title: ÐÐ²ÑÑ Ð²Ð°Ð»ÑÐ½ÑÐ¹ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹Ñ ÑÑÐ³Ð¾Ð¹Ð½Ð° Ð¿Ð¾Ð»Ð½Ð¾Ð¼ ÑÐ¾ÑÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ð¸ 49ÐºÐ (5740 ÐºÐ³Ñ)
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-shaft turbojet engine with afterburner with full boost thrust of 49 kN (5740 kgf)
Creators: name: Ð¢ÑÑÐ¸ÐºÐ¾Ð², ÐÐ³Ð¾Ñ
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: 2021
Subjects: Ð¢Ð ÐÐÐ¤
Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Â«Ð Ð-33Â»
ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð²Ð½Ð°Ñ ÑÑ ÐµÐ¼Ð° Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ
ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÑÑÐ±Ð¸Ð½Ð°
ÑÐ°ÑÑÐµÑ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² ÑÑÑÐ±Ð¸Ð½Ñ
turbofan engine
RD-33 engine
engine design diagram gas-dynamic calculation
compressor
combustion chamber
turbine
calculation of the strength of the turbine elements

description: Ð¢ÐµÐ¼Ð° Ð²ÑÐ¿ÑÑÐºÐ½Ð¾Ð¹ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÑ: Â«Ð Ð°ÑÑÐµÑ ÐÐ²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ Ð½Ð° ÑÑÐ³Ðµ 54 ÐºÐ Ð½Ð° Ð±Ð°Ð·Ðµ Ð Ð-33Â» Ð ÑÐ°Ð±Ð¾ÑÐµ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½ Ð¿ÑÐ¾ÐµÐºÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð·Ð° Ð¾ÑÐ½Ð¾Ð²Ñ ÐºÐ¾ÑÐ¾ÑÐ¾Ð³Ð¾ Ð±ÑÐ» Ð²Ð·ÑÑ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ Â«Ð Ð-33Â». Ð Ð°Ð±Ð¾ÑÐ° ÑÐ°Ð·Ð´ÐµÐ»ÐµÐ½Ð° Ð½Ð° 6 Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ Ð³Ð»Ð°Ð², ÑÐµÐ»ÑÑ ÐºÐ¾ÑÐ¾ÑÐ¾Ð¹ ÑÐ²Ð»ÑÐµÑÑÑ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð¸Ðµ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ñ ÑÐ¾ÑÑÐ°Ð¶Ð½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÐ¾Ð¹ Ð¸ ÑÑÐ³Ð¾Ð¹ 54 ÐºÐ. Ð Ð¿ÐµÑÐ²Ð¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¾Ð¸Ð·Ð²Ð¾Ð´ÑÑÑÑ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ½ÑÐµ ÑÐ°ÑÑÐµÑÑ ÑÐ¸ÐºÐ»Ð° ÐÐ¢Ð Ð² Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ðµ Ð2GTE, Ð²ÑÐ±Ð¾Ñ ÑÐ°ÑÑÐµÑÐ½Ð¾Ð³Ð¾ ÑÐµÐ¶Ð¸Ð¼Ð° ÑÐ°Ð±Ð¾ÑÑ Ð¸ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐµÑÑÐ°. Ð ÑÐ¸ÑÑÐµÐ¼Ðµ âGasTurb v.13â Ð²ÑÐ¿Ð¾Ð»Ð½ÑÐµÑÑÑ ÑÑÐ¾ÑÐ½ÑÑÑÐ¸Ð¹ ÑÐ°ÑÑÐµÑ Ð²ÑÐ±ÑÐ°Ð½Ð½Ð¾Ð³Ð¾ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ° ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐµÑÑÐ° Ð¸ Ð½Ð°ÑÐ¾Ð¶Ð´ÐµÐ½Ð¸Ðµ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÑÐµÐ»Ð° Ð² Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐµÑÐµÐ½Ð¸ÑÑ Ð´Ð²ÑÑÐºÐ¾Ð½ÑÑÑÐ½Ð¾Ð³Ð¾ ÑÑÑÐ±Ð¾ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾Ð³Ð¾ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ, Ð±ÑÐ» Ð²ÑÐ±ÑÐ°Ð½ ÑÐ¸ÐºÐ» Ñ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ°Ð¼Ð¸ Ï_Ðº^*=20 Ð¸ Ð¢3*= 1550 Ð. ÐÐ¾ Ð²ÑÐ¾ÑÐ¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½ Ð¿ÑÐ¸Ð±Ð»Ð¸Ð¶ÐµÐ½Ð½ÑÐ¹ ÑÐ°ÑÑÐµÑ Ð´Ð²ÑÑÐºÐ°ÑÐºÐ°Ð´Ð½Ð¾Ð³Ð¾ Ð¾ÑÐµÐ²Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°. ÐÑÐ»Ð¸ Ð¿Ð¾Ð»ÑÑÐµÐ½Ñ Ð³Ð°Ð±Ð°ÑÐ¸ÑÐ½ÑÐµ ÑÐ°Ð·Ð¼ÐµÑÑ Ð¸ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÑ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°. Ð