A connection device for heat shield in combustion chamber of gas turbine and heat shield

Abstract

The present application provides a connection device for a heat screen in a gas turbine combustion chamber, which is arranged between two adjacent heat screens and is used to fixedly connect the heat screen and the combustion chamber shell. The connection device includes a fixed connection part, a limiting cooling part, and a cooling cavity. The fixed connection part fixes the heat screen to the combustion chamber shell. The bottom of the limiting cooling part is vertically connected to the other end of the fixed connection part, and the top of the limiting cooling part extends to one side of the heat screen, and its top is clamped on the groove. The cooling cavity is arranged inside the limiting cooling part, which is used to connect with the cooling gas source on the combustion chamber shell and transport cooling gas to cool the connection device. The bearing surface is protected by the limiting groove, the guard plate, and the guard wing, which effectively avoids direct contact between the bearing surface and the hot gas. The connection device provided by the present application can effectively reduce the harmful effects of hot gas leaking between the heat screens, reduce the probability of fracture and failure of the connection device, effectively reduce the loss of the connection device, and facilitate popularization and use.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to a connection device and a heat shield for a combustion chamber of a gas turbine. Background Art

[0002] The combustion process in a gas turbine occurs within the combustion chamber casing. Because it operates in a high-temperature environment, refractory insulation is required. This refractory insulation layer typically consists of multiple sheet-like tiles arranged circumferentially around the rotor axis, completely covering the inner surface of the combustion chamber casing. These tiles are typically secured to the combustion chamber casing via connectors that contact the side edges of the tiles.

[0003] In actual use, gaps exist between adjacent tiles to allow for thermal expansion, allowing hot air to penetrate and reach the connector. This infiltration of hot air between adjacent tiles in adjacent rows, or within the same row, can lead to significant wear and tear on the connector. In particular, the fastening area between the connector and the tile is the most directly and most susceptible to high temperatures, prone to oxidation and potentially fracture failure under these conditions. Furthermore, excessively high temperatures can cause thermoviscous creep and relaxation of the connector material, leading to failure of the fastening mechanism.

[0004] In summary, it is necessary to provide an improved technical solution to address the above-mentioned deficiencies in the existing technology. Summary of the Invention

[0005] An object of the embodiments of the present application is to provide a connection device and a heat shield for a gas turbine combustion chamber heat shield, which can effectively reduce the direct harmful effects caused by the penetration of hot gas from the combustion chamber.

[0006] In a first aspect, a connection device for a gas turbine combustion chamber heat shield is provided, which is disposed between two adjacent heat shields and is used to securely connect the insulation tiles to the combustion chamber housing. The connection device includes a fixed connection portion, a limiting cooling portion, and a cooling cavity.

[0007] One end of the fixed connection portion is used to extend between the insulation tile and the combustion chamber shell and is fixedly connected to the combustion chamber shell. The position-limiting cooling portion is a T-shaped structure with a predetermined thickness. A groove is provided on the peripheral side of the insulation tile. The bottom of the position-limiting cooling portion is perpendicularly connected to the other end of the fixed connection portion, and the top of the position-limiting cooling portion extends toward one side of the insulation tile. The top of the position-limiting cooling portion is clamped on the groove to limit the axial displacement of the insulation tile. A cooling chamber is provided within the position-limiting cooling portion for conveying cooling gas.

[0008] An air inlet is provided on the bottom surface of the position-limiting cooling portion, and the air inlet is connected to the cooling cavity. An air outlet is provided on the top of the position-limiting cooling portion, and the air outlet is connected to the cooling cavity. The cooling gas is used to be delivered into the groove and then into the combustion chamber through the gap between two adjacent insulation tiles.

[0009] In one embodiment, the limiting cooling part includes a first cooling part and a second cooling part, the first cooling part is arranged horizontally, the second cooling part is arranged longitudinally, the first cooling part and the second cooling part form a T-shaped structure, and the first cooling part is clamped on the bottom surface of the groove.

[0010] In one embodiment, a limiting groove is opened on the bottom surface of the groove, the arrangement direction of the limiting groove is the same as the arrangement direction of the groove, the length of the limiting groove is the same as the length of the first cooling part, and the first cooling part is clamped in the limiting groove.

[0011] A through slot is provided in the middle of the limiting slot, the through slot extends toward the combustion chamber housing, and the through slot is used for installing the second cooling part.

[0012] In one embodiment, the bottom surface of the first cooling part is a load-bearing surface, and a protective plate is provided on the top surface of the first cooling part.

[0013] In one embodiment, the bearing surface includes an inclined section.

