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 CFM-56 Ð³ÑÐ°Ð¶Ð´Ð°Ð½ÑÐºÐ¾Ð³Ð¾ Ð½Ð°Ð·Ð½Ð°ÑÐµÐ½Ð¸Ñ ÑÑÐ³Ð¾Ð¹ 115 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: CFM-56 civil dualâcircuit turbojet engine with a thrust of 115 kN
Creators: name: ÐÑÑÐ°ÐºÐ¾Ð², ÐÐ²Ð³ÐµÐ½Ð¸Ð¹
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: 2023
Subjects: ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ñ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¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ
turbojet engine
dual circuit engine
aircraft engine
compressor
combustion chamber
turbine
robustness

description: ÐÐ°Ð½Ð½Ð°Ñ Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð° ÑÐ°ÑÑÐµÑÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐ²Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð³ÑÐ°Ð¶Ð´Ð°Ð½ÑÐºÐ¾Ð³Ð¾ Ð½Ð°Ð·Ð½Ð°ÑÐµÐ½Ð¸Ñ ÑÑÐ³Ð¾Ð¹ 115 ÐºÐ Ð¿Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ñ CFM-56, ÑÑÑÐ°Ð½Ð°Ð²Ð»Ð¸Ð²Ð°ÐµÐ¼Ð¾Ð¼Ñ Ð¿ÑÐµÐ¸Ð¼ÑÑÐµÑÑÐ²ÐµÐ½Ð½Ð¾ Ð½Ð° ÑÑÐµÐ´Ð½ÐµÐ¼Ð°Ð³Ð¸ÑÑÑÐ°Ð»ÑÐ½ÑÐµ Ð°Ð²Ð¸Ð°Ð»Ð°Ð¹Ð½ÐµÑÑ. ÐÐ»Ñ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ñ Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ Ð±ÑÐ»Ð¸ ÑÐµÑÐµÐ½Ñ ÑÐ»ÐµÐ´ÑÑÑÐ¸Ðµ Ð·Ð°Ð´Ð°ÑÐ¸: 1. ÐÐ·Ð½Ð°ÐºÐ¾Ð¼Ð»ÐµÐ½Ð¸Ðµ Ñ ÑÑÑÑÐ¾Ð¹ÑÑÐ²Ð¾Ð¼ Ð¸ Ð¾ÑÐ¾Ð±ÐµÐ½Ð½Ð¾ÑÑÑÐ¼Ð¸ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÑâÐ¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° CFM-56. 2. ÐÑÑÑÐµÑÑÐ²Ð»ÐµÐ½Ð¸Ðµ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð³Ð¾ ÑÐ°ÑÑÐµÑÐ° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð²ÑÐ±Ð¾ÑÐ¾Ð¼ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ°. 3. ÐÐ·ÑÑÐµÐ½Ð¸Ðµ Ð¸ ÑÐ°ÑÑÐµÑ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¸ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¸Ñ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐ·Ð»Ð¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, ÑÐ°ÐºÐ¸Ñ ÐºÐ°Ðº ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ, ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ð¸ ÑÑÑÐ±Ð¸Ð½Ð°, Ð° ÑÐ°ÐºÐ¶Ðµ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ 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. 4. ÐÑÑÑÐµÑÑÐ²Ð»ÐµÐ½Ð¸Ðµ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½Ð¾Ð³Ð¾ ÑÐ°ÑÑÐµÑ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 Ð¸ ÑÐ¾ÑÐ¾ÑÐ° Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ. ÐÐ»Ñ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ñ ÑÐ°Ð±Ð¾ÑÑ Ð±ÑÐ»Ð¾ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¾ ÑÐ»ÐµÐ´ÑÑÑÐµÐµ Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð¾Ðµ Ð¾Ð±ÐµÑÐ¿ÐµÑÐµÐ½Ð¸Ðµ: MS Excel, SolidWorkes, ÐÐÐÐÐÐ¡-3D, Ansys Workbench, MathCAD Ð ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐµ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ñ ÑÐ°Ð±Ð¾ÑÑ Ð±ÑÐ»Ð¸ Ð¿Ð¾Ð»ÑÑÐµÐ½Ñ Ð·Ð½Ð°ÑÐµÐ½Ð¸Ñ Ð²Ð°Ð¶Ð½ÑÑ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ (ÑÐ°ÐºÐ¸Ñ ÐºÐ°Ðº ÐÐÐ, Ð¼Ð¾ÑÐ½Ð¾ÑÑÑ Ð¸ Ñ. Ð´.), ÑÐ²ÐµÑÐ´Ð¾ÑÐµÐ»ÑÐ½ÑÐµ Ð¼Ð¾Ð´ÐµÐ»Ð¸ 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 Ð¸ ÑÐ¾ÑÐ¾ÑÐ° Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÐµÑÑÐµÐ¶ Ð¿ÑÐ¾Ð´Ð¾Ð»ÑÐ½Ð¾Ð³Ð¾ ÑÐ°Ð·ÑÐµÐ·Ð° Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÑÐµÐ¼Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ.
description: This final qualification work is devoted to the calculation and design of a doubleâcircuit twin-shaft aviation turbojet engine of civilian thrust of 115 kN by CFM-56 prototype, installed mainly on medium-haul airliners. To perform the graduate qualification work, the following tasks were solved: 1. Familiarization with the structure and design features of the CFM-56 prototype engine. 2. Performing thermal calculation of the engine and selecting the best option. 3. Study and calculation of gas dynamic and geometric parameters of the main engine components, such as compressor, combustion chamber and turbine, as well as design of the working blade of the last turbine stage. 4. Performing the strength calculation of the working blade and disc of the last stage of the turbine and lowâpressure rotor. The following software was used to perform the work: MS Excel, SolidWorkes, KOMPAS-3D, Ansys Workbench, MathCAD. As a result of the work, we obtained values of important engine characteristics (such as efficiency, power, etc.), solid models of the blade and disc of the last stage of the turbine and low-pressure rotor, as well as a longitudinal sectional drawing of the engine under design.