title: ÐÐ²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ ÑÑÐ³Ð¾Ð¹ 55 ÐºÐ
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: Dual-circuit engine with afterburner with a thrust of 55 kN
Creators: name: Ð¢ÑÐ¸ÑÐ¾Ð½Ð¾Ð², 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: 2020
Subjects: Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
General Electric f 404
ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð¸ÑÑÑÐµÐ±Ð¸ÑÐµÐ»Ñ
Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
gas turbine engine
turbojet engine
turbojet dual engine
fighter
aircraft 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±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ° Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ñ ÑÐ°ÑÑÑÑ Ð¸ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, ÑÐ°Ð±Ð¾ÑÐ°ÑÑÐµÐ³Ð¾ Ð½Ð° ÐºÐµÑÐ¾ÑÐ¸Ð½Ðµ, ÐºÐ¾ÑÐ¾ÑÑÐ¹ ÑÐ²Ð»ÑÐµÑÑÑ ÐºÐ¾Ð½Ð²ÐµÑÑÐ¸ÐµÐ¹ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ General Electric f 404. ÐÐ°Ð½Ð½ÑÐ¹ Ð¿ÑÐ¾ÐµÐºÑ ÑÐ²Ð»ÑÐµÑÑÑ Ð°Ð»ÑÑÐµÑÐ½Ð°ÑÐ¸Ð²Ð½Ð¾Ð¹ Ð¿ÑÐ¾ÑÐ°Ð±Ð¾ÑÐºÐ¾Ð¹, ÐµÐ³Ð¾ Ð¾ÑÐ»Ð¸ÑÐ°ÐµÑ Ð²Ð¾Ð·Ð¼Ð¾Ð¶Ð½Ð¾ÑÑÑ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¸Ñ ÑÐ·Ð»Ð¾Ð² Ð±Ð°Ð·Ð¾Ð²Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ General Electric f 404, ÑÑÐ¾ Ð´ÐµÐ»Ð°ÐµÑ ÐµÐ³Ð¾ ÑÐºÐ¾Ð½Ð¾Ð¼Ð¸ÑÐ½ÑÐ¼ Ð¸ Ð»ÐµÐ³ÐºÐ¸Ð¼ Ð¿ÑÐ¸ Ð¾ÑÐ²Ð¾ÐµÐ½Ð¸Ð¸ Ð² Ð¿ÑÐ¾Ð¸Ð·Ð²Ð¾Ð´ÑÑÐ²Ðµ. Ð¢Ð°ÐºÐ¸Ð¼ Ð¾Ð±ÑÐ°Ð·Ð¾Ð¼, Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° ÑÐ²Ð»ÑÐµÑÑÑ Ð°ÐºÑÑÐ°Ð»ÑÐ½Ð¾Ð¹ Ð¸ Ð²Ð¾ÑÑÑÐµÐ±Ð¾Ð²Ð°Ð½Ð½Ð¾Ð¹. ÐÐ°Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð½Ð°Ð¿ÑÐ°Ð²Ð»ÐµÐ½Ð° Ð½Ð° Ð¾Ð±Ð¾ÑÐ½Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¿ÑÐ¸ÑÐ¸Ð½ Ð½ÐµÐ¾Ð±ÑÐ¾Ð´Ð¸Ð¼Ð¾ÑÑÐ¸ ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ¸, Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ð¸ Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð² ÑÐ¸Ð»Ñ Ð±Ð¾Ð»ÑÑÐ¾Ð¹ ÐºÐ¾Ð½ÐºÑÑÐµÐ½ÑÐ¸Ð¸ Ð¼ÐµÐ¶Ð´Ñ ÑÑÑÐ°Ð½Ð°Ð¼Ð¸. Ð¡Ð¾Ð´ÐµÑÐ¶Ð°Ð½Ð¸Ðµ ÑÐ°ÑÑÐµÑÐ½Ð¾-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, Ð²ÑÐ±Ð¾Ñ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½ÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÑÐ°Ð±Ð¾ÑÑ; 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Ð±Ð¾ÑÐ½Ð¾Ð²Ð°Ð½Ð¸Ðµ ÑÐµÑÑÑÑÐ° ÑÐ°Ð±Ð¾ÑÑ: Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½ÑÐµ ÑÐ°ÑÑÐµÑÑ Ð¿ÐµÑÐ²Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ. Ð ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐµ ÑÐ°ÑÑÑÑÐ° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð¼Ñ Ð´Ð¾ÑÑÐ¸Ð³Ð»Ð¸ Ð½ÑÐ¶Ð½ÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð², Ð¿Ð¾ÑÑÐ¸ Ð½Ðµ Ð¸Ð·Ð¼ÐµÐ½Ð¸Ð² Ð´Ð¸Ð°Ð¼ÐµÑÑÐ°Ð»ÑÐ½ÑÐµ ÑÐ°Ð·Ð¼ÐµÑÑ Ð²Ð½ÑÑÑÐµÐ½Ð½ÐµÐ³Ð¾ ÐºÐ¾Ð½ÑÑÑÐ°, ÑÐ¾ÑÑÐ°Ð½Ð¸Ð² Ð¿ÑÐ¸ ÑÑÐ¾Ð¼ ÑÐ¾ÑÐ¾ÑÐ¸Ð¹ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½Ñ Ð¿Ð¾Ð»ÐµÐ·Ð½Ð¾Ð³Ð¾ Ð´ÐµÐ¹ÑÑÐ²Ð¸Ñ Ð¸ ÑÐ´ÐµÐ»ÑÐ½ÑÐ¹ ÑÐ°ÑÑÐ¾Ð´. 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¸Ð¼ÐµÐµÑ ÑÐºÐ¾Ð½Ð¾Ð¼Ð¸ÑÐµÑÐºÐ¸Ðµ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸ÐºÐ¸, ÑÐ¾Ð¿Ð¾ÑÑÐ°Ð²Ð¸Ð¼ÑÐµ Ñ Ð·Ð°ÑÑÐ±ÐµÐ¶Ð½ÑÐ¼Ð¸ Ð°Ð½Ð°Ð»Ð¾Ð³Ð°Ð¼Ð¸ Ð² Ð´Ð°Ð½Ð½Ð¾Ð¹ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ½Ð¾Ð¹ ÐºÐ°ÑÐµÐ³Ð¾ÑÐ¸Ð¸.
description: In this graduation qualification work of the bachelor, the calculation and design of a gas turbine engine operating on kerosene, which is a conversion of an aviation turbojet two-contour engine General Electric f 404, was performed. This project is an alternative study it is distinguished by the possibility of using the components of the base engine General Electric f 404, which makes it economical and easy to master in production. Thus, the work done is relevant and in demand. This work is aimed at justifying the reasons for the need to develop, design and manufacture this engine due to the great competition between countries. The contents of the settlement and explanatory notes: 1) Alternative thermal calculations, the choice of optimal operating parameters; 2) Gas-dynamic calculations of the compressor, the combustion chamber and the turbine; 3) Justification of the work resource: strength calculations of the first stage of the turbine. As a result of the calculation of the engine, we have reached the desired parameters, almost without changing the diametrical dimensions of the internal contour, while maintaining a good efficiency and specific consumption. The calculations showed that this gas turbine engine has economic characteristics comparable to foreign analogues in this power category.