Investigation of effects of multistage compressor final stage blading shape on compressor performance and flow pattern

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 Federation

A. V. Krivcov

Samara State Aerospace University

Email: a200009@rambler.ru

Magistrand

Russian Federation

D A. Kolmakova

Samara State Aerospace University

Email: kolmakova.daria@gmail.com

Magistrand

Russian Federation

References

  1. 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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