다단 소형 터빈에서의 부분분사 특성에 관한 연구

국문 초록 (Abstract)

본 연구에 적용된 터빈은 반경류형이며, 동익의 외경은 108 ㎜이다. 터빈은 1.4-4.1%의 낮은 부분분사율에서 작동하므로 익형은 축류형으로 설계되었으며 3단으로 구성되었다. 터빈에서 부분분사율과 팁간극 및 노즐유동각의 변화에 따른 성능의 변화를 측정하였다. 또한 터빈의 단수를 변경하면서 각 단수에서 발생되는 출력의 차이에 대한 측정이 이루어졌다. 본 연구의 터빈은 다양한 작동조건에서 운전되므로 넓은 작동범위에 따른 비교를 위하여 회전수를 변경하면서 탈설계 영역에서의 성능 평가가 이루어졌다. 뿐만 아니라 다양한 작동조건에 합당한 시스템의 평가를 위하여 총비오크가 얻어졌다. 아울러 소형터빈의 설계 및 성능예측을 위하여 유동해석을 수행하였으며 얻어진 예측의 결과는 실험으로 얻어진 결과와 잘 일치하였다.

다국어 초록 (Multilingual Abstract)

In this study, a radial inflow type turbine was applied and the outer diameter of the turbine rotor was 108 mm. The turbine blade on a circular plate disc was designed as an axial-type because its partial admission rate was 1.4-4.1%. The turbine consisted of three stages. The performance test has been conducted with various admission rates, tip clearances and nozzle flow angles. The turbine output power was measured on each stage. The turbine performance was obtained in a wide rotational speed range in order to compare its performance according to various operating conditions. The net specific output torque was also measured to compare its overall performance. Computational analysis was conducted for predicting turbine performance. The computed results were in good agreement with the experimental results.

목차 (Table of Contents)

• ABSTRACT
• 초록
• Ⅰ. 서론
• Ⅱ. 실험장치
• Ⅲ. 결과 및 토의
• Ⅳ. 결론
• 후기
• 참고문헌

참고문헌 (Reference)

1 조종현, "부분분사에서 작동하는 소형터빈에서 두 번째 단의 효과에 관한 연구" 한국항공우주학회 36 (36): 898-906, 2008

2 "version 11"

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