[0014] In one embodiment, arc-shaped wings are provided at both ends of the first cooling portion.

[0015] In one embodiment, the thickness of the first cooling portion along the axial direction of the combustion chamber housing is greater than the depth of the limiting groove.

[0016] In one embodiment, the air outlet includes a first air outlet provided on the top surface of the first cooling portion and a second air outlet provided on a side surface of the first cooling portion.

[0017] In one embodiment, a circular arc groove is provided on the bottom surface of the first cooling portion, and the air inlet is provided in the circular arc groove, and the circular arc groove is used to gather the cooling gas at the air inlet.

[0018] In one embodiment, a reed is provided on the upper surface of the fixed connection portion, and the reed is used to absorb vibration of the thermal insulation tile.

[0019] According to the second aspect of the present application, a heat shield for a gas turbine combustion chamber is also provided, comprising a plurality of circles of thermal insulation tiles arranged axially along the combustion chamber casing, each circle of thermal insulation tiles comprising a plurality of said thermal insulation tiles evenly distributed circumferentially along the combustion chamber casing, each of said thermal insulation tiles being fixedly connected to the combustion chamber casing via the connecting device provided by the first aspect.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] In the technical solution of this application, the bearing surface is fully protected by recessed retaining grooves within the insulation tile cavities, as well as the guard plates and wings. This effectively prevents direct contact between the bearing surface and hot gas, reducing the service temperature of the bearing surface in the event of hot gas leakage. Simultaneously, cooling gas flows through the cooling cavity and the air outlet to cool the bearing surface, guard plates, and wings, reducing the temperature rise of the bearing surface caused by heat conduction and the risk of failure due to excessive bearing surface temperature. Furthermore, if hot gas leakage occurs, the guard plates and wings act as a first layer of protection, replacing the bearing surface with the high temperature failure, thus extending the time it takes for hot gas leakage to reach the bearing surface and cause failure. The provision of inclined sections axially limits the insulation tiles, preventing the axial gap between the tiles from increasing and reducing the risk of gas intrusion. Therefore, this application effectively mitigates the harmful effects of hot gas leaking between adjacent insulation tiles in a heat shield, reduces the probability of fracture and failure of the connecting device, and effectively reduces wear and tear on the connecting device, facilitating widespread use. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic assembly diagram of a connection device for a heat shield in a gas turbine combustion chamber according to an embodiment of the present invention.

[0023] Figure 2 It is a schematic diagram of the three-dimensional structure of a connection device for a heat shield in a gas turbine combustion chamber according to an embodiment of the present invention.

[0024] Figure 3 The figure is a schematic diagram of the connection structure of the connection device for the heat shield of the combustion chamber of a gas turbine according to an embodiment of the present invention, and the heat insulation tiles and the combustion chamber shell.

[0025] Figure 4 yes Figure 3 AA cross-section diagram.

[0026] The description of the accompanying drawings is as follows:

[0027] 1. Combustion chamber shell; 2. Insulation tile; 3. Connecting device body; 4. Slender plate; 5. Spring; 6. Fixed connection part; 7. Side; 8. Cooling cavity; 9. Bearing surface; 10. Guard plate; 11. Guard wing; 12. Joint connection part; 13. Cooling gas; 14. Cooling gas channel; 15. Second gap; 16. Cavity; 17. First gap; 18. Insertion groove; 19. First air outlet; 20. Limiting groove; 21. First cavity; 22. Inclined section; 23. Second air outlet. DETAILED DESCRIPTION

[0028] The following is a further detailed description of the specific embodiments of the present invention in conjunction with the accompanying drawings. These embodiments are only used to illustrate the present invention and are not intended to limit the present invention.

[0029] In the description of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inside," and "outside" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0030] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0031] Furthermore, in the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0032] According to the first aspect of this application, see Figures 1 to 4 First, a connection device for a gas turbine combustion chamber heat shield is provided, which is arranged between two adjacent insulation tiles 2 and is used to fix the insulation tiles 2 to the combustion chamber housing 1. The connection device includes a fixed connection portion 6, a limiting cooling portion, and a cooling cavity 8.

[0033] The fixed connection part 6 is a plate-shaped structure, one end of which is used to extend between the heat insulating tile 2 and the combustion chamber shell 1 and be fixedly connected to the combustion chamber shell 1. The heat insulating tile 2 and the combustion chamber shell 1 are fixedly connected by the fixed connection part 6.

