CN211058869U - Ceramic-metal combined turbine guide vane and gas turbine thereof - Google Patents
Ceramic-metal combined turbine guide vane and gas turbine thereof Download PDFInfo
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- CN211058869U CN211058869U CN201922042622.1U CN201922042622U CN211058869U CN 211058869 U CN211058869 U CN 211058869U CN 201922042622 U CN201922042622 U CN 201922042622U CN 211058869 U CN211058869 U CN 211058869U
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Abstract
A ceramic-metal bonded turbine guide vane comprising: the rear half blade body is arranged on one side of the tail edge and is made of metal; the front half blade body is arranged on one side of the front edge and is designed to be separated from the rear half blade body, and the front half blade body and the rear half blade body form a complete blade structure; the front half blade body is made of ceramic and used for reducing the cold air demand for cooling. The utility model adopts a split design method, wherein the front half blade body adopts ceramic material to form a solid blade base body, the rear half blade body, the inner edge plate and the outer edge plate adopt traditional metal materials, and adopt a traditional air cooling structure; due to the high-temperature resistance of the ceramic, the front half blade body does not need to be cooled, the amount of cold air required by the turbine blade is obviously reduced, and the overall performance of the gas turbine is greatly improved.
Description
Technical Field
The utility model relates to a gas turbine blade technical field especially relates to a turbine guide vane and gas turbine that pottery-metal combined together.
Background
The turbine inlet temperature of a future gas turbine can reach more than 1500 ℃, the safe working temperature of the most advanced high-temperature alloy blade at present is about 900 ℃, the comprehensive cooling effect required by the first-stage guide vane of the turbine is about 0.65-0.7, the cooling air demand of a turbine part can reach more than 20% according to the existing air cooling technical level, the performance of the gas turbine can be reduced by increasing the cooling air consumption, and the cooling air demand is contrary to the design requirement of a high-efficiency gas turbine, so that the development of a ceramic blade structure has important significance for improving the gas turbine technology in China.
Compared with a metal blade, the ceramic blade has the main characteristics of high temperature resistance, wear resistance, high hardness, corrosion resistance and other mechanical properties, so that the ceramic blade can directly work in a high-temperature gas environment. However, ceramic blades have not been used for many years in mass engineering applications, primarily because of the poor toughness, flexibility, and installability of ceramics.
SUMMERY OF THE UTILITY MODEL
In view of the above, the main object of the present invention is to provide a ceramic-metal combined turbine guide vane and a gas turbine thereof, which are intended to at least partially solve at least one of the above mentioned technical problems.
To achieve the above object, as one aspect of the present invention, there is provided a ceramic-metal combined turbine guide vane, comprising:
the rear half blade body is arranged on one side of the tail edge and is made of metal;
the front half blade body is arranged on one side of the front edge and is designed to be separated from the rear half blade body, and the front half blade body and the rear half blade body form a complete blade structure;
the front half blade body is made of ceramic and used for reducing the cold air demand for cooling.
As another aspect of the present invention, there is also provided a gas turbine including a ceramic-metal bonded turbine guide vane as described above.
Based on the above technical scheme, the utility model discloses at least, have following beneficial effect one of them or one of them part:
(1) the blades are of a split structure, the front half blade bodies are made of ceramic materials, and the blade bodies of the ceramic parts do not need to be cooled, so that the cold air demand can be greatly reduced under the same gas incoming flow condition; considering that the trailing edge of the turbine guide blade is too thin, generally about 1mm, the design that the front half blade body made of ceramic materials is arranged on one side of the front edge and the rear half blade body made of metal is arranged on one side of the trailing edge is adopted, and a fragile area of the pure ceramic blade is avoided;
(2) because the inner edge plate and the outer edge plate are still made of metal and are connected with the rear half blade body, the utility model keeps the installation performance of the pure metal blade;
(3) the utility model provides an adopt the elastic gasket to come to encapsulate first half blade, solve under the hot state ceramic part blade because the coefficient of linear expansion is less than the metal part blade and can't satisfy the problem of cooperation requirement.
