Authors : Aleksandr I. Ermakov, Aleksandr O. Shklovets, Grigorii M. Popov and Daria A. Kolmakova
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.
Aleksandr I. Ermakov, Aleksandr O. Shklovets, Grigorii M. Popov and Daria A. Kolmakova, 2014. Investigation of the Effect of the Gas Turbine Compressor Supports on Gas Flow Circumferential Nonuniformity. Research Journal of Applied Sciences, 9: 684-690.