Patents by Inventor Huali YIN

Huali YIN has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Ventilation structure of core chamber of turbofan engine having large bypass ratio and ventilation method therefor
    Patent number: 12196134
    Abstract: A ventilation structure of a core chamber of a turbofan engine having a large bypass ratio, said structure comprising: an outer bypass wall surface (1), a core chamber wall surface (4) and a core casing (7). An outer bypass flow channel (2) is formed between the outer bypass wall surface (1) and the core chamber wall surface (4). A core chamber (6) is formed between the core chamber wall surface (4) and the core casing (7). An air intake annular cavity (3) is provided in the core casing and is located at the upstream position. The air intake annular cavity (3) is used to put the outer bypass flow channel (2) and the core chamber (6) in communication. An exhaust grille (5) is further provided on the core chamber wall surface (4) and is located at a tail position.
    Type: Grant
    Filed: April 22, 2022
    Date of Patent: January 14, 2025
    Assignee: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS
    Inventors: Yong Shan, Huali Yin, Hao Liu, Ming Deng, Qiang Zhao, Xiaoming Tan, Jingzhou Zhang
  • VENTILATION STRUCTURE OF CORE CHAMBER OF TURBOFAN ENGINE HAVING LARGE BYPASS RATIO AND VENTILATION METHOD THEREFOR
    Publication number: 20240328356
    Abstract: A ventilation structure of a core chamber of a turbofan engine having a large bypass ratio, said structure comprising: an outer bypass wall surface (1), a core chamber wall surface (4) and a core casing (7). An outer bypass flow channel (2) is formed between the outer bypass wall surface (1) and the core chamber wall surface (4). A core chamber (6) is formed between the core chamber wall surface (4) and the core casing (7). An air intake annular cavity (3) is provided in the core casing and is located at the upstream position. The air intake annular cavity (3) is used to put the outer bypass flow channel (2) and the core chamber (6) in communication. An exhaust grille (5) is further provided on the core chamber wall surface (4) and is located at a tail position.
    Type: Application
    Filed: April 22, 2022
    Publication date: October 3, 2024
    Applicant: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS
    Inventors: Yong SHAN, Huali YIN, Hao LIU, Ming Deng, Qiang ZHAO, Xiaoming TAN, Jingzhou ZHANG