A gas turbine low pressure turbine support ring structure

Abstract

A kind of gas turbine low-pressure turbine support ring structure belongs to gas turbine structural design field.It includes support ring shell, power support column, support shell, bearing seat, conical part, shell, first outer shell, second outer shell, inner shell, fairing, gas supply pipe, oil supply pipe and oil discharge pipe;Power support column is connected with support ring shell and support shell, support shell is equipped with conical part, shell is connected with bearing seat and the rear support of low-pressure turbine rotor, first outer shell, second outer shell and inner shell are equipped with multiple fairings, gas supply pipe and a fairing constitute support ring gas supply structure, oil supply pipe and a fairing constitute support ring oil supply structure, oil discharge pipe and a fairing constitute support ring oil discharge structure.Solve the problem that existing support ring structure is greatly influenced by external shell thermal expansion, shock absorption effect is not good, there is no matching oil inlet and oil return structure, effectively reduce external shell thermal expansion, for oil supply, oil discharge and gas supply into rotor interior.

Description

Technical Field

[0001] This invention relates to a low-pressure turbine support ring structure for a gas turbine, belonging to the field of gas turbine structural design. Background Technology

[0002] The fuel-fired gas turbine has a low-pressure turbine. The low-pressure turbine support ring is used to set the rear support of the low-pressure turbine rotor and form a flow passage between the low-pressure turbine and the power turbine. The existing support ring structure is greatly affected by the thermal expansion of the outer shell, resulting in poor vibration damping. It also lacks matching oil inlet and return structures, making it unsuitable for supplying oil, draining oil, and supplying gas into the rotor.

[0003] Therefore, there is an urgent need to propose a new type of low-pressure turbine support ring structure for gas turbines to solve the above-mentioned technical problems. Summary of the Invention

[0004] The purpose of this invention is to address the problems of existing support ring structures being significantly affected by the thermal expansion of the outer shell, resulting in poor vibration damping, lack of matching oil inlet and outlet structures, and the inability to use the support ring for oil supply, drainage, and air supply to the rotor. A brief overview of the invention is provided below to offer a basic understanding of certain aspects of it. It should be understood that this overview is not an exhaustive summary of the invention. It is not intended to identify key or essential parts of the invention, nor is it intended to limit the scope of the invention.

[0005] The technical solution of this invention:

[0006] A low-pressure turbine support ring structure for a gas turbine includes a support ring housing, a thermal expansion compensator, a power strut, a pin, a support housing, bolts, a bearing housing, a tapered component, a housing, a first outer cover, a second outer cover, an inner cover, a first wall, a flow guide, a gas supply pipe, an oil supply pipe, and an oil discharge pipe.

[0007] One end of the power strut is connected to the outer wall of the support ring housing via a thermal expansion compensator. The other end of the power strut is connected to the support housing via a pin inside the support ring housing. A bearing seat and a tapered component are installed below the support housing via bolts. One side of the housing is connected to the bearing seat, and the other side of the housing is connected to the rear support of the low-pressure turbine rotor. The support ring housing contains a first outer shell, a second outer shell, and an inner shell. The first and second outer shells are respectively located on the inner and outer sides of the power strut. The first outer shell is connected to the lower part of the support housing via a first wall. Multiple guide shields are provided between the first outer shell, the second outer shell, and the inner shell. The multiple guide shields are connected to the support housing via the inner shell. The air supply pipe and one of the guide shields together constitute the air supply structure of the support ring. The oil supply pipe and one of the guide shields together constitute the oil supply structure of the support ring. The oil discharge pipe and one of the guide shields together constitute the oil discharge structure of the support ring.

[0008] Preferably, a cavity is provided between the first outer shell and the second outer shell and the support ring shell, and the cavity is filled with heat-insulating fiber.

[0009] Preferably, it also includes a second wall, through which the tapered member is connected to the power turbine disk.

[0010] Preferably, the bearing housing establishes a contact seal with the rear support of the low-pressure turbine rotor through the third sealing cover and the first sealing cover, respectively, and the support housing establishes a contact seal with the rear support of the low-pressure turbine rotor through the second sealing cover.

[0011] Preferably, an air supply pipe is provided between the support ring housing and the bearing seat, and the air supply pipe is fixed in the bearing seat by a pin. The air supply structure of the support ring is connected to the inner cavity of the tapered part.

[0012] Preferably, the rear support of the low-pressure turbine rotor is a roller bearing, the outer ring of the roller bearing sleeve is provided with a damper, the adjusting ring and the outer ring of the roller bearing are clamped by a third sealing cover, and a graphite sealing ring is provided along the third sealing cover.

[0013] Preferably, the oil supply pipe is equipped with an oil filter.

