Approach to control of low-emission aeroengine combustor on artificial intelligence base is presented. The neural network as model of artificial intelligence is used. The main problem of neural network designing for smart controllers, particularly on first stage, is availability of identical object mathematical expert-model, that is need for neural network training. The on-board aeroengine models is widely used in the modern control and monitoring systems now. However the low emission combustor is essentially more unlinear and stochastic object and working out of the object model is very complicated task. Moreover the NOx emission is the parameter of great importance the same as thrust or engine life.

In the paper conception of the model is presented. The mathematical model is based on Zeldovich mechanism equation. The model special feature is assumption about superposition of diffusion and technically premixed flames. The model take space and time air-fuel concentration ununiformity in consideration, using probability density function (PDF). The PDF forms are determined by sum of harmonical signal (thermo-acoustical waves influence) and gaussian noise for technically premixed flame and only gaussian distribution for diffusion flame.

The model data (PDF etc.) are based on 4D combustor mathematical model numerical simulation and experimental
results.

Keywords: low emission combustor, control, artificial intelligence, mathematical model.

Valery G. Avgustinovich (Perm, Russian Federation) – Doctor of Technical Science, Professor, Department of Aircraft Engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: august.valery@yandex.ru).

Tatyana A. Kuznetsova (Perm, Russian Federation) – CSc in Technical Sciences, Associate Professor, Department of Design and Technologies in Electronics, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: tatianaakuznetsova@gmail.com).

Almir I. Fatykov (Perm, Russian Federation) – PhD student, Department of Aircraft Engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: fatykov-ai@avid.ru).

Aleksey D. Nugumanov (Perm, Russian Federation) – PhD Student, Departament of Aviation Engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: nugumanov@avid.ru).

1. Kutsenko, YU. G. Metodologiya proyektirovaniya maloemissionnykh kamer sgoraniya GTD na osnove matematicheskikh modeley fiziko-khimicheskikh protsessov [Methodology for design of low-emission combustion chambers GTE based on mathematical models of physicochemical processes]. Doctor dissertation, Perm, PSTU, 2010. (In Russian).
2. Avgustinovich V.G., Kutsenko Y.G. Creation and Application of Combined Calculation Methodo­logy for Low Emission Combastion Chamber. Russian Aeronautics, 2011, v.54, #2, p.170-178.
3. Bhagwan R., Wollgarten J.C., Habisreuther P., Zarzalis N. Experimental Investigation on Lean Blow Out of Piloted Aero-Engine Burner. Proc. ASME Conf. Turbo Expo GT2014-25199, Dusseldorf, 2014, 9 pp.
4. Lauer M., Farber J., Reith F., Masalme J.E. Model Based Prediction of Off-Design Operation Condition NOx Emission from DLE Gas Turbine Combustors. Proc. ASME Conf. Turbo Expo GT2017-63063, Charlotte, NC, USA, 2017, 11pp.
5. Vanderhaegen E., Deneve M. Predictive Emissions Monitoring Using a Continuously Updating Neural Network. Proc. ASME Conf. Turbo Expo GT2010-22899, Glasgow, 2010, 7 pp.
6. Lamont W.G., Roa M., Lucht R. Application of Artificial Neural Networks for the Prediction of Pollutant Emissions and Outlet Temperature in Fuel Staged Gas Turbine Combustion Rig. Proc. ASME Conf. Turbo Expo GT2014-25030, Dusseldorf, 2014, 10 pp.
7. V. G. Avgustinovich, A. V. Trusin, S. A. Shalamov S.V. Metodika postroyeniya konechno-elementnoy setochnoy modeli na primere kamery sgoraniya gazoturbinnogo dvigatelya [Method for constructing a finite element grid model using the example of a combustion chamber of a gas turbine engine]. Perm, PNRPU Aerospace Engineering Bulletin, 2013, no. 35, 18 p. (In Russian).
8. Belokon A., Khirtov K., Klyachko L., Tschepin S., Zakharov V. Prediction of Combustion Efficiency and N_Ox Level for Diffusion Flame Combustors in HAT Cycles. Proc. ASME Conf. Turbo Expo GT2002-30609, Amsterdam, 2002, 9 pp.
9. Nazukin V., Avgustinovich V. CFD Analysis of Swirling Flows in Premixers. Proc. ASME Conf. Turbo Expo GT2014-25785, Dusseldorf, 2014, 10 pp.
10. Campa G. Juniper M. Obtaining Bifurcation Diagrams with a Thermoacoustical Network Model. Proc. ASME Conf.Turbo Expo GT2012-68241, Copenhagen, 2012, 11 pp.
11. Campa G., Cademartori R. Influence of Nonlinear Flame Models on Thermoacoustic Instabilities in Combustion Chambers. Proc. ASME Conf. Turbo Expo GT2016-57129, Seoul, 2016, 11 pp.
12. Hummel T., Berger F., Hertweck M., Schuermans B. High-Frequency Thermoacoustic Modulation Mechanisms in Swirl-Stabilized Gas Turbine Combustors. Part Two: Modeling and Analysis. Proc. ASME Conf. Turbo Expo GT2016-57500, Seoul, 2016, 13 pp.
13. Gotoda H., Hayashi K., Tsujimoto R., Domeo S., Tachibama S. Dynamic Properties of Combustion Instability in a Laboratory-Scale Gas Turbine Model Combustor. Proc. ASME Conf. Turbo Expo GT2016-58170, Seoul, 2016, 8 pp.
14. Saurabh A., Moeck J. Swirl Flame Response to Simultaneous Axial and Transverse Velocity
    Fluctuations. Proc. ASME Conf. Turbo Expo GT2016-57428, Seoul, 2016, 9 pp.
15. Blumner R., Paschereit C.O., Oberleithner K., Cosic B. Experimental Analysis of High-Amplitude Temporal Equivalence Ratio Oscillations in the Mixing Section of a Swirl-Stabilized Burner. Proc. ASME Conf. Turbo Expo GT2016-56585, Seoul, 2016, 10 pp.
16. Hong Z., Haynes J., Herbon J., McManus K. Dynamic Suppresion in Liquid-Fueled Combustors Using Fuel Modulation. Proc. ASME Conf. Turbo Expo GT2012-69703, Copenhagen, 2012, 10 pp.
17. Kuznetsova T.A., Avgustinovich V.G. Voprosy teorii i praktiki razrabotki robastnykh sistem upravleniya aviatsionnymi dvigatelyami na baze vstroyennykh matematicheskikh modeley [Problems of Designing Aero-Engine Robust Control on Base On-Board Engine Model]. Perm: PNRPU, 2018, 265 p.

