title: Ð¢ÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 77 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: Turbojet dual-circuit aviation engine with a thrust of 77 kN
Creators: name: ÐÑÐ¼ÐµÑÐ¾Ð²Ð°, Ð Ð°Ð»Ð¸Ð½Ð°
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: 2024
Subjects: Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð¾ÑÐµÐ²Ð¾Ð¹ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÑÑÐ±Ð¸Ð½Ð°
ÑÐ°Ð±Ð¾ÑÐ°Ñ Ð»Ð¾Ð¿Ð°ÑÐºÐ°
ÑÐ¸ÑÑÐµÐ¼Ð° ÑÐ°ÑÐ¿ÑÐ»Ð¸Ð²Ð°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð°
ÑÐ½Ð¸Ð¶ÐµÐ½Ð¸Ðµ Ð²ÑÐµÐ´Ð½ÑÑ Ð²ÑÐ±ÑÐ¾ÑÐ¾Ð²
Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ñ ÑÐ°Ð±Ð¾ÑÐ¸Ñ Ð¿ÑÐ¾ÑÐµÑÑÐ¾Ð²
gas-turbine engine
axial compressor
combustion chamber
turbine
impeller
fuel spray system
reduction of harmful emissions
optimization of working processes

description: Ð¦ÐµÐ»ÑÑ Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ ÑÐ²Ð»ÑÐµÑÑÑ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 77 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° SaM 146. ÐÐ°Ð´Ð°ÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµ Ð±ÑÐ»Ð¸ ÑÐµÑÐµÐ½Ñ Ð² ÑÐ¾Ð´Ðµ ÑÐ°Ð±Ð¾ÑÑ: 1. Ð Ð°ÑÑÐµÑ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÑÐµÐ¼Ñ, Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ð°Ð½Ð¸Ð¸ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð² ÐºÐ¾ÑÐ¾ÑÐ¾Ð³Ð¾ Ð²ÑÐ±Ð¸ÑÐ°ÐµÑÑÑ ÑÑÐµÐ¿ÐµÐ½Ñ Ð¿Ð¾Ð²ÑÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð² ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐµ Ð¸ ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÐ° Ð½Ð° Ð²ÑÐ¾Ð´Ðµ Ð² ÑÑÑÐ±Ð¸Ð½Ñ; 2. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ Ð¾ÑÐµÐ²Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°; 3. Ð Ð°ÑÑÐµÑ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ñ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð¸ÐµÐ¼ ÐµÐµ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¸Ñ ÑÐ°Ð·Ð¼ÐµÑÐ¾Ð² Ð¸ ÑÐºÐ¾Ð»Ð¾Ð³Ð¸ÑÐµÑÐºÐ¸Ñ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº; 4. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ ÑÑÑÐ±Ð¸Ð½ Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð¸ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ; 5. Ð Ð°ÑÑÐµÑ Ð·Ð°ÐºÑÑÑÐºÐ¸ Ð¿Ð¾ÑÐ¾ÐºÐ° Ð´Ð»Ñ Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ; 6. ÐÐ¾ÑÑÑÐ¾ÐµÐ½Ð¸Ðµ ÑÑÐµÑÐ¼ÐµÑÐ½Ð¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»Ð¸ ÑÐ°Ð±Ð¾ÑÐµÐ¹ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¸ Ð´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; 7. Ð Ð°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÐºÐ¾Ð»ÐµÑÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ; 8. Ð Ð°ÑÑÐµÑ Ð²Ð¸Ð±ÑÐ¾Ð½Ð°Ð´ÐµÐ¶Ð½Ð¾ÑÑÐ¸ Ð²Ð°Ð»Ð° ÑÐ¾ÑÐ¾ÑÐ° Ð¸ ÑÐ°Ð±Ð¾ÑÐµÐ¹ 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; 9. ÐÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¿ÑÐ¾ÑÐµÑÑÐ¾Ð² Ð³Ð¾ÑÐµÐ½Ð¸Ñ Ð¸ ÑÐ¸ÑÑÐµÐ¼Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð¾Ð¿Ð¾Ð´Ð°ÑÐ¸ Ñ ÑÐµÐ»ÑÑ ÑÐ½Ð¸Ð¶ÐµÐ½Ð¸Ñ ÑÐ¼Ð¸ÑÑÐ¸Ð¸ Ð²ÑÐµÐ´Ð½ÑÑ Ð²ÐµÑÐµÑÑÐ².
description: The purpose of this work is to design an aviation engine with a thrust of 77 kN based on the prototype of the SaM 146. Tasks that were solved during the work: 1. Calculation of the thermal circuit, based on the results of which the degree of pressure increase in the compressor and the temperature at the turbine inlet are selected; 2. Gas dynamic calculation of the axial compressor; 3. Calculation of the combustion chamber to obtain its geometric dimensions and environmental characteristics; 4. Gas-dynamic calculation of a high and low-pressure turbine; 5. Calculation of the flow twist for the last stage of the power turbine; 6. Construction of a three-dimensional model of the working blade and disk of the last stage of the low-pressure turbine; 7. Calculation of the strength of the impeller of the last stage of the low-pressure turbine; 8. Calculation of vibration reliability of the rotor shaft and working blade of the last stage of the low-pressure turbine; 9. Study of combustion processes and fuel supply systems aimed at reducing harmful emissions.