[0014] Preferably, the lower part of the oil supply pipe is screwed into the bearing seat and sealed with a first sealing ring, the upper part of the oil supply pipe is fixedly connected to the support ring housing through a first flange, a second sealing ring is provided between the oil supply pipe and the first flange, the oil supply pipe is fixedly connected to the first flange through a first locking device, and left and right third sealing rings are provided between the oil supply pipe and the support ring housing.

[0015] Preferably, the oil drain pipe is screwed into the bearing housing, the joint between the oil drain pipe and the bearing housing is sealed with a gasket, the oil drain pipe is fixedly connected to the support ring housing through the second flange, a fourth sealing ring 33 is provided between the oil drain pipe and the second flange, and the oil drain pipe is fixedly connected to the second flange through the second locking device.

[0016] The present invention has the following beneficial effects:

[0017] 1. The present invention effectively reduces the thermal expansion of the outer casing, and at the same time provides several guide shields for supplying oil, draining oil and supplying air into the rotor;

[0018] 2. In order to reduce the thermal expansion of the support ring shell, the cavity between the outer shell and the outer cover shell of the present invention is filled with heat-insulating fiber;

[0019] 3. The first sealing cover, the second sealing cover, and the third sealing cover fixedly connected at the front end of the present invention form a support ring oil chamber and an air chamber, which are used to increase the contact seal of the rear support of the low-pressure turbine rotor and to supply air for cooling the power turbine shaft.

[0020] 4. The outer ring of the roller bearing with interference fit of the present invention is fitted with a damper to shift the critical speed of the rotor (rotor resonance vibration) to a lower value and eliminate rotor vibration energy;

[0021] 5. This invention provides a good match between the oil inlet and return structures, while also taking into account the design of the internal air cooling path. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of a low-pressure turbine support ring structure for a gas turbine according to the present invention;

[0023] Figure 2 This is a diagram showing the installation of the air guide cover with the air supply pipe, oil supply pipe and oil discharge pipe of the present invention;

[0024] Figure 3 This is a schematic diagram of the support ring air supply structure of the present invention;

[0025] Figure 4 This is a schematic diagram of the support ring oil supply structure of the present invention;

[0026] Figure 5 This is a schematic diagram of the support ring oil drainage structure of the present invention.

[0027] In the diagram: 1-Support ring housing, 2-Thermal expansion compensator, 3-Power strut, 4-Pin, 5-Support housing, 6-Bolt, 7-Bearing seat, 8-Conical part, 9-Housing, 10-Outer cover, 11-Outer cover, 12-Inner cover, 13-First wall, 14-Guide shield, 15-Air supply pipe, 16-Oil supply pipe, 17-Oil drain pipe, 18-Second wall, 19-First sealing gland, 20-Second sealing gland, 21-Third sealing gland, 22-Roller bearing, 23-Damper, 24-Adjusting ring, 25-Oil filter, 26-First sealing ring, 27-First flange, 28-Second sealing ring, 29-First locking device, 30-Third sealing ring, 31-Gasket, 32-Second flange, 33-Fourth sealing ring, 34-Second locking device. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0029] The connections mentioned in this invention are divided into fixed connections and detachable connections. Fixed connections, also known as non-detachable connections, include but are not limited to conventional fixed connection methods such as folded connections, riveted connections, adhesive connections, and welded connections. Detachable connections include but are not limited to conventional disassembly methods such as threaded connections, snap-fit ​​connections, pin connections, and hinged connections. When a specific connection method is not explicitly defined, it is assumed that at least one existing connection method can always be found to achieve the function, and those skilled in the art can choose according to their needs. For example, a welded connection can be chosen for fixed connections, and a hinged connection can be chosen for detachable connections.

[0030] Specific implementation method one: Combining Figures 1-5 This embodiment describes a low-pressure turbine support ring structure for a gas turbine, comprising a support ring housing 1, a thermal expansion compensator 2, a power strut 3, a pin 4, a support housing 5, a bolt 6, a bearing seat 7, a tapered component 8, a housing 9, a first outer cover 10, a second outer cover 11, an inner cover 12, a first wall 13, a flow guide 14, a gas supply pipe 15, an oil supply pipe 16, an oil discharge pipe 17, and a second wall 18.