[0034] It should be noted that an insertion groove 18 is provided on the connection surface where the combustion chamber housing 1 contacts the heat-insulating tile 2 , and the fixed connection portion 6 is inserted into the insertion groove 18 and fixedly connected to the combustion chamber housing 1 via fasteners.

[0035] The limiting cooling portion is a T-shaped structure of a predetermined thickness. A groove is defined along the periphery of the insulating tile 2. The bottom of the limiting cooling portion is perpendicularly connected to the other end of the fixed connection portion 6, and the top of the limiting cooling portion extends toward the side of the insulating tile 2. The top of the limiting cooling portion engages the groove, limiting axial displacement of the insulating tile 2 along the combustion chamber housing 1.

[0036] It should be noted that the grooves on the connecting surfaces of two adjacent insulation tiles 2 are connected to form a cavity 16 , and the cooling gas 13 flowing into the cavity 16 will enter the combustion chamber through the gaps between the insulation tiles 2 .

[0037] A cooling chamber 8 is provided within the limited cooling section. An air inlet is provided on the bottom surface of the limited cooling section and communicates with the cooling chamber 8. The air inlet is used to connect to a cooling air source on the combustion chamber housing 1 and deliver cooling gas 13. An air outlet is provided on the top of the limited cooling section and communicates with the cooling chamber 8. The air outlet is used to deliver cooling gas 13 into the groove and into the combustion chamber through the gap between adjacent insulating tiles 2. Furthermore, the provision of the cooling chamber 8 cools the main body of the connecting device, reducing thermal damage to the connecting device body 3 caused by leaking hot combustion gases.

[0038] It should be noted that the connection device provided in this embodiment is an elastic structure to ensure stable installation of the multiple insulation tiles 2.

[0039] In one embodiment, the limiting cooling part includes a first cooling part and a second cooling part, the first cooling part is arranged horizontally, and the second cooling part is arranged longitudinally, the first cooling part and the second cooling part form a T-shaped structure, the arrangement direction of the first cooling part is opposite to the arrangement direction of the groove, and the first cooling part is arranged on the bottom surface of the groove to limit the axial displacement of the insulation tile 2 along the combustion chamber shell 1.

[0040] In one embodiment, Figure 1 As shown, a limiting groove 20 is provided on the bottom surface of the groove. The limiting groove 20 is arranged in the same direction as the groove, the length of the limiting groove 20 is the same as the length of the first cooling portion, and the shape of the limiting groove 20 matches the shape of the bottom surface of the first cooling portion. The first cooling portion is fixed in the limiting groove 20. By fixing the first cooling portion in the limiting groove 20, the axial displacement of the insulating tile 2 can be limited. The bottom surface of the first cooling portion is placed in the limiting groove 20, so that it does not directly contact the leaking hot gas, thereby reducing the service temperature of the bottom surface of the first cooling portion in the event of hot gas leakage.

[0041] In one embodiment, the bottom surface of the first cooling part is a bearing surface 9, which is used to bear the axial load of the insulating tile 2. The bearing surface 9 is set in the limiting groove 20, so that it is not in direct contact with the leaking hot gas, thereby reducing the service temperature of the bearing surface 9 in the event of hot gas leakage, and reducing the risk of failure caused by excessive temperature of the bearing surface 9. A protective plate 10 is set on the top surface of the first cooling part. The protective plate 10 preferentially bears the leaking hot gas to prevent the leaking hot gas from continuing to erode the bearing surface 9 downward. If hot gas leakage occurs, the protective plate 10 can play the role of the first layer of protection, replacing the bearing surface 9 to withstand high temperature failure, and prolonging the time required for the hot gas to leak to the bearing surface 9 and cause the bearing surface 9 to fail.

[0042] In one embodiment, an inclined section 22 is provided on the bearing surface 9. The provision of the inclined section 22 further constrains the thermal insulation tile 2 in the axial direction.

[0043] In one embodiment, arc-shaped wings 11 are provided at both ends of the first cooling portion, and the leaked hot gas is guided into the groove along the arc surface of the wings 11, reducing the hot gas flowing downward onto the bearing surface 9.

[0044] In one embodiment, the thickness of the first cooling portion is greater than the depth of the limiting groove 20 , so that the gas outlet is higher than the bottom surface of the groove, which is beneficial to the discharge of the cooling gas 13 .

[0045] In one embodiment, the air outlet includes a first air outlet 19 located on the top surface of the first cooling portion and a second air outlet 23 located on the side surface 7 of the first cooling portion. Cooling gas 13 discharged through the first air outlet 19 is discharged into the groove and then into the combustion chamber through the gap between two adjacent insulation tiles 2. The second air outlet 23 discharges cooling gas 13 between two adjacent insulation tiles 2, cooling the outside of the connecting device.

