title: Ð¢ÑÑÐ±Ð¾Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÐ¸Ð¿Ð° Ð¢Ð3-117
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 type TV3-117
Creators: name: Ð Ð¾Ð¼Ð°Ð½Ð¾Ð², Ð¤ÐµÐ´Ð¾Ñ
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
Ð¢Ð3-117
Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÐ°ÑÑÑÑ
gas turbine engine
turboshaft engine
TV3-117
helicopter engine
calculation

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»Ð¸ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ñ ÑÐ°ÑÑÑÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ (ÐÐÐ¢Ð) Ð¼Ð¾ÑÐ½Ð¾ÑÑÑÑ 1850 ÐºÐÑ. ÐÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð¾Ð¼ Ð±ÑÐ» Ð²ÑÐ±ÑÐ°Ð½ Ð²ÐµÑÑÐ¾Ð»ÐµÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¢Ð3-117, ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐ°Ð½Ð½ÑÐ¹ ÐÐ Â«ÐÐÐ-ÐÐ»Ð¸Ð¼Ð¾Ð²Â».
ÐÐ²Ð¸Ð³Ð°ÑÐµÐ»Ð¸ Ð¢Ð3-117 Ð¸, Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ð½ÑÐµ Ð½Ð° ÐµÐ³Ð¾ Ð±Ð°Ð·Ðµ, ÑÐ²Ð»ÑÑÑÑÑ Ð½Ð°Ð¸Ð±Ð¾Ð»ÐµÐµ ÑÐ°ÑÐ¿ÑÐ¾ÑÑÑÐ°Ð½ÑÐ½Ð½ÑÐ¼Ð¸ Ð² ÑÐ²Ð¾ÐµÐ¼ ÐºÐ»Ð°ÑÑÐµ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ¸ Ð¸ Ð°ÐºÑÐ¸Ð²Ð½Ð¾ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·ÑÑÑÑÑ Ð½Ðµ ÑÐ¾Ð»ÑÐºÐ¾ Ð½Ð° Ð²ÑÐµÐ¹ ÑÐµÑÑÐ¸ÑÐ¾ÑÐ¸Ð¸ Ð Ð¾ÑÑÐ¸Ð¸ Ð¸ Ð² ÑÑÑÐ°Ð½Ð°Ñ Ð¡ÐÐ, Ð½Ð¾ Ð¸ Ð² Ð·Ð°ÑÑÐ±ÐµÐ¶Ð½ÑÑ ÑÑÑÐ°Ð½Ð°Ñ. ÐÐ¾ÑÐ°Ð±Ð¾ÑÐºÐ° Ð¸ Ð¼Ð¾Ð´ÐµÑÐ½Ð¸Ð·Ð°ÑÐ¸Ñ ÑÑÐ¸Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÐµÐ¹ ÑÐ²Ð»ÑÑÑÑÑ ÑÑÑÐ°ÑÐµÐ³Ð¸ÑÐµÑÐºÐ¸Ð¼Ð¸ Ð·Ð°Ð´Ð°ÑÐ°Ð¼Ð¸ Ð´Ð»Ñ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¾ÑÑÐºÐ¾Ð³Ð¾ Ð±ÑÑÐ¾ ÐÐ Â«ÐÐÐ-ÐÐ»Ð¸Ð¼Ð¾Ð²Â». Ð¡Ð»ÐµÐ´ÑÑ Ð¸Ð· ÑÑÐ¾Ð³Ð¾, ÑÐµÐ¼Ñ Ð¼Ð¾Ð¶Ð½Ð¾ ÑÑÐ¸ÑÐ°ÑÑ Ð°ÐºÑÑÐ°Ð»ÑÐ½Ð¾Ð¹.
