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Gas turbine disk cavity sealing structure

A technology of sealing structure and gas turbine, which is applied in the direction of gas turbine devices, mechanical equipment, engine components, etc., can solve the problems of easy wear, poor sealing, complex structure, etc., and achieve the effect of ensuring sealing effect, reducing damage and simplifying structure

Active Publication Date: 2021-12-31
HANGZHOU TURBINE POWER GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at various problems such as complex structure, easy wear, and poor sealing performance of the gas turbine disk cavity sealing structure in the prior art, it is necessary to find a gas turbine disk cavity sealing structure that makes the structure simple and easy to operate while ensuring the sealing performance , while achieving the purpose of avoiding structural wear and reducing costs

Method used

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  • Gas turbine disk cavity sealing structure
  • Gas turbine disk cavity sealing structure
  • Gas turbine disk cavity sealing structure

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Embodiment 1

[0034] figure 1 Is a schematic view of the prior art sealing structure, comprising a vane, an interstage seal ring 3, the honeycomb seal 6, the seal teeth 12, the disk seal extending wings 13, the sealing plate 8, the wheel 9, a seal 10 and monodentate extending an outer end of the wheel 14; wherein the monodentate seal tooth as a single seal assembly.

[0035] Honeycomb seals seal between the ring 6 is located 3-stage lower surface; seal extending seal teeth 13 located on the disk surface of the wing. Further, the roulette wheel 9 forming an outer seal extending outwardly extended end 13. Seal ring 3, with the inter-stage seal ring is formed between an air supply chamber 2 the sealing plate 8 and the stage vanes. Monodentate sealing ring seals 10 positioned on the stage 3, the outer end of the wheel 14 with projecting sealing.

[0036] Wheel 9, the sealing plate 8, an interstage seal ring 3 and the inner vane shroud outwardly extending end of the upstream movement plate chamber ...

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Abstract

The invention provides a turbine disc cavity sealing structure of a gas turbine, which relates to the technical field of gas turbines. Disc seal protruding wing (13), vane inner shroud (24), stator vane inner shroud outer extension end (15), vent hole (16), spring member (17), T-shaped slot (18), shaft To the limit bolt (20) and the axial limit groove (21), the vent hole (16) is located inside the outer extension end (15) of the inner shroud of the stator vane, and passes through the outer extension end of the inner shroud of the stator blade ( 15). The sealing structure of the present invention is simple and easy to operate, can avoid the wear of the honeycomb seal, further reduces the cost, and simultaneously simplifies the circulation path of the sealing air and increases the safety of operation.

Description

Technical field [0001] The present invention relates to the field of gas turbine technology, particularly relates to a gas turbine turbine disk cavity seal structure. Background technique [0002] In the gas turbine, the rotor disk higher working temperature, if not control of its temperature, its high temperature will lead to a decrease in strength, thereby affecting the safe operation of the unit. After the usual practice to introduce cooling air to the cooling wheel, the cooling air from the air supply chamber gas generally peripheral band at the vanes, the vanes gas flows through the internal passageway into the enclosure between the seal band and the inner stage stator blade ring consisting of air inlet chamber, and finally through the upper, downstream of the seal teeth respectively on the downstream side wheel is cooled, finally, the cooled gas movement through disc space into the mainstream will play a movement of the sealing gap Yan, to prevent intrusion of hot gas chamb...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/28F01D9/02F01D11/00
CPCF02C7/28F01D9/02F01D11/00F01D11/003
Inventor 蓝吉兵张发生张伟赵旭洋李柳明赵鸿琛隋永枫辛小鹏
Owner HANGZHOU TURBINE POWER GRP
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