A turbine interstage casing vent structure with enclosed passage

Abstract

The application provides a turbine inter-casing gas exhaust structure with a closed channel, and belongs to the technical field of gas turbines. The gas exhaust structure comprises a load outer casing, a power turbine casing connected with the load outer casing, a gas exhaust pipeline installed on the load outer casing, a guide vane installed on an outer ring, and an outer ring connected with the load outer casing and the power turbine casing. A cooling cavity is formed between the load outer casing and the outer ring. The outer ring is provided with a gas exhaust hole at a front section, and is provided with a boss structure. A gas exhaust support ring is fixed at the boss structure in combination with a gas exhaust mounting seat. A connecting nozzle is installed in the gas exhaust mounting seat and the gas exhaust pipeline to form a closed channel. A sealing ring is arranged at a front end of the outer ring, and a gas exhaust flow channel is formed between the sealing ring and the outer ring. The gas in a main flow channel flows out from the gas exhaust pipeline along the gas exhaust flow channel and the closed channel. A hollow support plate is arranged in the load outer casing at a front side of the gas exhaust flow channel. The hollow support plate, the sealing ring and the outer ring are provided with cooling holes for forming a cooling flow path.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of gas turbines, and particularly relates to a turbine inter casing gas exhaust structure with a closed channel. BACKGROUND

[0002] The turbine inter casing is a support casing of a rear support point of a gas turbine and a front support point of a power turbine. Compared with a structure of a traditional gas turbine supporting a power turbine rotor, the support on the turbine inter casing can avoid rotor vibration coupling to a certain extent, improve the vibration condition of the whole machine, and meet the impact resistance requirement of the whole machine. The power turbine guide is arranged on the turbine inter casing, and a load shedding gas exhaust regulating system is arranged. Figure 1

[0003] Since the turbine inter casing is between the gas turbine and the power turbine, the gas turbine works at a high temperature level, the temperature of the gas exhausted by the gas exhaust regulating system is high, the temperature level of the adjacent load bearing outer casing 15 and the power turbine casing 16 near the gas exhaust port 14 is high, and the service life of the turbine components is affected. SUMMARY

[0004] The application aims to provide a turbine inter casing gas exhaust structure with a closed channel to solve or alleviate at least one problem in the background art.

[0005] The technical scheme of the application is a turbine inter casing gas exhaust structure with a closed channel, comprising a load bearing outer casing, a gas exhaust pipeline, a power turbine casing, a hollow support plate, a sealing ring, a gas exhaust support ring, a gas exhaust mounting seat, a connecting nozzle, an outer ring and a guide vane.

[0006] The gas exhaust pipeline is mounted on the load bearing outer casing.

[0007] The load bearing outer casing is connected with the power turbine casing and fixedly connected with the outer ring, and a cooling cavity is formed between the load bearing outer casing and the outer ring.

[0008] The guide vane is mounted on the outer ring.

[0009] The outer ring is provided with a gas exhaust hole, and the outer ring is provided with a boss structure, the gas exhaust support ring and the gas exhaust mounting seat are fixed at the boss structure after being combined, and the connecting nozzle is mounted in the gas exhaust mounting seat and the gas exhaust pipeline to form a closed channel.

[0010] The sealing ring is arranged at the front end of the outer ring, and a gas exhaust flow channel is formed between the sealing ring and the outer ring, and the gas in the main flow channel flows out from the gas exhaust pipeline along the gas exhaust flow channel and the closed channel. ​

[0011] The hollow support plate is arranged in the load outer casing on the front side of the air bleed flow channel, the hollow support plate, the sealing ring and the outer ring are provided with cooling holes forming a cooling flow path, cooling gas is introduced into the cavity of the hollow support plate, and the cooling gas cools the load outer casing, the outer ring and the power turbine casing through the cooling flow path.

[0012] In an optional embodiment of the present application, the outer ring is clamped between the load outer casing and the power turbine casing, and the load outer casing, the power turbine casing and the outer ring are fixedly connected through the same connecting piece.

