 2 to form a bulge frame, and the pipe cavity of the hollow bulge 6 is used as a part of a heat flow transmission channel and is communicated with the high-temperature alloy cooling pipe network 2; the outer surface of the high-temperature alloy blank 1 and the outer surface of the high-temperature alloy cooling pipe network 2 are both attached with a ceramic composite material transition layer 3, the surface of the ceramic composite material transition layer 3 is attached with a ceramic layer 4, and the high-temperature alloy cooling pipe network 2 also forms a three-dimensional reticular framework structure for connecting the high-temperature alloy blank 1, the ceramic composite material transition layer 3 and the ceramic layer 4. The embodiment relates to the structural form of ceramics and high-temperature alloy, and the composite structure of ceramics and alloy with the micron-scale coating improved to the mm-scale coating is improved.
In the present embodiment, referring to fig. 3 to 5, cooling holes 5 are arranged on the entire surface of the ceramic superalloy stator blade in thermodynamic distribution, the cooling holes 5 are mainly disposed in the ceramic layer 4, and the cooling holes 5 are communicated with the superalloy cooling pipe network 2 to form a complete cooling channel. The cooling holes 5 are connected with the high-temperature alloy cooling pipe network 2 to form a complete cooling channel.
In the present embodiment, referring to fig. 4 and 5, hollow protrusions 6 are cast on the surface of the superalloy blank 1 in a staggered configuration at locations on the surface of the superalloy blank 1 corresponding to the cooling holes 5 in the ceramic layer 4 to form cooling channels for the primary tube-in-wheel manifold structure. The hollow bulge 6 can support the high-temperature alloy cooling pipe network 2, and the hollow channel of the hollow bulge 6 is welded with the alloy pipeline to form a complete cooling pipe network. The hollow bulge 6 is a hollow structure and is connected with a cooling channel inside the high-temperature alloy blank 1.
In this embodiment, referring to fig. 3 to 7, a part of the pipeline of the superalloy cooling pipe network 2 forms a cooling channel inside the superalloy blank 1, and the superalloy cooling pipe network 2 is woven into a spatial network structure by using a superalloy cooling pipe made of the same material as the superalloy blank 1, so that the raised frame and the network structure are connected to form a layer of frame structure suspended outside the superalloy blank 1. The high-temperature alloy blank 1 is cast by cobalt-based high-temperature alloy or nickel-based high-temperature alloy.
In this embodiment, referring to fig. 3 to 7, the ceramic composite transition layer 3 is made of a composition gradient material, and the composite composition of the ceramic composite transition layer 3 changes in a gradient manner from the high temperature alloy surface layer combined with the high temperature alloy blank 1 to the ceramic surface layer combined with the ceramic layer 4, so as to form a functional material layer for buffering the internal stress of the material difference in cold and hot states.
In the present embodiment, referring to fig. 3 to 7, the superalloy blank 1 is directly cast for structural shaping, and the superalloy cooling pipe network 2 is welded for structural shaping. After the high-temperature alloy cooling pipe network 2 is prepared, heat treatment is carried out to eliminate forming stress; the surface treatment and the external dimension control are also carried out on the surface of the high-temperature alloy billet 1 and the surface of the high-temperature alloy cooling pipe network 2.
In this embodiment, referring to fig. 3 to 7, when preparing the ceramic layer 4, fixing the alloy blank after completing the preparation procedure of the ceramic composite material transition layer 3 on a tool and setting the alloy blank in a stationary blade mold, pouring the ceramic liquid slurry of the ceramic layer 4 into the stationary blade mold, and performing centrifugal vibration to sufficiently combine the ceramic slurry with the high temperature alloy mesh structure outside the high temperature alloy blank 1 and the surface of the high temperature alloy blank 1; and then after the stationary blade is formed and fixed, removing the mold, transferring the formed stationary blade to a blade firing furnace, performing firing forming, and then performing punching treatment on the surface of the ceramic layer 4 to manufacture the cooling hole 5.
