title: ÐÐ¾Ð´ÐµÑÐ½Ð¸Ð·Ð¸ÑÐ¾Ð²Ð°Ð½Ð½ÑÐ¹ ÑÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÐ¾ ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ð¾Ð¹ Ð¢Ð3-117Ð
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: Modernized turboshaft engine with power turbine TV3-117V
Creators: name: ÐÐ°ÑÑÑÑÐ¾Ð², ÐÐ¸ÑÐ°Ð¸Ð»
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: 2019
Subjects: ÑÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð¢Ð3-117ÐÐ
Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð´Ð²ÑÑ Ð²Ð°Ð»ÑÐ½ÑÐ¹ ÐÐ¢Ð
turboshaft engine
TV3-117VM
gas turbine engine
helicopter engine
two spool GTE

description: Ð Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð±ÑÐ»Ð¾ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¾ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ ÑÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ (ÐÐ¢Ð) Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 2ÐÐÑ, Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¢Ð3-117ÐÐ ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ¸ ÐÐ Â«ÐÐÐ-ÐÐ»Ð¸Ð¼Ð¾Ð²Â».
Ð Ð´Ð¸Ð¿Ð»Ð¾Ð¼Ð½ÑÑ ÑÐ°Ð±Ð¾ÑÑ Ð²ÑÐ¾Ð´ÑÑ 3 Ð¾ÑÐ½Ð¾Ð²Ð½ÑÐµ Ð³Ð»Ð°Ð²Ñ, Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð½ÑÐµ ÑÐ°ÑÑÐµÑÐ°Ð¼ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð²Ð²ÐµÐ´ÐµÐ½Ð¸Ðµ, Ð·Ð°ÐºÐ»ÑÑÐµÐ½Ð¸Ðµ. ÐÑÐ¾Ð¼Ðµ ÑÐ¾Ð³Ð¾, Ð² ÑÐ°Ð±Ð¾ÑÑ Ð²ÐºÐ»ÑÑÐµÐ½Ð° ÑÐµÑÐ½Ð¾Ð»Ð¾Ð³Ð¸ÑÐµÑÐºÐ°Ñ ÑÐ°ÑÑÑ, Ð¿Ð¾ÑÐ²ÑÑÑÐ½Ð½Ð°Ñ Ð»Ð¸ÑÐµÑÐ°ÑÑÑÐ½Ð¾Ð¼Ñ Ð¾Ð±Ð·Ð¾ÑÑ ÑÐµÑÐ½Ð¾Ð»Ð¾Ð³Ð¸ÑÐµÑÐºÐ¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐµÑÑÐ° Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð¸ÑÐºÐ¾Ð² ÑÑÑÐ±Ð¸Ð½Ñ Ð¿ÐµÑÐ²Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÐ¿ÐµÑÐ¸Ð°Ð»ÑÐ½ÑÑ ÑÐ°ÑÑÑ, ÑÐ¾Ð´ÐµÑÐ¶Ð°ÑÑÑ ÑÐ°ÑÑÐµÑ ÑÑÑÐ±Ð¾ÑÑÐ°ÑÑÐµÑÐ° Ð¢Ð¡-21. 
Ð¡Ð¾Ð´ÐµÑÐ¶Ð°Ð½Ð¸Ðµ Ð¿Ð¾ÑÑÐ½Ð¸ÑÐµÐ»ÑÐ½Ð¾Ð¹ Ð·Ð°Ð¿Ð¸ÑÐºÐ¸:
1. ÐÐ°ÑÐ¸Ð°Ð½ÑÐ½ÑÐµ ÑÐ°ÑÑÐµÑÑ ÑÐ¸ÐºÐ»Ð° ÐÐ¢Ð, Ð²ÑÐ±Ð¾Ñ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ° Ð¸ ÑÑÐ¾ÑÐ½ÐµÐ½Ð¸Ðµ Ð²ÑÐ±ÑÐ°Ð½Ð½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ°;
2. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ðµ ÑÐ°ÑÑÐµÑÑ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ;
3. ÐÑÐ¾ÑÐ½Ð¾ÑÑÐ½ÑÐµ ÑÐ°ÑÑÐµÑÑ ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ñ: Ð»Ð¾Ð¿Ð°ÑÐºÐ¸, Ð´Ð¸ÑÐºÐ°, ÑÐ¾ÑÐ¾ÑÐ°; ÑÐ¾ÑÑÐ°Ð²Ð»ÐµÐ½Ð¸Ðµ Ð²Ð¸Ð±ÑÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ Ð´Ð¸Ð°Ð³ÑÐ°Ð¼Ð¼Ñ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¸ ÑÐ¾ÑÐ¾ÑÐ°.