[0013] In an optional embodiment of the present application, the inner side of the front end and the rear end of the outer ring is provided with a front hanging point and a rear hanging point extending rearward, the upper edge plate of the guide vane is respectively provided with a front hook and a rear hook at the front and rear, and the upper edge plate of the guide vane is centered and matched with the front hanging point and the rear hanging point of the outer ring by the outer surface of the front hook and the inner surface of the rear hook.

[0014] In an optional embodiment of the present application, the front section of the outer ring is provided with a plurality of air bleed holes for discharging main flow channel gas, and the plurality of air bleed holes are uniformly distributed in the circumferential direction.

[0015] In an optional embodiment of the present application, the air bleed support ring and the air bleed mounting seat are integrally formed through welding, and are fixed to the boss structure of the outer ring through welding.

[0016] In an optional embodiment of the present application, the cooling holes on the hollow support plate are located at the rear end of the hollow support plate.

[0017] In an optional embodiment of the present application, the cooling holes on the sealing ring are located on the upper end of the sealing ring between the load outer casing and the outer ring.

[0018] In an optional embodiment of the present application, the cooling holes on the outer ring are located at the lower side of the clamping surface between the load outer casing and the power turbine casing.

[0019] The turbine inter-casing air bleed structure with a closed channel provided by the present application can cool the load outer casing and the power turbine casing, effectively reduce the temperature of the rear end of the load outer casing and the front end of the power turbine casing, and effectively improve the service life of the turbine structure. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions provided by the present application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the present application.

[0021] Figure 1 The existing air bleed adjustment system flow path is shown in the figure.

[0022] Figure 2A schematic diagram of a turbine inter- casing bleed structure according to the present application.

[0023] Figure 3 A schematic diagram of a turbine inter- casing bleed structure according to the present application. Figure 2

[0024] Figure 4 A schematic diagram of a turbine inter- casing bleed structure according to the present application.

[0025] Figure 5 A schematic diagram of a turbine inter- casing bleed structure according to the present application. Figure 2

[0026] Figure 6 A schematic diagram of a turbine inter- casing bleed structure according to the present application. Figure 2

[0027] Figure 7 A schematic diagram of a turbine inter- casing bleed structure according to the present application.

[0028] Reference signs:

[0029] 20 - turbine inter- casing bleed structure

[0030] 21 - load bearing outer casing

[0031] 22 - bleed line

[0032] 23 - power turbine casing

[0033] 24 - hollow struts, 241 - first cooling holes

[0034] 25 - seal ring, 251 - second cooling holes

[0035] 26 - bleed support ring

[0036] 27 - bleed mounting seat, 271 - through holes

[0037] 28 - adapter

[0038] 29 - outer ring, 291 - boss structure, 292 - third cooling holes, 293 - third bleed holes

[0039] 30 - guide vanes DETAILED DESCRIPTION

[0040] In order to make the purposes, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings of the embodiments of the present application.

[0041] ​​​The application provides a turbine inter-casing gas exhaust structure with a closed channel, which meets the traditional gas exhaust function requirements, adopts a structure of welding a gas exhaust seat and a connecting nozzle to form a closed channel, reduces the contact area of main flow channel gas and the load-bearing outer casing, reduces the temperature rise rate of the load-bearing outer casing, adopts a cooling measure to cool the gas outlet, reduces the working temperature of the load-bearing outer casing and the power turbine casing, prolongs the service life of the load-bearing outer casing and the power turbine casing, and meets the use requirements of long service life of the gas turbine turbine casing.

[0042] As shown in Figures 2 to 6 The turbine inter-casing gas exhaust structure 20 provided by the application mainly comprises a load-bearing outer casing 21, a gas exhaust pipeline 22, a power turbine casing 23, a hollow support plate 24, a sealing ring 25, a gas exhaust support ring 26, a gas exhaust mounting seat 27, a connecting nozzle 28, an outer ring 29 and a guide vane 30.

