title: Ð Ð°ÑÑÑÑ Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÑÐ³Ð¾Ð¹ 110 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° CFM-56
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: Calculation of the double-circuit engine with 110kN thrust based on the prototype CFM-56
Creators: name: ÐÐ°ÑÐºÐ¾Ð², ÐÐ»Ñ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: 2023
Subjects: Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
cfm56
ÑÑÐ³Ð°
ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÑÑÐ±Ð¸Ð½Ð°
dual-circuit engine
thrust
compressor
combustion chamber
turbine

description: Ð¦ÐµÐ»ÑÑ Ð´Ð°Ð½Ð½Ð¾Ð¹ Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ° ÑÐ²Ð»ÑÐµÑÑÑ ÑÐ°ÑÑÐµÑ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð¾Ð±ÐµÑÐ¿ÐµÑÐ¸Ð²Ð°ÑÑÐµÐ³Ð¾ ÑÑÐ³Ñ Ð² ÑÐ°Ð·Ð¼ÐµÑÐµ 110ÐºÐ. Ð ÑÐ°Ð±Ð¾ÑÐµ Ð¾ÑÑÑÐµÑÑÐ²Ð»ÑÐµÑÑÑ Ð°Ð½Ð°Ð»Ð¸Ð· Ð¸ÑÑÐ¾Ð´Ð½Ð¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° CFM56 Ð¸ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¸Ðµ ÐµÐ³Ð¾ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¸Ñ ÑÐ°Ð·Ð¼ÐµÑÐ¾Ð² Ð´Ð»Ñ ÑÐ°ÑÑÐµÑÐ° Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾ÑÐ°, ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð¸ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ñ ÑÐµÐ»ÑÑ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ñ ÐµÐ³Ð¾ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº Ð¸ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð². ÐÐ°Ð´Ð°ÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµÂ  Ð²ÑÐ¿Ð¾Ð»Ð½ÑÑÑÑÑÂ  Ð²Â  Ð¿ÑÐ¾ÑÐµÑÑÐµÂ  Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸ÑÂ  Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ: 1. Ð¢ÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÐ°ÑÑÐµÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð²ÑÐ±Ð¾ÑÐ¾Ð¼ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ° Ð´Ð»Ñ Ð´Ð°Ð»ÑÐ½ÐµÐ¹ÑÐµÐ³Ð¾ ÑÐ°ÑÑÐµÑÐ°; 2. ÐÐ½Ð°Ð»Ð¸Ð· Ð´Ð°Ð½Ð½ÑÑ Ð¾ÑÐ´ÐµÐ»ÑÐ½ÑÑ ÑÐ·Ð»Ð¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð¿Ð¾Ð¼Ð¾ÑÑÑ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð¸ ÑÐ°ÑÑÑÑÐ¾Ð² ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ; 3. Ð Ð°ÑÑÐµÑ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ¸, Ð¿Ð¾Ð»ÑÑÐ°ÐµÐ¼Ð¾Ð¹ Ð¿ÑÐ¸ ÑÐ°Ð±Ð¾ÑÐµ ÑÑÑÐ±Ð¸Ð½Ñ, Ð¸ Ð´Ð°Ð»ÑÐ½ÐµÐ¹ÑÐ¸Ð¹ Ð²ÑÐ²Ð¾Ð´ Ð¾ ÑÐ°Ð±Ð¾ÑÐ¾ÑÐ¿Ð¾ÑÐ¾Ð±Ð½Ð¾ÑÑÐ¸ Ð¸ ÑÑÑÐµÐºÑÐ¸Ð²Ð½Ð¾ÑÑÐ¸ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ; 4. ÐÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸, Ð´Ð¸ÑÐºÐ° Ð¸ ÑÐ¾ÑÐ¾ÑÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð½Ð¾Ð¹ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸; 5. ÐÐ¾ÑÐ°Ð±Ð¾ÑÐºÐ° Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¸Ñ Ð¼Ð°ÑÐµÐ¼Ð°ÑÐ¸ÑÐµÑÐºÐ¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð² Ð½Ð°Ð»Ð°Ð´ÐºÐµ Ð°Ð³ÑÐµÐ³Ð°ÑÐ° ÑÐ¿ÑÐ°Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÐµÐ¼. ÐÐ°Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° ÑÑÐ¸ÑÐ°ÐµÑÑÑ Ð°ÐºÑÑÐ°Ð»ÑÐ½Ð¾Ð¹ ÑÐ°Ðº ÐºÐ°Ðº, Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐµ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐµ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ð¸ ÑÐµÑÐ¸Ð¸ CFM56 Ð¸ÑÐ¿Ð¾Ð»ÑÐ·ÑÐµÐ¼ÑÐµ Ð´Ð»Ñ Ð¿Ð°ÑÑÐ°Ð¶Ð¸ÑÑÐºÐ¸ÑÂ  ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ¾Ð² Ð½ÑÐ¶Ð´Ð°ÑÑÑÑ Ð² Ð¸Ð¼Ð¿Ð¾ÑÑÐ¾Ð·Ð°Ð¼ÐµÑÐµÐ½Ð¸Ð¸, Ð±ÐµÐ· ÑÐµÑÑÐµÐ·Ð½ÑÑ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð²Ð½ÑÑ Ð²Ð¼ÐµÑÐ°ÑÐµÐ»ÑÑÑÐ² ÐºÐ°Ðº Ð¸ Ð² ÑÐ°Ð¼ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, ÑÐ°Ðº Ð¸ Ð² Ð¼Ð¾ÑÐ¾Ð³Ð¾Ð½Ð´Ð¾Ð»Ñ Ð»ÐµÑÐ°ÑÐµÐ»ÑÐ½ÑÑ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ¾Ð². Ð Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ° Ð±ÑÐ» Ð¿ÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÑ ÑÐ°Ð±Ð¾ÑÑ Ð½Ð°Ð´ Ð¼Ð°ÑÐµÐ¼Ð°ÑÐ¸ÑÐµÑÐºÐ¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»ÑÑ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÐ¶Ðµ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·ÑÑÑÑÑ Ð² Ð¿ÑÐ¾Ð¸Ð·Ð²Ð¾Ð´ÑÑÐ²Ðµ.
description: The purpose of this final qualification work of the bachelor is to calculate a double-circuit engine that provides a thrust of 110 kN. The work analyzes the original prototype CFM56 and uses its geometric dimensions to calculate the fan, compressor and combustion chamber in order to determine its main characteristics and parameters. The tasks that are performed during the study of the aircraft gas turbine engine: 1. Thermal calculation of engine parameters with selection of optimal option for further calculation; 2. Analysis of data of individual engine units using gas-dynamic parameters and calculations of compressor, combustion chamber and turbine; 3. Calculation of power obtained during turbine operation and further conclusion on engine operability and efficiency; 4. Strength test of the blade, disk and rotor of the last stage of the presented structure; 5. Rework of use of mathematical model in adjustment of engine control unit. This work is considered relevant since the CFM56 series aircraft gas turbine engines used for passenger aircraft need import substitution, without serious design interventions, both in the engine itself and in the engine nacelle of aircraft. In the final qualification work of the bachelor, the main parameters of the engine were calculated, as well as the results of work on a mathematical model of an aircraft gas turbine engine are already used in production.