title: ÐÐ²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 165 ÐºÐ
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: A by-pass engine with a thrust of 165 kN
Creators: name: ÐÐ²Ð°Ð½Ð¾Ð²Ð°, Ð®Ð»Ð¸Ñ
Publisher: name: Ð¡Ð°Ð½ÐºÑ-ÐÐµÑÐµÑÐ±ÑÑÐ³ÑÐºÐ¸Ð¹ Ð¿Ð¾Ð»Ð¸ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ½Ð¸Ð²ÐµÑÑÐ¸ÑÐµÑ ÐÐµÑÑÐ° ÐÐµÐ»Ð¸ÐºÐ¾Ð³Ð¾
Year: 2020
Subjects: Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹
ÐÐ¡-90Ð
ÑÑÐ³Ð° 165 ÐºÐ
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Ð°Ð½Ð°Ð»Ð¸Ð· Ñ Ð°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº ÑÑÐ´Ð´
by-pass engine
PS-90A
thrust 165 kN
turbo-fan
air intake
axial compressor
ring combustion chamber
axial turbine
strength
analysis of characteristics

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description: The purpose of the work is to design an engine with a thrust of 165 kN based on the prototype of a PS - 90A turbofan aircraft engine. The work consists of eight main chapters. The first chapter is devoted to advance thermal calculation of the engine, determining the optimal degree of increase in pressure and gas temperature in front of the turbine. This is followed by the calculation of the subsonic air intake, determining the area of the inlet section into the fan duct. The next section is the calculation of the compressor, which includes the calculation of the fan, low-pressure compressor, high-pressure compressor with the determination of gas-dynamic parameters, dimensions of the air channel, rotational speeds and the required capacities for the necessary discharge before the turbine. Based on the data from the calculation of the compressor, the calculation of the annular combustion chamber is performed. Next, the gas-dynamic calculation of the turbine, profiling the gas channel, determining the power and efficiency, calculating the swirl of the flow of the blades of the last stage and constructing the profile of the blade in five sections. A 3D model of a blade with a tail connection and a disk is built over sections. The stresses of the blades, shanks, disks are calculated, so the calculation of the natural frequencies of the blades and rotor. The seventh chapter is a brief description of the main components of a gas turbine engine. The final chapter is a review and comparative analysis of the characteristics of native and foreign by-pass aircraft engines (turbofan engines). Mainly modern passenger aircraft engines are considered, prospects of native engines are estimated.