The manufacturing method and technical realization elements of the cage bar's turbine inter-stage support

Technical realization elements:

6. The purpose of the present invention is to address the shortcomings of the prior art and provide a cage-shaped inter-stage support for turbines. The cage-type elastic support structure is integrated into the load-bearing inner ring, and the load-bearing inner ring is a cage bar. The structure can achieve the critical speed reduction and vibration reduction requirements of the engine rotor without the need for separate elastic support, and reduce the thermal stress of the support between the turbine stages, and reduce the heat conduction of high-temperature gas to the bearing seat and the bearing.

7. According to one aspect of the present invention, there is provided a turbine interstage support with cage bars, comprising a bearing outer ring, a bearing support plate and a bearing inner ring, the bearing outer ring and the bearing inner ring There is a turbine gas flow passage. One end of the bearing support plate is fixed to the bearing outer ring, and the other end of the bearing bearing plate is fixed to the bearing inner ring. The bearing inner ring includes an inner ring mounting edge and a cage bar. The inner ring mounting side is fixedly connected to the bearing seat, the bearing seat is centered and matched with the turbine rotor bearing, one end of the cage-type sleeve is fixedly connected to the inner ring mounting side, and the cage The axial section of the structure composed of the cylindrical sleeve and the inner edge plate is U-shaped. The cage strip sleeve is provided with a plurality of cage strips and supporting parts for fixing the two ends of the cage strip. The cage strips are circumferentially distributed on the turbine The rotor is used for elastic support between turbine stages.

8. According to a preferred embodiment of the present invention, the load-bearing outer ring includes an outer ring mounting edge, a connecting sleeve and an outer edge plate, one end of the connecting sleeve is arc-shaped and excessively connected to the outer side of the tail of the outer edge plate, and the connection The other end of the sleeve is fixedly connected to the outer ring mounting edge, which is fixedly connected to the outer casing or the mounting section of the engine, and the outer ring is indirectly connected through the connecting sleeve.

The ring mounting edge and the outer edge plate can effectively reduce the overall thermal stress of the load-bearing outer ring.

9. According to a preferred embodiment of the present invention, the inner edge plate and the outer edge plate are the inner and outer boundaries of the turbine gas flow channel, respectively.

10. According to a preferred embodiment of the present invention, the axis of the connecting sleeve is consistent with the axis of the turbine rotor, which is beneficial to the stability of the overall structure of the outer ring.

11. According to the preferred embodiment of the present invention, the radial cross section of the cage bar is circular, elliptical or rectangular. The cage bar structure with a smaller cross-sectional area can directly reduce the heat conduction of the gas to the bearing seat and the bearing, and is rigid. The smaller structure also has less thermal stress when resisting thermal deformation, which in turn significantly increases the overall life and safety of the turbine inter-stage support, the bearing seat and the bearing.

12. According to a preferred embodiment of the present invention, the chamfer radius r at the connection between the cage bar and the supporting part is 3-10mm.

13. According to a preferred embodiment of the present invention, the length l of the cage bar is 60

100mm, number n is 16

20, the cross-sectional width b and height h are 310mm and 24mm.

14. According to a preferred embodiment of the present invention, the bearing support plate is in the shape of a cylinder, an elliptic cylinder or a blade, and the bearing support plate directly passes through the turbine gas flow channel in the radial direction, and can only provide a transmission rotor mechanism. The function of force can also have the blade profile at the same time, which can bear the function of accelerating and deflecting the gas of the guide in the flow channel, with good rigidity and high strength.

15. According to a preferred embodiment of the present invention, the load bearing support plate can be solid or hollow. The hollow support plate can be directly ventilated or ventilated for cooling or lubricating the bearing, or in the hollow support plate. The inner tube is continued to be sleeved in the hollow support plate for ventilation or oil.

16. According to a preferred embodiment of the present invention, the number of the bearing support plate is 4

There are 24, the load-bearing support plates are divided into large support plates and small support plates, and the number of small support plates is more than that of the large support plates.

17. Compared with the prior art, the beneficial effects of the present invention are:

18.1. Integrate the cage-type elastic support structure into the load-bearing inner ring. This structure can simultaneously meet the needs of bearing capacity of the turbine stage support, controlling the critical speed of the rotor and damping vibration, reducing the number of parts, facilitating assembly and reducing costs.

19.2 The cage-type sleeve matches the flexibility required by the engine rotor to subtract the independent elastic support assembled in the bearing seat assembly and simplify the structure. The cage-type bearing inner ring can reduce the flow channel hot gas from the inner ring to the bearing seat. And the heat transfer of the bearing, reduce the thermal stress of the bearing inner ring, lower the working temperature of the bearing, and improve the life and safety of the support between the turbine stages and the bearing.

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