Development of Test Stand for High Temperature Abradability Test of Ceramic Coating for Turbine Shroud

Cheulwoo Baek; Junyoung Ko; Siwoo Lee

doi:10.6108/KSPE.2024.28.5.069

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2024 Vol.28, Issue 5 Preview Page Next Page

TECHNICAL PAPERS

Development of Test Stand for High Temperature Abradability Test of Ceramic Coating for Turbine Shroud 터빈 슈라우드 마모성 세라믹코팅 고온 내마찰 시험장치 개발

31 October 2024. pp. 69-77

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Abstract

A test stand for checking the abradability of an abradable ceramic coating applied to control the gap sealing between the turbine shroud and blade tip of the high-pressure turbine shroud at TIT 1,800K class gas turbine engine was designed and manufactured. A blade tip speed was simulated up to 450 m/s by using a 120kW drive motor, and a combustion-type gas burner was applied to expose the surface temperature of the test specimen to approximately 1,100℃. The ceramic-coated specimen was mounted on the specimen holder, and the incursion rate and depth were controlled by the specimen position driving system according to the test conditions. The DAS system was developed to communicate with the control panel to control the drive motor, specimen position, etc., and has the function of measuring and storing temperature/vibration/speed/force/gap.

Keywords

Gas Turbine Engine

TIT

Gap Sealing Control

Abradable Ceramic Coating

Abradability Test

터빈입구온도(TIT, Turbine Inlet Temperature) 1,800 K급 가스터빈 엔진 개발과 관련하여 고압터빈부의 터빈 슈라우드와 블레이드 사이의 간극 제어를 위해 적용되는 마모성 세라믹코팅의 내마찰 특성을 확인하기 위한 시험 장치를 설계 및 제작하였다. 120 kW급 구동모터를 통해 로터디스크를 회전시켜 최대 450 m/s에 해당하는 블레이드 팁 속도를 모사하였으며, 연소식 가스버너를 적용하여 시험 시편의 표면 온도가 약 1,100℃에 노출되도록 하였다. 세라믹코팅 시편은 시편홀더부에 장착되어 시편 위치 구동시스템에 의해 침입속도(Incursion rate)와 깊이(Incursion depth)를 시험조건에 맞게 제어할 수 있도록 하였으며, DAS 시스템은 제어 패널과 통신하여 구동 모터, 시편위치 등을 제어하고 온도/진동/속도/힘/간극을 측정 및 저장할 수 있도록 개발하였다.

키워드

가스터빈엔진

터빈입구온도

간극제어

마모성 세라믹코팅

내마찰 시험

References

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Bakan, E., Mack, D.E., Mauer, G., Vaßen, R., Lamon, J. and Padture, N.P., "High- temperature materials for power generation in gas turbines," In Advanced Ceramics for Energy Conversion and Storage, Elsevier, pp. 3-62. 2020.

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Metco, S., "Improve efficiency and re duce emissions with high pressure turbine abradable coatings for industrial gas turbines," Solution Flash, SF0015.1, pp. 1-8, 2014.

Chupp, R.E., Hendricks, R.C., Lattime, S.B., and Steinetz, B.M., "Sealing in turbomachinery," Journal of Propulsion and Power, Vol. 22, No. 2, pp. 313-349, 2006.

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NASA/TM-2011-216986, Mach 0.3 Burner Rig Facility at the NASA Glenn Materials Research Laboratory.

Information

Publisher :The Korean Society of Propulsion Engineers
Publisher(Ko) :한국추진공학회
Journal Title :Journal of the Korean Society of Propulsion Engineers
Journal Title(Ko) :한국추진공학회지
Volume : 28
No :5
Pages :69-77
Received Date : 2024-06-11
Revised Date : 2024-08-19
Accepted Date : 2024-08-26
DOI :https://doi.org/10.6108/KSPE.2024.28.5.069

Journal of the Korean Society of Propulsion Engineers ISSN:1226-6027(Print) 2288-4548(Online) 한국추진공학회지

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