title: Ð¢ÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 2 ÐÐÑ
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: 2 MW turboprop engine
Creators: name: ÐÐµÐ»Ð¾ÑÑÐ¾Ð², ÐÐ¾Ð½ÑÑÐ°Ð½ÑÐ¸Ð½
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: Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð¹
Ð¾ÑÐµÑÐµÐ½ÑÑÐ¾Ð±ÐµÐ¶Ð½ÑÐ¹ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÑÐ¸Ð»Ð¾Ð²Ð°Ñ ÑÑÑÐ±Ð¸Ð½Ð°
ÑÐ°ÑÑÐµÑ ÑÐ¾ÑÐ¾ÑÐ°
ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ° Ð¼ÐµÑÐ¾Ð´Ð¸ÐºÐ¸
aircraft engine
turboprop
axial centrifugal compressor
power turbine
rotor calculation
method development

description: Ð Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð¾Ð¿Ð¸ÑÐ°Ð½Ð° Ð¼ÐµÑÐ¾Ð´Ð¸ÐºÐ° Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 2 ÐÐÑ. ÐÑÐ»Ð¸ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ñ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÐµ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸ÐºÐ¸ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, ÑÐ°ÐºÐ¶Ðµ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÑ ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐµÑÑÐ° Ð² ÐºÐ¾Ð½ÑÑÐ¾Ð»ÑÐ½ÑÑ ÑÐµÑÐµÐ½Ð¸ÑÑ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ ÑÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð³Ð¾ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, ÑÐ°ÑÑÐ¼Ð¾ÑÑÐµÐ½Ð¾ Ð¾Ð±ÑÐµÐµ Ð¾Ð¿Ð¸ÑÐ°Ð½Ð¸Ðµ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. ÐÑÐ¿Ð¾Ð»Ð½ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ ÑÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ¸ 2 ÐÐÑ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ ÑÑÑÐµÑÑÐ²ÑÑÑÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° Ð¢Ð7-117Ð¡. ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÑÐµÐ¼Ñ, ÑÐ°ÑÑÐµÑ Ð¾ÑÐµÑÐµÐ½ÑÑÐ¾Ð±ÐµÐ¶Ð½Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð¿ÑÐ¾ÑÐ¸Ð²Ð¾Ñ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° Ð¸ ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ñ, ÑÐ°ÑÑÐµÑ Ð·Ð°ÐºÑÑÑÐºÐ¸ Ð¿Ð¾ÑÐ¾ÐºÐ° Ð² Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ñ. ÐÑÐ» Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² ÑÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð² Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð°Ñ MathCAD, SolidWorks, Ansys Workbench: Ð»Ð¾Ð¿Ð°ÑÐºÐ¸, Ð´Ð¸ÑÐºÐ° Ð¸ ÑÐ¾ÑÐ¾ÑÐ°; Ð²ÑÐ±ÑÐ°Ð½ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð» Ð´Ð»Ñ ÑÐ°Ð±Ð¾ÑÐ¸Ñ Ð»Ð¾Ð¿Ð°ÑÐ¾Ðº Ð¸ Ð´Ð¸ÑÐºÐ°. Ð ÐºÐ°ÑÐµÑÑÐ²Ðµ ÑÐ¿ÐµÑÐ¸Ð°Ð»ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ Ð² Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð±ÑÐ»Ð¾ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¾ Ð¼Ð¾Ð´ÐµÐ»Ð¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð¸ ÑÐ°ÑÑÐµÑ ÑÐ±Ð¾ÑÐºÐ¸ ÑÐ¾ÑÐ¾ÑÐ° Ñ ÐºÐ¾ÑÐ¿ÑÑÐ¾Ð¼ Ð² Ð¾ÑÐµÑÐµÑÑÐ²ÐµÐ½Ð½Ð¾Ð¼ Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð¾Ð¼ Ð¿ÑÐ¾Ð´ÑÐºÑÐµ DYNAMICS R4.
description: This paper describes the design methodology for an aircraft turboprop engine, 2 MW. The main characteristics of the aviation gas turbine engine were determined, also the parameters of the working process in the control sections of the flow section of the turboprop aircraft engine, the general description of the engine was considered. The calculation and design of a 2 MW turboprop engine based on the existing prototype TV7-117C was performed. The calculation of the thermal scheme, calculation of the axial centrifugal compressor, calculation of the countercurrent combustion chamber, gas-dynamic calculation of the flow part of the compressor turbine and free turbine, calculation of the flow twist in the last stage of the free turbine. Strength calculation of the main elements of turboprop engine in MathCAD, SolidWorks, Ansys Workbench programs: blade and rotor; material for working blades and disk was selected. As a special part of this work, modeling and calculation of the rotor and housing assembly was performed in the domestic software product DYNAMICS R4.