Rim sealing structure capable of inhibiting non-uniform multi-scale gas invasion

A sealed structure, multi-scale technology, applied to the supporting elements of the blade, machine/engine, stator, etc., can solve problems such as weakening performance improvement, fuel consumption increase, and overall machine efficiency reduction.

Pending Publication Date: 2021-03-02
BEIJING UNIV OF CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Gas turbines usually extract excess cold air from the side of the compressor to “charge” the turbine disc cavity to prevent gas intrusion. The amount of cooling air extracted from the compressor by advanced gas turbines currently in use has exceeded 18% of the inlet f

Method used

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  • Rim sealing structure capable of inhibiting non-uniform multi-scale gas invasion
  • Rim sealing structure capable of inhibiting non-uniform multi-scale gas invasion

Examples

Experimental program
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Effect test

Embodiment Construction

[0026] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0027] to combine Figure 1~2 , the gear ring 2 in the static rotating chamber is installed on the turbine static disk or the stator blade guard ring 1, the inner gear ring baffle 3 is installed on the gear ring 2 in the rotating static chamber at a certain angle, the inner gear ring baffle and the rotating The installation angle of the gear ring in the static volume chamber is α. The cold air intake hole 4 of the vane guard ring is located at the outlet of the internal cooling channel of the guide vane, and the cold air intake hole 4 of the vane guard ring is connected with the side jet hole 5 of the wheel rim. The end wall 6 of the trailing edge of the turbine guide vane, the gear ring 2 in the rotating static chamber and the inner gear ring baffle 3 form an approximately closed "quiet" system housing chamber 10, and the gear ring 2 in the rotating static chamb...

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Abstract

The invention discloses a rim sealing structure capable of inhibiting non-uniform multi-scale gas invasion. The structure comprises a high-pressure turbine guide vane end wall, a rotating static containing cavity inner gear ring, an inner gear ring baffle and a rim lateral jet hole. According to the rim sealing structure, the flow resistance of gas invasion flow is increased through a combined gap, a rotating static disc cavity is divided through the rotating static containing cavity inner gear ring, then high-temperature invasion gas is limited at a high-radius position, and the circumstancethat a wheel disc is ablated due to the fact that the high-temperature invasion gas goes deep into a disc center is avoided. A static-static system containing cavity is constructed through the inner gear ring baffle so as to reduce the tangential speed ratio of the invasion flow, the high-temperature and high-speed invasion flow is buffered, and the sealing efficiency is improved. In addition, therim lateral jet hole forms high-pressure cold air outflow, so that the sealing efficiency is improved, thermal stress distribution of the inner gear ring and the inner gear ring baffle is improved, the thermal operation deformation of a turbine disc is reduced, rubbing of a rotating static component is avoided, and the reliability of the sealing structure is improved.

Description

technical field [0001] The invention relates to a wheel rim sealing structure capable of suppressing non-uniform multi-scale gas intrusion, which is applied to a rotating static disc cavity inside a turbine rotor of a gas turbine and a wheel rim of a turbine wheel, and belongs to the technical field of gas turbine sealing. Background technique [0002] When the internal pressure of the turbine rotor-stationary disk cavity is lower than the mainstream pressure, the mainstream high-temperature gas will enter the turbine disk cavity to form gas intrusion. Due to the limitation of the material, structure and cooling method of the turbine disk, once the high-temperature gas invades the disk cavity, it will quickly ablate the surface of the disk without cooling gas protection, causing the temperature gradient between the rim and the inner diameter to increase sharply, resulting in thermal stress exceeding the disk. Design stress reserve, causing harmful deformation or even wheel b...

Claims

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Application Information

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IPC IPC(8): F01D11/08F01D9/02F01D9/06F01D5/14
CPCF01D11/08F01D9/02F01D9/065F01D5/147
Inventor 贾兴运何立东闫伟王健王胜利
Owner BEIJING UNIV OF CHEM TECH
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