[0046] It should be noted that the first air outlet 19 and the second air outlet 23 can be set to one or more. Figure 2 As shown, in this embodiment, there are two first air outlets 19 and two second air outlets 23, and both are symmetrically arranged along the axial direction of the connecting device. While ensuring a uniform cooling effect, it can also ensure the injection pressure of the cooling gas 13, further ensuring the cooling effect.

[0047] In one embodiment, an arc groove is provided on the bottom surface of the first cooling portion, and the air inlet is provided in the arc groove. The arc groove is used to gather the cooling gas 13 at the air inlet.

[0048] It should be noted that a plurality of cooling gas channels 14 are provided on the combustion chamber housing 1 , and each cooling gas channel 14 corresponds to the position of the air inlet, which can ensure that the cooling gas 13 is accurately delivered to the cooling cavity 8 through the air inlet.

[0049] In one embodiment, Figure 2 As shown, the fixed connection portion 6 includes an elongated plate 4 and a reed 5. The reed 5 is located on the upper surface of the elongated plate 4. Because the gases in the combustion chamber vibrate in combination with the sound, the insulation tiles 2 vibrate and are washed by the high-temperature gas. This in turn causes the insulation tiles 2 to shift in the direction of the airflow, increasing the axial gap between the insulation tiles 2 and the combustion chamber housing 1. Therefore, the reed 5 is provided on the elongated plate to absorb the vibrational kinetic energy of the insulation tiles 2, preventing the axial gap between the insulation tiles 2 from increasing and reducing the risk of gas intrusion.

[0050] It should be noted that if Figure 3 As shown, the connection devices provided by the present application are arranged in groups, with two connection devices respectively arranged between two adjacent insulation tiles 2. The fixed connection portion 6 of one connection device is inserted between the insulation tile 2 on one side and the combustion chamber shell 1, and the fixed connection portion 6 of the other connection device is inserted between the insulation tile 2 on the other side and the combustion chamber shell 1. The two connection devices are used in combination. Multiple groups of connection devices can be arranged between two adjacent insulation tiles 2 to connect to the combustion chamber shell 1, so that multiple insulation tiles 2 are evenly fixedly connected to the inner side of the combustion chamber shell 1 around the circumference of the combustion chamber.

[0051] Specifically, the connecting device provided in this embodiment is made of nickel-based alloy, and can be formed by additive manufacturing or joined by welding.

[0052] In one embodiment, Figure 2 As shown, the connection between the fixed connection part 6 and the limiting cooling part is a joint connection part 12. The fixed connection part 6 and the limiting cooling part are welded together through the joint connection part 12, or the fixed connection part 6, the limiting cooling part and the joint connection part 12 are integrally formed by a mold.

[0053] The cooling process of the connection device provided in this application is as follows:

[0054] like Figure 3 and Figure 4 As shown, the cooling gas 13 enters the area between the combustion chamber housing 1 and the insulating tiles 2 through the cooling gas channel 14 on the combustion chamber housing 1, and cools the joint connection 12. A portion of the cooling gas 13 flows into the cavity 16 through the second gap 15 between the joint connection parts 12 of adjacent connecting devices. Another portion of the cooling gas 13 flows into the cooling cavity 8 through the air inlet. The cooling cavity 8 in the first cooling part is the first cavity 21. The cooling gas 13 in the first cavity 21 cools the bearing surface 9 and the guard plate 10, and then enters the cavity 16 through the first air outlet 19 and the second air outlet 23 on the outer surface. After the cooling gas 13 merges in the cavity 16, it enters the combustion chamber through the first gap 17 between the insulating tiles 2.

[0055] According to the second aspect of the present application, a heat shield for a gas turbine combustion chamber is also provided, comprising a plurality of circles of thermal insulation tiles arranged axially along the combustion chamber casing 1, each circle of thermal insulation tiles comprising a plurality of thermal insulation tiles 2 evenly distributed circumferentially along the combustion chamber casing 1, each thermal insulation tile 2 being fixedly connected to the combustion chamber casing 1 via the connecting device provided in the first aspect.

