지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 발행연도
- 2024.12
- 수록면
- 62 - 71 (10page)
- DOI
- 10.5293/kfma.2024.27.6.062
이용수
초록· 키워드
오류제보하기
Generally, compressor blade shapes are categorized into hot blades and cold blades. A hot blade refers to a shape that has deformed under external loads during operation, while a cold blade refers to a shape designed without any loads. This distinction between the hot and cold blade shapes significantly influences aerodynamic performance. Therefore, accurate performance evaluation requires using the hot blade shape that corresponds to the specific operating conditions. To achieve this, it is necessary to derive a cold blade shape and convert this shape into the corresponding hot blade shape for a given operating condition. This process is known as the hot-to-cold (H2C) method. The H2C method employs a displacement-based inverse analysis to derive the cold blade shape from the initial hot blade shape. In this study, the cold blade shape was derived using the H2C method on NASA rotor 37, a transonic axial compressor. Subsequently, the hot blade shape for the specified operating conditions was derived from the cold blade shape. In this study, the aerodynamic performance of the initial hot blade shape and the hot blade shape was compared under operating conditions, and the structural integrity of the cold blade shape was evaluated under operating conditions. As a result of the study, it was found that the aerodynamic performance of the hot blade shape under operating conditions was improved compared to the initial hot blade shape. In addition, it was confirmed that as the rotational speed increased, the cold blade became more structurally vulnerable, and there was a possibility of resonance in higher-order mode.
목차
ABSTRACT
1. 서론
2. 수치해석
3. 결과 및 고찰
4. 결론
References
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