CN218717023U - Gas turbine exhaust device and gas turbine - Google Patents
Gas turbine exhaust device and gas turbine Download PDFInfo
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- CN218717023U CN218717023U CN202223070681.8U CN202223070681U CN218717023U CN 218717023 U CN218717023 U CN 218717023U CN 202223070681 U CN202223070681 U CN 202223070681U CN 218717023 U CN218717023 U CN 218717023U
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- tail cone
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Abstract
The application discloses gas turbine exhaust apparatus and gas turbine. The gas turbine exhaust device comprises an outer ring exhaust pipe, a rectification support plate and an inner ring exhaust tail cone; the outer ring exhaust pipe is used for being arranged at a turbine outlet of the gas turbine and is provided with a positioning hole; the inner ring exhaust tail cone is positioned on the inner side of the outer ring exhaust pipe, the inner ring exhaust tail cone and the outer ring exhaust pipe form a gas channel, and the rectification support plate is fixedly connected in the gas channel; the first end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is connected with the inner ring exhaust tail cone in a welding mode, and the second end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is detachably connected with the outer ring exhaust pipe through a connecting part; the connecting part comprises a connecting piece, the connecting piece extends into the gas channel through the connecting hole, and the connecting piece is detachably connected with the second end of the rectifying support plate. The utility model provides a gas turbine exhaust apparatus, the rectification extension board can freely stretch out and draw back along the radial of outer loop blast pipe, can avoid the rectification extension board to take place to damage, can improve gas turbine unit operational reliability.
Description
Technical Field
The application relates to the technical field of gas turbines, in particular to a gas turbine exhaust device and a gas turbine.
Background
The exhaust device is an important component of the gas turbine, has the functions of speed reduction and pressure expansion, can reduce the air flow loss in an exhaust pipeline, and improves the pressure drop ratio of the turbine. The exhaust device mainly includes two types, namely an axial exhaust device and a lateral exhaust device according to the exhaust form, wherein the axial exhaust device is widely applied to the gas turbine due to the advantages of simple structure, better performance, lower cost and the like.
The axial exhaust device is usually positioned at the turbine outlet of a gas turbine and mainly comprises an outer ring exhaust pipe, an inner ring exhaust tail cone, a rectification support plate and the like, wherein the front mounting edge of the outer ring exhaust pipe is connected with a turbine or a volute casing of a combustion chamber, the rear mounting edge of the outer ring exhaust pipe is connected with a downstream extension pipeline, the inner ring exhaust tail cone is positioned in the outer ring exhaust pipe, a gas channel is formed by the inner ring exhaust tail cone and the outer ring exhaust pipe, and the rectification support plate is connected between the outer ring exhaust pipe and the inner ring exhaust tail cone, namely the rectification support plate is positioned in the gas channel.
The existing axial exhaust device is generally formed by welding, and two ends of a rectification support plate are respectively welded with an outer ring exhaust pipe and an inner ring exhaust tail cone. Because the outlet of the turbine is high-temperature gas, the temperature field distribution is uneven, and the temperature in the gas channel is higher than the temperature outside the casing, so that the thermal deformation of the rectifying support plate is greater than that of the casing, the thermal deformation is uncoordinated to generate great thermal stress, the rectifying support plate is easy to damage after long-time working, such as the welding seam crack of the rectifying support plate or the cracking and deformation of the rectifying support plate, the use cost is increased, and the exhaust tail cone of the inner ring and the turbine rotor are cut and rubbed in serious cases, thereby endangering the use safety of the unit.
SUMMERY OF THE UTILITY MODEL
The embodiment of the application provides a gas turbine exhaust apparatus and a gas turbine to solve the problem that a rectification supporting plate is easy to damage.
On one hand, the embodiment of the application provides a gas turbine exhaust device, which comprises an outer ring exhaust pipe, a rectifying support plate and an inner ring exhaust tail cone; the outer ring exhaust pipe is used for being arranged at a turbine outlet of the gas turbine and is provided with a positioning hole; the inner ring exhaust tail cone is positioned on the inner side of the outer ring exhaust pipe, and the inner ring exhaust tail cone and the outer ring exhaust pipe form a gas channel; the rectifying support plate is fixedly connected in the gas channel, the first end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is welded with the inner ring exhaust tail cone, and the second end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is detachably connected with the outer ring exhaust pipe through a connecting part; the connecting part comprises a connecting piece, and the connecting piece extends into the gas channel through the positioning hole and is detachably connected with the second end of the rectifying support plate.
