AIP면 유동측정 정확도 향상을 위한 가스터빈엔진 입구덕트 설계 연구

다국어 초록 (Multilingual Abstract)

In this study, gas turbine engine inlet duct was designed to satisfy uniform flow at aerodynamic interface plane (AIP). Haack-series was selected as nose cone profile and duct outer radius(r<SUB>o</SUB>) was designed to satisfy to match with area change rate between the nose cone and outer duct wall by the 1-D sizing. The design object of the inlet duct wall profile which has the gradual area change rate was uniform Mach number in the core flow region and minimum boundary later thickness at the both inner nose wall and outer duct wall. The flow characteristics inside the inlet duct was evaluated using CFD. The static pressure distribution at the AIP showed uniform pattern within 0.16%. Based on Mach number profile, the boundary layer thickness was 2% of channel height. Kiel temperature rake location was decided less than 100 mm in front of nose cone where the Mach number is less than 0.1 in order to maximize the temperature probe recovery rate.

참고문헌 (Reference)

1 이보화, "입구덕트 공기유량 및 압력손실 예측방법" 한국추진공학회 14 (14): 48-55, 2010

2 Werner, F. D., "Total Temperature Probes" Flight 1961

3 Crowell Sr, G.A., "The Descriptive Geometry of Nose Cones"

4 Bobula, G. A., "Inlet Reynolds Number and Temperature Effects on the Steady-state Performance of a TFE731-2 Turbofan Engine"

5 Lee, K., "Inlet Distortion Test with Gas Turbine Engine in the Altitude Engine Test Facility" AIAA 2010

6 Lucas, J. R., "Effect of BLI-Type Inlet Distorsion on Turbofan Engine Performance" GT 2014

7 Huerta, J., "A Feasibility Study on Drag Reduction of a Cone at Low Speeds" 1971