A gas turbine structure with a blade tip brush seal

By introducing a blade tip brush seal structure into the gas turbine, the angle and distance of the brush filaments can be adjusted in real time, solving the problem that the blade tip clearance cannot be restored after the graphite coating wears out. This improves the operating efficiency and reliability of the gas turbine and reduces maintenance costs.

CN224550192UActive Publication Date: 2026-07-24CHINA UNITED GAS TURBINE TECH CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
CHINA UNITED GAS TURBINE TECH CO LTD
Filing Date
2025-06-30
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

After the graphite coating of existing gas turbines wears down, the blade tip clearance cannot be restored, leading to blade tip clearance leakage, which affects compressor efficiency and stability margin, and makes it impossible to adjust the blade clearance.

Method used

It adopts a blade tip brush seal structure, including an annular rotor, a brush bristle adjustment section and a brush seal section. The angle of the brush seal section and the blade tip distance can be adjusted in real time through the viewing adjustment hole. Stainless steel, nickel-chromium alloy or carbon fiber brush bristles are used instead of hard graphite coating.

Benefits of technology

It significantly reduces tip leakage, improves compressor operating efficiency and stability margin, extends component lifespan, enhances equipment reliability and adaptability, and reduces maintenance costs.

✦ Generated by Eureka AI based on patent content.

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    Figure CN224550192U_ABST
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Abstract

The utility model discloses a kind of gas turbine structures with brush sealing of blade tip, including blade (5) and outer cylinder (6), it is characterized by further including annular rotor (1), brush filament adjusting part (2), brush sealing part (3) and peep adjusting hole (4), the annular rotor (1) is located in the inner side surface of the outer cylinder (6), the peep adjusting hole (4) is through in the outer cylinder (6), the brush filament adjusting part (2) is located on the annular rotor (1), the brush sealing part (3) is located on the brush filament adjusting part (2), the utility model can adjust the angle and blade tip distance of brush sealing part in real time, significantly reduce blade tip leakage, which not only improves the efficiency and stability margin when compressor operates, but also enhances the overall operating efficiency of gas turbine.
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