According to an aspect of the embodiment of the present application, the connecting portion further includes a sealing gasket, and the sealing gasket is sleeved on the connecting member.
According to an aspect of the embodiment of the application, the connecting piece is of a pin structure, the second end of the rectifying support plate is provided with a connecting hole, and the connecting piece is fixedly connected in the connecting hole.
According to an aspect of an embodiment of the present application, the connecting member is threadedly coupled to the connecting hole.
According to an aspect of an embodiment of the present application, the rectifying plate has a first gap with an inner wall of the outer ring exhaust pipe.
According to an aspect of the embodiment of the application, the plurality of the rectifying support plates are arranged around the inner ring exhaust tail cone at intervals.
According to an aspect of an embodiment of the present application, a cross-sectional shape of the rectifying support plate along an axial direction of the outer ring exhaust pipe is a drop shape.
According to an aspect of the embodiment of the application, the inner ring exhaust tail cone inner side is provided with a tail cone retainer ring, and a heat insulation layer is arranged between the inner ring exhaust tail cone and the tail cone retainer ring.
According to an aspect of an embodiment of the present application, there is a second clearance between the tail cone retainer ring and the turbine.
In another aspect, embodiments of the present application are directed to a gas turbine including a gas turbine exhaust as described above.
The gas turbine exhaust apparatus that the embodiment of the application provided, the welded subassembly that constitutes rectification extension board and inner ring exhaust tail cone is connected with the outer loop blast pipe through the connecting piece, realize location and centering of the welded subassembly that rectification extension board and inner ring exhaust tail cone constitute, the second end of rectification extension board passes through connecting portion with the outer loop blast pipe and can dismantle the connection, the rectification extension board can freely stretch out and draw back along the radial of outer loop blast pipe, warp, thereby the work thermal stress that non-uniform temperature field produced can be released effectively, avoid the rectification extension board to take place to damage, can reduce gas turbine exhaust apparatus's use and maintenance cost, improve gas turbine unit operational reliability.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic assembly view of a gas turbine exhaust provided in an embodiment of the present application;
FIG. 2 is a schematic structural diagram of a gas turbine exhaust provided by an embodiment of the present application;
fig. 3 is a schematic structural diagram of a flow straightening plate of a gas turbine exhaust device according to an embodiment of the present application.
Reference numerals:
the method comprises the following steps of 1-a turbine, 2-a turbine disc body, 4-an extension pipeline, 5-a casing, 6-an outer ring exhaust pipe, 7-a connecting piece, 8-a rectifying support plate, 9-an inner ring exhaust tail cone, 11-a tail cone retainer ring, 13-a gas channel, 14-a cooling air cavity, 15-a heat insulation layer, 16-a front flange, 17-a rear flange, 19-a connecting hole, 22-a locking nut, 23-a turbine shaft and 24-a sealing gasket.
Detailed Description
Embodiments of the present application will be described in further detail below with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the application and are not intended to limit the scope of the application, i.e., the application is not limited to the described embodiments.
In the description of the present application, it is noted that, unless otherwise indicated, the terms "first" and "second," etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; "plurality" means two or more; the terms "inner", "outer", and the like, indicate an orientation or positional relationship based on that shown in the drawings, merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present application.
For ease of understanding, the application scenario of the gas turbine exhaust apparatus to which the present application relates will be first explained. The exhaust device of the gas turbine provided by the embodiment of the application can be adapted to the gas turbine, for example, can be adapted to a medium-small-sized gas turbine, and can be used as the exhaust device of the gas turbine.
Referring to fig. 1 and 2, fig. 1 is a schematic view illustrating an assembly of a gas turbine exhaust apparatus according to an embodiment of the present disclosure, and fig. 2 is a schematic view illustrating a structure of the gas turbine exhaust apparatus according to the embodiment of the present disclosure. As shown in fig. 1 and fig. 2, the gas turbine exhaust device provided in the embodiment of the present application may include an outer ring exhaust pipe 6, a rectifying plate 8, and an inner ring exhaust tail cone 9.