The calculations of efficiency of suboxide AlO interaction with particles surface during combustion of aluminum powder ASD-1 air-suspension are executed. Estimation of influence of coefficients of AlO molecules impingement efficiency (accommodation coefficients) with metal particles surface free from oxide – a_E31 and with oxizidated surface – a_E32 on burn-out parameters is implemented. Dependencies of relative burn-out length on a_E32 и a_E31 are constructed. Relative burn-out length is ratio of length which corresponds to burning-out of 90% metal particles mass at given a_E32 to length which corresponds to zero value of a_E32. Investigations are implemented for 0,0001£a_E31£1 and 0,0001£a_E32£1 with taking into account of nonequilibrium thermodynamics of burning processes. Processes of AlO molecules interaction with free and oxizidated surface are established to result in increase of prescribed completeness of aluminum combustion, reduction of chamber length. Dependencies of AlO pressure in flow and near particles surface on a_E32 и a_E31 are obtained. The dependencies reveal that AlO molecules should settle on particles surface within the wide limits of accommodation coefficients variation. Also the dependencies show that AlO pressure differs from zero significantly near particles surface even under limiting value a_E31=1. Also dependencies of AlO pressure on initial particles radius are revealed. These dependencies (obtained for quasi-steady combustion regime) reflect that particles of coarse-grained fractions interact with AlO at noticeably greater degree than particles of small-grained fractions. For the first time the finite value of rate of AlO interaction with particles surface (of suboxide Al₂O formation during AlO coupling with metal) is considered. Such approach is more adequate description of combustion processes than combustion processes description in investigations carried out earlier.

Keywords: mathematical modelling, combustion, air-suspension, aluminium, suboxide, accommodation coefficient (interaction efficiency), relative burn-out length, completeness of combustion, nonequilibrium thermodynamics

Aleksey Yu. Kryukov (Perm, Russian Federation) – CSc in Technical Sciences, Associate Professor, Department of Innovation Technologies of Machine Engineering, Perm National Research Polytechnic
University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: alexkryukov@list.ru).

Vladimir I. Malinin (Perm, Russian Federation) – Doctor of Technical Sciences, Professor, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic
University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: malininvi@mail.ru).