In the present embodiment, referring to fig. 3 to 7, in manufacturing the ceramic-coated superalloy stator blade of the present embodiment, the following steps are adopted:
a. the high-temperature alloy blank 1 is formed by precision casting, and in consideration of a special hollow protrusion 6 structure, the protrusion part of the stator blade blank is processed after the stator blade blank is cast, so that the stator blade blank is conveniently welded with a high-temperature alloy cooling pipe network 2; after the high-temperature alloy cooling pipe network 2 is preheated, the pipeline positions are arranged according to the cooling requirements of the blades; welding to form a cooling pipe network;
b. after the cooling pipe network is welded, carrying out heat treatment to eliminate stress in the welding process, and simultaneously carrying out surface treatment on the high-temperature alloy blank 1 and the surface of the pipe network structure, wherein the size control is required for the round angle part and the pipeline connecting part;
c. spraying the ceramic composite material transition layer 3, replacing different coating materials at each set thickness, and standing after spraying;
d. arranging blade-shaped molds according to a certain number, fixing the alloy blanks sprayed with the transition layers on a tool, pouring ceramic slurry of the ceramic layer into the blade-shaped molds, and fully combining the ceramic slurry with the net structure of the high-temperature alloy cooling pipe network 2 and the high-temperature alloy blank 1 through centrifugal vibration; after the blade is molded and fixed, removing the mold, transferring the mold together with the tool to a blade firing furnace, and firing and molding;
e. and finishing the primary finished product of the ceramic-coated high-temperature alloy stator blade after sintering, after correcting the blade-shaped surface, positioning and processing a high-temperature alloy connecting part through five points, clamping the high-temperature alloy part after finishing, and performing punching treatment on the surface of ceramic to finally obtain the ceramic-coated high-temperature alloy stator blade product.
The ceramic-coated high-temperature alloy stationary blade comprises a high-temperature alloy blank 1, a high-temperature alloy cooling pipe network 2, a ceramic composite material transition layer 3 and a ceramic layer 4. There is a cooling channel inside the superalloy blank 1, the internal cooling channel portion being in accordance with conventional turbomachine stator vane design. The difference from the conventional design is that the surface of the cooling pipe network is provided with a hollow bulge 6 for supporting the alloy pipe network, and the bulge is welded with the alloy pipe network after being hollow to form a complete cooling pipe network. The bulge is of a hollow structure and is connected with a cooling channel in the blank. The high-temperature alloy cooling pipe network 2 is formed by connecting high-temperature alloy pipes and is welded with the hollow bulges 6 on the high-temperature alloy blank 1 to form a high-temperature alloy frame cooling pipe network system, so that a complete cooling pipe network structure is formed. Wherein, the pipe network has a clearance distance from the surface of the high-temperature alloy blank 1, which is convenient for the attachment of the ceramic layer 4. The ceramic composite material transition layer 3 combines the ceramic composite material on the surfaces of the high-temperature alloy blank 1 and the alloy pipe through a spraying process and is used for buffering the physical difference of the cold and hot thermal expansion and heat conduction of the alloy and the ceramic. The composite composition has a gradient from the high temperature buildup layer to the ceramic layer. The ceramic layer 4 is attached to the high-temperature alloy blank 1 and the alloy pipe network. Can tolerate higher temperature, and ceramic layer 4 is located between high temperature alloy body 1 and the pipe network structure, and the different pottery on ceramic layer 4 and the pipe network structure form a whole, wholly adheres to on this embodiment structure, and thickness reaches the mm level. The cooling holes are distributed on the whole surface of the ceramic high-temperature alloy stator blade according to thermodynamic distribution, the holes are uniformly distributed on the surfaces of all the composite stator blades, and the cooling holes 5 are connected with the high-temperature alloy cooling pipe network 2 to form a complete cooling channel. The cooling system formed in this way is complete and has excellent cooling effect.