Ð Ð¿ÑÐ¾ÑÐµÑÑÐµ ÑÐ°ÑÑÐµÑÐ° Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð±ÑÐ»Ð° Ð¿ÐµÑÐµÐ¿ÑÐ¾ÑÐ¸Ð»Ð¸ÑÐ¾Ð²Ð°Ð½Ð° Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð°Ñ ÑÐ°ÑÑÑ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, Ð¸Ð·Ð¼ÐµÐ½ÐµÐ½ ÑÐ¸Ð¿ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ° Ð½Ð° Ð¾ÑÐµÑÐµÐ½ÑÑÐ¾Ð±ÐµÐ¶Ð½ÑÐ¹, ÑÐ¼ÐµÐ½ÑÑÐµÐ½Ð¾ ÐºÐ¾Ð»Ð¸ÑÐµÑÑÐ²Ð¾ ÑÑÑÐ¿ÐµÐ½ÐµÐ¹ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, Ð¸Ð·Ð¼ÐµÐ½ÐµÐ½Ð° ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ð½Ð° Ð¿ÑÐ¾ÑÐ¸Ð²Ð¾ÑÐ¾ÑÐ½ÑÑ, Ð¿ÐµÑÐµÐ¿ÑÐ¾ÑÐ¸Ð»Ð¸ÑÐ¾Ð²Ð°Ð½Ð° Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð°Ñ ÑÐ°ÑÑÑ ÑÑÑÐ±Ð¸Ð½Ñ. ÐÑÐ¸ ÑÐ¼ÐµÐ½ÑÑÐµÐ½Ð¸Ð¸ Ð´Ð»Ð¸Ð½Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÐ´Ð°Ð»Ð¾ÑÑ Ð´Ð¾Ð±Ð¸ÑÑÑÑ ÑÐ²ÐµÐ»Ð¸ÑÐµÐ½Ð¸Ñ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ¸, ÑÑÐµÐ¿ÐµÐ½Ð¸ Ð¿Ð¾Ð²ÑÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð² ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐµ, ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÑ Ð³Ð°Ð·Ð° Ð¿ÐµÑÐµÐ´ ÑÑÑÐ±Ð¸Ð½Ð¾Ð¹.
 ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð½ÑÐµ ÑÐ°ÑÑÐµÑÑ Ð¿Ð¾ÐºÐ°Ð·Ð°Ð»Ð¸, ÑÑÐ¾ Ð´Ð°Ð½Ð½ÑÐ¹ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¿Ð¾ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸ÐºÐ°Ð¼ Ð½Ðµ ÑÑÑÑÐ¿Ð°ÐµÑ Ð·Ð°ÑÑÐ±ÐµÐ¶Ð½ÑÐ¼ Ð°Ð½Ð°Ð»Ð¾Ð³Ð°Ð¼.
description: In the qualifying work, was designed turboshaft aircraft gas turbine engine (GTE) with capacity of 2 MW, based on the TV3-117VM helicopter engine developed by JSC Â«UEC-KlimovÂ».
 The graduate work includes 3 chapters, which dedicated engine calculations, introduction and conclusion. In addition, the work includes technological part, devoted to the literature review technological process of manufacturing turbine disk of first stage, also special part, devoted calculate of the turbo starter TS-21.
 The content of the explanatory note:
1. Variable thermal calculations of the GTE cycle, selection of the optimal variant and refinement of the selected option;
2. Gas-dynamic calculation of the compressor, combustion chamber and turbine;
3. Strength calculations of power turbine: blade, disk, rotor.
In the process of designing the engine redeveloped flow part of the compressor, was changed type of the compressor on acentropic, the number of stages compressor was reduced, the type of combustion chamber was been changed on countercurrent, and the flow part of turbine was redesigned. Length reduction engine allowed gain power, compressor pressure ratio, burner exit temperature.
Calculations illustrated, what the gas turbine engine doesnât worse than foreign engines characters.