Development of a Thermal Shock Resistance Evaluation Device for Coatings in Aviation

Keekeun Kim; Chungryeol Lee; Cheulwoo Baek; Myungho Kim; Jinhyung Kim; Seunghee Kim; Siwoo Lee

doi:10.6108/KSPE.2026.30.1.014

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2026 Vol.30, Issue 1 Preview Page Next Page

RESEARCH PAPERS

Development of a Thermal Shock Resistance Evaluation Device for Coatings in Aviation 항공용 열차폐코팅 내구수명 평가를 위한 열충격 시험장치의 개발

28 February 2026. pp. 14-21

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Abstract

In this study, a test device was developed to evaluate the thermal shock resistance performance of thermal barrier coatings, which are being developed for application in aviation engines. To simulate the combustion conditions of an aviation engine, compressed air and aviation fuel were burned to generate a high-temperature jet flow, which was used to heat the front surface of the thermal barrier coating. At the same time, cooling air was injected onto the rear surface to create a thermal gradient in the test specimen. The developed device was capable of generating a jet flow with a mass flow rate of 32 g/s, a temperature of 1200°C, and a velocity of 300 m/s, demonstrating high operational reliability within a temperature deviation of 10°C. Through thermal shock testing on the developed combustion and turbine coatings, the test device was verified to be suitable for evaluating long-term durability as well.

Keywords

Thermal Barrier Coating

Thermal Shock Test

Burner Rig

Thermal Cyclic Test

본 연구에서는 항공 엔진 적용을 목표로 개발되고 있는 열차폐코팅에 대하여 열충격 저항성능을 평가하고자 시험장치를 개발하였다. 항공 엔진의 연소조건을 모사하기 위해 압축공기와 항공유를 연소하여 고온의 제트 유동을 형성하였고, 제트 유동을 통해 열차폐코팅의 전면을 가열하는 동시에 후면에 냉각공기를 분사하여 시험편에 열구배를 부가할 수 있도록 시험 시스템을 구축하였다. 개발장치는 약 유량 32 g/s, 온도 1200℃, 유속 300 m/s의 제트 유동을 형성할 수 있었으며, 오차 10℃ 이내 높은 운용신뢰도를 보였다. 개발 연소기 및 터빈용 코팅에 대한 열충격 시험 결과 각각 500 회 시험 후 건전성이 확인됨에 따라 시험장치 또한 장기간 내구수명 평가가 가능함이 검증되었다.

키워드

열차폐코팅

열충격 시험

버너리그

열주기 시험

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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 : 30
No :1
Pages :14-21
Received Date : 2025-06-10
Revised Date : 2025-10-15
Accepted Date : 2025-11-27
DOI :https://doi.org/10.6108/KSPE.2026.30.1.014

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

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