VESTNIK of Samara University. Aerospace and Mechanical EngineeringVESTNIK of Samara University. Aerospace and Mechanical Engineering2542-04532541-7533Samara National Research University258410.18287/1998-6629-2014-0-5-4(47)-158-165UnknownCalculation of exciting aerodynamic load on a gas turbine engine compressor blade induced by the effect of a non-uniform gas flowErmakovA. I.<p>Doctor of Science (Engineering), Professor</p>fdla@ssau.ruShklovetsA. O.<p>Associate research fellow of sectoral research laboratory "Vibration resistance and reliability of aeronautical products"</p>ssau_shklovets@mail.ruFedorchenkoD. G.<p>Candidate of Science (Engineering)</p>
<p>Chief designer</p>dgfedorchenko@yandex.ruSamara State Aerospace UniversityJoint-Stock Company «Metallist-Samara»23122014135-41581652207201522072015Copyright © 2015, VESTNIK of the Samara State Aerospace University2015<p>Work is devoted to the creation of a design procedure of the exciting loads occurring on the impeller blades of GTE in situations of uneven circumferential gas load. The presence in the path of the engine bluff bodies, such racks engine mounts, causing substantial circumferential flow unevenness. Consequently, in blades having dangerous resonant vibrations that can lead to product failure. Determination of amplitude of the excited harmonics in the design phase will assess the severity of forced oscillations of the blades. The technique of determining the excitation of harmonics in the flow allows the calculation of the amplitude, to determine the impact of structural changes in the running of the engine on them. The finite element model consists of the inlet guide vane, rotor blades and bearing racks. Gas dynamic load is determined in units of rotor blades, but a small number of blades, eg for fan impellers, the accuracy of the excitation amplitudes of harmonics may be insufficient. Using the capabilities of Ansys CFX, gas-dynamic load is defined in additional areas path between the rotor blades. In work changing amplitudes of harmonics based on the number of measurement points of load.</p>Gas turbine enginebladeguide vanecircumferential variationforced oscillationsharmonic waveAnsysCFXГазотурбинный двигательрабочая лопатканаправляющий аппаратокружная неравномерностьвынужденные колебаниявозбуждающая гармоникаAnsysCFX[1. Ivanov V.P. Kolebaniya rabochikh koles turbomashin [Fluctuations impellers of turbomachiner]. Moscow: Mashinostroenie Publ., 1983. 224 p.][2. Aksenov A.P. Matematicheskiy analiz (ryady Fur'e): uchebnoe posobie [Mathematical analysis (Fourier series)]. SPb.: Nestor Publ., 1999. 85 p.][3. Inozemtsev А.А., Nihamkin M.A., Sandratskiy V.L. Osnovy konstruirovaniya aviatsionnykh dvigateley i energeticheskikh ustanovok: uchebnik dlya VUZov. [Basics of designing aircraft engines and power plants. V. 5]. Moscow: Mashinostroenie Publ., 2008. 198 p.][4. Shklovets A.O., Popov G.M., Kolmakova D.A. Optimization of the compressor stage blading of gas turbine engine to ensure the dynamic strength in rotor blade row // Vestnik dvigatelestroeniya. 2013. No. 2. P. 192-197. (In Russ.)]