Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Study on the High Pressure Combustion Performance Characteristics of the 1st Row Pintle Injector using LOx-Kerosene as Propellant

LOx와 Kerosene을 추진제로 하는 1열 핀틀 분사기의 고압 연소성능 특성에 관한 연구

  • Kang, Donghyuk (Combustion Chamber Team, Rocket Engine Development Office, Korea Aerospace Research Institute) ;
  • Kim, Jonggyu (Combustion Chamber Team, Rocket Engine Development Office, Korea Aerospace Research Institute) ;
  • Ryu, Chulsung (Combustion Chamber Team, Rocket Engine Development Office, Korea Aerospace Research Institute) ;
  • Ko, Youngsung (School of Aerospace Engineering, Chungnam National University)
  • 강동혁 (한국항공우주연구원 엔진개발부 연소기팀) ;
  • 김종규 (한국항공우주연구원 엔진개발부 연소기팀) ;
  • 유철성 (한국항공우주연구원 엔진개발부 연소기팀) ;
  • 고영성 (충남대학교 항공우주공학과)
  • Received : 2022.05.04
  • Accepted : 2022.09.06
  • Published : 2022.10.31
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Abstract

The pintle injector has many advantages in the key characteristics of a liquid rocket engine, such as combustion stability, combustion efficiency, and wide range of comprehensive thrust control, design and manufacture, and test fired under supercritical conditions. The pintle injector is manufactured with a rectangular, single-row orifice for thrust control and production considerations. In order to verify the combustion performance of the pintle injector and its potential as a commercial injector, the combustion characteristics were analyzed by varying the TMR (Total Momentum Ratio) and BF (Blockage Factor). The result of the hot firing test showed that the heat flux increased as TMR increased, and it confirmed that the characteristic velocity efficiency was more affected by BF than TMR. Suppose a single-row pintle injector with efficiency characteristics insensitive to changes in TMR can achieve high efficiency at low fuel differential pressure conditions. In that case, the variable pintle injector's design flexibility can be increase.

액체로켓엔진의 중요한 특성인 연소 안정성, 연소효율 및 넓은 범위의 추력 조절 등에서 장점이 많은 핀틀 분사기를 설계 및 제작하여 초임계 조건에서 연소시험을 수행하였다. 핀틀 분사기는 추력 제어 및 제작성을 고려하여 직사각형의 1열 형상의 오리피스를 갖는 핀틀 분사기로 제작하였다. 핀틀 분사기의 연소성능 및 상용 분사기로써의 가능성을 검증하기 위해 TMR(Total Momentum Ratio)과 BF(Blockage Factor)를 변화하여 연소 특성을 분석하였다. 연소시험 결과 열유속은 TMR 증가에 따라 증가하는 경향이 나타났으며, 특성속도 효율은 TMR보다 BF에 영향을 받는 것으로 확인되었다. 따라서 TMR 변화에 둔감한 효율 특성을 갖는 1열 핀틀 분사기는 낮은 연료 차압 조건에서 높은 효율을 달성할 수 있다면, 가변 핀틀 분사기 설계 유연성이 높아질 수 있다.

Keywords

Acknowledgement

본 연구는 한국항공우주연구원 주요사업 시드과제(과제번호 FR21P24)로 수행되었습니다.

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