Oil film damper of gas turbine

Abstract

An oil film damper of a gas turbine comprises a supporting casing, the flange end of the supporting casing is fixedly connected with a stator casing of the gas turbine, a bearing used for supporting a rotor is installed in the cantilever end of the supporting casing, a supporting sleeve is arranged on the outer side of the supporting casing, and a sealing ring used for controlling end oil drainage is arranged between the cantilever end of the supporting casing and the supporting sleeve. A group of oil supply ports are formed in the cantilever end of the supporting casing, an oil outlet hole for supplying oil to a bearing and a throttling hole penetrating through the supporting casing are formed in the tail end of each oil supply port, another group of oil supply ports are formed in the cantilever end of the supporting casing, and an oil outlet hole for supplying oil to the bearing and a throttling hole penetrating through the supporting casing are formed in the tail end of each oil supply port; the oil film circulates in a closed space formed by the supporting casing, the supporting sleeve and the sealing rings on the two sides, the structure is simple, maintenance is convenient, and the service life is long.

Description

Technical Field

[0001] The utility model relates to the field of gas turbines, and particularly to an oil film damper for a gas turbine. Background Art

[0002] The squeeze film damper is a new technology developed in the 1960s. Due to its remarkable vibration reduction effect, simple structure, small occupied space, and relatively easy manufacturing, it has received high attention in the 1980s and was first applied to aeroengines. Currently, it has become a typical design for reducing the vibration of ships and industrial gas turbines, improving stability, and extending service life.

[0003] The existing oil film damper of a gas turbine usually sets a special elastic ring between the support casing and the support sleeve. The oil film circulates between the support casing, the support sleeve, and the elastic ring bracket to achieve the purpose of the oil film absorbing the vibration energy of the rotor. This mechanism is relatively complex, not only inconvenient for maintenance, but also has a short service life of the oil film damper, affecting the normal use of the gas turbine. Summary of the Utility Model

[0004] Aiming at the above deficiencies of the existing technology, the utility model provides an oil film damper for a gas turbine, in which the oil film circulates between the support casing and the support sleeve, with a simple structure, convenient for maintenance, and a long service life.

[0005] The purpose of the utility model is realized through the following technical solutions:

[0006] An oil film damper for a gas turbine includes a support casing. The flange end of the support casing is fixedly connected to the stator casing of the gas turbine. A bearing for supporting the rotor is installed inside the cantilever end of the support casing. A support sleeve is arranged outside the support casing. A sealing ring for controlling end oil leakage is arranged between the cantilever end of the support casing and the support sleeve. A group of oil supply ports are arranged inside the cantilever end of the support casing. An oil outlet hole for supplying oil to the bearing and a throttle hole passing through the support casing are arranged at the end of each oil supply port.

[0007] A through hole is formed in the middle of the support casing, and a group of waist-shaped grooves penetrating the support casing are uniformly arranged on one side of the through hole.

[0008] A stepped hole is arranged near the cantilever end of the support casing. A counterbore is arranged outside the stepped hole, and a bearing hole is arranged outside the counterbore. A bearing for supporting the rotor is installed in the bearing hole.

[0009] A group of oil supply ports are uniformly arranged outside the stepped hole. An oil outlet hole for supplying oil to the bearing and a throttle hole penetrating the support casing are arranged at one end of each oil supply port close to the bearing. A group of throttle holes are communicated through an oil groove arranged on the cylindrical surface of the support casing.

[0010] Sealing grooves are respectively arranged on both sides of the oil groove, and a sealing ring is respectively arranged in each sealing groove.

[0011] Beneficial effects: A group of oil supply ports are provided inside the cantilever end of the support casing. An oil outlet hole for supplying oil to the bearing and a throttle hole passing through the support casing are provided at the end of each oil supply port. A group of throttle holes are connected to the oil groove, and the oil film circulates in the closed space formed by the support casing, the support sleeve and the sealing rings on both sides. The structure is simple, easy to maintain and has a long service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 The utility model is a schematic diagram of the cross-sectional structure of the oil film damper of the gas turbine.

[0013] Figure 2 This is a schematic diagram of the supporting casing structure described in the utility model.

[0014] Figure 3 It is a schematic diagram of the cross-sectional structure of the support casing described in the utility model.

[0015] Figure 4 This is a schematic diagram of the support sleeve structure described in the utility model.

