CN211058869U - Ceramic-Metal Combined Turbine Guide Vane and Its Gas Turbine - Google Patents

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

Ceramic-Metal Combined Turbine Guide Vane and Its Gas Turbine

technical field

The utility model relates to the technical field of gas turbine turbine blades, in particular to a ceramic-metal combined turbine guide blade and a gas turbine thereof.

Background technique

In the future, the turbine inlet temperature of gas turbines will reach above 1500℃, while the safe working temperature of the most advanced superalloy blades is about 900℃, and the comprehensive cooling efficiency required by the first-stage guide vanes of the turbine is about 0.65-0.7. At the level of air cooling technology, the cooling air demand for turbine components will reach more than 20%, and the increase in cooling air consumption will reduce the performance of gas turbines, which is contrary to the design requirements of high-efficiency gas turbines. Technology is important.

Compared with a metal blade, the ceramic blade is mainly characterized by high temperature resistance, wear resistance, high hardness, corrosion resistance and other mechanical properties, so that it can directly work in a high temperature gas environment. However, ceramic blades have not been applied in batch engineering for many years, mainly because the toughness, elasticity and installability of ceramics are too poor.

Utility model content

In view of this, the main purpose of the present invention is to provide a ceramic-metal combined turbine guide vane and a gas turbine thereof, so as to at least partially solve at least one of the above-mentioned technical problems.

In order to achieve the above purpose, as an aspect of the present utility model, a ceramic-metal combined turbine guide vane is provided, comprising:

The rear half of the airfoil is arranged on one side of the trailing edge, and the material of the rear half of the airfoil is metal;

The front half of the airfoil is arranged on one side of the front edge, and is designed separately from the rear half of the airfoil, and the front half of the airfoil and the rear half of the airfoil form a complete airfoil structure;

Wherein, the material of the front half of the airfoil is ceramic, which is used to reduce the demand of cold air for cooling.

As another aspect of the present invention, a gas turbine is also provided, comprising the above-mentioned ceramic-metal combined turbine guide vanes.

Based on the above technical solutions, the present invention has at least one or a part of the following beneficial effects:

(1) The blade adopts a split structure, and the front half of the blade is made of ceramic material. Since the blade body of the ceramic part does not need to be cooled, the demand for cold air will be greatly reduced under the same gas flow conditions; The trailing edge of the flat guide vane is too thin, usually about 1mm. The front half of the vane made of ceramic material is set on one side of the leading edge, and the rear half of the vane is set on the trailing edge to avoid a fragile area of pure ceramic blades;

(2) Because the inner edge plate and the outer edge plate are still made of metal and are connected to the rear half of the blade body, the utility model retains the installation performance of pure metal blades;

(3) The utility model proposes to use elastic gaskets to encapsulate the front half of the airfoil to solve the problem that the ceramic part of the airfoil cannot meet the matching requirements because the linear expansion coefficient is smaller than that of the metal part of the airfoil in a hot state.

Description of drawings

Fig. 1 is the assembly schematic diagram of the ceramic-metal combined turbine guide vane of the present invention;

2 is a schematic diagram of the assembly of the inner edge plate of the ceramic-metal combined turbine guide vane of the present invention;

3 is a schematic diagram of the cooling structure in the middle of the ceramic-metal combined turbine guide vane of the present invention;

FIG. 4 is a cross-sectional schematic diagram of a horizontal half-section of a ceramic-metal combined turbine guide vane according to an embodiment of the present utility model;

FIG. 5 is a cross-sectional view taken along line A-A of FIG. 4 .

In the above drawings, the meanings of the reference signs are as follows:

1. Front airfoil; 2. Rear airfoil; 3. Elastic gasket; 4. Cover plate; 5. Air film hole; 6. Groove; 7. Mounting edge; 8. Inner edge plate; 801. Positioning concave Slot; 9. Outer edge plate.

Detailed ways

The blade structure of the combination of ceramic and metal materials proposed by the utility model makes full use of the characteristics of the gas turbine turbine blade body with the thickest leading edge and the thinnest trailing edge, and adopts a split design scheme, which is a kind of engineering Feasible blade structure scheme. The characteristic is that the front half of the airfoil is made of ceramic material, and the ceramic part of the airfoil is embedded in the rest of the metal part of the airfoil. It is used in the structural design of gas turbine guide vanes, which can significantly reduce the cooling air volume of gas turbine turbine vanes.

In order to make the purpose, technical solutions and advantages of the present utility model clearer, the present utility model will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

In an embodiment of the present invention, a ceramic-metal combined turbine guide vane is provided, comprising:

The rear half of the airfoil is arranged on one side of the trailing edge, and the material of the rear half of the airfoil is metal;

The front half of the airfoil is arranged on one side of the front edge and is designed as a separate body from the rear half of the airfoil, and the front half of the airfoil and the rear half of the airfoil form a complete airfoil structure;

Among them, the material of the front half of the blade is ceramic, which is used to reduce the demand for cold air for cooling.

In the embodiment of the present invention, the interface between the front half of the airfoil and the rear half of the airfoil is at a position of 0.3-0.6 relative to the axial chord length of the complete airfoil.

In the embodiment of the present utility model, the two ends of the rear half of the airfoil are respectively fixedly connected to the inner edge plate and the outer edge plate; the inner edge plate and the outer edge plate are of the same material as the rear half of the airfoil; A mounting edge is provided on the opposite side of the body.

In the embodiment of the present invention, the rear half of the airfoil, the outer edge plate, the inner edge plate and the mounting edge are all made of high-temperature alloy materials and cast in one piece.

In the embodiment of the present invention, the ceramic-metal combined turbine guide vane further includes an elastic gasket and a cover plate; a positioning groove for encapsulating the front half of the vane is provided on the side where the inner edge plate is connected to the rear half of the vane ; Install mounting holes at corresponding positions on the outer edge plate; the elastic gasket and the cover plate are arranged on one side of the mounting holes;

Wherein, one end of the front half of the airfoil penetrates the installation hole and is embedded in the positioning groove, and the other end of the front half of the airfoil is encapsulated by the elastic gasket and the cover plate in sequence at the installation hole. More specifically, the elastic gasket is sandwiched between the front half blade body and the cover plate, and the cover plate and the outer end surface of the outer edge plate are welded.

In the embodiment of the present invention, the positioning groove includes a groove bottom and a groove side wall; the groove bottom is a plane, and the groove side wall is a conical surface.

In the embodiment of the present utility model, grooves are arranged at the blade basin of the front mating surface where the rear half of the blade body is in contact with the front half of the blade body, or the blade basin and the blade back are respectively provided with grooves; the groove is radially provided with a groove Or a plurality of them are arranged at intervals along the radial direction; the cross-sectional shape of the groove is rectangular.

In the embodiment of the present utility model, a plurality of air film holes are arranged on the groove, which are used to communicate the outside with the cooling cavity of the rear half of the airfoil.

In the embodiment of the present invention, the gas film holes are made by electrical machining or laser drilling.

As another aspect of the present invention, a gas turbine is also provided, comprising the above-mentioned ceramic-metal combined turbine guide vanes.

The structure of a ceramic-metal combined turbine guide vane provided by the present invention will be further described below with reference to specific embodiments.

Example 1

As shown in Figures 1 and 4, in the ceramic-metal combined turbine guide vane structure of the present invention, the front half of the blade body 1 is made of ceramic material, and the metal blade part includes the rear half of the blade body 2, the inner edge plate 8, the outer The edge plate 9 and the mounting edge 7 are integrally cast with high temperature alloy materials. As shown in FIG. 2 , one end of the front half of the airfoil 1 is embedded in the positioning groove 801 of the inner edge plate 8 of the blade, and chamfered around the positioning groove 801; as shown in FIGS. 1 and 5 , the front half of the airfoil 1 The other end is encapsulated by elastic gasket 3 and sealing metal cover plate 4 . As shown in FIG. 3 , the cooling method of the front part of the metal airfoil is given, and grooves 5 and air film holes 6 are respectively opened in the blade basin and the blade back of the mating surface of the front part of the rear half of the airfoil 2 . The grooves 5 can be continuous or discontinuous, and the gas film holes 6 can be of any hole type. The groove 5 is directly cast, and the gas film hole 6 is made by electrical machining or laser drilling.

The specific embodiments described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above are only specific embodiments of the present invention and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included within the protection scope of the present utility model.

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.

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