Abstract
AbstractThis paper addresses a fundamental design guideline for rotational components of a micro‐scale gas turbine engine considering an interaction between geometrical structure and aerodynamics. The rotational components of the micro‐scale gas turbine engine may be subjected to the centrifugal stress due to high‐speed rotation. The efficiency of each component is strongly controlled by geometrical clearance between rotational and stationary components, and heat transfer from the turbine to the compressor. Therefore, the elastic deformations due to the centrifugal stress and heat transfer have important role to determine the practical aerodynamic performance of the rotational components. A new sophisticated geometrical structure was introduced to the rotational components to control the elastic deformation and maintain the compressor efficiency that is necessary to hold the minimum requirement for the thermodynamic cycle.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
