The influence of blade profile shape of inlet guide vane on performance map of centrifugal compressor stage

• Main Authors: V. V. Karabanova, A. D. Vanyashov, V. L. Yusha
• Format: Article
• Language: English
• Published: Omsk State Technical University, Federal State Budgetary Educational Institution of Higher Education 2020-12-01
• Series: Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение"
• Subjects: centrifugal compressor stage; inlet guide vane; performance map; angles of attack; transonic flow; computational fluid dynamics
• Online Access: https://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2020/%D0%A2.%204,%20%E2%84%96%204%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/41-48%20%D0%9A%D0%B0%D1%80%D0%B0%D0%B1%D0%B0%D0%BD%D0%BE%D0%B2%D0%B0%20%D0%92.%20%D0%92.,%20%D0%92%D0%B0%D0%BD%D1%8F%D1%88%D0%BE%D0%B2%20%D0%90.%20%D0%94.,%20%D0%AE%D1%88%D0%B0%20%D0%92.%20%D0%9B..pdf

The object of the study is a centrifugal compressor stage with an inlet guide vane. The performance map of the stage are investigated in the modes of combined regulation by changing the rotor speed and changing the swirl of the flow in front of the impeller by turning the blades of the inlet guide vane. Two variants of the design of the profile of the blades of the inlet guide vane are considered and the method of turning the blades by performance map. As a result of the study, it is found that a profile with a fixed inlet part at large swept angles has a lower loss coefficient, which contributes to an increase in the efficiency of the stage. The effect of regulation to achieve the set point in terms of pressure and flow for the re-profile stage is achieved at lower speeds