VESTNIK of Samara University. Aerospace and Mechanical EngineeringVESTNIK of Samara University. Aerospace and Mechanical Engineering2542-04532541-7533Samara National Research University249010.18287/1998-6629-2014-0-5-1(47)-132-138UnknownAssessing reduction gear mass in the problem of optimizing parameters of the working process of a turboprop engine at the initial design stageGrigoryevV. A.<p>Doctor of Science (Engineering)</p>
<p>Professor of the Aircraft Engines Theory Department</p>va_grig@ssau.ruZagrebelnyiA. O.<p>Engineer Education and Research Center of Gas Dynamics Studies</p>zao_sam156@mail.ruProkaevA. S.<p>Engineer Aircraft Engines Theory Department</p>prok.alexey@mail.ruKuznetsovS. P.<p>Candidate of Science (Engineering), Professor</p>
<p><br />Deputy General Designer</p>saturn@npo-saturn.ruSamara State Aerospace UniversityScience-and-Production Association “Saturn”20122014135-11321381806201518062015Copyright © 2015, VESTNIK of the Samara State Aerospace University2015<p>The paper analyzes mathematical models of the mass of the reduction gear as part of a turboprop enginepower plant in the problem of optimizing the parameters of the working process of the gas turbine engine at theinitial design stage. The necessity of optimal matching of the main parameters of the power plant and the aircraftbased on their system performance criteria is the main feature of the initial design of turboprop engines. To solvethe problem of optimizing the parameters of the engine work process, under certain design constraints, it is importantto know the take-off weight of the aircraft in the formation of which the weight of the power plant with aturboprop engine is one of important components that actually determine the coordination of the aircraft andengine parameters. The mass of the reduction gear of a turboprop engine makes up a significant part of the powerplant mass. The existing models of the mass of the power plant with a turboprop engine do not separate theweight of the gear from the weight of the power plant. Thereby, the reduction gear weight is erroneously associatedwith gear parameters used in the model of the mass of the engine. This does not include theobvious dependence of the gear mass on the transmitted power which is closely linked to the distribution of the free energy of the turboprop engine.</p>Reduction gearmassmathematical modelparametersРедуктормассаматематическая модельпараметры[1. Grigoriev V.A., Zrelov V.A., Ignatkin Yu.M. et. al. Vertoletnye gazoturbinnye dvigateli [Helicopter gas turbine engines] / edited by V.A. Grigoriev, B.A. Ponomarev. Moscow: Mashinostroyeniye Publ., 2007. 491 p.][2. Maslov V.G., Kuz'michev V.S., Kovartsev A.N., Grigoriev V.A. Teoriya I metody nachal'nykh etapov proektirovaniya aviatsionnykh GTD [Theory and methods of the initial stages of aircraft GTE design]. Samara: Samara State Aerospace University Publ., 1996. 147 p.][3. Dvigateli 1944-2000: Aviatsionnye, raketnye, morskie, nazemnye [Engines 1944-2000: Аircraft, rocket, marine, ground-based / ed. by I.G. Shustov]. Moscow: AKSKonversalt Publ., 2000. 434 p.]