title: ÐÐ²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 40 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: Double-circuit engine with a 40 kN thrust
Creators: name: ÐÐ¾ÑÐ²Ð¸Ð½ÐºÐ¸Ð½Ð°, ÐÐ°ÑÐ¸Ñ
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: ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÑÑÐ³Ð° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÐÐ-22
Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð¿Ð°ÑÑÐ°Ð¶Ð¸ÑÑÐºÐ¾Ð³Ð¾ ÑÐ°Ð¼Ð¾Ð»ÑÑÐ°
turbojet engine
engine thrust
AI-22
passenger aircraft engine

description: Ð¢ÐµÐ¼Ð° Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ: Â«ÐÐ²ÑÑÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÑÑÐ³Ð¾Ð¹ 40 ÐºÐÂ». Ð¦ÐµÐ»ÑÑ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ ÑÐ²Ð»ÑÐµÑÑÑ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° ÐÐ-22. ÐÑÐ½Ð¾Ð²Ð½ÑÐ¼Ð¸ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ°Ð¼Ð¸, Ð² Ð±Ð¾Ð»ÑÑÐµÐ¹ ÑÑÐµÐ¿ÐµÐ½Ð¸ Ð²Ð»Ð¸ÑÑÑÐ¸Ð¼Ð¸ Ð½Ð° Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð½ÑÐ¹ ÑÐ°ÑÑÑÑ, Ð²ÑÑÑÑÐ¿Ð°ÑÑ ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÐ° Ð·Ð° ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ, ÑÑÐµÐ¿ÐµÐ½Ñ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾ÑÑÐ¸ Ð¸ ÑÑÐ³Ð° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ. ÐÐ°Ð´Ð°ÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµ ÑÐµÑÐ°ÑÑÑÑ Ð² ÑÐ¾Ð´Ðµ Ð´Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ: 1. ÐÐ·ÑÑÐµÐ½Ð¸Ðµ Ð¾ÑÐ¾Ð±ÐµÐ½Ð½Ð¾ÑÑÐµÐ¹ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° Ð°Ð²Ð¸Ð°Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ ÐÐ-22. 2. ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¸Ðµ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ½Ð¾Ð³Ð¾ ÑÐµÐ¿Ð»Ð¾Ð²Ð¾Ð³Ð¾ ÑÐ°ÑÑÑÑÐ° ÑÐ¸ÐºÐ»Ð° Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð²ÑÐ±Ð¾ÑÐ¾Ð¼ Ð¾Ð¿ÑÐ¸Ð¼Ð°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ°. 3. ÐÐ½Ð°Ð»Ð¸Ð· Ð´Ð°Ð½Ð½ÑÑ Ð¾ÑÐ´ÐµÐ»ÑÐ½ÑÑ ÑÐ·Ð»Ð¾Ð² Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½Ð¾Ð³Ð¾ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ Ð¿Ð¾Ð¼Ð¾ÑÑÑ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¸ Ð¿ÑÐ¸Ð±Ð»Ð¸Ð¶ÐµÐ½Ð½ÑÑ ÑÐ°ÑÑÑÑÐ¾Ð² ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°, ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ Ð¸ ÑÑÑÐ±Ð¸Ð½Ñ. 4. ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¸Ðµ Ð¿ÑÐ¾Ð²ÐµÑÐºÐ¸ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸, Ð´Ð¸ÑÐºÐ° Ð¸ ÑÐ¾ÑÐ¾ÑÐ° Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð½Ð¾Ð¹ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸. 