[0031] One end of the power strut 3 is connected to the outer wall of the support ring housing 1 through the thermal expansion compensator 2. The other end of the power strut 3 is connected to the support housing 5 inside the support ring housing 1 through the pin 4. The bearing seat 7 and the tapered part 8 are respectively installed below the support housing 5 through the bolts 6. One side of the housing 9 is connected to the bearing seat 7, and the other side of the housing 9 is connected to the rear support of the low-pressure turbine rotor. The flow part in the support ring is organized by the first outer cover 10, the second outer cover 11, the inner cover 12 and the first wall 13. That is, the support ring housing 1 is provided with the first outer cover 10, the second outer cover 11 and the inner cover 12. The first outer cover 10 and the second outer cover 11 are respectively provided on the inner and outer sides of the power strut 3. The first outer cover 10 is connected to the lower part of the support housing 5 through the first wall 13. Multiple flow guides 14 are provided between the first outer cover 10, the second outer cover 11 and the inner cover 12. The multiple flow guides 14 are connected to the support housing 5 through the inner cover 12.

[0032] This embodiment provides an implementation with 9 air deflectors 14, such as... Figure 2 As shown, the air supply pipe 15, oil supply pipe 16, and oil discharge pipe 17 pass through three of the guide shields 14. The air supply pipe 15 and one of the guide shields 14 together form a support ring air supply structure; the oil supply pipe 16 and one of the guide shields 14 together form a support ring oil supply structure; and the oil discharge pipe 17 and one of the guide shields 14 together form a support ring oil discharge structure. To reduce the size of the chamber, the conical member 8 is connected to the power turbine disk through the second wall 18, that is, the upper end of the second wall 18 extends into and engages with the nozzle device of the power turbine disk.

[0033] A cavity is provided between the first outer shell 10 and the second outer shell 11 and the support ring shell 1, and the cavity is filled with heat-insulating fiber in order to reduce the thermal expansion of the support ring shell 1.

[0034] The bearing housing 7 establishes a contact seal with the rear support of the low-pressure turbine rotor through the third sealing cover 21 and the first sealing cover 19, respectively. The support housing 5 establishes a contact seal with the rear support of the low-pressure turbine rotor through the second sealing cover 20, forming a support ring oil chamber and an air chamber. This is used to increase the contact seal of the rear support of the low-pressure turbine rotor and to supply air for cooling the power turbine shaft. The air used for pressurizing the support ring oil chamber and cooling the power turbine shaft is introduced from the reducing joint through two pipes fixed on the flanges on the low-pressure turbine support ring housing 1.

[0035] An air supply pipe 15 is provided between the support ring housing 1 and the bearing seat 7. The air supply pipe 15 passes through the guide shroud 14 and is fixed in the bearing seat 7 by a pin. The air supply structure of the support ring is connected to the inner cavity of the conical part 8. That is, a part of the air is sent to the inner cavity of the conical part 8 through the cavity between the air supply pipes 15 to cool the power turbine shaft.

[0036] The rear support of the low-pressure turbine rotor is a roller bearing 22. The outer ring of the bearing sleeve of the roller bearing 22 with interference fit is provided with a damper 23. The adjusting ring 24 is used to adjust the oil flow through the damper 23. The adjusting ring 24 and the outer ring of the roller bearing 22 are clamped by a third sealing cover 21. A graphite sealing ring is provided along the third sealing cover 21 to separate the air chamber and oil chamber of the support ring.

[0037] The oil supply pipe 16, via the guide shield 14, is used to supply oil for lubrication and cooling of the roller bearing and to supply oil to the oil damper. An oil filter 25 is installed inside the oil supply pipe 16. The lower part of the oil supply pipe 16 is screwed into the bearing housing 7 and sealed with a first sealing ring 26. The upper part of the oil supply pipe 16 is fixedly connected to the support ring housing 1 via a first flange 27. A second sealing ring 28 is provided between the oil supply pipe 16 and the first flange 27. To prevent overturning, the oil supply pipe 16 is used to directly supply oil to the gap between the housing 9 and the damper 23. The oil supply pipe 16 is fixedly connected to the first flange 27 via a first locking device 29. Left and right third sealing rings 30 are provided between the oil supply pipe 16 and the housing 9 to achieve sealing in the raceway connection between the oil supply pipe 16 and the housing 9.

[0038] The oil drain pipe 17 is screwed into the bearing housing 7 after passing through the guide cover 14. Oil is drained from the support ring through the oil drain pipe 17. The joint between the oil drain pipe 17 and the bearing housing 7 is sealed with a gasket 31. At the outlet of the support ring, the oil drain pipe 17 is fixedly connected to the support ring housing 1 through the second flange 32. A fourth sealing ring 33 is provided between the oil drain pipe 17 and the second flange 32. To prevent overturning, the oil drain pipe 17 is fixedly connected to the second flange 32 through the second locking device 34.

[0039] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be permuted and combined. Those skilled in the art can exhaust all possibilities based on the mathematical knowledge of permutation and combination. Therefore, the present invention will not describe the technical solutions after permutation and combination one by one, but it should be understood that the technical solutions after permutation and combination have been disclosed by the present invention.

