Patents by Inventor Seungyeong CHOI

Seungyeong CHOI 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).

  • Patent number: 12043379
    Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.
    Type: Grant
    Filed: October 4, 2021
    Date of Patent: July 23, 2024
    Assignee: UIF (UNIVERSITY INDUSTRY FOUNDATION), YONSEI UNIVERSITY
    Inventors: Hyung Hee Cho, Seungyeong Choi, Jihyuk Kim, Juyeong Nam, Maroosol Yun, Taedoo Yoon, Minho Bang, Joon-soo Lim
  • Patent number: 11788418
    Abstract: Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique. In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.
    Type: Grant
    Filed: May 12, 2022
    Date of Patent: October 17, 2023
    Assignee: Industry-Academic Cooperation Foundation, Yonsei University
    Inventors: Hyung Hee Cho, Ho Seop Song, Minho Bang, Heeseung Park, Taehyun Kim, Seungyeong Choi, Jeong Ju Kim
  • Patent number: 11746661
    Abstract: A turbine blade having cooling holes formed therein and a turbine including the same are provided. The turbine blade includes an airfoil having a leading edge and a trailing edge formed thereon and a cooling passage defined for flow of a cooling fluid therethrough, and a cooling hole configured to communicate between the cooling passage and outside in the airfoil and having an inlet and an outlet, wherein the cooling hole includes an expanded portion and a grooved portion formed in the outlet, the grooved portion being recessed from the expanded portion toward the trailing edge.
    Type: Grant
    Filed: June 22, 2022
    Date of Patent: September 5, 2023
    Inventors: Ye Jee Kim, Hyung Hee Cho, Minjoo Hyun, Hee Seung Park, Seungyeong Choi, Taehyun Kim
  • Patent number: 11655716
    Abstract: A cooling structure for a trailing edge of a turbine blade is provided. The cooling structure for the trailing edge of the turbine blade comprising an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge, and a cavity channel formed in the blade part and through which a cooling fluid flows, the cooling structure including slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains, wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot, and wherein the cooling fluid is introduced through a micro-channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface.
    Type: Grant
    Filed: July 21, 2021
    Date of Patent: May 23, 2023
    Assignee: DOOSAN ENERBILITY CO., LTD.
    Inventors: Chang Yong Lee, Hyung Hee Cho, JeongJu Kim, Seungyeong Choi, Hee Seung Park
  • Publication number: 20230016532
    Abstract: Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique. In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.
    Type: Application
    Filed: May 12, 2022
    Publication date: January 19, 2023
    Inventors: Hyung Hee Cho, Ho Seop Song, Minho Bang, Heeseung Park, Taehyun Kim, Seungyeong Choi, Jeong Ju Kim
  • Publication number: 20220412217
    Abstract: A turbine blade having cooling holes formed therein and a turbine including the same are provided. The turbine blade includes an airfoil having a leading edge and a trailing edge formed thereon and a cooling passage defined for flow of a cooling fluid therethrough, and a cooling hole configured to communicate between the cooling passage and outside in the airfoil and having an inlet and an outlet, wherein the cooling hole includes an expanded portion and a grooved portion formed in the outlet, the grooved portion being recessed from the expanded portion toward the trailing edge.
    Type: Application
    Filed: June 22, 2022
    Publication date: December 29, 2022
    Inventors: Ye Jee KIM, Hyung Hee Cho, Minjoo Hyun, Hee Seung Park, Seungyeong Choi, Taehyun Kim
  • Publication number: 20220127964
    Abstract: A cooling structure for a trailing edge of a turbine blade is provided. The cooling structure for the trailing edge of the turbine blade comprising an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge, and a cavity channel formed in the blade part and through which a cooling fluid flows, the cooling structure including slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains, wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot, and wherein the cooling fluid is introduced through a micro-channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface.
    Type: Application
    Filed: July 21, 2021
    Publication date: April 28, 2022
    Inventors: Chang Yong LEE, Hyung Hee Cho, Jeong Ju Kim, Seungyeong Choi, Hee Seung Park
  • Publication number: 20220106035
    Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.
    Type: Application
    Filed: October 4, 2021
    Publication date: April 7, 2022
    Inventors: Hyung Hee CHO, Seungyeong CHOI, Jihyuk KIM, Juyeong NAM, Maroosol YUN, Taedoo YOON, Minho BANG, Joon-soo LIM