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논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 정진택
- 발행연도
- 2018
- 저작권
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In this study, the effect of splitter vane placement on flow characteristics and performance characteristics for downsizing of a transonic centrifugal compressor was investigated through numerical analysis. A numerical investigation was performed on a centrifugal compressor with a 10% reduction in the diameter of the refer
ence model. A splitter vane was applied to anticipate the performance degradation of the reduced size model. To suppress the flow loss, which is the main loss in the diffuser passage. Three different position of splitter vane were investigated; 25%, 50%, and 75 % from pressure side of main vane in pitchwise direction. Flow field and performance evaluation analyzed based on design point. Also, performance curve was investigated through the off-design points. For computational model, 4:1 pressure ratio transonic centrifugal compressor. Commercial code ANSYS CFX 18.0 was used to solve 3D Reynolds Averaged Navier-Stokes equation(RANS). Computational domain is consisted of one impeller passage and two diffuser vane set. In order to preserve the boundary layer effect, Y plus was kept less than two. Stage(mixing-plane) interface model was used between rotating and stationary domains. The k-w Shear Stress Transport (SST) closure w
as selected as turbulence model which is the most efficient and accurate turbulence model in aerodynamic simulations of turbomachinery. The pressure recovery was improved in case of the splitter vane is adopted in
the middle of the diffuser passage, and the surge margin was increased by suppressing the flow separation at the wall surface. To reducing the size of transonic centrifugal compressor, splitter vane is applicable in middle of passage.
ence model. A splitter vane was applied to anticipate the performance degradation of the reduced size model. To suppress the flow loss, which is the main loss in the diffuser passage. Three different position of splitter vane were investigated; 25%, 50%, and 75 % from pressure side of main vane in pitchwise direction. Flow field and performance evaluation analyzed based on design point. Also, performance curve was investigated through the off-design points. For computational model, 4:1 pressure ratio transonic centrifugal compressor. Commercial code ANSYS CFX 18.0 was used to solve 3D Reynolds Averaged Navier-Stokes equation(RANS). Computational domain is consisted of one impeller passage and two diffuser vane set. In order to preserve the boundary layer effect, Y plus was kept less than two. Stage(mixing-plane) interface model was used between rotating and stationary domains. The k-w Shear Stress Transport (SST) closure w
as selected as turbulence model which is the most efficient and accurate turbulence model in aerodynamic simulations of turbomachinery. The pressure recovery was improved in case of the splitter vane is adopted in
the middle of the diffuser passage, and the surge margin was increased by suppressing the flow separation at the wall surface. To reducing the size of transonic centrifugal compressor, splitter vane is applicable in middle of passage.
목차
목 차 iiList of Figures ivList of Table viiiNomenclature ix제 1장 서 론 11. 1 연구 배경 11. 2 관련 연구 동향 51. 3 연구필요성 및 목적 8제 2장 수치해석 이론 및 방법 92. 1 수치해석 이론 92. 1. 1 지배방정식 92. 1. 2 이산화 방정식 112. 1. 3 난류 모델 132. 2 해석모델 152. 3 해석 방법 192. 3. 1 격자계 생성 192. 3. 2 해석 영역 및 경계조건 222. 3. 3 난류 모델 선정 24제 3장 해석결과 및 고찰 263. 1 해석 결과 검증 263. 1. 1 격자독립성 검토 263. 1. 2 해석 검증 283. 2 설계 운전조건에서의 유동 특성 분석 303. 2. 1 디퓨저 길이감소에 따른 고찰 303. 2. 2 스플리터 베인 위치에 따른 고찰 383. 3 성능특성 고찰 473. 3. 1 설계 운전조건에서의 성능 특성 고찰 473. 3. 2 성능 곡선 고찰 51제 4장 결 론 55참 고 문 헌 57
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