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Ð¹ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð¹ ÑÐ°ÑÑÐµÑ ÑÐ¸ÐºÐ»Ð° ÐÐ¢Ð, Ð²ÑÐ±Ð¾Ñ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½ÑÑ Ð´Ð°Ð½Ð½ÑÑ;
2. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÑÑ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°;
3. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÑÑ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ;
4. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÑÑ ÑÑÑÐ±Ð¸Ð½Ñ;
5. Ð¡ÑÐ°Ð²Ð½ÐµÐ½Ð¸Ðµ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÑÐ°ÑÑÑÐ¸ÑÐ°Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð¾Ð¼;
6. Ð Ð°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸, Ð´Ð¸ÑÐºÐ° Ð¸ ÑÐ¾ÑÐ¾ÑÐ°;
7. ÐÐ¿Ð¸ÑÐ°Ð½Ð¸Ðµ ÑÐµÑÐ½Ð¾Ð»Ð¾Ð³Ð¸Ð¸ Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ Ð»Ð¾Ð¿Ð°ÑÐ¾Ðº ÑÑÑÐ±Ð¸Ð½Ñ;
8. ÐÑÐ»ÐµÐ·Ð°ÑÐ¸ÑÐ½ÑÐµ ÑÑÑÑÐ¾Ð¹ÑÑÐ²Ð°, ÑÑÑÐ°Ð½Ð°Ð²Ð»Ð¸Ð²Ð°ÐµÐ¼ÑÐµ Ð½Ð° Ð¢Ð3-117.
Ð Ð¿ÑÐ¾ÑÐµÑÑÐµ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð±ÑÐ»Ð¾ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¾ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¿Ð¾ Ð·Ð½Ð°ÑÐ¸ÑÐµÐ»ÑÐ½Ð¾Ð¼Ñ ÑÐ²ÐµÐ»Ð¸ÑÐµÐ½Ð¸Ñ ÑÑÐµÐ¿ÐµÐ½Ð¸ Ð¿Ð¾Ð²ÑÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð·Ð° ÑÑÐµÑ Ð½ÐµÐ±Ð¾Ð»ÑÑÐ¾Ð³Ð¾ ÑÐ²ÐµÐ»Ð¸ÑÐµÐ½Ð¸Ñ Ð½Ð°ÑÑÐ¶Ð½Ð¾Ð³Ð¾ Ð´Ð¸Ð°Ð¼ÐµÑÑÐ° ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°. Ð Ð¸ÑÐ¾Ð³Ðµ ÑÐ´Ð°Ð»Ð¾ÑÑ Ð´Ð¾Ð±Ð¸ÑÑÑÑ ÑÐ²ÐµÐ»Ð¸ÑÐµÐ½Ð¸Ñ ÑÑÐµÐ¿ÐµÐ½Ð¸ Ð¿Ð¾Ð²ÑÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð² 1,7 ÑÐ°Ð·Ð°, Ð¿Ð¾ ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ñ Ñ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð¾Ð¼. Ð¢Ð°ÐºÐ¶Ðµ, ÑÐ´Ð°Ð»Ð¾ÑÑ ÑÐ²ÐµÐ»Ð¸ÑÐ¸ÑÑ Ð¼Ð¾ÑÐ½Ð¾ÑÑÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð½Ð° 380 ÐºÐÑ.
description: In this thesis the calculation and the design of aircraft gas-turbine engine (AGTE) in size of 1850 kilowatts were realized. The helicopter engine TV3-117, developed by JSC ââUEC-Klimovââ, was chosen as a prototype. 
TV2-117 engines and others built on its base are the most widespread in their power class and are actively exploited not only throughout Russia and in CIS states, but also in foreign countries. Enhancement and modernization of these engines are strategic objectives for engineering office of JSC ââUEC-Klimovââ. The chosen topic for studies could, therefore, be considered as relevant.
The content of explanatory note:
1) Variants thermal calculation of the gas-turbine engine cycle, the choice of optimized data; 
2) Gas dynamic calculation of compressor;
3) Gas dynamic calculation of combustion chamber;
4) Gas dynamic calculation of turbine;
5) Comparison of characteristics of the calculated engine with its prototype;
6) Structural analyses of blade, disc and rotor;
7) Description of manufacturing technology of turbine blades;
8) Dustproof mechanisms installed on TV3-117 engines. 
A study based on considerable increase of engine pressure ratio due to a slight increase of the outer diameter of compressor was carried out as a part of the process of engine design. As a result, it was possible to achieve an increase in the engine pressure ratio by 1.7 times compared with the prototype. Also, it was possible to increase the engine power by 380 kW.