[0016] Figure 5 This is a schematic diagram of the lubricating oil flow structure described in the utility model. DETAILED DESCRIPTION

[0017] The utility model is further described in detail below according to the accompanying drawings and embodiments:

[0018] refer to Figures 1 to 4 The device includes a support casing 110, the flange end of which is connected and fixed to the stator casing of the gas turbine. A through hole 115 is provided in the middle of the support casing 110, and a group of waist grooves 111 penetrating the support casing 110 are evenly provided on one side of the through hole 115, so that the support casing 110 moves radially when subjected to force, thereby reducing the bending vibration generated when the rotor moves.

[0019] refer to Figure 2 , 3 A step hole 116 is provided near the cantilever end of the through hole 115, a countersunk hole 119 is provided outside the step hole 116, a bearing hole 121 is provided outside the countersunk hole 119, and a bearing 140 for supporting the rotor is installed in the bearing hole 121.

[0020] refer to Figure 2 , 3, a group of oil supply ports 117 are evenly arranged outside the stepped hole 116. An oil outlet hole 118 for supplying oil to the bearing 140 is arranged at one end of each oil supply port 117 close to the bearing to ensure the lubrication of the bearing 140. A throttling hole 113 penetrating the support casing 110 is arranged on one side of the oil outlet hole 118. A group of throttling holes 113 are communicated through an oil groove 112 arranged on the cylindrical surface of the support casing 110. Sealing grooves 114 are respectively arranged on both sides of the oil groove 112, and a sealing ring 130 is arranged in each sealing groove 114.

[0021] Reference Figure 5 , when the lubricating oil enters the support casing 110 through the oil supply port 117, a part of the lubricating oil is distributed to the bearing 140 through the oil outlet hole 118 to play a lubricating role, and another part of the lubricating oil enters the oil groove 112 through the throttling hole 113 above. The oil in the oil groove 112 enters the closed space formed by the support casing 110, the support sleeve 120, and the sealing ring 130. Under the action of extrusion, the lubricating oil moves in both the left and right directions respectively. The oil forms an oil film in the closed space formed by the support casing 110, the support sleeve 120, and the sealing ring 130. This oil film can absorb the transmitted vibration and make the whole system more stable. The support casing is designed with a pre-eccentric structure. After installation, affected by the gravity, the eccentricity will become the center line, making the whole damper more stable.

[0022] A group of oil supply ports 117 are arranged inside the cantilever end of the support casing 110. An oil outlet hole 118 for supplying oil to the bearing 140 and a throttling hole 113 passing through the support casing 110 are arranged at the end of each oil supply port 117. A group of throttling holes 113 are communicated with the oil groove 112. The oil film circulates in the closed space formed by the support casing 110, the support sleeve 120, and the sealing rings 130 on both sides. The structure is simple, easy to maintain, and has a long service life.

Claims

1. An oil film damper for a gas turbine, characterized in that : It includes a support casing (110). The flange end of the support casing (110) is fixedly connected to the stator casing of a gas turbine. A bearing (140) for supporting the rotor is installed inside the cantilever end of the support casing (110). A support sleeve (120) is provided outside the support casing (110). A sealing ring (130) for controlling end oil leakage is provided between the cantilever end of the support casing (110) and the support sleeve (120). A group of oil supply ports (117) are provided inside the cantilever end of the support casing (110). An oil outlet hole (118) for supplying oil to the bearing (140) and a throttling hole (113) passing through the support casing (110) are provided at the end of each oil supply port (117).

2. The oil film damper of a gas turbine according to claim 1, characterized in that : A through hole (115) is provided in the middle of the support casing (110). A group of waist slots (111) penetrating the support casing (110) are evenly provided on one side of the through hole (115).

3. The oil film damper of a gas turbine according to claim 1, characterized in that : A stepped hole (116) is provided near the cantilever end of the support casing (110). A counterbore (119) is provided outside the stepped hole (116). A bearing hole (121) is provided outside the counterbore (119). A bearing (140) for supporting the rotor is installed in the bearing hole (121).

4. The oil film damper of a gas turbine according to claim 3, characterized in that : A group of oil supply ports (117) are evenly provided outside the stepped hole (116). An oil outlet hole (118) for supplying oil to the bearing (140) and a throttling hole (113) penetrating the support casing (110) are provided at one end of each oil supply port (117) close to the bearing. A group of throttling holes (113) are communicated through an oil groove (112) provided on the cylindrical surface of the support casing (110).

5. The oil film damper of a gas turbine according to claim 4, characterized in that : Sealing grooves (114) are respectively provided on both sides of the oil groove (112). A sealing ring (130) is respectively provided in each sealing groove (114).

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