Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Off-design Performance Analysis based on Experimental Data of a Micro Gas Turbine Engine

실험데이터 기반 마이크로 가스터빈엔진 탈 설계점 성능해석

  • Kim, Seungjae (Aerospace Engineering Department, Chonbuk National University) ;
  • Choi, Seongman (Aerospace Engineering Department, Chonbuk National University) ;
  • Rhee, Dongho (Aeropropulsion Office, Korea Aerospace Research Institute)
  • Received : 2018.08.06
  • Accepted : 2018.10.13
  • Published : 2018.12.01
Download PDF
⟨ Previous Next ⟩

Abstract

It is essential to understand the characteristics of gas turbine components in order to carry out an off-design analysis of a gas turbine engine. In this study, a micro gas turbine engine test system was constructed to understand the performance characteristics of gas turbines. The temperature and pressure in the flow path of the micro gas turbine was collected by measuring the engine spool speed, and a compressor map was constructed by using the experimental data. The exhaust gas was collected at the turbine outlet and the combustion efficiency was calculated. An off-design performance analysis at ground static was performed using GasTurb software by applying the compressor map and combustion efficiency obtained from the experimental data. Futhermore, we compared and evaluated the analysis results with engine operating data.

가스터빈엔진의 탈설계점 운전 성능해석을 수행하기 위해서는 구성품의 성능 특성을 파악하는 것이 필수적이다. 본 연구에서는 가스터빈의 성능특성을 이해하기 위하여 마이크로 가스터빈엔진 성능시험 장치를 구축하였다. 구축된 마이크로 가스터빈 시험 장치를 이용하여 엔진의 회전수에 따른 유동장내의 온도와 압력 데이터를 수집하였으며, 수집된 실험 데이터를 이용하여 압축기 성능선도를 구성하였다. 터빈 출구부에서 배기가스를 포집하여 연소효율을 계산하였다. 구성된 압축기 성능선도와 연소효율을 GasTurb 성능해석 소프트웨어에 적용하여 지상 정지시의 탈설계점 성능해석을 수행하였고, 측정된 엔진성능데이터와 비교분석을 수행하였다.

Keywords

References

  1. Sellers, J.F. and Daniele, C.J., "DYNGEN-A Program for calculating Steady-state and Transient Performance of Turbojet and Turbofan Engines," NASA TN D-7901, 1975.
  2. Kim, S.J., Kim, D.H., Son, C.M., Kim, J.S., Kim, Y.I., Min, S.K., "A Comparative Study on Performance Map Generation Methods for an Axial Compressor of Gas Turbine Engine," Korean Society of Propulsion Engineers Fall Conference, Yeosu, Korea, pp. 440-445, Nov. 2012.
  3. Ronald J.S., "A Computer Code for Predicting Multistage Axial-Flow Compressor Performance by a Meanline Stage-Stacking Method," NASA Technical Paper 2020, 1982.
  4. Park, T.J., Yoon, S.H. and Baek, J.H., "Perfoemance Prediction Comparison of Multi-Stage Axial-Compressor by Stage-Stacking Method," Proceedings of the KFMA Annual Meeting, Daejeon, Korea, pp.143-148, Nov. 2001.
  5. Kurzke, J., "Model Based Gas Turbine Parameter Corrections," ASME Turbo Expo, Atlanta, Georgia, USA, GT2003-38234, Jun. 2003.
  6. Kurzke, J., "Modeling the Thrust Management of Commercial Airliners," International Symposium on Air Breathing Engine, Busan, Korea, ISABE-2013-1430, Sep. 2013.
  7. Kurzke, J., GasTurb 12-Design and Off-Design Performance of Gas Turbine, 2012.
  8. Klassen, H.A., Wood, J.R. and Schuman, L. F., "Experimental performance of a 16.10-centimeter tip diameter sweptback centrifugal compressor designed for a 6:1 pressure ratio," NASA TMX-3552, 1977.