[0056] In summary, the connection device and heat shield provided in this application for a gas turbine combustion chamber heat shield can effectively reduce the harmful effects of hot gas leaking between two adjacent insulation tiles 2 in the heat shield. The bearing surface 9 is fully protected by the recessed limit groove 20 in the cavity 16, as well as the guard plate 10 and the guard wings 11. This effectively prevents direct contact between the bearing surface 9 and the hot gas, thereby reducing the service temperature of the bearing surface 9 in the event of hot gas leakage. Simultaneously, the cooling gas 13 cools the bearing surface 9, the guard plate 10, and the guard wings 11 through the cooling cavity 8 and the gas outlet, reducing the temperature rise of the bearing surface 9 caused by heat conduction and the risk of failure due to excessive temperature of the bearing surface 9. Furthermore, if hot gas leakage occurs, the guard plate 10 and the guard wings 11 can serve as a first layer of protection, replacing the bearing surface 9 in the event of high temperature failure, thereby extending the time required for hot gas leakage to the bearing surface 9 and causing failure of the bearing surface 9. By setting the inclined section 22, the heat insulating tiles 2 are axially limited, thereby preventing the axial gap between the heat insulating tiles 2 from increasing and reducing the risk of gas intrusion.

[0057] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present invention. These improvements and substitutions should also be regarded as the scope of protection of the present invention.

Claims

1. A connection device for a heat shield in a gas turbine combustion chamber, characterized in that: It is provided between two adjacent heat-insulating tiles (2) and is used to fixedly connect the heat-insulating tiles (2) and the combustion chamber shell (1); the connecting device comprises: A fixed connection portion (6), one end of the fixed connection portion (6) is used to extend between the heat-insulating tile (2) and the combustion chamber shell (1), and is fixedly connected to the combustion chamber shell (1); The limiting cooling portion is a T-shaped structure with a predetermined thickness, a groove is provided on the peripheral side of the heat insulating tile (2), the bottom of the limiting cooling portion is connected to the other end of the fixed connection portion (6), and the top of the limiting cooling portion extends toward one side of the heat insulating tile (2); the top of the limiting cooling portion is clamped on the groove to limit the axial displacement of the heat insulating tile (2); A cooling chamber (8) is provided inside the position-limiting cooling portion and is used for conveying cooling gas (13); An air inlet is provided on the bottom surface of the position-limiting cooling portion and is in communication with the cooling cavity (8); An air outlet is provided at the top of the limiting cooling portion and is in communication with the cooling cavity (8); it is used to transport the cooling gas (13) into the groove and into the combustion chamber through the gap between two adjacent heat-insulating tiles (2); The limiting cooling portion includes a first cooling portion and a second cooling portion arranged vertically, the first cooling portion and the second cooling portion forming a T-shaped structure, the first cooling portion and the groove are arranged in the same direction and are clamped on the bottom surface of the groove; A limiting groove (20) is provided on the bottom surface of the groove, the arrangement direction of the limiting groove (20) is the same as the arrangement direction of the groove, the length of the limiting groove (20) is the same as the length of the first cooling part, and the first cooling part is clamped in the limiting groove (20); A through slot is provided in the middle of the limiting slot (20), the through slot extending toward the combustion chamber housing (1), and the through slot is used for installing the second cooling portion.

2. The connection device for a gas turbine combustion chamber heat shield according to claim 1, characterized in that: The bottom surface of the first cooling part is a load-bearing surface (9), and a protective plate (10) is provided on the top surface of the first cooling part.

3. The connection device for a gas turbine combustion chamber heat shield according to claim 2, characterized in that: The load-bearing surface (9) includes an inclined section (22).

4. The connection device for a gas turbine combustion chamber heat shield according to claim 2, characterized in that: Guard wings (11) are provided at both ends of the first cooling portion.

5. The connection device for a gas turbine combustion chamber heat shield according to claim 1, characterized in that: The thickness of the first cooling portion along the axial direction of the combustion chamber housing (1) is greater than the depth of the limiting groove (20).

6. The connection device for a gas turbine combustion chamber heat shield according to claim 1, characterized in that: The air outlet comprises a first air outlet (19) provided on the top surface of the first cooling portion and a second air outlet (23) provided on the side surface (7) of the first cooling portion.

7. The connecting device for a heat shield in a gas turbine combustion chamber according to any one of claim 1, characterized in that: A reed (5) is provided on the upper surface of the fixed connection portion (6), and the reed (5) is used to absorb vibration of the heat-insulating tile (2).

8. A heat shield for a gas turbine combustion chamber, characterized in that: The invention comprises a plurality of circles of heat-insulating tiles arranged axially along a combustion chamber casing (1), each circle of heat-insulating tiles comprising a plurality of heat-insulating tiles (2) uniformly distributed circumferentially along the combustion chamber casing (1), and each heat-insulating tile (2) being fixedly connected to the combustion chamber casing (1) by a connecting device according to any one of claims 1 to 7.

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