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Investigation of effects of multistage compressor final stage blading shape on compressor performance and flow pattern
- Authors: Popov G.M.1, Krivcov A.V.1, Kolmakova DA.1
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Affiliations:
- Samara State Aerospace University
- Issue: Vol 11, No 5-1 (2012): Special Issue
- Pages: 184-190
- Section: CONFERENCE MATERIALS
- URL: https://journals.ssau.ru/vestnik/article/view/1863
- DOI: https://doi.org/10.18287/2541-7533-2012-0-5-1(36)-184-190
- ID: 1863
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Abstract
The influence of rotor blades with anti-vibration shroud and Shvarov's profile compared to conventional blades on compressor efficiency is investigated. The variation of compressor efficiency is quantitatively evaluated at 4 operation modes.
About the authors
G. M. Popov
Samara State Aerospace University
Author for correspondence.
Email: grishatty@mail.ru
Engineer
Russian FederationA. V. Krivcov
Samara State Aerospace University
Email: a200009@rambler.ru
Magistrand
Russian FederationD A. Kolmakova
Samara State Aerospace University
Email: kolmakova.daria@gmail.com
Magistrand
Russian FederationReferences
- Шкловец, А.О. Расчет вынужденных колебаний лопаток рабочего колеса компрессора авиационного газотурбинного двигателя, возникающих от действия окружной неоднородности газового потока [Текст] / А.О. Шкловец, Г.М. Попов, Д.А. Колмакова // Известия Самарского научного центра Российской академии наук. - Том 14, №1(2). – 2012. - С.517-520.
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