title: Ð¢ÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 8 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: Turboshaft engine power 8 MW
Creators: name: ÐÑÐ±Ð¸Ð´Ð°Ð½, Ð Ð¾Ð¼Ð°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: 2019
Subjects: Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
gas-turbine engine
turbo-shaft engine
helicopter engine

description: Ð Ð´Ð°Ð½Ð½Ð¾Ð¹ 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 8 ÐÐÑ, Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð-136. 
ÐÐ¸Ð¿Ð»Ð¾Ð¼Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð²ÐºÐ»ÑÑÐ°ÐµÑÑÑ Ð² ÑÐµÐ±Ñ Ð²Ð²ÐµÐ´ÐµÐ½Ð¸Ðµ, ÑÐµÑÑÑÐµ Ð³Ð»Ð°Ð²Ñ Ð¸ Ð·Ð°ÐºÐ»ÑÑÐµÐ½Ð¸Ðµ. ÐÑÐ¾Ð¼Ðµ ÑÐ¾Ð³Ð¾, Ð² ÑÐ°Ð±Ð¾ÑÑ Ð²ÑÐ¾Ð´Ð¸Ñ ÑÐ¿ÐµÑÐ¸Ð°Ð»ÑÐ½Ð°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 Ð¿Ð¾ ÑÐµÐ¼Ðµ Ð¿ÑÐ»ÐµÐ·Ð°ÑÐ¸ÑÐ½ÑÐµ ÑÑÑÑÐ¾Ð¹ÑÑÐ²Ð° Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÐµÐ¹.
 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ÐµÐ¿Ð»Ð¾Ð²Ñ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Ð½Ð¾Ðµ Ð¾Ð±Ð¾ÑÐ½Ð¾Ð²Ð°Ð½Ð¸Ðµ ÑÐµÑÑÑÑÐ° ÑÐ°Ð±Ð¾ÑÑ ÐÐ¢Ð: Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½ÑÐµ ÑÐ°ÑÑÐµÑÑ Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ, 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 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¸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°.
description: In this final qualifying work, the design of a turbo-jet aircraft gas turbine engine (GTE) with a capacity of 8 MWt was performed, based on the D-136. 
The graduate work includes an introduction, four chapters and a conclusion. In addition, the work includes a special part devoted to the literature review on the topic of aircraft engine dust protection devices. 
The contents of the explanatory note: 
1. Variant thermal calculations of the GTE cycle, selection of the optimal variant and refinement of the selected option; 
2. Gas-dynamic calculations of the compressor, combustion chambers and turbines; 
3. Strength calculations of the last stage of the turbine, compilation of the vibration diagram of the blade. 
In the process of designing the engine, in comparison with the prototype, the combustion chamber was shortened, and the flow part of the turbine was redesigned. At the same time, it was possible to maintain high efficiency and economy of the prototype engine.