title: ÐÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ, ÑÐ°ÑÑÐµÑ Ð¸ ÐºÐ¾Ð½ÑÑÑÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð°Ð²Ð¸Ð°Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÐÐ-32
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: Design, calculation and development of the aircraft engine NK-32
Creators: name: ÐÐ¾Ð»ÐºÐ¾Ð², ÐÐ³Ð¾Ñ
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: 2021
Subjects: Ð°Ð²Ð¸Ð°Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð³Ð°Ð·Ð¾Ð²Ð°Ñ ÑÑÑÐ±Ð¸Ð½Ð°
ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÐ°ÑÑÐµÑ
Ð¾ÑÐµÐ²Ð¾Ð¹ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÐ¸Ð»Ð¾Ð²Ð°Ñ ÑÑÑÐ°Ð½Ð¾Ð²ÐºÐ°
Ð±Ð¸ÑÐ¾ÑÐ°ÑÐ¸Ð²Ð½Ð°Ñ ÑÑÑÐ±Ð¸Ð½Ð°
Ð¿ÑÐ¾ÑÐ¸Ð²Ð¾Ð²ÑÐ°ÑÐµÐ½Ð¸Ðµ ÐºÐ°ÑÐºÐ°Ð´Ð¾Ð² ÑÑÑÐ±Ð¸Ð½Ñ
jet engine
gas turbine
heat calculation
axial compressor
combustion chamber
aircraft engine
birotative turbine
turbine cascade counter rotation

description: Ð¦ÐµÐ»ÑÑ Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ ÑÐ²Ð»ÑÐµÑÑÑ ÑÐ°ÑÑÐµÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 140 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ ÑÑÑÐµÑÑÐ²ÑÑÑÐµÐ¹ ÑÐ¸Ð»Ð¾Ð²Ð¾Ð¹ ÑÑÑÐ°Ð½Ð¾Ð²ÐºÐ¸ ÐÐ-32. Ð ÑÐ°Ð±Ð¾ÑÐµ Ð¿ÑÐ¸Ð²ÐµÐ´ÐµÐ½Ð¾ Ð¾Ð±ÑÐµÐµ Ð¾Ð¿Ð¸ÑÐ°Ð½Ð¸Ðµ ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐ°Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¸ Ð¾ÑÐ¾Ð±ÐµÐ½Ð½Ð¾ÑÑÐ¸ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸. ÐÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½Ñ ÑÐ°ÑÑÑÑÑ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÑÐµÐ¼Ñ, Ð¿ÑÐ¸Ð±Ð»Ð¸Ð¶ÑÐ½Ð½ÑÐ¹ ÑÐ°ÑÑÑÑ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (ÐÐÐ, Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾Ñ), ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° ÑÑÐµÐ´Ð½ÐµÐ³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (Ð¢Ð¡Ð) Ð¸ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (ÐÐÐ), ÑÐ°ÑÑÑÑ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ (ÐÐ¡), Ð¿Ð¾Ð´ÑÐ¾Ð±Ð½ÑÐ¹ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÑÑ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (Ð¢ÐÐ), ÑÑÑÐ±Ð¸Ð½Ñ ÑÑÐµÐ´Ð½ÐµÐ³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (Ð¢Ð¡Ð) Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (Ð¢ÐÐ), ÑÐ°ÑÑÑÑ Ð·Ð°ÐºÑÑÑÐºÐ¸ Ð¿Ð¾ÑÐ¾ÐºÐ° Ð² Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ Ð¢ÐÐ, Ð¢Ð¡Ð Ð¸ Ð¢ÐÐ, Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐµÑ Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¸ Ð´Ð¸ÑÐºÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ±Ð¸Ð½Ñ. Ð¡Ð¾Ð´ÐµÑÐ¶Ð¸Ð¼Ð¾Ðµ ÑÐ°Ð±Ð¾ÑÑ Ð¿ÑÐµÐ´ÑÑÐ¼Ð°ÑÑÐ¸Ð²Ð°ÐµÑ ÑÐµÑÐµÑÐ°Ñ, Ð²Ð²ÐµÐ´ÐµÐ½Ð¸Ðµ, 7 Ð³Ð»Ð°Ð², Ð·Ð°ÐºÐ»ÑÑÐµÐ½Ð¸Ðµ Ð¸ Ð±Ð¸Ð±Ð»Ð¸Ð¾Ð³ÑÐ°ÑÐ¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ¿Ð¸ÑÐ¾Ðº. ÐÐ±ÑÐµÐµ ÑÐ¸ÑÐ»Ð¾ ÑÑÑÐ°Ð½Ð¸Ñ â 171.
description: The purpose of this work is to calculate and design 140 kN thrust aircraft gasturbineengine, which is based on the existing jet engine NK-32. The work presents developed engine general description and design features. The heatcalculations, the low-pressure compressor (LPC, fan), the mid-pressure compressor (MPC) andthe heigh-pressure compressor (HPC) approximate calculations, combustion chamber (CC)calculations, the high-pressure (HPT), the mid-pressure (MPT) and the low-pressure turbine(LPT) detailed gas-dynamic calculations, including the flow swirl calculations in the cascadeslast stages, the last stage last vane and disk strength calculations.The work includes the abstract, the introduction, 7 chapters, the conclusion and thebibliography. The total pages number is 171.