Drawings
FIG. 1 is a schematic view of the assembly of a ceramic-metal bonded turbine guide vane of the present invention;
FIG. 2 is a schematic illustration of the assembly of the ceramic-metal bonded turbine guide vane inner rim plate of the present invention;
FIG. 3 is a schematic view of a ceramic-metal bonded turbine guide vane mid-section cooling configuration of the present invention;
FIG. 4 is a schematic cross-sectional side view of a ceramic-metal bonded turbine guide vane according to an embodiment of the present invention;
fig. 5 is a sectional view taken along line a-a of fig. 4.
In the above drawings, the reference numerals have the following meanings:
1. the front half of the blade body; 2. a rear half blade body; 3. an elastic pad; 4. a cover plate; 5. a gas film hole; 6. a groove; 7. installing edges; 8. an inner edge panel; 801. a positioning groove; 9. an outer edge plate.
Detailed Description
The utility model provides a blade structure of two kinds of material combinations of pottery-metal, make full use of gas turbine blade body in the characteristics of leading edge thickest, trailing edge thinnest, adopted the components of a whole that can function independently design scheme, be a blade structure scheme that has the engineering feasibility. Is characterized in that the front half blade body is made of ceramic material, and the ceramic part blade body is embedded into the rest metal part blade body. The design method is used for the structural design of the guide vane of the gas turbine, and can obviously reduce the cooling air quantity of the turbine vane of the gas turbine.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings.
In an embodiment of the present invention, there is provided a ceramic-metal combined turbine guide vane, comprising:
the rear half blade body is arranged on one side of the tail edge and is made of metal;
the front half blade body is arranged on one side of the front edge and is designed to be separated from the rear half blade body, and the front half blade body and the rear half blade body form a complete blade structure;
wherein, the material of the first half blade body is ceramic for reducing the cooling air demand for cooling.
In the embodiment of the present invention, the interface between the front half blade body and the rear half blade body is located at the position of 0.3-0.6 of the relative axial chord length of the complete blade profile.
In the embodiment of the utility model, two ends of the rear half blade body are respectively fixedly connected with the inner edge plate and the outer edge plate; the inner edge plate and the outer edge plate are made of the same material as the rear half blade body; the inner edge plate is provided with a mounting edge at one side opposite to the rear half blade body.
The embodiment of the utility model provides an in, latter half blade body, outer fringe board, interior fringe board and installation limit all adopt high temperature alloy material, integrative casting.
In an embodiment of the present invention, the ceramic-metal combined turbine guide vane further comprises an elastic gasket and a cover plate; a positioning groove used for packaging the front half blade body is arranged at the connecting side of the inner edge plate and the rear half blade body; mounting holes are arranged at corresponding positions on the outer edge plate; the elastic gasket and the cover plate are arranged on one side of the mounting hole;
one end of the front half blade body penetrates through the mounting hole to be embedded into the positioning groove, and the other end of the front half blade body is packaged at the mounting hole through the elastic gasket and the cover plate in sequence. More specifically, the elastic gasket is clamped between the front half blade body and the cover plate, and the cover plate is welded with the outer end face of the outer edge plate.
In an embodiment of the present invention, the positioning groove includes a groove bottom and a groove sidewall; the bottom of the groove is a plane, and the side wall of the groove is a conical surface.
In the embodiment of the utility model, the leaf basin of the front matching surface where the rear half blade body contacts with the front half blade body is provided with a groove, or the leaf basin and the leaf back are respectively provided with a groove; one or more grooves are arranged along the radial direction at intervals; the cross section of the groove is rectangular.
In the embodiment of the utility model, set up a plurality of air film holes on the recess for be linked together the cooling cavity of external and latter half blade body.
The embodiment of the utility model provides an in, the air film hole adopts electromachining or laser beam to punch to make.
As another aspect of the present invention, there is also provided a gas turbine including a ceramic-metal bonded turbine guide vane as described above.
The structure of a ceramic-metal combined turbine stator blade according to the present invention will be further described with reference to the following embodiments.
