천음속 축류 압축기의 블레이드 H2C 변형이 공력 성능 및 구조적 건전성에 미치는 영향 (Effect of Blade H2C Deformation on Aerodynamic Performance and Structural Integrity of Transonic Axial Compressor)

서지정보

· 발행기관 : 한국유체기계학회
· 수록지 정보 : 한국유체기계학회 논문집 / 27권 / 6호 / 62 ~ 71페이지
· 저자명 : 김수빈, 강현수, 김윤제

초록

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.

영어초록

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.

참고자료

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