[0043] The load-bearing outer casing 21 is provided with a gas exhaust port, and the gas exhaust port is provided with the gas exhaust pipeline 22. The rear side of the load-bearing outer casing 21 is fixedly connected with the power turbine casing 23 through a connecting piece, and the outer ring 29 is clamped between the load-bearing outer casing 21 and the power turbine casing 23. The three are connected and fixed through the same bolt connecting piece.

[0044] The outer side of the outer ring 29 is provided with a boss structure 291 for fixing the gas exhaust support ring 26. The gas exhaust support ring 26 is fixedly combined with the gas exhaust mounting seat 27 and is installed on the boss structure 291 of the outer ring 29. The connecting nozzle 28 is arranged in the gas exhaust mounting seat 27 and the gas exhaust pipeline 22, so as to form a closed channel. The outer ring 29 has a gap with the load-bearing outer casing 21, so as to form a cooling cavity B.

[0045] In the application, the gas exhaust support ring 26 is an integral ring structure, and circular holes are uniformly arranged on the gas exhaust support ring 26 corresponding to the positions of the gas exhaust holes of the load-bearing outer casing 21. The gas exhaust mounting seat 27 is installed at each circular hole. The middle part of the gas exhaust mounting seat 27 is a larger-diameter through hole 271 for the main flow channel gas to enter the gas exhaust pipeline 22. The gas exhaust support ring 26 and the gas exhaust mounting seat 27 are integrally fixed on the boss structure 291 of the outer ring 9 to form an outer ring assembly, so that the contact area of the main flow channel gas and the load-bearing outer casing 21 changes from an annular cavity to several closed cylindrical channels, thereby reducing the heat transfer contact area of the main flow channel gas and the rear end of the load-bearing outer casing 21 and the outer ring 29, and reducing the temperature rise rate of the rear end of the load-bearing outer casing 21 and the front end of the power turbine casing 23, as shown in Figure 4 In some embodiments of the application, the gas exhaust support ring 26 and the gas exhaust mounting seat 27 are integrally formed by welding, and are fixed on the boss structure 291 of the outer ring 29 by welding.

[0046] The outer ring 29 has a front and rear mounting point extending rearward (in the direction of airflow) at its inner front and rear ends. The upper edge plate of the guide vane 30 has a front hook and a rear hook at its front and rear, respectively. The upper edge plate of the guide vane 30 uses the outer surface of the front hook and the inner surface of the rear hook to center and engage with the front and rear mounting points of the outer ring 29. The front section of the outer ring 29 has multiple vent holes 293 for exhausting the main flow channel. In some embodiments of this application, the vent holes 293 are evenly distributed circumferentially.

[0047] The sealing ring 25 is installed on the load-bearing outer casing 21 and located at the front end of the outer ring 29. The sealing ring 25 and the outer ring 29 form a load-shedding venting channel. The gas from the main channel flows along the venting channel, passes through the venting hole 293 on the front section of the outer ring 29 and the through hole 271 of the venting mounting seat 27, and enters the exhaust pipe 22.

[0048] A hollow support plate 24 is installed at the front end of the venting air path of the load-bearing outer casing 21. The hollow support plate 24 contains cooling air drawn from the compressor. A first cooling hole 241 is provided at the rear end of the hollow support plate 24. Combined with... Figure 5 and Figure 6 As shown, the sealing ring 25 and the outer ring 29 are respectively provided with a second cooling hole 251 and a third cooling hole 292, forming a cooling flow path through the three cooling holes. In this application, the second cooling hole 251 is located at the upper end of the sealing ring 25 between the load-bearing outer casing 21 and the outer ring 29, and the third cooling hole 292 is located on the lower side of the outer ring 29 at the clamping surface between the load-bearing outer casing 21 and the power turbine casing 23.

