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: Turboprop engine power of 2.2 MW
Creators: name: ÐÑÐ¹Ð¼Ð¸ÑÑÑÐ¾Ð²Ð°, ÐÐ½Ð½Ð°
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: 2020
Subjects: Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð´Ð²ÑÑ Ð²Ð°Ð»ÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
gas turbine engine
two-shaft engine
aircraft engine

description: Ð¦ÐµÐ»ÑÑ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ ÑÐ²Ð»ÑÐµÑÑÑ ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ° ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° â ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð 95Ð¨ ÑÐ¾ ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ð¾Ð¹. ÐÐ°Ð´Ð°ÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµ ÑÐµÑÐ°Ð»Ð¸ÑÑ Ð² ÑÐ¾Ð´Ðµ ÑÐ°Ð±Ð¾ÑÑ: 1. ÐÑÐ±Ð¾Ñ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð²Ð½Ð¾Ð¹ ÑÑÐµÐ¼Ñ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. 2. ÐÑÐ±Ð¾Ñ Ð½Ð°Ð¸Ð±Ð¾Ð»ÐµÐµ ÑÐ°ÑÐ¸Ð¾Ð½Ð°Ð»ÑÐ½ÑÑ ÑÑÐµÐ¼ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. 3. Ð£Ð´Ð¾Ð²Ð»ÐµÑÐ²Ð¾ÑÐµÐ½Ð¸Ðµ Ð¾Ð±ÑÐ¸Ñ ÑÑÐµÐ±Ð¾Ð²Ð°Ð½Ð¸Ð¹ Ðº Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÐºÐ¸ Ð·ÑÐµÐ½Ð¸Ñ Ð²Ð¾Ð·Ð¼Ð¾Ð¶Ð½Ð¾ÑÑÐ¸ ÑÐºÑÐ¿Ð»ÑÐ°ÑÐ°ÑÐ¸Ð¸ ÐµÐ³Ð¾ Ð¿Ð¾ ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¾Ð¼Ñ ÑÐ¾ÑÑÐ¾ÑÐ½Ð¸Ñ. ÐÐ»Ñ Ð´Ð¾ÑÑÐ¸Ð¶ÐµÐ½Ð¸Ñ Ð¿Ð¾ÑÑÐ°Ð²Ð»ÐµÐ½Ð½Ð¾Ð¹ ÑÐµÐ»Ð¸, Ð½Ð°Ð¼ Ð½ÐµÐ¾Ð±ÑÐ¾Ð´Ð¸Ð¼Ð¾ Ð¿ÑÐ¾Ð²ÐµÑÑÐ¸ ÑÐ»ÐµÐ´ÑÑÑÐ¸Ðµ ÑÐ°ÑÑÑÑÑ: â ÐÐ°ÑÐ¸Ð°Ð½ÑÐ½ÑÐµ ÑÐµÑÐ¼Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸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°; â 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; â ÐÑÐ¾Ð¸Ð·Ð²ÐµÑÑÐ¸ ÑÐ°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ. Ð ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐµ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð½ÑÑ ÑÐ°ÑÑÐµÑÐ¾Ð² ÑÐ´Ð°Ð»Ð¾ÑÑ ÑÐ¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°ÑÑ ÑÐ¾Ð²ÑÐµÐ¼ÐµÐ½Ð½ÑÐ¹ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¸Ð½ÑÑÐ¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð°. â
description: The given work is devoted to the development of the design of a gas turbine engine based on the prototype - the R95Sh turbojet engine with a free turbine. The research set the following goals: 1. The choice of engine design. 2. The choice of the most rational schemes of engine elements. 3. Satisfaction of the general requirements for the engine in terms of the possibility of its operation according to the technical condition. The work includes a preliminary calculation of the engine parameters, gas-dynamic calculation of the compressor, gas-dynamic calculation of the countercurrent combustion chamber, gas-dynamic calculation of the turbine, and strength analysis of the working blade of the last stage of the turbine. To achieve this goal, we need to carry out the following calculations: â Variant thermodynamic calculations of the gas turbine engine cycle, selection of the best option and refinement of the chosen option; â Gas-dynamic calculations of the compressor, combustion chamber and turbine; â Calculate the strength of the blades of the last stage of the turbine. As a result of the calculations, it was possible to design a modern aircraft engine based on the adopted prototype.