1. Malinin V.I., Kolomin E.I., Antipin I.S. Model goreniya vysokoskorostnogo potoka aerovzvesi chastits alyuminiya, uchityvayushchaya kinetiku protsessov i osobennosti nakopleniya okisla [The model of combustion of high-velocity flow of air suspension of aluminium particles according to kinetics and accumulation of
   oxides]. Khimicheskaya fizika, 1998, vol. 17, no. 10, pp. 80-92.
2. Malinin V.I., Kolomin E.I., Antipin I.S. Vosplameneniye i goreniye aerovzvesi alyuminiya v reaktore vysokotemperaturnogo sinteza poroshkoobraznogo oksida alyuminiya [Ignition and combustion of aluminum-air suspensions in a reactor for high-temperature synthesis of alumina powder]. Combustion, explosion, and shock waves, 2002, Vol. 38, no. 5, pp. 525-534.
3. Shafirovich E., Varma A. Technology Requirements for Mars Sample Return using CO₂. Metal
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4. Chao Li, Chunbo Hu, Xin Xin, Yue Li, Haijun Sun. Experimental study on the operation characteristics of aluminum powder fueled ramjet. Acta Astronautica, 129 (2016), pp. 74-81.
5. Beksted M.V., Liang U., Padduppakkam K.V. Matematicheskoe modelirovanie goreniya odinochnoy alyuminievoy chastitsy (obzor) [Mathematical modeling combustion of single aluminium particle (review)]. Combustion, explosion, and shock waves, 2005, vol. 41, no. 6, pp. 15-33.
6. Gremyachkin V.M., Istratov A.G., Leypunovskiy O.I. K teorii gorenija metallicheskih chastits. Protsessy goreniya i vzryva [For the theory of combustion of metallic particles. Physical processes during combustion and explosion]. Moscow: Atomizdat, 1980, pp. 4-68.
7. Babuk V.A., Vasilev V.A., Romanov O.Ya. Fiziko-khimicheskie prevrashcheniya kapel Al–Al₂O₃ v potoke aktivnogo gaza [Physicochemical conversion of Al-Al₂O₃ drops in active gas flow]. Combustion, explosion, and shock waves, 1993, vol. 29, no. 3, pp. 129-133.
8. Kryukov A.Yu., Malinin V.I. Raschjot soderzhanija suboksidov v produktakh sgoranija aluminievovozdushnoi smesi po modeli neravnovesnoi termodinamiki [Computation of suboxides in the combustion pro­ducts of aluminium air mixture by model of nonequilibrium thermodynamics]. PNRPU Aerospace Engineering Bulletin, 2016, no. 44, pp. 116-131.
9. Zolotko A.N., Vovchuk Ya.I., Poletayev N.I., Florko A.V., Altman I.S. Sintez nanooksidov v dvukhfaznykh laminarnykh plemenakh [Synthesis of nanooxides in two-phase laminar flames]. Combustion,
   explosion, and shock waves, 2015, Volume 32, Issue 3, pp. 262-269.
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11. Yagodnikov D.A. Vosplamenenije i gorenije poroshkoobraznykh metallov [Ignition and combustion of powdery metals]. Moscow: Izdatelstvo MSTU imeni N.E. Baumana, 2009, 432 p.
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13. Bucher P., Yetter R.A., Dryer F.L., et al. Observations on aluminum particles burning in various oxidizers //33rd JANNAF Combustion Meeting. V. II. CPIA Publ. N 653. Laurel, MD, 1996, pp. 449-458.
14. Bucher P., Yetter R.A., Dryer F.L. et al. Aluminum particle gas-phase flame structure // 34^th JANNAF Combustion Meeting. V II. CPIA Pub. N 662. Laurel, MD, 1997, pp. 295-305.
15. Kryukov A.Yu., Malinin V.I. Matematicheskoye modelirovaniye goreniya pereobogashchënnoy alyuminiyevovozdushnoy smesi na osnove neravnovesnoy termodinamiki protsessov [Mathematical Modeling of the Combustion of an Overfueled Aluminum–Air Mixture Based on the Nonequilibrium Thermodynamics of the Process]. Combustion, explosion, and shock waves, 2018, Vol. 54, Is. 1, pp. 35-46.
16. Demidov S.S., Malinin V.I., Bulbovich R.V. Modelirovanie vosplamenenija poroshka alymonija, raspredel’onnogo v gazovom potoke [Modeling the ignition of aluminium powder dispersed in the gas flow with high content of oxigen]. PNRPU Aerospace Engineering Bulletin, 2016, no. 46, pp. 73-78.
17. Egorov A.G. Protsessy gorenija poroshkoobraznovo alyminija v prjamotochnykh kamerakh sgoranija reaktivnykh dvigatel’nykh ustanovok [Burning processes of powdery aluminum in straight flow chambers of jet propulsion systems]. Samara: Izdatelstvo Samarskogo nauchnogo tsentra RAS, 2004, 376 p.

rate of magnetorheological fluid. Therefore the article is devoted to the methods of modeling and forecasting the properties of magnetorheological media by external energy fields: temperature, mechanical, electromagnetic. The text contains the examples of modeling and calculation of magnetorheological medias witch exhibit viscoplastic, pseudoplastic, dilatant properties. The controllable generation of similar rheological effects allows organizing the combined management of the flow characteristics of magnetorheological fluids. The using of described methodology improves accuracy of numerical modeling of operating parameters of magnetorheological high-pressure drive systems in the design process; consequently, it enhances the efficiency of their operation.

