Aerospace Technic and Technology

The article considers the method of improving the characteristics of the ring inlet device, taking into account the influence of the propeller of an aircraft power plant with a turboprop engine. It is shown that increasing the total pressure loss in the inlet device by 5% increases, approximately, the specific fuel consumption by 3% and reduces engine thrust by 6%, and uneven flow at the inlet to the engine is the cause of unstable compressor of the turboprop engine. It is proposed to improve the characteristics of the input device by modifying the shape of its shell and channel. Evaluation of the influence of the shape of the shell and the channel of the annular axial VP on its main aerodynamic characteristics, taking into account the non-uniformity of the flow on the fan in the calculated mode of operation of the SU is carried out by calculating the full pressure recovery factor. The object of the study is an annular axial input device in front of which is a coaxial fan turboprop fan. The process of modeling the influence of the shape of the shell and the channel on the recovery factor of total pressure, circular and radial non-uniformity of the flow through the input device is implemented in the software system of finite element analysis ANSYS CFX. Geometric models of coaxial screw fan, fairing and inlet device are built in ANSYS SpaceClaim and transferred using the built-in import function in ANSYS Workbench. Block-structured grid models of air propellers of the first and second rows of the fan in the amount of 1.9 million, fairing and inlet device, in the amount of 3.9 million, are built in the ANSYS TurboGrid environment. The standard Stern (Shear Stress Transport) Gamma Theta Transition was used to close the Navier-Stokes equation system. Based on the results of mathematical modeling of flow in coaxial fans and subsonic ring inlet device on the maximum cruising mode of the turboprop engine, the full pressure recovery factor is calculated and it is established that the most influential factor that increases its full pressure recovery factor.

input device; screw fan; coaxial screw; modeling; turbulent viscosity; calculation grid; characteristics of the input device; efficiency of the input device

Nechaev, Ju. N., Fedorov, R. M., Kotovskij, V. N., Polev, A. S. Teorija aviacionnyh dvigatelej. Chast’ 1. [Theory of aircraft engines. Part 1]. Moscow, VVIA im. prof. N. E. Zhukovskogo Publ., 2012. 366 p.

Tereshchenko, Yu. M., Kuly`k, M. S., Panin, V. V. Integraciya aviacijny`x sy`lovy`x ustanovok lital`ny`x aparativ [Integration of aircraft power plants]. Kyiv, NAU-druk Publ., 2009. 344 p.

Sobester, A. Tradeoffs in jet inlet design: a historical perspective. Journal of Aircraft, 2007, vol. 44, no. 3. рр. 705-717.

Boles, M. A., Stockman, N. O. Use of experimental separation limits in the theoretical design of V/STOL inlets. NASA Technical Memorandum, 1977, no. 73709.

Chou, D. C., Luidens, R. W., Stockman, N. O. Prediction of boundary-layer flow separation in V/STOL engine inlets. Journal of Aircraft, 1978, vol. 15, no. 8. рр. 474–481.

Chou, D. C., Lee, H. C., Luidens, R. W., Stockman, N. O. Methods for calculating the transonic boundary layer separation for V/STOL inlets at high incidence angles. AIAA Conference Paper, 1978, no. 1340. рр. 100–106.

Shmyrjov, V. F. Osobennosti proektirovanija noska vozduhozabornika turboventiljatornogo dvigatelja [Design features of the air intake nose of a turbofan engine]. Otkrytye informacionnye i komp'juternye integrirovannye tehnologi: sb. nauch. tr. Nac. ajerokosmich. un-ta im. N. E. Zhukovskogo «HAI» – Open information and computer integrated technologies: collection of scientific papers of the National Aerospace University named after N.E. Zhukovsky "KhAI", 2019, no. 86, рр. 25-36.

Free Engineering Simulation Software to Students. ANSYS Inc. Available at: https://anysilicon.com/free-engineering-simulation-software-students/ (accessed 12.04.2021).

Ivanov, D. V., Dol', A. V. Vvedenie v Ansys Workbench: Ucheb.-metod. posobie dlja studentov estestvenno-nauchnyh disciplin [Ansys Workbench Introduction: A Tutorial Method. manual for students of natural sciences]. Saratov, Amirit Publ., 2016. 56 р.

Rukovodstvo po tehnicheskoj jekspluatacii soosnogo vintoventiljatora SV-27 [Technical operation manual for coaxial propfan SV-27]. Stupino, OAO NPP «Aerosilа» Publ., 1989. 1216 р.

Molchanov, A. M., Shherbakov, M. A., Janyshev, D. S., Kuprikova, M. Ju., Bykov, L. V. Postroenie setok v zadachah aviacionnoj i kosmicheskoj tehniki [Meshing in problems of aviation and space technology]. Moscow, 2013. 260 р.

Menter, F. R. Two-equation eddy-viscosity turbulence model to engineer in applications. AIAAJ, 1994, vol. 32, no. 8. рр. 1598–1605.

Samolet An-70 № 01-02. Ocenka harakteristik vhodnogo ustrojstva marshevoj dvigatel'noj ustanovki s modernizirovannym vintoventiljatorom SV-27 [An-70 aircraft No. 01-02. Evaluation of the characteristics of the entrance device of the sustainer propulsion system with the upgraded SV-27 propfan]. ANTK im. O. K. Antonova. Teh. otchet № 70.702.032.D1-12, 2012. 100 p.