The ceramic alloy-coated stator blade comprises a high-temperature alloy blank 1, a high-temperature alloy cooling pipe network 2, a ceramic composite material transition layer 3 and a ceramic layer 4. The high-temperature alloy billet 1 is cast by cobalt-based or nickel-based high-temperature alloy, a cooling channel is arranged in the high-temperature alloy billet 1, raised frames are cast at the cooling holes on the surface of the channel, a cooling pipe network is woven by a high-temperature alloy cooling pipe network 2 which is made of the same material as the high-temperature alloy billet 1 into a net shape, and the raised frames and the net structure are connected to form a layer of structure suspended outside the billet. The ceramic transition layer is sprayed on the green body and the reticular structure to form a ceramic composite material transition layer 3. The ceramic layer 4, the ceramic composite material transition layer 3, the high-temperature alloy cooling pipe network 2 and the high-temperature alloy blank 1 are integrated to form the integral stator blade. The frame network structure increases the ceramic bonding thickness, and the transition layer and the network structure counteract the stress during thermal shock. The ceramic alloy coated stationary blade can improve the turbine inlet temperature and the efficiency of a turbomachine and prolong the service life of the turbine.
Example two:
this embodiment is substantially the same as the first embodiment, and is characterized in that:
in the embodiment, corresponding hollow protrusions 6 are cast on the surface of the high-temperature alloy blank 1 corresponding to the cooling holes 5 in the ceramic layer 4 to form a cross-shaped cooling channel. The arrangement of the high-temperature alloy cooling pipe network 2 fully considers the distribution of blade cooling, and all the pipe distribution positions are the positions of the outermost ceramic layer with cooling holes, so that a complete cooling system is formed.
Example three:
this embodiment is substantially the same as the previous embodiment, and is characterized in that:
in this embodiment, referring to fig. 3 to 7, the superalloy blank 1 and the superalloy cooling pipe network 2 are structurally formed by 3D printing, and the 3D printing enables rapid manufacturing of a complex spatial structure. The connection between the high-temperature alloy blank 1 and the high-temperature alloy cooling pipe network 2 is not limited to welding, but an integral cooling cavity is formed by an additive manufacturing method, and meanwhile, the internal stress of the cooling cavity is eliminated by matching with a heat treatment process, so that the diversified manufacturing requirements of different ceramic-coated high-temperature alloy stationary blades can be met.
While the embodiments of the present invention have been described with reference to the accompanying drawings, the present invention is not limited to the above embodiments, but various changes, modifications, substitutions, combinations or simplifications may be made according to the purpose of the invention, and any changes, modifications, substitutions, combinations or simplifications made according to the spirit and principle of the present invention shall be made as equivalent substitutions, and shall fall within the protection scope of the present invention as long as the purpose of the present invention is met, without departing from the technical principle and inventive concept of the ceramic-coated superalloy stator vane of the present invention.
Claims (10)
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104564350A (en) * | 2013-10-10 | 2015-04-29 | 阿尔斯通技术有限公司 | Arrangement for cooling component in the hot gas path of gas turbine |
| CN106761950A (en) * | 2017-01-13 | 2017-05-31 | 大连理工大学 | A kind of hot plate samming is without blending turbine blade cooling device and method |
| CN107013253A (en) * | 2017-05-19 | 2017-08-04 | 南京航空航天大学 | A kind of efficient cooling blade of gas-turbine unit |
| CN107835887A (en) * | 2015-07-13 | 2018-03-23 | 西门子公司 | Blade and its manufacture method for fluid dynamic machinery |
| CN108979731A (en) * | 2017-05-31 | 2018-12-11 | 通用电气公司 | The cooling path adaptively opened |
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| CN104564350A (en) * | 2013-10-10 | 2015-04-29 | 阿尔斯通技术有限公司 | Arrangement for cooling component in the hot gas path of gas turbine |
| CN107835887A (en) * | 2015-07-13 | 2018-03-23 | 西门子公司 | Blade and its manufacture method for fluid dynamic machinery |
| CN106761950A (en) * | 2017-01-13 | 2017-05-31 | 大连理工大学 | A kind of hot plate samming is without blending turbine blade cooling device and method |
| CN107013253A (en) * | 2017-05-19 | 2017-08-04 | 南京航空航天大学 | A kind of efficient cooling blade of gas-turbine unit |
| CN108979731A (en) * | 2017-05-31 | 2018-12-11 | 通用电气公司 | The cooling path adaptively opened |
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