Keywords: magnetorheological media, numerical simulation, non-Newtonian fluids, magnetorheological drives, rheological anomalies.

Katharina V. Naigert (Chelyabinsk, Russian Federation) – CSc in Technical Sciences, Senior Researcher, Scientific and Production Enterprise “Avionics and Mechatronics” (16, Kalinina st., Chelyabinsk, 454084, Russian Federation, e-mail: kathy_naigert@mail.ru).

Vladimir A. Tselischev (Ufa, Russian Federation) – Doctor of Technical Sciences, Professor, Head of Department of Applied Hydromechanics, Ufa State Aviation Technical University (11, K. Marksa st., Ufa, 450008, Russian Federation, e-mail: pgl.ugatu@mail.ru).

1. Motavkin A.V., Pokrovsky E.M., Skorodumov V.F. Opredeleniye reologicheskikh parametrov polimernykh kompozitov [The determination of rheological parameters of polymer composites]. Polymer
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DOI: 10.3390/min4010089

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Additive technologies make it possible to obtain complex profiles of different nomenclature with a high coefficient of material use. For the manufacture of parts by the methods of additive technologies, powders made of aluminum alloys have become very popular due to their high processability. For the fullest use of the possibilities of additive technologies, it is necessary to apply new approaches to the design of parts, one of which is based on the principles of topological optimization. On the example of the hull parts of the reducer, topological optimization of their structures for reducing the mass is carried out. As a result of optimization, the structures of the rebuilt hull parts reduced by 19-42% of the mass were obtained in comparison with the original part. The analysis of the results obtained in the work showed the possibility of applying topological optimization in the design of hull details, taking into account their manufacturing methods of additive technologies in order to reduce the mass and detuning from the critical vibration frequencies. In order to reduce the laboriousness of the process of manufacturing body parts from casting alloys, the possibility of its replacement with AlSi10Mg aluminum alloy used in additive production has been worked out. As a result of the analysis it was established that the replacement of the ML5 material by AlSi10Mg is advisable with a weight reduction of more than 33%.

Keywords: Additive technologies, topological optimization, body part, AlSi10Mg alloy, ML5 alloy, SIMP-method, finite element method, optimal design, helical reducer, weight reduction

Anton M. Hitrin (Perm, Russian Federation) – senior engineer-technologist, Reductor-PM Corporation (105, Geroev Hasana st., Perm, 614010, Russian Federation, e-mail: Xitrinam_87@mail.ru).

Mariya M. Erofeeva (Perm, Russian Federation) – leading specialist in new technologies, Reductor-PM Corporation (105, Geroev Hasana st., Perm, 614010, Russian Federation, e-mail: erofeeva@reductor-pm.com).

Vitaliy R. Tuktamyshev (Perm, Russian Federation) – CSc in Technical Sciences, associate professor, Department of Innovative Technologies of Mechanical Engineering, Perm National Research Polytechnic University (15, Akademika Koroleva st., Perm, 614013, Russian Federation, e-mail: tuktvr@gmail.com).

Aleksey A. Shiryaev (Perm, Russian Federation) – PhD student, Department of Dynamics and Strength of Machines, Perm National Research Polytechnic University (15, Akademika Koroleva st., Perm, 614013, Russian Federation, e-mail: alex.shiryaev.pstu@gmail.com).

1. Zlenko М.А., Popovich A.A., Mutylina I.N. Additivnye tekhnologii v mashinostroenii [Additive technologies in mechanical engineering]. St. Petersburg, Izdatelstvo politekhnicheskogo universiteta, 2013, 221 p.
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   international solid freeform fabrication symposium, 2011, pp. 348-362.
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   exposition, 2014, Vol. 7A, pp. 1-10. doi: 10.1115/GT2014-25637
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   a method for enabling additive manufacture of support-free optimal structures. Mater Des, 2014, Vol. 63,
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    gosudarstvennyy aerokosmicheskiy universitet, 2012, 123 p.
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The article presents mathematical models and algorithms for solving the problem of predicting the fatigue life of bladed disks with a mistuning. In the example with real bladed disk are investigated various options for introducing a mistuning into the design by changing the stiffness of the sections of the blades. Own and forced oscillations of the impeller with different variants of disorder are investigated. The results of calculation of dynamic stresses under forced vibrations of the impeller are presented. With the help of the ANSYS software, the fatigue life of the bladed disk with different variants of mistuning has been calculated. The results of fatigue life calculations gives a good agreement with the experimental data. The comparative analysis of results of application of various hypotheses of accumulation of fatigue damages (Palmgren–Miner, Haibach, Corten–Dolan, Serensen) is also carried out. For this construction is received that the most suitable hypothesis are Corten–Dolan and Serensen, Palmgren–Miner hypothesis works for carbonaceous steels better. The considered options of mistuning are the first step for regulation of dynamic characteristics and durability of the high-loaded elements of turbines.