Example 1
As shown in fig. 1 and 4, the front half blade body 1 of the ceramic-metal combined turbine guide blade structure of the present invention is made of ceramic material, and the metal blade part includes a rear half blade body 2, an inner edge plate 8, an outer edge plate 9 and a mounting edge 7, and is made of high temperature alloy material by integral casting. As shown in fig. 2, one end of the front half blade body 1 is embedded into the positioning groove 801 of the blade inner edge plate 8 and is in bevel fit around the positioning groove 801; as shown in fig. 1 and 5, the other end of the front half blade body 1 is sealed by an elastic gasket 3 and a sealed metal cover plate 4. As shown in figure 3, the cooling mode of the front part of the metal blade body is given, and a blade basin and a blade back of the front matching surface of the rear half blade body 2 are respectively provided with a groove 5 and an air film hole 6. The grooves 5 can be continuous or discontinuous, and the film holes 6 can be of any hole type. The grooves 5 are directly cast, and the air film holes 6 are manufactured by electric machining or laser drilling.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A ceramic-metal bonded turbine guide vane comprising:
the rear half blade body is arranged on one side of the tail edge and is made of metal;
the front half blade body is arranged on one side of the front edge and is designed to be separated from the rear half blade body, and the front half blade body and the rear half blade body form a complete blade structure;
the front half blade body is made of ceramic and used for reducing the cold air demand for cooling.
2. The ceramic-metal bonded turbine guide vane of claim 1 wherein the interface of the forward and aft half-bodies is between 0.3 and 0.6 of the relative axial chord length of the full airfoil.
3. The ceramic-metal combined turbine stator blade according to claim 1, wherein both ends of the rear half body are fixedly connected with an inner edge plate and an outer edge plate respectively; the inner edge plate and the outer edge plate are made of the same material as the rear half blade body; and one side of the inner edge plate, which is opposite to the rear half blade body, is provided with a mounting edge.
4. The ceramic-metal combined turbine stator blade according to claim 3, wherein the rear half body, the outer peripheral plate, the inner peripheral plate and the mounting rim are integrally cast from a high temperature alloy material.
5. The ceramic-metal bonded turbine guide vane of claim 3 or 4, further comprising a resilient shim and a cover plate; a positioning groove used for packaging the front half blade body is arranged at the connecting side of the inner edge plate and the rear half blade body; mounting holes are arranged at corresponding positions on the outer edge plate; the elastic gasket and the cover plate are arranged on one side of the mounting hole.
6. The ceramic-metal bonded turbine guide vane of claim 5, wherein said positioning groove comprises a groove bottom and a groove sidewall; the bottom of the groove is a plane, and the side wall of the groove is a conical surface.
7. The ceramic-metal combined turbine guide vane according to claim 1, wherein a groove is provided at a blade basin of a front mating surface where the rear half blade body and the front half blade body are in contact with each other, or a groove is provided at a blade basin and a blade back respectively; one or more grooves are arranged along the radial direction at intervals; the cross section of the groove is rectangular.
8. The ceramic-metal combined turbine stator blade according to claim 7, wherein a plurality of film holes are provided in the groove for communicating the outside with the cooling cavity of the rear half-body.
9. The ceramic-metal combined turbine guide vane of claim 8, wherein said film holes are machined by electro-machining or laser drilling.
10. A gas turbine comprising a ceramic-metal bonded turbine guide vane according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922042622.1U CN211058869U (en) | 2019-11-21 | 2019-11-21 | Ceramic-metal combined turbine guide vane and gas turbine thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922042622.1U CN211058869U (en) | 2019-11-21 | 2019-11-21 | Ceramic-metal combined turbine guide vane and gas turbine thereof |
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| Publication Number | Publication Date |
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| CN211058869U true CN211058869U (en) | 2020-07-21 |
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| CN201922042622.1U Active CN211058869U (en) | 2019-11-21 | 2019-11-21 | Ceramic-metal combined turbine guide vane and gas turbine thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112901279A (en) * | 2021-01-29 | 2021-06-04 | 大连理工大学 | Turbine blade adopting bolt-fixed ceramic armor |
-
2019
- 2019-11-21 CN CN201922042622.1U patent/CN211058869U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112901279A (en) * | 2021-01-29 | 2021-06-04 | 大连理工大学 | Turbine blade adopting bolt-fixed ceramic armor |
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