[0049] like Figure 7 As shown, the cooling air in the cavity of the hollow support plate 24 flows out through the first cooling hole 241, passes through the second cooling hole 251 of the sealing ring 25, and enters the cooling cavity B to cool the rear section of the load-bearing outer casing 21 and the outer ring 29. Then, it passes through the third cooling hole 292 at the rear end of the outer ring 9 and is discharged into the main channel from the rear end of the upper edge plate of the guide vane 30 to cool the front end of the power turbine casing 23.

[0050] The turbine casing venting structure with a closed channel provided in this application forms a cooling airflow path by setting cooling holes on the hollow support plate, sealing ring and outer ring. The cooling airflow path achieves cooling of the rear end of the load-bearing outer casing and the front end of the power turbine casing. The cooling airflow path is independent of the main exhaust channel, which can avoid the mixing of cold air and main exhaust channel combustion gas, effectively reduce the temperature of the rear end of the load-bearing outer casing and the front end of the power turbine casing, and effectively improve the service life of the turbine structure.

[0051] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A turbine interstage casing bleed structure with enclosed passage, characterized by, The utility model relates to a turbine engine outer casing structure, comprising: a load-bearing outer casing, a bleed pipe, a power turbine casing, a hollow support plate, a seal ring, a bleed support ring, a bleed mounting seat, a connecting nozzle, an outer ring and a guide vane; the bleed pipe is mounted on the load-bearing outer casing; the load-bearing outer casing is connected with the power turbine casing and fixedly connected with the outer ring, and a cooling cavity is formed between the load-bearing outer casing and the outer ring; the guide vane is mounted on the outer ring; a bleed hole is arranged at the front end of the outer ring, a boss structure is arranged on the outer ring, the bleed support ring and the bleed mounting seat are fixed at the boss structure after being combined, and the connecting nozzle is mounted in the bleed mounting seat and the bleed pipe to form a closed channel; the seal ring is arranged at the front end of the outer ring, and a bleed flow channel is formed between the seal ring and the outer ring, and the gas in the main flow channel flows out from the bleed pipe along the bleed flow channel and the closed channel; the hollow support plate is arranged in the load-bearing outer casing on the front side of the bleed flow channel, cooling holes for forming a cooling flow path are arranged on the hollow support plate, the seal ring and the outer ring, cooling gas is introduced into the cavity of the hollow support plate from the compressor, and the cooling gas cools the load-bearing outer casing, the outer ring and the power turbine casing through the cooling flow path.

2. The closed passage turbine inter-stage casing bleed structure of claim 1, wherein, The outer ring is clamped between the load-bearing outer casing and the power turbine casing, and the load-bearing outer casing, the power turbine casing and the outer ring are fixedly connected through the same connecting piece.

3. The closed passage turbine inter-stage casing bleed structure of claim 1, wherein, The inner side of the outer ring is provided with a front hanging point and a rear hanging point extending rearward at the front end and the rear end, the upper edge plate of the guide vane is respectively provided with a front hook and a rear hook at the front and the rear, and the upper edge plate of the guide vane is centered and matched with the front hanging point and the rear hanging point of the outer ring through the outer surface of the front hook and the inner surface of the rear hook.

4. The closed passage turbine inter-stage casing bleed structure of claim 3, wherein, The front end of the outer ring is provided with a plurality of bleed holes for discharging the gas in the main flow channel, and the plurality of bleed holes are uniformly distributed in the circumferential direction.

5. The closed passage turbine inter-stage casing bleed structure of claim 1, wherein, The bleed support ring and the bleed mounting seat form an integral structure through welding and are fixed at the boss structure of the outer ring through welding.

6. The closed passage turbine clearance chine bleed structure of claim 1, wherein, The cooling hole on the hollow support plate is located at the rear end of the hollow support plate.

7. The closed passage turbine clearance chine bleed structure of claim 1, wherein, The cooling hole on the seal ring is located on the upper end of the seal ring between the load-bearing outer casing and the outer ring.

8. The closed passage turbine clearance chine bleed structure of claim 4, wherein, The cooling hole on the outer ring is located on the lower side of the clamping surface of the load-bearing outer casing and the power turbine casing.

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