Analysis of the results of the research allowed to develop recommendations to increase the durability of the bladed disks with a mistuning.

Keywords: bladed disk, turbomachinery, vibrations, frequencies, finite element method, mathematical model, stiffness, fatigue life, mistuning, stress, ANSYS.

Oleg V. Repetskii (Irkutsk, Russian Federation) – Doctor of Technical Sciences, Professor, Vice-Rector for International Relations, Irkutsk State Agrarian University named after A.A. Ezhevsky, (Molodezhny settlement, Irkutsk, 664007, Russian Federation, e-mail: repetckii@igsha.ru).

Igor N. Ryzhikov (Irkutsk, Russian Federation) – CSc in Technical Sciences, Associate Professor, Engineering Technologies and Materials Department, Irkutsk National Research Technical University (83, Lermontov st., Irkutsk, 664064, Russian Federation, e-mail: rin111@list.ru).

Nguyen Tien Quyet (Irkutsk, Russian Federation) – PhD Student, Engineering Technologies and Materials Department, Irkutsk National Research Technical University (83, Lermontov st., Irkutsk, 664064, Russian Federation, e-mail: cavoixanh@mail.ru).

1. Ryzhikov I.N., Repetskiy O.V., Nguyen Tien Quyet. Odin iz podkhodov k otsenke dolgovechnosti rabochikh koles turbomashin [An approach to turbomachinery bladed disc durability estimation]. Proceedings of Irkutsk State Technical University, 2015, no. 5(100), pp. 22-27.

2. Bernd Beirow. Grundlegende Untersuchungen zum Schwingungsverhalten von Verdichterlaufrädern in Integralbauweise, EAN: 9783832287290/ ISBN: 3832287299, Сottbus, 2009.

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pp. 187-210.

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6. Klauke T. Schaufelschwingungen realer integraler Verdichterräder im Hinblick auf Verstimmung und Lokalisierung (Cottbus: Der Andere Verlag), 2008, 169 p.

7. Temis Yu.M., Yakushev D.A. Optimal design of the compressor blade form. Problems of strength and plasticity Problems of strength and plasticity, 2011, Vol. 73, pp. 141-149.

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9. Wei S.T. Localization phenomena in Mistuned Assemblies with Cyclic Symmetry Part II: Forced
Vibration. Journal of Vibration, Acoustics, Stress and Reliability in Design, 1988, Vol. 110, no.4, pp. 439-449.

1. Repetckii O., Tien Quyet Nguyen, Ryzhikov I. Investigation of vibration and fatigue life of mistuned bladed disks. Proceedings of the international conference “Actual issues of mechanical engineering 2017” (AIME 2017), Tomsk Polytechnic University, Tomsk, RUSSIA AER-Advances in Engineering Research, 2017, Vol. 133, p. 702-707.
2. Repetskiy O., Ryzhikov I., Schmidt R. Investigation of impact of various types of mistuning on bladed disks vibration and fatigue life. 8^th IFToMM International Conference on Rotordynamics, Seoul, 2010.
3. Repetski O., Zainchkovski K. Sensitivity analysis for life estimation of turbine blades. American
   Society of Mechanical Engineers (Paper). Proceedings of the 1997 ASME ASIA Congress & Exhibition. Singapore, 1997.
4. Elovenko D.A., Repetckii O.V. Analiz naprjazhennogo sostojania poluploskosti, nagruzhennoi postojanim davleniem na ogranichennich promezhutochnich uchastkach s sadannim periodom metodom konechnih elementov na base programmnogo komplexa MSC.MARS [Analysis of stress state of elastic
   half-plane loaded with constant pressure at limited intermediate sections with specified period by finite element method based on MSC Mars software]. BSU News, no 5. pp. 171-175.

 14. Repetskiy O.V., Ryzhikov I.N., Nguyen Tyen Kuyet. Chislennoye issledovaniye dinamiki i dolgovechnosti rabochikh koles turbomashin s rasstroykoy parametrov [Numerical investigation of dynamics and durability of bladed disk of turbomachinery with mistuning parameters]. PNRPU Aerospace Engineering Bulletin, 2017, no. 51. pp. 39-51.