Wherein the outer ring exhaust duct 6 may be arranged at the outlet of the turbine 1 of the gas turbine. Specifically, the front flange 16 of the outer ring exhaust pipe 6 may be connected with the volute casing 5 of the combustion chamber of the gas turbine, and the rear flange 17 of the outer ring exhaust pipe 6 may be connected with the downstream extension pipe 4. The outer ring exhaust pipe 6 may have a positioning hole, and the positioning hole may penetrate through a pipe wall of the outer ring exhaust pipe 6.
The inner ring exhaust tail cone 9 can be positioned inside the outer ring exhaust pipe 6, and the inner ring exhaust tail cone 9 and the outer ring exhaust pipe 6 form a gas channel 13. The outer surface of the inner ring exhaust tail cone 9 can be connected with an inner flow passage of the turbine 1, so that the air flow separation can be slowed down, and the exhaust loss is reduced. The inner ring exhaust tail cone 9 can be conical, the gas channel 13 can be an expansion channel, namely the radial sectional area of the gas channel 13 can be gradually increased along the airflow direction, and the airflow deceleration and diffusion functions are realized.
The rectification extension plate 8 can be fixedly connected in the gas channel 13, the rectification extension plate 8 can be welded with the inner ring exhaust tail cone 9 along the radial first end of the outer ring exhaust pipe 6, and the rectification extension plate 8 can be detachably connected with the outer ring exhaust pipe 6 through a connecting part along the radial second end of the outer ring exhaust pipe 6. In specific implementation, the connecting portion may include a connecting member 7, and the connecting member 7 may extend into the gas channel 13 through the positioning hole and be detachably connected to the second end of the rectifying support plate 8.
In this embodiment, the welding assembly formed by the rectifying support plate 8 and the inner ring exhaust tail cone 9 is connected with the outer ring exhaust pipe 6 through the connecting piece 7, so that the positioning and centering of the welding assembly formed by the rectifying support plate 8 and the inner ring exhaust tail cone 9 are realized, the second end of the rectifying support plate 8 is detachably connected with the outer ring exhaust pipe 6 through the connecting part, the rectifying support plate 8 can freely stretch out and draw back and deform along the radial direction of the outer ring exhaust pipe 6, thereby effectively releasing the working thermal stress generated by the non-uniform temperature field, avoiding the rectifying support plate 8 from being damaged, reducing the use and maintenance cost of the gas turbine exhaust device, and improving the operation reliability of the gas turbine unit.
As an alternative embodiment, the connecting part may further comprise a sealing washer 24, and the sealing washer 24 may be sleeved on the connecting part 7. The sealing washer 24 is arranged to enhance the sealing between the connecting piece 7 and the outer ring exhaust pipe 6.
In a specific implementation, the connecting member 7 may be a pin structure, the second end of the rectifying support plate 8 may be provided with a connecting hole 19, and the connecting member 7 may be fixedly connected in the connecting hole 19. The rectification support plate 8 and the inner ring exhaust tail cone 9 which are welded and connected into a whole can be fixedly connected to the outer ring exhaust pipe 6 through a pin structure, so that the inner ring exhaust tail cone 9 and the outer ring exhaust pipe 6 are positioned and centered. In specific implementation, the connecting member 7 and the connecting hole 19 may be connected by a screw thread, that is, the pin is structurally provided with a screw thread structure, and the connecting hole 19 is a screw hole.
In actual setting, the connecting piece 7 and the connecting hole 19 can adopt smaller clearance fit, so that connection is facilitated, and the welding assembly formed by the rectifying support plate 8 and the inner ring exhaust tail cone 9 can be prevented from shaking after being connected with the outer ring exhaust pipe 6. For reference, the gap value between the connecting member 7 and the connecting hole 19 may be 0.03 to 0.06mm.
In a specific implementation, the rectifying support plate 8 and the inner wall of the outer ring exhaust pipe 6 can have a first gap therebetween. The arrangement of the first gap enables the incongruous thermal deformation of the rectifying support plate 8 caused by the nonuniform temperature field of the upstream gas channel 13 to freely stretch out and draw back along the radial direction of the outer ring exhaust pipe 6, so that the rectifying support plate 8 can release the thermal stress caused by nonuniform temperature distribution in the working process, and the positioning and centering of the inner ring exhaust tail cone 9 and the outer ring exhaust pipe 6 can be ensured.