[0040] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A low-pressure turbine support ring structure for a gas turbine, characterized in that: It includes a support ring housing (1), a thermal expansion compensator (2), a power strut (3), a pin (4), a support housing (5), a bolt (6), a bearing seat (7), a tapered part (8), a housing (9), a first outer cover (10), a second outer cover (11), an inner cover (12), a first wall (13), a flow guide (14), an air supply pipe (15), an oil supply pipe (16), and an oil drain pipe (17); One end of the power strut (3) is connected to the outer wall of the support ring housing (1) through a thermal expansion compensator (2), and the other end of the power strut (3) is connected to the support housing (5) inside the support ring housing (1) through a pin (4). A bearing seat (7) and a tapered piece (8) are respectively installed below the support housing (5) through bolts (6). One side of the housing (9) is connected to the bearing seat (7), and the other side of the housing (9) is connected to the rear support of the low-pressure turbine rotor. The support ring housing (1) is provided with a first outer cover (10), a second outer cover (11), and an inner cover (12). The first outer cover (10) and the second outer cover (11) are respectively located on the inner and outer sides of the power strut (3). The first outer cover (10) is connected to the support through the first wall (13). A connection is established below the housing (5). Multiple guide shields (14) are provided between the first outer shell (10), the second outer shell (11), and the inner shell (12). The multiple guide shields (14) are connected to the support housing (5) through the inner shell (12). The air supply pipe (15) and one of the guide shields (14) together form a support ring air supply structure. The oil supply pipe (16) and one of the guide shields (14) together form a support ring oil supply structure. The oil discharge pipe (17) and one of the guide shields (14) together form a support ring oil discharge structure. The first sealing cover, the second sealing cover, and the third sealing cover, which are fixedly connected at the front end, form a support ring oil chamber and an air chamber, which are used to increase the contact seal of the rear support of the low-pressure turbine rotor and to supply air for cooling the power turbine shaft.

2. The gas turbine low-pressure turbine support ring structure according to claim 1, characterized in that: A cavity is provided between the first outer shell (10) and the second outer shell (11) and the support ring shell (1), and the cavity is filled with heat insulation fiber.

3. The gas turbine low-pressure turbine support ring structure according to claim 2, characterized in that: It also includes a second wall (18), through which the conical member (8) is connected to the power turbine disk.

4. The gas turbine low-pressure turbine support ring structure according to claim 3, characterized in that: The bearing housing (7) establishes a contact seal with the rear support of the low-pressure turbine rotor through the third sealing cover (21) and the first sealing cover (19), respectively, and the support housing (5) establishes a contact seal with the rear support of the low-pressure turbine rotor through the second sealing cover (20).

5. The gas turbine low-pressure turbine support ring structure according to claim 4, characterized in that: An air supply pipe (15) is provided between the support ring housing (1) and the bearing seat (7). The air supply pipe (15) is fixed in the bearing seat (7) by a pin. The air supply structure of the support ring is connected to the inner cavity of the conical part (8).

6. The gas turbine low-pressure turbine support ring structure according to claim 5, characterized in that: The rear support of the low-pressure turbine rotor is a roller bearing (22). The outer ring of the bearing sleeve of the roller bearing (22) is provided with a damper (23). The adjusting ring (24) and the outer ring of the roller bearing (22) are clamped by the third sealing cover (21). A graphite sealing ring is provided along the third sealing cover (21).

7. The gas turbine low-pressure turbine support ring structure according to claim 6, characterized in that: An oil filter (25) is installed inside the oil supply pipe (16).

8. The gas turbine low-pressure turbine support ring structure according to claim 7, characterized in that: The lower part of the oil supply pipe (16) is screwed into the bearing seat (7) and sealed with the first sealing ring (26). The upper part of the oil supply pipe (16) is fixedly connected to the support ring housing (1) through the first flange (27). A second sealing ring (28) is provided between the oil supply pipe (16) and the first flange (27). The oil supply pipe (16) is fixedly connected to the first flange (27) through the first locking device (29). Left and right third sealing rings (30) are provided between the oil supply pipe (16) and the housing (9).

9. The gas turbine low-pressure turbine support ring structure according to claim 7, characterized in that: The oil drain pipe (17) is screwed into the bearing housing (7). The joint between the oil drain pipe (17) and the bearing housing (7) is sealed with a gasket (31). The oil drain pipe (17) is fixedly connected to the support ring housing (1) through the second flange (32). A fourth sealing ring (33) is provided between the oil drain pipe (17) and the second flange (32). The oil drain pipe (17) is fixedly connected to the second flange (32) through the second locking device (34).

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