15. Petrov, E.P. and Iglin, S. P. Search of the worst and best mistuning patterns for vibration amplitudes of bladed disks by the optimization methods using sensitivity coefficients. In Proceedings of the 1st ASSMO UK Conference. Engineering Design Optimization (UK, 1999), pp. 303-310.

Numerical study of dynamics of intracameral processes is one of the main tasks in the development and design of a rocket engine on solid fuel (RESF). Modern RESF is a complex technical system in which a number of interrelated non–stationary and nonlinear physico-chemical processes take place simultaneously. Rocket engine solid fuel the special layout scheme has its own functional and design features. To optimize the parameters of the rocket engine, an attempt is made to directly numerical study the dynamics of its intracameral processes. The conjugate formulation of the problem, which includes: - operation of the igniter; - heating, ignition and subsequent non-stationary and turbulent combustion of a solid fuel charge; - non-stationary shock wave and vortex homogeneous-heterogeneous flow of air and combustion products in the combustion chamber, flues and nozzle blocks; - depressurization of the combustion chamber. Each of the subtasks is considered in the relationship and resolved at the same time-one step at a time. To solve this problem, a physical and mathematical model, a set of computer applications and their testing were developed.

Keywords: rocket engine solid fuel, intrachamber processes, combustion, gas dynamics, formulation of the numerical experiment.

Mikhail Yu. Egorov (Perm, Russian Federation) – Doctor of Physical and Mathematical Sciences, Professor, Department of Higher Mathematics, Perm National Research Polytechnic University (29, Komso­molsky av., Perm, 614990, Russian Federation, e-mail: egorov-m-j@yandex.ru).

Dmitry M. Egorov (Perm, Russian Federation) – CSc in technical Sciences. Deputy leading engineer, JSC "Scientific-Research Institute of Polymeric Materials" (16, Chistopolskaya st., Perm, 614113, Russian Federation, e-mail: egorovdimitriy@mail.ru).

Sergey M. Egorov (Perm, Russian Federation) – CSc in of Physical and Mathematical Sciences, Chief Researcher, JSC "Scientific-Research Institute of Polymeric Materials" (16, Chistopolskaya st., Perm, 614113, Russian Federation, e-mail: know_nothing@bk.ru).

1. Alemasov V.E., Dregalin A.F., Tishin A.P. Teoriya raketnykh dvigateley [Theory of rocket engines]. Moscow: Mashinostroyeniye, 1980, 533 p.
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3. Emelyanov V.N. Gazovyye techeniya v soplakh energoustanovok [Gas flows in nozzles of power plants]. Moscow: FIZMATLIT, 2017, 328 p.
4. Egorov M.Yu., Egorov Ya.V., Egorov S.M. Issledovanie neustoychivosti rabochego protsessa v dvukhkamernom RDTT [Study of working process instability in the two chamber solid propellant rocket engine]. Izvestiya vysshikh uchebnykh zavedeniy. Russian Aeronautics, 2007, no. 4, pp. 39-43.
5. Egorov M.Yu., Egorov S.M., Egorov D.M. Chislennoe issledovanie perekhodnykh vnutrikamernykh protsessov pri vykhode na rezhim raboty RDTT [Numerical study of transient interchamber processes when reaching the SPRE]. Izvestiya vysshikh uchebnykh zavedeniy. Russian Aeronautics, 2010, no. 3, pp. 41-45.
6. Egorov M.Yu., Egorov D.M. Chislennoye modelirovaniye vnutrikamernykh protsessov v bessoplovom RDTT [Numerical Modeling Interchamber processes in at nozzleless solid propellant rocket motors]. Editors: Kuznetsov G.V., Uskov V.N., Matveev S.K., Zapryahaev V.I., Zharov I.K., Tuber E.E., Borisov B.V., Zakharevych A.V., Maslov E.A. In the collections of: XXIII seminar on the jet, tear and unsteady flow (with international participation). Collections of Labor. National Research Tomsk Polytechnic University, 2012, pp. 124-127.
7. Egorov M.Yu. Chislennoe issledovanie dinamiky vnutrikamernykh protsessov pri srabatyvaniy
   specializirovannogo RDTT [Numerical Research of Intra-Chamber Processes Dynamics during Startup of Special Solid Propellant Engine]. Izvestiya vysshikh uchebnykh zavedeniy. Russian Aeronautics, 2017, no. 4, pp. 104-111.
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9. Davydov Yu.M., Egorov M.Yu. CHislennoye modelirovaniye nestatsionarnykh perekhodnykh protsessov v aktivnykh i reaktivnykh dvigatelyakh [Numerical simulation of unsteady transition processes in active and jet engines]. Moscow: NAPS Russia, 1999, 272 p.
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12. Nigmatulin R.I. Dinamika mnogofaznykh sred [Dynamics of multiphase media]. Moscow: Nauka, 1987, Part I, 464 p, Part II, 360 p.
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15. Egorov M.Y. Metod Davydova – sovremennyy metod postanovki vychislitelnogo eksperimenta v raketnom tvërdotoplivnom dvigatelestroyenii [Davydov method – modern method of statement of computing experiment in solid rocket motors industry]. PNRPU Aerospace Engineering Bulletin, 2014, no. 37, pp. 6-70.
16. Stahnov A.A. Linux. St.Peterburg.: BHV-Petersburg, 2004, 912 p.
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18. Programming Guide. AMD Accelerated Parallel Processing OpenCL. Advanced Micro Devices, 2011
19. Egorov M.Y., Egorov S.M., Egorov D.M. Primeneniye graficheskikh uskoriteley dlya povysheniya proizvoditelnosti vychisleniy pri chislennom modelirovanii funktsionirovaniya slozhnykh tekhnicheskikh sistem [The use of graphics accelerators to enhance computing performance for numerical simulation of the functioning of complex technical systems]. PNRPU Aerospace Engineering Bulletin, 2015, no. 40, pp. 81-91.

