阅读说明：本技术 覆陶高温合金静叶片 (Ceramic-coated high-temperature alloy stator blade ) 是由 于铠瑞 郝霄鹏 王文 于 2019-09-02 设计创作，主要内容包括：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-coated alloy stationary blade, which comprises a high-temperature alloy blank, a high-temperature alloy cooling pipe network, a ceramic composite material transition layer and a ceramic layer. The high-temperature alloy blank is cast by cobalt-based or nickel-based high-temperature alloy, the alloy blank is provided with a cooling channel, raised frames are cast at the surface cooling holes of the channel, a cooling pipe network is woven by high-temperature alloy cooling pipes made of the same material into a net shape, and the raised frames and the net structure are connected to form a layer of structure suspended outside the blank. 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 the stator 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.)

1. The utility model provides a cover ceramic superalloy stationary blade, includes superalloy blank (1), its characterized in that: sequentially combining a ceramic composite material transition layer (3) and a ceramic layer (4) on the surface of a high-temperature alloy blank (1), enabling the ceramic composite material transition layer (3) to be located between the high-temperature alloy blank (1) and the ceramic layer (4) to form an intermediate material layer with buffering, energy conduction and force transmission functions, enabling the high-temperature alloy blank (1), the ceramic composite material transition layer (3) and the ceramic layer (4) to form an integrated composite material stationary blade, arranging a high-temperature alloy cooling pipe network (2) in the integrated composite material stationary blade, and enabling the high-temperature alloy cooling pipe network (2) to penetrate through the high-temperature alloy blank (1), the ceramic composite material transition layer (3) and the ceramic layer (4) to form a heat flow transmission channel; the high-temperature alloy blank (1) is provided with a cast hollow bulge (6) which is connected with a 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 a 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); high-temperature alloy body (1) surface and high-temperature alloy cooling pipe network (2) surface all adhere to ceramic composite transition layer (3), ceramic composite transition layer (3) surface adheres to ceramic layer (4), high-temperature alloy cooling pipe network (2) still forms the connection the three-dimensional netted skeleton texture of high-temperature alloy body (1), ceramic composite transition layer (3) and ceramic layer (4).

2. The ceramic-coated superalloy stator vane of claim 1, wherein: cooling holes (5) are distributed on the whole surface of the ceramic high-temperature alloy stationary blade according to thermodynamic distribution, the cooling holes (5) are mainly arranged in the ceramic layer (4), and the cooling holes (5) are communicated with the high-temperature alloy cooling pipe network (2) to form a complete cooling channel.

3. The ceramic-coated superalloy stator vane of claim 2, wherein: according to the structure that the surface positions of the high-temperature alloy blank (1) corresponding to the cooling holes (5) in the ceramic layer (4) are staggered, hollow protrusions (6) are cast on the surface of the high-temperature alloy blank (1) to form a cooling channel of a main pipe rotor tube structure.

4. The ceramic-coated superalloy stator vane of claim 2, wherein: corresponding hollow bulges (6) are cast at the surface positions 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.

5. The ceramic-coated superalloy stator vane of claim 1, wherein: the pipeline of the high-temperature alloy cooling pipe network (2) forms a cooling channel arranged in the high-temperature alloy blank (1), the high-temperature alloy cooling pipe network (2) adopts high-temperature alloy cooling pipes made of the same material as the high-temperature alloy blank (1) to weave into a spatial net structure, and a protruding frame and the net structure are connected to form a suspended frame structure arranged outside the high-temperature alloy blank (1).

6. The ceramic-coated superalloy stator vane of claim 1, wherein: the high-temperature alloy blank (1) is cast by cobalt-based high-temperature alloy or nickel-based high-temperature alloy.

7. The ceramic-coated superalloy stator vane of claim 1, wherein: the ceramic composite material transition layer (3) is prepared from a component gradient material, and the composite material components of the ceramic composite material transition layer (3) are subjected to gradient change from a high-temperature alloy surface layer combined with the high-temperature alloy blank (1) to a ceramic surface layer combined with the ceramic layer (4) to form a functional material layer for buffering the internal stress of the cold and hot material difference.

8. The ceramic-coated superalloy stator vane of claim 1, wherein: and the high-temperature alloy blank (1) and the high-temperature alloy cooling pipe network (2) are subjected to structural forming through welding, 3D printing or direct casting.

9. The ceramic-coated superalloy stator vane of claim 1, wherein: after the high-temperature alloy cooling pipe network (2) is prepared, carrying out heat treatment to eliminate forming stress; and carrying out surface treatment and external dimension control on the surface of the high-temperature alloy blank (1) and the surface of the high-temperature alloy cooling pipe network (2).

10. The ceramic-coated superalloy stator vane of claim 1, wherein: when the ceramic layer (4) is prepared, an alloy blank which completes the preparation procedure of the ceramic composite material transition layer (3) is fixed on a tool and is arranged in a stationary blade die, then ceramic liquid slurry of the ceramic layer (4) is poured into the stationary blade die, and the ceramic slurry is fully and tightly combined with a high-temperature alloy net structure outside the high-temperature alloy blank body (1) and the surface of the high-temperature alloy blank body (1) through centrifugal vibration; and then after the stationary blade is formed and fixed, removing the mould, 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).

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; 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: