Heat insulation device of gas turbine

Abstract

The utility model provides a gas turbine heat insulation device, which relates to the technical field of gas turbines, and comprises a heat insulation ceramic chip and a gas turbine blade, the front side arc surface of the heat insulation ceramic chip clings to the gas turbine blade, the heat insulation ceramic chip is internally provided with a cooling cavity, the upper end of the cooling cavity is provided with cooling air holes, and the cooling air holes are communicated with the gas turbine blade. An aerogel interlayer and an aluminum silicate fiber inner layer are embedded and fixed to the arc face of the front side of the heat insulation ceramic piece, the aerogel interlayer is located between the heat insulation ceramic piece and the aerogel interlayer, and an air outlet groove is formed in the surface of the aluminum silicate fiber inner layer. The utility model solves the problem that the combined heat insulation form of air film cooling and impact cooling in the prior art is easy to generate larger pressure and vibration on the ceramic tile and the gas turbine blade.

Description

Technical Field

[0001] The utility model relates to the technical field of gas turbines, in particular to a heat insulation device for a gas turbine. Background Art

[0002] A gas turbine is an internal combustion power machine that uses a continuously flowing gas as a working medium to drive the impeller to rotate at high speed, converting the energy of the fuel into useful work. It is a rotating impeller heat engine. In order to protect the inner and outer cylinders of the gas turbine combustion chamber and avoid failure due to overheating, a heat insulation device needs to be installed to reduce the heat transfer of high-temperature gas. After searching, the prior art (application number: CN202320090915.0) records that "This application adopts a combination of air film cooling and impingement cooling. Through the setting of a sealed cavity, the cooling gas after deceleration and expansion is obliquely ejected through the cooling air duct of the upper cover plate, and then a layer of cooling air film is formed on the outer surface of the upper cover plate together with the hot gas flow. , impact cooling is used on the sides to cool the gap, and the closed insulation tile structure prevents the cooling gas from scattering, thereby improving the utilization rate of the cooling gas. The present application can insulate and cool the insulation tiles through the cooling air film while ensuring that the cold air does not increase, thereby avoiding the direct impact of the hot gas and effectively improving the heat resistance of the insulation tiles. The present application improves the thermal insulation performance and cooling efficiency, ensures the cooling effect, overcomes the existing problems of ceramic tile fragmentation and metal tile ablation, enhances the life of the insulation tiles, and ensures the safe operation of the gas turbine. However, the combined insulation form of air film cooling and impact cooling in the prior art is prone to cause greater pressure and vibration on the ceramic tiles and gas turbine blades. Utility Model Content

[0003] In order to overcome the defects of the prior art, a gas turbine insulation device is provided to solve the problem that the combined insulation form of film cooling and impingement cooling in the prior art easily generates greater pressure and vibration on ceramic tiles and gas turbine blades.

[0004] In order to achieve the above object, a gas turbine heat insulation device is provided, comprising: a heat insulation ceramic sheet and a gas turbine blade, wherein the front arc surface of the heat insulation ceramic sheet is in close contact with the gas turbine blade.

[0005] A cooling cavity is provided inside the thermal insulation ceramic sheet, cooling air holes are distributed on the upper end of the cooling cavity, an aerogel interlayer and an aluminum silicate fiber inner layer are inlaid and fixed on the front curved surface of the thermal insulation ceramic sheet, the aerogel interlayer is located between the thermal insulation ceramic sheet and the aerogel interlayer, and an air outlet groove is provided on the surface of the aluminum silicate fiber inner layer.

[0006] Furthermore, the front end of the thermal insulation ceramic sheet is snap-fitted to the left and right end surfaces of the gas turbine blade, and the rear side surface of the gas turbine blade is adhered with an inner layer of aluminum silicate fiber.

[0007] Furthermore, a cooling docking block is fixed to the upper end surface of the heat-insulating ceramic sheet, and cooling air holes are arranged on the surface of the cooling docking block; and cooling cavities are correspondingly distributed below the cooling air holes.

[0008] Furthermore, a buffer cavity pad made of polyimide material is glued to the cavity wall at the bottom of the cooling cavity.

[0009] Furthermore, the front end of the cooling cavity is connected to the air outlet groove through the air outlet cavity; and the front side of the cooling cavity is correspondingly connected to two groups of air outlet grooves.

[0010] Furthermore, the aerogel interlayer is made of zirconium oxide aerogel material and fixedly glued between the thermal insulation ceramic sheet and the aerogel interlayer.

[0011] Furthermore, the thermal insulation ceramic sheet, the aerogel interlayer and the aluminum silicate fiber inner layer constitute a high-efficiency thermal insulation device for gas turbine blades.

[0012] The beneficial effect of the utility model is that the gas turbine thermal insulation device of the utility model utilizes a thermal insulation ceramic sheet to be clamped on the side of the gas turbine blade, and reduces the heat transfer of the high-temperature gas through the three-layer thermal insulation structure of the thermal insulation ceramic sheet, the aerogel interlayer and the aluminum silicate fiber inner layer, and at the same time uses a cooling airflow to cool the surface of the gas turbine blade through the cooling cavity in the thermal insulation ceramic sheet, thereby facilitating the enhancement of the thermal insulation of the gas turbine thermal insulation device, ensuring that the thermal insulation ceramic sheet and the gas turbine blade fit closely, and prolonging the service life of the gas turbine thermal insulation device. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a front view structural schematic diagram of a gas turbine heat insulation device according to an embodiment of the utility model.

[0014] Figure 2 The figure is a schematic top view of the structure of the gas turbine heat insulation device according to an embodiment of the utility model.

[0015] Figure 3 It is a schematic diagram of the top cross-sectional structure of the gas turbine heat insulation device according to an embodiment of the utility model.

[0016] Figure 4 It is a schematic diagram of a top view of a partial cross-sectional structure of the internal cooling cavity of the heat-insulating ceramic sheet according to an embodiment of the utility model.

[0017] In the figure: 1. Insulating ceramic sheet; 11. Air outlet groove; 12. Cooling cavity; 13. Air outlet cavity; 14. Buffer cavity pad; 2. Cooling docking block; 21. Cooling air hole; 3. Gas turbine blade; 4. Aerogel interlayer; 5. Aluminum silicate fiber inner layer. DETAILED DESCRIPTION

[0018] Reference Figures 1 to 4As shown, the utility model provides a gas turbine heat insulation device, comprising: a heat insulation ceramic sheet 1 and a gas turbine blade 3, wherein the front arc surface of the heat insulation ceramic sheet 1 is closely attached to the gas turbine blade 3,

[0019] A cooling cavity 12 is provided inside the insulating ceramic sheet 1, and cooling air holes 21 are distributed on the upper end of the cooling cavity 12. An aerogel interlayer 4 and an aluminum silicate fiber inner layer 5 are inlaid and fixed on the front curved surface of the insulating ceramic sheet 1. The aerogel interlayer 4 is located between the insulating ceramic sheet 1 and the aerogel interlayer 4, and an air outlet groove 11 is provided on the surface of the aluminum silicate fiber inner layer 5.

[0020] Working principle: The heat insulating ceramic sheet 1 is clamped on the side of the gas turbine blade 3, and the heat transfer of the high-temperature gas is reduced by the three-layer insulation structure of the heat insulating ceramic sheet 1, the aerogel interlayer 4 and the aluminum silicate fiber inner layer 5. At the same time, the cooling air flow is used to cool the surface of the gas turbine blade 3 through the cooling cavity 12 in the heat insulating ceramic sheet 1, so as to enhance the thermal insulation of the gas turbine insulation device, ensure that the heat insulating ceramic sheet 1 and the gas turbine blade fit closely, and improve the service life of the gas turbine insulation device.

[0021] In this embodiment, the front end of the heat insulating ceramic sheet 1 is snap-fitted to the left and right end surfaces of the gas turbine blade 3 , and the rear side surface of the gas turbine blade 3 is adhered with an aluminum silicate fiber inner layer 5 .

[0022] As a preferred embodiment, the aluminum silicate fiber inner layer 5 facilitates strengthening of the aluminum silicate fiber inner layer 54 , so that the thermal insulation ceramic sheet 1 and the gas turbine blade 3 are fully fitted together, thereby ensuring a stable connection between the thermal insulation ceramic sheet 1 and the gas turbine blade 3 .

[0023] In this embodiment, a cooling docking block 2 is fixed to the upper end surface of the heat-insulating ceramic sheet 1 , and cooling air holes 21 are arranged on the surface of the cooling docking block 2 ; and cooling cavities 12 are correspondingly distributed below the cooling air holes 21 .

[0024] As a preferred embodiment, the heat-insulating ceramic sheet 1 is movably connected to the nozzle of the cooling airflow through the cooling docking block 2, and the cooling airflow is injected into the cooling cavity 12 through the existing cooling impact technology.

[0025] In this embodiment, a buffer cavity pad 14 made of polyimide is glued to the cavity wall at the bottom of the cooling cavity 12 .

[0026] As a preferred embodiment, the buffer cavity pad 14 buffers the cooling air flow injected through the cooling air holes 21, reduces the impact pressure of the cooling air flow, and makes the thermal insulation ceramic sheet 1 more durable.

[0027] In this embodiment, the front end of the cooling cavity 12 is connected to the air outlet groove 11 through the air outlet cavity 13 ; and the front side of the cooling cavity 12 is correspondingly connected to two groups of air outlet grooves 11 .

[0028] As a preferred embodiment, the cooling cavity 12 discharges the incoming cold air from the air outlet slot 11 through the air outlet cavity 13 to cool the gas turbine blades 3 .

[0029] In this embodiment, the aerogel interlayer 4 is made of zirconium oxide aerogel material and is fixedly glued between the thermal insulation ceramic sheet 1 and the aerogel interlayer 4 .

[0030] As a preferred embodiment, the aerogel interlayer 4 made of zirconia aerogel is resistant to high temperatures, has strong heat insulation and is lightweight, which is convenient for reducing the weight of existing insulation ceramic sheets and improving the rotation efficiency of the gas turbine blades 3 .

[0031] In this embodiment, the heat-insulating ceramic sheet 1 , the aerogel interlayer 4 and the aluminum silicate fiber inner layer 5 constitute a high-efficiency heat-insulating device for the gas turbine blade 3 .

[0032] As a preferred embodiment, the high-efficiency thermal insulation device of the gas turbine blade 3 facilitates enhancing the thermal insulation effect of the gas turbine blade 3, ensuring that the thermal insulation ceramic sheet and the gas turbine blade fit closely, and reducing the damage caused by resonance between the thermal insulation device and the gas turbine blade 3.

[0033] The gas turbine thermal insulation device of the utility model can effectively solve the problem in the prior art that the combined thermal insulation form of film cooling and impact cooling easily generates greater pressure and vibration on ceramic tiles and gas turbine blades, facilitates enhancing the thermal insulation of the gas turbine thermal insulation device, ensures that the thermal insulation ceramic sheets and gas turbine blades fit closely, and increases the service life of the gas turbine thermal insulation device, and is suitable for gas turbine thermal insulation devices.

Claims

1. A gas turbine heat insulation device, comprising: A heat-insulating ceramic sheet (1) and a gas turbine blade (3), wherein the front curved surface of the heat-insulating ceramic sheet (1) is in close contact with the gas turbine blade (3), and is characterized in that: A cooling cavity (12) is provided inside the thermal insulation ceramic sheet (1), cooling pores (21) are distributed at the upper end of the cooling cavity (12), an aerogel interlayer (4) and an aluminum silicate fiber inner layer (5) are embedded and fixed on the front curved surface of the thermal insulation ceramic sheet (1), the aerogel interlayer (4) is located between the thermal insulation ceramic sheet (1) and the aerogel interlayer (4), and an air outlet groove (11) is provided on the surface of the aluminum silicate fiber inner layer (5).

2. A gas turbine heat insulation device according to claim 1, characterized in that: The front end of the heat-insulating ceramic sheet (1) is snap-fitted to the left and right end surfaces of the gas turbine blade (3), and the rear side of the gas turbine blade (3) is bonded with an aluminum silicate fiber inner layer (5).

3. A gas turbine heat insulation device according to claim 1, characterized in that: A cooling docking block (2) is fixed to the upper end surface of the heat-insulating ceramic sheet (1), and cooling air holes (21) are arranged on the surface of the cooling docking block (2); and cooling cavities (12) are correspondingly distributed below the cooling air holes (21).

4. A gas turbine heat insulation device according to claim 1, characterized in that: A buffer cavity pad (14) made of polyimide material is glued to the cavity wall at the bottom of the cooling cavity (12).

5. A gas turbine heat insulation device according to claim 1, characterized in that: The front end of the cooling cavity (12) is connected to the air outlet groove (11) via the air outlet cavity (13); and the front side of the cooling cavity (12) is correspondingly connected to two groups of air outlet grooves (11).

6. A gas turbine heat insulation device according to claim 1, characterized in that: The aerogel interlayer (4) is made of a zirconium oxide aerogel material and is fixedly glued between the thermal insulation ceramic sheet (1) and the aerogel interlayer (4).

7. A gas turbine heat insulation device according to claim 1, characterized in that: The thermal insulation ceramic sheet (1), the aerogel interlayer (4) and the aluminum silicate fiber inner layer (5) form a high-efficiency thermal insulation device for a gas turbine blade (3).

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