Aerospace Technic and Technology

The results of mathematical modeling processes in the turboshaft gas turbine engine (GTE) are presented. The using calculation method based on a high-level GTE mathematical model, which is founded on a multi-stage axial compressor blade-to-blade description. The model was developed at the Aviation Theory Chair of National Aerospace University “KhAI”. The model is based on a multistage axial compressor thermodynamic parameters calculations using a 1D and 2D approaches to analyzing of the flow. The model named above allows one to take into account air intakes from of the compressor blade gaps, as well as adjusting the angles of installation of the rotary stator vanes depending on the rotational speed. The GTE model has a modular structure. To determine the compressor parameters the modules for 1D or 2D flow calculation can be connected. As the initial data, besides the data traditionally specified in the 1st level GTE models it is necessary to set the geometrical parameters of the compressor flow path and blades on the medium radius (for the 2nd level GTE model) or along with the blade height (for the 3rd level). Both calculating compressor parameters methods are verified and have a fairly wide experience of practical use. The article presents the results of calculating the maps of the GTE multi-stage compressor using one- and two-dimensional approaches. Comparison of the compressor performances achieved by using of these two methods among themselves and with the experimental data has shown their good agreement. The approach used to simulate the flow in compressors makes it possible to estimate, by calculation, the surge margin, to consider the incidence angles and other flow parameters in the blade gaps in a wide range of GTE operation modes. Such results, as well as a comparison with experimental data, are presented in the article. The article also demonstrates the results of applying the described above model to the gas turbine engine performances calculation. The engine has the 12-stage axial compressor with the stator blades position of the first stages regulation. The calculated line of joint operation modes of the gas generator units, the dependence of the power and specific fuel consumption on the rotational speed. Presented are the processes in GTE on stationary modes analyzing results given in the article showed the used model advantage, reliability and expediency of its practical application.

Tunakov, A.P. Metody optimizacii pri dovodke i proektirovanii gazoturbinnyh dvigatelej [Optimization methods for the refinement and design of gas turbine engines]. Moscow, Mashinostroenie Publ., 1979. 184 p.

Ahmedzjanov, A. M., Alekseev, Ju. S., Gumerov, H. S. and others. Proektirovanie aviacionnyh gazoturbinnyh dvigatelej [Design of aircraft gas turbine engines]. Moscow, Mashinostroenie Publ., 2000. 454 p.

Kurzke, J. A. Physics Based Methodology for Building Accurate Gas Turbine Performance Models. Proc. of ISABE, 2015, no. 20220. 11 p.

Boyko, L. G., Karpenko, E. L. Razrabotka metoda rascheta harakteristik turboval'nogo dvigatelja s povencovym opisaniem mnogostupenchatogo osevogo kompressora [Development of a method for calculating the characteristics of a turboshaft engine with a rotation description of a multi-stage axial compressor]. Vestnik dvigatelestroenija, 2007, no. 3, pp. 143-146.

Boyko, L. G., Kislov, O. V., Pizhankova, N. V. Metod rascheta termogazodina-micheskih parametrovturboval'nogo GTD na osnovanii povencovogo opisanija lopatochnyh mashinch. Chast’ 1. Osnovnye uravnenija [Turboshaft engine thermogasdynamic parameters calculation method blade-to blade description turbomashines based. Part I. Main equations]. Aviacijno-kosmicna tehnika i tehnologia - Aerospace technic and technology, 2018, no. 1(145), pp. 48-58. DOI: 10.32620/aktt.2018.1.05.

Boyko, L. G., Karpenko, E. L. Vlijanie ugla ustanovki lopatki vhodnogo napravljajushhego apparata na jekspluatacionnye harakteristiki gazoturbinnogo dvigatelja [Influence of the installation angle of the blade of the inlet guide vane on the operating characteristics of a gas turbine engine]. Aviacijno-kosmicna tehnika i tehnologia - Aerospace technic and technology, 2008, no. 4 (51), pp. 43-50.

Boyko, L. G., Demin, A. E., Pizhankova, N. V. Metody rascheta termogazodinamicheskih parametrov turboval'nogo gazoturbinnogo dvigatelja na osnove povencovogo opisanija lopatochnyh mashin. Chast' II. Opredelenie parametrov stupenej i mnogostupenchatyh kompressorov [Turboshaft engine thermogasdynamic parameters calculation method blade-to blade description turbomashines based. Part II. Stage and multistage compressors parameters determination]. Aviacijno-kosmicna tehnika i tehnologia - Aerospace technic and technology, 2019, no. 1(153), pp. 18-28. DOI: 10.32620/aktt.2019.1.02

Boyko, L. G., Ershov, V. N., Girich, G. A. and others. Metody rascheta dvumernogo techenija v mno-gostupenchatom osevom kompressore [Method of calculation of the two-dimensional flow in the multi-stage axial compressor]. Izv. Vuzov, 1989, no. 5, pp. 56-60.

Ershov, V. N. Neustojchivye rezhimy turbomashin [Unstable modes of turbomachines]. Moscow, Mashinostroenie Publ., 1966. 180 p.

Liblein, S. Loss and Stall analysis of Compressor Cascade. Trans. ASME, 1959, no. 3, pp. 387-400.

Internet Museum of Russian Aviation. Available at: http://авиару.рф/ (Accessed 5.03.2019)