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 Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÑÐ³Ð¾Ð¹ 147 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 bypass aircraft engine with a thrust of 147 kN
Creators: name: ÐÐ°Ð½ÑÐ¾Ð², ÐÑÑÑÐ¼
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: 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ÐÐ ) Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð° ÑÐ°ÑÑÐµÑÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐ²Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð³ÑÐ°Ð¶Ð´Ð°Ð½ÑÐºÐ¾Ð³Ð¾ Ð½Ð°Ð·Ð½Ð°ÑÐµÐ½Ð¸Ñ Ñ ÑÑÐ³Ð¾Ð¹ 147 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° ÐÐ-14, ÑÐ¾ÑÑÐ¸Ð¹ÑÐºÐ¾Ð³Ð¾ ÑÑÑÐ±Ð¾Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ 5-Ð³Ð¾ Ð¿Ð¾ÐºÐ¾Ð»ÐµÐ½Ð¸Ñ, Ð¿ÑÐµÐ´Ð½Ð°Ð·Ð½Ð°ÑÐµÐ½Ð½Ð¾Ð³Ð¾ Ð´Ð»Ñ ÑÑÐµÐ´Ð½ÐµÐ¼Ð°Ð³Ð¸ÑÑÑÐ°Ð»ÑÐ½Ð¾Ð³Ð¾ ÑÐ·ÐºÐ¾ÑÑÐ·ÐµÐ»ÑÐ¶Ð½Ð¾Ð³Ð¾ Ð¿Ð°ÑÑÐ°Ð¶Ð¸ÑÑÐºÐ¾Ð³Ð¾ ÑÐ°Ð¼Ð¾Ð»ÑÑÐ° ÐÐ¡-21. Ð ÑÐ¾Ð´Ðµ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ñ ÐÐÐ  Ð±ÑÐ»Ð¾ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¾: 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 ÐÐ-14. 2. ÐÑÐ±Ð¾Ñ ÑÐµÐ¶Ð¸Ð¼Ð° ÑÐ°Ð±Ð¾ÑÑ Ð¸ Ð¾ÑÑÑÐµÑÑÐ²Ð»ÐµÐ½Ð¸Ðµ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ½Ð¾Ð³Ð¾ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð³Ð¾ ÑÐ°ÑÑÐµÑÐ° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. 3. Ð Ð°ÑÑÐµÑ 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Ð¾Ð¼ ÑÐ¸ÑÐ»Ðµ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ. 4. ÐÑÐ¾ÑÐ½Ð¾ÑÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐµÑ 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Ð°ÐºÐ¶Ðµ ÑÐ¾ÑÐ¾ÑÐ° Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ. 5. Ð Ð°ÑÑÐ¼Ð¾ÑÑÐµÐ½Ð¸Ðµ Ð²Ð¾Ð·Ð¼Ð¾Ð¶Ð½Ð¾ÑÑÐ¸ Ð¿ÑÐ¸Ð¼ÐµÐ½ÐµÐ½Ð¸Ñ ÐºÐµÑÐ°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ð¾Ð² Ð¸ ÐºÐ¾Ð¼Ð¿Ð¾Ð·Ð¸ÑÐ¾Ð² Ð² ÑÑÑÐ±Ð¸Ð½Ð¾ÑÑÑÐ¾ÐµÐ½Ð¸Ð¸. 6. ÐÐ¾ÑÑÑÐ¾ÐµÐ½Ð¸Ðµ Ð¿ÑÐ¾Ð´Ð¾Ð»ÑÐ½Ð¾Ð³Ð¾ ÑÐ°Ð·ÑÐµÐ·Ð° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»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 Ð¸ Word, SolidWorks, ÐÐÐÐÐÐ¡-3D, Ansys Workbench, MathCAD Ð¸ Siemens NX.
description: This final qualification work is devoted to the calculation and design of a turbojet two-circuit twin-shaft aviation engine of 147 kN directional thrust based on the ÐÐ-14 prototype, a Russian 5th generation turbofan engine intended for the medium-haul narrow-body passenger aircraft ÐÐ¡-21. To perform the graduate qualification work, the following tasks were solved: 1. Familiarization with construction and design features of the ÐÐ-14 engine. 2. Selecting the operating mode and performing a variant thermal calculation of the engine. 3. Calculation of the main engine components, such as the compressor, combustion chamber and turbine. Including gas-dynamic calculations and design of a low-pressure turbine. 4. Strength calculation of the working blade and disk of the last stage of the turbine and the low-pressure rotor. 5. Consideration of the possibility of using ceramic materials and composites in turbine construction. 6. Construction of a longitudinal section of the engine. The following software was used to perform the work: MS Excel and Word, SolidWorks, KOMPAS-3D, Ansys Workbench, MathCAD and Siemens NX.