title: ÐÐ²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 70 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: Two-circuit engine with 70 kN thrust
Creators: name: ÐÐ²Ð°Ð½Ð¾Ð²Ð°, ÐÐ»ÐµÐºÑÐ°Ð½Ð´Ñ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: Ð-36
Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹
ÑÑÐ³Ð° 70ÐºÐ
Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾Ñ
ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ¾Ð»ÑÑÐµÐ²Ð°Ñ ÐºÑ
ÑÑÑÐ±Ð¸Ð½Ð°
D-36
by-pass engine
thrust 70kN
fan
compressor
ring cc
turbine

description: ÐÐ°Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð° ÑÐ°ÑÑÑÑÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÑÐ³Ð¾Ð¹ 70 ÐºÐ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð-36. Ð Ð°Ð±Ð¾ÑÐ° ÑÐ°Ð·Ð´ÐµÐ»ÐµÐ½Ð° Ð½Ð° ÑÐµÐ¼Ñ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ Ð³Ð»Ð°Ð², Ð² ÐºÐ¾ÑÐ¾ÑÑÑ Ð±ÑÐ»Ð¸ ÑÐ°ÑÑÑÐ¸ÑÐ°Ð½Ñ Ð°Ð³ÑÐµÐ³Ð°ÑÑ ÑÑÑÐ°Ð½Ð¾Ð²ÐºÐ¸, ÑÐ°ÐºÐ¸Ðµ ÐºÐ°Ðº: Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾Ñ, ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ, ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ, ÑÑÑÐ±Ð¸Ð½Ð° Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ, ÑÑÑÐ±Ð¸Ð½Ð° Ð½Ð¸Ð·ÐºÐ¾-Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð¸ ÑÑÑÐ±Ð¸Ð½Ð° Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾ÑÐ°. ÐÐ¾ÑÐ»Ðµ ÑÐ°ÑÑÐµÑÐ° ÑÐ²Ð¾Ð±Ð¾Ð´Ð½Ð¾Ð¹ ÑÐ½ÐµÑÐ³Ð¸Ð¸ Ð¸ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÐÐ¢Ð Ð±ÑÐ» Ð¿ÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ Ð² Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ðµ A2GTE, ÐºÐ¾ÑÐ¾ÑÑÐ¹ Ð¿Ð¾Ð·Ð²Ð¾Ð»Ð¸Ð» Ð²ÑÐ±ÑÐ°ÑÑ ÑÑÐµÐ¿ÐµÐ½Ñ Ð¿Ð¾Ð²ÑÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð² ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐµ Ð¸ ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÑ Ð³Ð°Ð·Ð° Ð¿ÐµÑÐµÐ´ ÑÑÑÐ±Ð¸Ð½Ð¾Ð¹. Ð¡Ð»ÐµÐ´ÑÑÑÐ¸Ð¼ ÑÐ°Ð·Ð´ÐµÐ»Ð¾Ð¼ Ð±ÑÐ» ÑÐ°ÑÑÐµÑ Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾ÑÐ°, ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ¾Ð² Ð½Ð¸Ð·ÐºÐ¾Ð³Ð¾ Ð¸ Ð²ÑÑÐ¾ÐºÐ¾Ð³Ð¾ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ñ ÑÑÐµÑÐ¾Ð¼ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð°. Ð Ð°ÑÑÐµÑ Ð¿Ð¾Ð·Ð²Ð¾Ð»Ð¸Ð» Ð¿ÑÐµÑÑÑÐ¿Ð¸ÑÑ Ðº ÑÐ°ÑÑÐµÑÑ ÑÑÑÐ±Ð¸Ð½Ñ, Ð° ÑÐ°ÐºÐ¶Ðµ Ð±ÑÐ»Ð¸ Ð¿Ð¾Ð»ÑÑÐµÐ½Ñ Ð³Ð°Ð±Ð°ÑÐ¸ÑÐ½ÑÐµ ÑÐ°Ð·Ð¼ÐµÑÑ, ÐºÐ¾ÑÐ¾ÑÑÐµ Ð±ÑÐ»Ð¸ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ñ Ð´Ð»Ñ Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ð¸Ñ ÑÐµÑÑÐµÐ¶Ð° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ ÑÑÑÐ±Ð¸Ð½Ñ, Ð² ÐºÐ¾ÑÐ¾ÑÐ¾Ð¼ Ð±ÑÐ»Ð¾ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¾ Ð¿ÑÐ¾ÑÐ¸Ð»Ð¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð¼Ð¾ÑÐ½Ð¾ÑÑÐ¸ Ð¸ ÐÐÐ, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÐ°ÑÑÐµÑ Ð·Ð°ÐºÑÑÑÐºÐ¸ Ð¿Ð¾ÑÐ¾ÐºÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð¸ Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ð¸Ðµ Ð¿ÑÐ¾ÑÐ¸Ð»Ñ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¿Ð¾ Ð¿ÑÑÐ¸ ÑÐ°ÑÑÑÐ¸ÑÐ°Ð½Ð½ÑÐ¼ ÑÐµÑÐµÐ½Ð¸ÑÐ¼. ÐÐ¾ Ð¿ÑÐ¾ÑÐ¸Ð»ÑÐ¼ ÑÐµÑÐµÐ½Ð¸Ð¹ Ð¸ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð½ÑÐ¼ Ð¸Ñ ÑÐµÐ½ÑÑÐ°Ð¼ Ð¼Ð°ÑÑ Ð±ÑÐ»Ð° Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ð° Ð¾Ð±ÑÐµÐ¼Ð½Ð°Ñ Ð¼Ð¾Ð´ÐµÐ»Ñ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸. Ð­ÑÐ¾ Ð¿Ð¾Ð·Ð²Ð¾Ð»Ð¸Ð»Ð¾ Ð¿ÑÐ¾Ð²ÐµÑÑÐ¸ ÐµÐµ ÑÐ°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ. Ð¢Ð°Ðº Ð¶Ðµ Ð±ÑÐ»Ð¸ Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ñ Ð¸ ÑÐ°ÑÑÑÐ¸ÑÐ°Ð½Ñ Ð´Ð¸ÑÐº Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ Ð¸ ÑÐ¾ÑÐ¾Ñ Ð²ÐµÐ½ÑÐ¸Ð»ÑÑÐ¾ÑÐ°, Ð² ÐºÐ¾ÑÐ¾ÑÐ¾Ð¼ Ð±ÑÐ» Ð¿ÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ ÐºÑÐ¸ÑÐ¸ÑÐµÑÐºÐ¸Ñ ÑÐ°ÑÑÐ¾Ñ Ð²ÑÐ°ÑÐµÐ½Ð¸Ñ. Ð ÑÐ¾ÑÐ¾Ñ Ð²ÑÐ¾Ð´Ð¸Ð»Ð¸ Ð²Ð°Ð» Ð¸ ÑÐµÑÑÑÐµ Ð´Ð¸ÑÐºÐ°. Ð ÑÐ°Ð±Ð¾ÑÐµ Ð¿ÑÐ¸ÑÑÑÑÑÐ²ÑÐµÑ ÐºÑÐ°ÑÐºÐ¾Ðµ Ð¾Ð¿Ð¸ÑÐ°Ð½Ð¸Ðµ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐ·Ð»Ð¾Ð² ÐÐ¢Ð. ÐÐ°Ð²ÐµÑÑÐ°ÐµÑ ÑÑÑ ÑÐ°Ð±Ð¾ÑÑ ÑÐ°ÑÑÐ¼Ð¾ÑÑÐµÐ½Ð¸Ðµ ÑÐµÑÐ½Ð¾Ð»Ð¾Ð³Ð¸Ð¸ Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð¸ÑÐºÐ° Ð¿ÐµÑÐ²Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸ Ð³Ð°Ð·Ð¾Ð²Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ñ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. Ð ÑÑÐ¾Ð¼ ÑÐ°Ð·Ð´ÐµÐ»Ðµ Ð¾Ð¿Ð¸ÑÑÐ²Ð°ÑÑÑÑ ÑÑÐµÐ±Ð¾Ð²Ð°Ð½Ð¸Ñ, ÑÐµÑÐ½Ð¾Ð»Ð¾Ð³Ð¸Ð¸ Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ, Ð²ÑÐ±Ð¾Ñ Ð·Ð°Ð³Ð¾ÑÐ¾Ð²Ð¾Ðº Ð¸ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ð¾Ð², Ð° ÑÐ°ÐºÐ¶Ðµ Ð¼ÐµÑÐ¾Ð´Ñ Ð¸Ð·Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð¸Ñ Ð´Ð¸ÑÐºÐ¾Ð².
description: This work is devoted to the calculation of the engine with a thrust of 70 kN on the basis of a prototype of gas-turbine aircraft engine D-36. The work is divided into seven main chapters in which the units of the unit have been calculated, such as: fan, low pressure compressor, high pressure turbine, low pressure turbine and fan turbine. After calculating free energy and GTE parameters, a calculation was made in the A2GTE program, which made it possible to select the degree of pressure increase in the compressor and the gas temperature before the turbine. The next section was the calculation of the fan, low and high pressure compressors with the prototype in mind. The calculation allowed the turbine to be calculated and the dimensions were obtained, which were used to construct the engine drawing. Gas-dynamic calculation of the turbine, which was carried out profiling of the flow part, the determination of power and efficiency, as well as the calculation of the twisting of the flow of the last stage of the turbine and the construction of the blade profile for five calculated sections. A volumetric model of the blade was built on the sections' profiles and their defined mass centers. This allowed its strength calculation to be carried out. The disk of the last stage of the turbine and the fan rotor were also constructed and calculated, in which critical speeds were calculated. The rotor included a shaft and four discs. In the work there is a brief description of the main components of the GTE. This work is completed by a review of the technology of manufacturing the first stage of the gas turbine disk of the aircraft engine. This section describes requirements, manufacturing techniques, selection of blanks and materials, as well as disc manufacturing methods.