한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제48권3호
  • /
  • Pages.207-215
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  • 2020
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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소형 초음속 연소시험 장치를 위한 형상 천이 노즐 설계

Design of a Shape Transition Nozzle for Lab-scale Supersonic Combustion Experimental Equipment

  • Sung, Bu-Kyeng (Department of Aerospace Engineering, Pusan National University) ;
  • Hwang, Won-Sub (Department of Aerospace Engineering, Pusan National University) ;
  • Choi, Jeong-Yeol (Department of Aerospace Engineering, Pusan National University)
  • 투고 : 2019.10.14
  • 심사 : 2020.02.22
  • 발행 : 2020.03.01
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초록

소형 초음속 연소시험 장치 구축의 일부로서 형상 천이 노즐 설계 연구를 수행하였다. 원형의 연소식 공기가열기에 정사각형 단면의 초음속 연소기를 연결하기 위하여 MOC 설계기법을 이용하여 초음속 형상 천이 노즐의 면적변화를 산출하였다. 천이율을 조절하기 위하여 형상 천이 함수를 도입하였다. 3차원 전산유체 해석을 통한 경계층 보정과 함께 몇 가지 형상 천이 함수의 영향을 살펴보았다. 본 연구의 형상 천이 노즐에서는 일반적인 사각단면 노즐에서 모서리에 발생하는 압력구배에 의한 재순환영역과 이에 의한 노즐 벽 중심부의 경계층 발달이 비교적 작게 나타남을 확인하였다.

Design of a shape transition nozzle is carried out as a part of building a lab-scale supersonic combustion experimental equipment. In order to connect directly the circular shaped vitiation air heater to the square shaped scramjet combustor, area change is evaluated by using the method of characteristics. Shape transition function is introduced to control the transition rate. Boundary layer correction was made through the three-dimensional computational fluid dynamics with the assessment on the several shape transition functions. The shape transition nozzle is proved minimizing the growth of boundary layer at the center of the rectangular nozzle surfaces that caused by the pressure gradient at the corners of the rectangular nozzle and the following recirculation regions.

키워드

참고문헌

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