title: Ð¢ÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÑÐ³Ð¾Ð¹ 60 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 bypass turbofan gas-turbine engine with a thrust of 60 kN
Creators: name: Ð¡ÐºÐ²Ð¾ÑÑÐ¾Ð², ÐÐ°Ð²ÐµÐ»
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: 2022
Subjects: Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÑÑÐ±Ð¸Ð½Ð°
Ð»Ð¾Ð¿Ð°ÑÐºÐ°
gas turbine engine
compressor
combustion chamber
turbine
blade

description: Ð Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð±ÑÐ»Ð¸ ÑÐ°ÑÑÐ¼Ð¾ÑÑÐµÐ½Ñ Ð¼ÐµÑÐ¾Ð´Ð¸ÐºÐ¸ ÑÐ°ÑÑÑÑÐ° Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ (ÐÐÐ¢Ð) ÑÑÐ³Ð¾Ð¹ 60 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ ÑÐ¶Ðµ ÑÑÑÐµÑÑÐ²ÑÑÑÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ (Ð¢Ð ÐÐÐ¤) Ð Ð-33. Ð¢Ð°ÐºÐ¶Ðµ Ð±ÑÐ»Ð¾ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð¾ Ð¾Ð±ÑÐµÐµ Ð¾Ð¿Ð¸ÑÐ°Ð½Ð¸Ðµ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¸ ÐµÐ³Ð¾ Ð¾ÑÐ¾Ð±ÐµÐ½Ð½Ð¾ÑÑÐ¸. Ð Ð°ÑÑÑÐ¸ÑÐ°Ð½Ð° ÑÐµÐ¿Ð»Ð¾Ð²Ð°Ñ ÑÑÐµÐ¼Ð° ÐÐ¢Ð, Ð¿ÑÐ¾Ð²ÐµÐ´ÑÐ½ Ð¿ÑÐ¸Ð±Ð»Ð¸Ð¶ÑÐ½Ð½ÑÐ¹ ÑÐ°ÑÑÑÑ Ð¾ÑÐµÐ²Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, ÑÐ°ÑÑÑÑ ÐºÐ¾Ð»ÑÑÐµÐ²Ð¾Ð¹ Ð¿ÑÑÐ¼Ð¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ, Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ ÑÑÑÐ±Ð¸Ð½Ñ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (ÐÐÐ) Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (ÐÐÐ), ÑÐ°ÑÑÑÑ Ð·Ð°ÐºÑÑÑÐºÐ¸ Ð¿Ð¾ÑÐ¾ÐºÐ°, ÑÐ¿ÑÐ¾ÑÐ¸Ð»Ð¸ÑÐ¾Ð²Ð°Ð½Ð° Ð»Ð¾Ð¿Ð°ÑÐºÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ (Ð¢ÐÐ), Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸. Ð Ð°ÑÑÐ¼Ð¾ÑÑÐµÐ½Ð¾ Ð²Ð»Ð¸ÑÐ½Ð¸Ðµ Ð²ÑÑÐ¾ÐºÐ¾ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÐ½Ð¾Ð¹ ÐºÐ¾ÑÑÐ¾Ð·Ð¸Ð¸ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ ÑÐ°Ð±Ð¾ÑÐ¸Ñ Ð»Ð¾Ð¿Ð°ÑÐ¾Ðº Ð¿ÐµÑÐ²Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ.
description: In this paper, we considered methods for calculating an aircraft gas turbine engine (AGTE) with a thrust of 60 kN based on an already existing prototype of a turbojet bypass gas turbine engine with an afterburner RD-33. A general description of the engine design and its features was also presented. The thermal scheme of the gas turbine engine was calculated, an approximate calculation of the axial compressor was carried out, the calculation of the annular direct-flow combustion chamber, the gas-dynamic calculation of the flow path of the low-pressure compressor (LPC) turbine and the high-pressure compressor (HPC) turbine, calculation of the flow swirling, profiled blade of the last stage of a low-pressure turbine (LPT), a calculation was made for the strength of structural elements. The influence of high-temperature corrosion on the strength of the working blades of the first stage of the turbine is considered.