title: Ð¢ÑÑÐ±Ð¾Ð²Ð¸Ð½ÑÐ¾Ð²Ð¾Ð¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 2,2 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: 2.2 MW Turboprop Engine
Creators: name: ÐÑÐ°ÑÐ¸Ð»ÑÐ½Ð¸ÐºÐ¾Ð², Ð¡ÐµÑÐ³ÐµÐ¹
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¸Ð½ÑÐ¾Ð²Ð¾Ð¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð¢Ð7-117
Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð´Ð²ÑÑ Ð²Ð°Ð»ÑÐ½ÑÐ¹ ÐÐ¢Ð
TV7-117
gas turbine engine
aircraft engine
twin-shaft gas turbine engine

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 2,2 ÐÐÑ, Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¢Ð7-117 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. 
Ð¡Ð¾Ð´ÐµÑÐ¶Ð°Ð½Ð¸Ðµ Ð¿Ð¾ÑÑÐ½Ð¸ÑÐµÐ»ÑÐ½Ð¾Ð¹ Ð·Ð°Ð¿Ð¸ÑÐºÐ¸:
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°;
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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 Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð¿Ð¾ ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ñ Ñ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð¾Ð¼, 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±ÑÐ»Ð° Ð¸Ð·Ð¼ÐµÐ½ÐµÐ½Ð° Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸Ñ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸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ÑÐ¾Ð¼ ÑÐ´Ð°Ð»Ð¾ÑÑ ÑÐ¾ÑÑÐ°Ð½Ð¸ÑÑ Ð²ÑÑÐ¾ÐºÐ¸Ðµ Ð¿Ð¾ÐºÐ°Ð·Ð°ÑÐµÐ»Ð¸ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½ÑÐ° Ð¿Ð¾Ð»ÐµÐ·Ð½Ð¾Ð³Ð¾ Ð´ÐµÐ¹ÑÑÐ²Ð¸Ñ Ð¸ ÑÐºÐ¾Ð½Ð¾Ð¼Ð¸ÑÐ½Ð¾ÑÑÐ¸ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð°.
 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 final qualifying work, the design of a turboshaft aviation gas turbine engine (GTE) with a capacity of 2.2 MW was carried out, based on the TV7-117 aircraft engine developed by JSC Â«UEC-KlimovÂ».
Thesis includes 3 main chapters on engine calculations, introduction, conclusion. In addition, the work included a technological part devoted to a literature review of the technological process of manufacturing disks of a turbine of the first stage, as well as a special part containing.
The contents of the explanatory note:
1. Variant calculations of the GTE cycle, selection of the optimal variant and refinement of the selected option;
2. Gas-dynamic calculations of the compressor, the combustion chamber and the turbine;
3. Strength calculations of a free turbine: blades, disk, rotor; compilation of the vibration diagram of the blade and the rotor.
In the process of designing the engine, in comparison with the prototype, the flow section of the compressor was redesigned, the geometry of the combustion chamber was changed, the flow section of the turbine was redesigned. At the same time, it was possible to maintain high rates of efficiency and efficiency of the prototype engine.
 The calculations showed that this gas turbine engine is not inferior in its characteristics to foreign analogues.