대한기계학회:학술대회논문집 (Proceedings of the KSME Conference)
- 대한기계학회 2002년도 학술대회지
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- Pages.603-606
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- 2002
항공기 가스터빈 엔진의 터빈 날개의 역설계
Inverse design of Aircraft Engine Turbine Blades.
초록
Numerical analysis and its inverse design process of 2nd stage of JT8D aircraft engine is described. One of the most important factors that affect the performante of turbomachine is secondary flow in the blade passage, so that the performance of turbomachine can be improved by controlling secondary flow. In this paper, as a method to control secondary flow, commercial inverse design program, TurboDesign is used. Meridional derivative of angular momentum is selected as a parameter to control blade leading in this program, To validate inverse designed model, computational analysis is applied which includes rotor-stator-interaction. In this paper, CFB results of both original and inverse designed model are compared to examine how much the performance improves without reduction of work output.