In recent years, the issue of utilization of oil gases has become especially topical. At low-yield deposits, it is advisable to use recycling microturbine plants with the generation of electric energy. To develop a universal combustion chamber of such an energy installation, calculation and experimental studies of the combustion characteristics of real oil gases are required. Oil gases of different deposits have a very different composition and thermal conductivity, and the content of non-combustible components in them can reach up to 90 %. In connection with this, it is very important to study the concentration limits of combustion of real ballasted oil gases. In this paper, the volumetric fractions of the fuel and the excess air coefficient at the upper and lower concentration limits of the combustion of real oil gases were calculated by calculation. As a result of the study, it was concluded that it is expedient to work in the utilization chambers near the upper concentration limit with excess air coefficients exceeding three. However, the region of stable combustion of oil gases is determined not only by concentration limits, but also by the ratio of the rates of the gas-air mixture and combustion. In the combustion of ballasted petroleum gases near the upper concentration boundary, the region of stable combustion strongly narrows under real conditions of delivery.

Keywords: ballast oil gas, concentration limits of combustion, gas-air mixture rate, air excess ratio.

Alyona A. Shilova (Perm, Russian Federation) – Student, Department of Rocket and Space Engineering and Power Generating Systems, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: alyona1203@gmail.com).

Nadezhda Yu. Bacheva (Perm, Russian Federation) – Senior Lecturer, Department of Applied Physics, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation,
e-mail: bnl54@yandex.ru).

1. Akhmadishin I.I., Zapasov R.A., Chernov I. A. Otsenka goryuchesti poputnogo neftyanogo gaza s bolshim soderzhaniyem azota [Assessment of flammability of associated petroleum gas with a high nitrogen content].Energoresursosberezheniye v promyshlennosti, zhilishchno-kommunalnom khozyaystve i agropro­mysh­len­nom komplekse: materialy regionalnogo nauchno-prakticheskogo seminara. Izhevsk: INNOVA, 2016, pp. 273-278.
2. Betinskaya O.A. (Zuyeva O.A.), Bachev N.L., Bulbovich R.V., Kleshchevnikov A.M. Vybor geometricheskikh, rezhimnykh i teplovykh parametrov vysokoresursnoy kamery sgoraniya dlya utilizatsii PNG [The choice of geometric, regime and thermal parameters of a high-resource combustion chamber for utilization of associated petroleum gas]. Gas Industry Magazine, 2013, no. 698, pp. 94-97.
3. Betinskaya O.A., Bachev N.L., Matyunin O.O, Bul'bovich R.V., Bacheva N.YU. Raschetnyye issledovaniya vnutrikamernogo protsessa pri utilizatsii neftyanogo gaza [Calculation studies of the intra-chamber process in the utilization of petroleum gas]. Neftyanoye khozyaystvo, 2017, no. 7, pp. 86-89.
4. Betinskaya O.A. (Zueva O.A.), Bachev N.L., Bulbovich R.V., Kleshchevnikov A.M. Razrabotka gazoturbinnoy ustanovki dlya utilizatsii neftyanogo gaza s vyrabotkoy elektricheskoy i teplovoy energii na malodebitnykh mestorozhdeniyakh [Development of a gas turbine plant for utilization of associated petroleum gas for gathering electrical and thermal energy at marginal fields]. Neftyanoe khozyaystvo, 2014, no. 1084, pp. 98-101.
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6. Betinskaya O.A. Predely ustoychivogo goreniya neftyanykh gazov [Limits of sustained combustion of petroleum gases]. Neftyanoye khozyaystvo, 2014, no. 1089, pp. 64-66.
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The increase in surface strength, wear resistance and corrosion resistance is an important direction in engineering. To obtain materials with the necessary characteristics, new methods are constantly being developed. Their development is limited by such factors as the cost of processing the product, the laboriousness of the process, the need for additional equipment of high complexity. The main task in engineering is to find the most cost-effective methods for improving the characteristics of processed materials. The method of increasing the surface quality at the finish cold treatment, called low plasticity burnishing, is considered. The principle of work of a method, the tool and machine tools for performance of works is considered. A qualitative comparison with other finishing methods of a similar action is presented, such as shot blasting and turning treatment. Based on the comparison and the results of practical tests, conclusions were drawn about the advantages of this method. Low plasticity burnishing method showed superiority in performance of shot peening on the results of multicycle fatigue effects on the alloy IN718. When comparing fine finishing with low-plastic smoothing, the surface roughness was reduced by 12.4 times under certain smoothing regimes. An example of the application of the method for improving the mechanical properties of the fan blades of the F404 engine is considered, as well as the testing of blades treated with this method with untreated vanes. The results of these tests showed the influence of the low-plastic burnishing method on increasing the strength of the blades and their resistance to damage by foreign objects.