ÑÑÐµÑÑÐµÐ¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¾Ð¸Ð·Ð²ÐµÐ´ÐµÐ½ ÑÐ°ÑÑÐµÑ ÐºÐ¾Ð»ÑÑÐµÐ²Ð¾Ð¹ Ð¿ÑÑÐ¼Ð¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÐºÐ°Ð¼ÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ. ÐÑÐ»Ð¸ Ð¿Ð¾Ð»ÑÑÐµÐ½Ñ Ð¾ÑÐ½Ð¾Ð²Ð½ÑÐµ Ð¿Ð¾ÐºÐ°Ð·Ð°ÑÐµÐ»Ð¸ ÐµÐµ ÑÐ°Ð±Ð¾ÑÑ Ð¸ Ð¸Ð½Ð´ÐµÐºÑÑ ÑÐ¼Ð¸ÑÑÐ¸Ð¸. Ð§ÐµÑÐ²ÐµÑÑÐ°Ñ Ð³Ð»Ð°Ð²Ð° Ð²ÑÐ¿Ð¾Ð»Ð½ÑÐµÑÑÑ Ð¿ÑÐ¾ÐµÐºÑÐ¸ÑÐ¾Ð²Ð¾ÑÐ½ÑÐ¹ Ð³Ð°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ Ð´Ð²ÑÑÐ²Ð°Ð»ÑÐ½Ð¾Ð¹ ÑÑÑÐ±Ð¸Ð½Ñ Ð¢Ð ÐÐÐ¤. ÐÑÑÐ°Ñ Ð³Ð»Ð°Ð²Ð° ÑÐ°Ðº Ð¶Ðµ ÑÐ¾ÑÑÐ¾Ð¸Ñ Ð¸Ð· Ð½ÐµÑÐºÐ¾Ð»ÑÐºÐ¸Ñ Ð¿Ð¾Ð´Ð¿ÑÐ½ÐºÑÐ¾Ð²: Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð° ÑÐ°ÑÑÐµÑÑ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² ÑÑÑÐ±Ð¸Ð½Ñ Ð½Ð° Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ. Ð ÑÐµÑÑÐ¾Ð¹ Ð³Ð»Ð°Ð²Ðµ Ð¿ÑÐ¸Ð²ÐµÐ´ÑÐ½ ÑÐ°ÑÑÐµÑ: Â«ÐÐ¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ñ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ ÑÐ²Ð¾ÑÑÐ¾Ð²Ð¾Ð³Ð¾ ÑÐ¾ÐµÐ´Ð¸Ð½ÐµÐ½Ð¸Ñ ÑÐ°Ð±Ð¾ÑÐµÐ¹ Ð»Ð¾Ð¿Ð°ÑÐºÐ¸ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ½ÑÑ ÑÐ°ÑÑÐµÑÐ¾Ð²Â». Ð ÑÐ°Ð±Ð¾ÑÐµ ÑÐ°ÐºÐ¶Ðµ Ð¿ÑÐ¸ÑÑÑÑÑÐ²ÑÑÑ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ñ, Ð¸Ð»Ð»ÑÑÑÑÐ¸ÑÑÑÑÐ¸Ðµ Ð²Ð°Ð¶Ð½ÑÐµ Ð°ÑÐ¿ÐµÐºÑÑ. ÐÐ½Ð¸ Ð¿Ð¾Ð¼Ð¾Ð³Ð°ÑÑ Ð¿Ð¾Ð´ÑÐ¾Ð±Ð½ÐµÐµ Ð´Ð¾Ð½ÐµÑÑÐ¸ ÑÑÑÑ Ð¿ÑÐ¾ÑÐµÑÑÐ¾Ð², Ð¾Ð¿Ð¸ÑÑÐ²Ð°ÐµÐ¼ÑÑ Ð² ÐÐÐ .
description: The topic of the final qualification work: "Calculation of a two-circuit turbojet engine with an afterburner at 54 kN thrust based on the RD-33Â» The paper presents the engine design, which was based on a two-circuit turbojet engine with an afterburner chamber "RD-33". The work is divided into 6 main chapters, the purpose of which is to design a two-circuit turbojet engine with an afterburner and a thrust of 54 kN. In the first chapter, the variant calculations of the gas turbine engine cycle in the A2GTE program are performed, the choice of the design mode of operation and the main parameters of the workflow is made. In the "GasTurb v. 13" system, a refinement calculation of the selected workflow option is performed and the parameters of the working fluid are found in the main sections of a two-circuit turbojet engine, a cycle with the parameters Ï_Ðº^*=20 and T3*= 1550 K was selected. The second chapter presents an approximate calculation of a two-stage axial compressor. Overall dimensions and parameters of the compressor were obtained. In the third chapter, the annular ramjet combustion chamber is calculated. The main indicators of its work and emission indices were obtained. The fourth chapter is the design gas-dynamic calculation of a two-shaft turbofan turbine. The fifth chapter also consists of several sub-paragraphs: it is devoted to the calculation of the turbine elements for strength. In the sixth chapter, the calculation is given: "Optimization of the design parameters of the tail joint of the working blade on the basis of variant calculations". The work also contains materials illustrating important aspects. They help to convey the essence of the processes described in the WRC in more detail.