In one possible embodiment, there may be a plurality of the flow straightening plates 8, and a plurality of the flow straightening plates 8 may be spaced around the inner ring exhaust tail cone 9. Specifically, the plurality of rectifying support plates 8 may be uniformly arranged along the circumferential direction of the inner ring exhaust tail cone 9.
Referring to fig. 3, fig. 3 is a schematic structural diagram illustrating a flow straightening plate of a gas turbine exhaust device according to an embodiment of the present disclosure. As shown in fig. 3, in a specific implementation, the cross-sectional shape of the flow straightening plate 8 in the axial direction of the outer ring exhaust pipe 6 may be a drop shape, in other words, an airfoil shape. Alternatively, the cross-sectional shape of the flow straightening plate 8 in the axial direction of the outer ring exhaust pipe 6 may be a curved airfoil shape or a symmetrical airfoil shape.
As an alternative embodiment, a tail cone retainer ring 11 can be arranged on the inner side of the inner ring exhaust tail cone 9, and a heat insulation layer 15 can be arranged between the inner ring exhaust tail cone 9 and the tail cone retainer ring 11. The heat insulation layer 15 can reduce the heat radiation of the high-temperature airflow in the gas channel 13 to the turbine disk body 2, the turbine shaft 23, the lock nut 22 and other components. Specifically, the heat insulating layer 15 may be made of a heat insulating material.
In a specific implementation, the tail cone retainer ring 11 and the turbine 1 may have a second clearance therebetween. Specifically, a second clearance may be provided between the tail cone retainer ring 11 and the turbine disk body 2, the turbine shaft 23 and the lock nut 22 to form the cooling air cavity 14, so that the heat radiation of the high-temperature air flow in the gas channel 13 to the turbine disk body 2, the turbine shaft 23 and the lock nut 22 can be further reduced.
It should be understood by those skilled in the art that the foregoing is only illustrative of the present invention, and is not intended to limit the scope of the present invention. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (9)
1. The exhaust device of the gas turbine is characterized by comprising an outer ring exhaust pipe, a rectifying support plate and an inner ring exhaust tail cone;
the outer ring exhaust pipe is used for being arranged at a turbine outlet of the gas turbine and is provided with a positioning hole;
the inner ring exhaust tail cone is positioned on the inner side of the outer ring exhaust pipe, and the inner ring exhaust tail cone and the outer ring exhaust pipe form a gas channel;
the rectifying support plate is fixedly connected in the gas channel, the first end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is welded with the inner ring exhaust tail cone, and the second end of the rectifying support plate along the radial direction of the outer ring exhaust pipe is detachably connected with the outer ring exhaust pipe through a connecting part; the connecting part comprises a connecting piece, and the connecting piece extends into the gas channel through the positioning hole and is detachably connected with the second end of the rectifying support plate.
2. The gas turbine exhaust of claim 1 wherein the connection further comprises a sealing gasket, the sealing gasket fitting over the connection.
3. The gas turbine exhaust system according to claim 1, wherein the attachment member is a pin structure, and the second end of the flow straightening plate is provided with a connection hole, and the attachment member is fixedly attached in the connection hole.
4. The gas turbine exhaust apparatus according to claim 1, wherein the connecting member is threadedly connected to the connecting hole.
5. The gas turbine exhaust of claim 1, wherein the flow straightening plate has a first gap with an inner wall of the outer ring exhaust pipe.
6. A gas turbine exhaust according to claim 1, wherein the plurality of fairing supports are spaced around the inner ring exhaust tail cone.
7. The gas turbine exhaust of claim 1, wherein a tail cone retainer ring is disposed inboard of the inner ring exhaust tail cone, and a thermal barrier layer is disposed between the inner ring exhaust tail cone and the tail cone retainer ring.
8. The gas turbine exhaust of claim 7, wherein a second clearance is provided between the tail cone retainer ring and the turbine wheel.
9. A gas turbine engine comprising a gas turbine exhaust as claimed in any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223070681.8U CN218717023U (en) | 2022-11-18 | 2022-11-18 | Gas turbine exhaust device and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223070681.8U CN218717023U (en) | 2022-11-18 | 2022-11-18 | Gas turbine exhaust device and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218717023U true CN218717023U (en) | 2023-03-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223070681.8U Active CN218717023U (en) | 2022-11-18 | 2022-11-18 | Gas turbine exhaust device and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218717023U (en) |
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2022
- 2022-11-18 CN CN202223070681.8U patent/CN218717023U/en active Active
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