Research Journal of Applied Sciences
ISSN: Online 1993-6079ISSN: Print 1815-932x
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Investigation of the Effect of the Gas Turbine Compressor Supports on Gas Flow Circumferential Nonuniformity
Aleksandr I. Ermakov, Aleksandr O. Shklovets, Grigorii M. Popov and Daria A. Kolmakova
Page: 684-690 | Received 21 Sep 2022, Published online: 21 Sep 2022
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Abstract
This study discusses the possibility to reduce the non-uniformity of the circumferential gas flow forcing on the blades of the rotor wheel of a gas turbine engine stage. Circumferential non-uniformity is caused by the availability of the middle support behind the compressor stage. This results in higher resonant stresses in the rotor blades which are made with anti-vibration blade shrouds. In order to exclude the antivibration blade shrouds it is necessary to reduce circumferential non-uniformity of gas flow that would lead to falling of the amplitude of the exciting harmonics. In the Software Package Numeca Fine Turbo there was developed a full-circle model of the compressor flow passage with middle support which allows to determine the distribution of the gas load on the working blade row and to investigate the effect of the supports on the amplitudes of exciting harmonics. Variation in the width and number of supports has led to a 2 fold reduction in the most dangerous harmonics.
How to cite this article:
Aleksandr I. Ermakov, Aleksandr O. Shklovets, Grigorii M. Popov and Daria A. Kolmakova. Investigation of the Effect of the Gas Turbine Compressor Supports on Gas Flow Circumferential Nonuniformity.
DOI: https://doi.org/10.36478/rjasci.2014.684.690
URL: https://www.makhillpublications.co/view-article/1815-932x/rjasci.2014.684.690