5. Ð Ð°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ° 3D Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð¿Ð¾ÑÐ»ÐµÐ´Ð½ÐµÐ¹ ÑÑÑÐ¿ÐµÐ½Ð¸ Ñ ÑÐ²Ð¾ÑÑÐ¾Ð²Ð¸ÐºÐ¾Ð¼, Ð´Ð¸ÑÐºÐ° Ð¸ ÑÐ¾ÑÐ¾ÑÐ°. Ð Ð°Ð±Ð¾ÑÐ° ÑÐ²Ð»ÑÐµÑÑÑ Ð°ÐºÑÑÐ°Ð»ÑÐ½Ð¾Ð¹ Ð² Ð²Ð¸Ð´Ñ ÑÐ¾Ð³Ð¾, ÑÑÐ¾ ÐÐ-22 Ð¸ÑÐ¿Ð¾Ð»ÑÐ·ÑÑÑÑÑ Ð½Ð° Ð¿Ð°ÑÑÐ°Ð¶Ð¸ÑÑÐºÐ¸Ñ ÑÐ°Ð¼Ð¾Ð»ÐµÑÐ°Ñ (Ð½Ð°Ð¿ÑÐ¸Ð¼ÐµÑ, Ð¢Ð£-32, Ð¯Ð½-48), Ð° ÑÐ°ÐºÐ¶Ðµ Ð½Ð° Ð±Ð°Ð·Ðµ Ð´Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð° ÑÐ¾Ð·Ð´Ð°ÑÑÑÑ Ð´ÑÑÐ³Ð¸Ðµ Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÐµÐ¹, ÐºÐ¾ÑÐ¾ÑÑÐµ Ð¿ÑÐ¸Ð¼ÐµÐ½ÑÑÑÑÑ Ð½Ð° ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ ÑÐ°Ð¼Ð¾Ð»ÑÑÐ°Ñ. Ð Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð±ÑÐ»Ð° Ð¿ÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½Ð° Ð¾ÑÐµÐ½ÐºÐ° Ð¸Ð·Ð¼ÐµÐ½ÐµÐ½Ð¸Ð¹ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ Ð² ÑÐ¾Ð´Ðµ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ, Ñ ÑÑÐµÑÐ¾Ð¼ Ð¸Ð·Ð¼ÐµÐ½ÐµÐ½Ð¸Ñ Ð½Ð°ÑÐ°Ð»ÑÐ½ÑÑ Ð´Ð°Ð½Ð½ÑÑ, Ð¾ÑÐ»Ð¸ÑÐ½ÑÑ Ð¾Ñ Ð´Ð°Ð½Ð½ÑÑ Ð´Ð»Ñ ÐºÐ¾Ð½ÐºÑÐµÑÐ½Ð¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿Ð°. Ð£Ð´Ð°Ð»Ð¾ÑÑ ÑÐ¾ÑÑÐ°Ð½Ð¸ÑÑ Ð´Ð¾ÑÑÐ¾Ð¹Ð½Ñ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¸ Ð´ÑÑÐ³Ð¸Ñ Ð²Ð°Ð¶Ð½ÑÑ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº.
description: The subject of the graduate qualification work is âDouble-circuit engine with a 40 kN thrustâ. The aim of the presented work is the design of the aircraft engine based on the prototype AI-22. The main parameters that affect the presented calcula-tion to a greater extent are the temperature behind the combustion chamber, the degree of two-circuit and engine thrust. Tasks that are solved in the course of this study: 1. Study of the design features of the prototype AI-22 aircraft engine. 2. Carrying out the variant of thermal calculation of the cycle of a gas tur-bine engine with the selection of the best option. 3. Data analysis of individual units of a gas turbine dual-circuit engine us-ing gasdynamic and approximate calculations of a compressor, a combustion chamber and a turbine. 4. Conducting a strength test of the blade, disk and rotor of the last stage of the presented design. 5. Development of 3D models of the last stage vanes with a shank, disk and rotor. Used in passenger aircraft (for example, Tu-32, Jan-48), as well as on the basis of prototypes of other engine models that use different types of aircraft. In the graduate qualification work, an assessment was made of the changes in various engine parameters obtained in the course of studies con-ducted taking into account changes in the initial data for a specific prototype. It was possible to maintain worthy indicators of efficiency ratios and other im-portant characteristics.