1,000마력급 터보샤프트엔진 역류형 환형 연소기 성능시험평가 연구 = Research on Performance Test of Reverse Flow Annular Combustor of 1,000 shp-Class Turboshaft Engine

국문 초록 (Abstract)

본 논문은 한국항공우주연구원과 한화에어로스페이스에서 수행하고 있는 1,000 마력급 터보샤프트엔진 개발과제에 활용될 역류형 환형 연소기 성능시험평가에 관한 내용이다. 연소기 개발과정은 노즐 버너시험, 섹터 연소기 성능시험, 환형 연소기 성능시험순으로 진행되었다. 연소기는 분무 성능이 뛰어난 공기 충돌 연료노즐과 유출냉각 방식이 적용된 라이너를 국내 최초로 사용하였다. 연소기 구성품의 성능시험 통해 엔진 개발 요구성능 목표 항목인 연소효율, 압력손실, Pattern Factor, Profile Factor의 성능 조건을 모두 만족함을 확인하였다.

다국어 초록 (Multilingual Abstract)

This paper presents research on the performance test evaluation of the reverse flow annular combustor used in the 1,000 shp(shaft horsepower)-class turboshaft engine development project conducted by the Korea Aerospace Research Institute and Hanwha Aerospace. The combustor development process was conducted in the order of fuel nozzle burner test, sector combustor performance test, and annular combustor performance test. An Air-blast fuel nozzle and a combustor liner with the Effusion Cooling method are used in gas turbine engines for the first time in Korea. Through the performance test of the combustor, the combustion test results demonstrated that all requirements for combustor performance, including maximum exit temperature, combustion efficiency, pattern factor, and profile factor, were met. The final shape of the combustor was derived.

참고문헌 (Reference)

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