Detailed Information
Cited 0 time in 
Cited 0 time in 
Cited 0 time in
Metadata Downloads
항공기용 가스터빈 엔진의 고압터빈에서 열유동 특성해석을 위한 전산해석기법 연구A Study on the Numerical Analysis Methodology for Thermal and Flow Characteristics of High Pressure Turbine in Aircraft Gas Turbine Engine
- Other Titles
- A Study on the Numerical Analysis Methodology for Thermal and Flow Characteristics of High Pressure Turbine in Aircraft Gas Turbine Engine
- Issue Date
- Nov-2013
- Publisher
- 한국유체기계학회
- Keywords
- High pressure turbine(고압터빈); Aerodynamic characteristic(공력특성); Computational fluid dynamics(전산유체역학); Numerical analysis(수치해석)
- Citation
- 한국유체기계학회 논문집, pp 116 - 116
- Pages
- 1
- Indexed
- DOMESTIC
- Journal Title
- 한국유체기계학회 논문집
- Start Page
- 116
- End Page
- 116
- ISSN
- 2287-9706
- Abstract
- In order to investigate thermal and flow characteristics of high pressure turbine, the numerical analysis methodology was set up using the k-ω based SST turbulent model with transition scheme. To validate the numerical methodology, C3X vane was selected. The surface pressure was not influenced by the viscous work term and transition models. However the surface temperature was affected by the viscous work term and transition models. We recommend γ transition model with viscous work term.
- Files in This Item
- Go to Link
- Appears in
Collections - 서울 공과대학 > 서울 기계공학부 > 1. Journal Articles
Items in ScholarWorks are protected by copyright, with all rights reserved, unless otherwise indicated.