Keywords: low plasticity burnishing, hardening of gas turbine blades, fatigue strength, residual stresses, resistance to damage by foreign objects

Ilya M. Aleksandrov (Perm, Russian Federation) – Student, Department of Aircraft engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: Ilyaalexa@yandex.ru).

Kirill E. Milyayev (Perm, Russian Federation) – Student, Department of Aircraft engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: daloros@inbox.ru).

Sergey V. Semenov (Perm, Russian Federation) – Assistant, Department of Aircraft engines, Perm National Research Polytechnic University (29, Komsomolsky av., Perm, 614990, Russian Federation, e-mail: sergey.semyonov@mail.ru).

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Mathematical model (MM) of the inverse thermogasdynamical task (ITT) and the corresponding computer program for the experimental and computational estimation of the turbine efficiency and the combustion chamber efficiency during their operation in the gas generator (GG) system of the gas turbine engine with the measurement in the course of the GG tests in the cross section behind the turbine of the fields of the total pressures and gas stagnation temperatures have been developed and numerically tested. The application of the developed MM ITT and computer programs in combination with the use of previously developed MM and computer programs for averaging the parameters of uneven gas flows is a technology that can be used in the practice of fine-tuning the advanced gas generators of modern gas turbine engines.

Keywords: gas turbine engine, turbine, combustion chamber, inverse thermogasdynamic problem, mathematical model, computer.

Vyacheslav М. Kofman (Ufa, Russian Federation) – CSc in Technical Sciences, Associate Professor, Department of Aviation Heat Engineering and Power System, Ufa State Aviation Technical University (12, K. Marx st., Ufa, 450000, Russian Federation, е-mail: stan@ufanet.ru).

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2. Kofman V.M. Metodika i programma na EVM dlya eksperimental’no-raschetnoy otsenki pokazateley effektivnosti kamery sgoraniya i turbiny po rezul’tatam ispytaniy gazogeneratora GTD s izmereniyem parametrov neravnomernogo gazovogo potoka v sechenii za turbinoy [Technique and computer program for the experimental and calculating evaluation of the efficiency of the combustion chamber and turbine based on the results of testing the GTE gas turbine with the measurement of the parameters of the uneven gas flow in the section behind the turbine]. Tezisy dokladov IV Mezhdunarodnoy nauchno-tekhnicheskoy konferentsii «Aviadvigateli XXI veka». Central Institute of Aviation Motors, 2015, pp. 69-71.

3. Kofman V.M. Svidetelstvo Rossiyskoy Federatsii o gosudarstvennoy registratsii programmy dlya EVM №2015662006. Eksperimentalno-raschetnoye opredeleniye pokazateley effektivnosti kamery sgoraniya i okhlazhdayemoy turbiny po rezultatam ispytaniy gazogeneratora gazoturbinnogo dvigatelya s izmereniyem parametrov neravnomernogo gazovogo potoka v sechenii za turbinoy [Certificate of incorporation of the computer program № 015662006. Experimental calculation of the efficiency of the combustion chamber and the cooled turbine based on the test results of the gas turbine engine gas generator with measurement of the parameters of the uneven gas flow in the section behind the turbine]. Stated 28/09/2015; Registered in Computer Programs list November 13, 2015.

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