title: ÐÐ²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½Ñ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: Aircraft engine with a thrust of 70 kN
Creators: name: ÐÐ¸Ð½ Ð§Ð¶Ð°Ð¾Ð¶ÑÐ½Ñ
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: 2023
Subjects: Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
Ð¿ÑÐ¾ÑÐ¾ÑÐ¸Ð¿ Ð°Ð»-31Ñ
Ð´Ð²ÑÑ ÐºÐ¾Ð½ÑÑÑÐ½ÑÐ¹ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÐ¹ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ
ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
ÐºÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ
ÑÑÑÐ±Ð¸Ð½Ð°
turbojet engine
prototype al-31f
turbofan aircraft engine
axial compressor
combustor
turbine

description: Ð Â«Ð¿ÑÐ¾ÑÑÐ¾Ð¼Â» ÑÐµÑÐ¼Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¾Ð¼ ÑÐ¸ÐºÐ»Ðµ ÐÐ¢Ð Ðº Ð¿Ð¾ÑÐ¾ÐºÑ ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÑÐµÐ»Ð° Ð¿Ð¾Ð´Ð²Ð¾Ð´Ð¸ÑÑÑ ÑÐµÐ¿Ð»Ð¾. Ð ÐÐ¢Ð ÑÑÐ¾Ñ Ð¿ÑÐ¾ÑÐµÑÑ Ð¾ÑÑÑÐµÑÑÐ²Ð»ÑÐµÑÑÑ Ð² ÐºÐ°Ð¼ÐµÑÐµ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ (ÐÐ¡). Ð¢ÐµÐ¿Ð»Ð¾ Ð¿Ð¾Ð´Ð²Ð¾Ð´Ð¸ÑÑÑ Ð·Ð° ÑÑÐµÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð°, Ñ. Ðµ. Ð¿ÑÐµÐ¾Ð±ÑÐ°Ð·Ð¾Ð²Ð°Ð½Ð¸Ñ ÑÐ¸Ð¼Ð¸ÑÐµÑÐºÐ¾Ð¹ ÑÐ½ÐµÑÐ³Ð¸Ð¸ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð° Ð² ÑÐµÐ¿Ð»Ð¾Ð²ÑÑ, Ð¿ÑÐ¸ ÑÑÐ¾Ð¼ ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÐ° ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÑÐµÐ»Ð° Ð²Ð¾Ð·ÑÐ°ÑÑÐ°ÐµÑ Ð¾Ñ Ð·Ð½Ð°ÑÐµÐ½Ð¸Ñ 2 (Ð·Ð° ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ¾Ð¼) Ð´Ð¾ 3 (Ð½Ð° Ð²ÑÐ¾Ð´Ðµ Ð² ÑÑÑÐ±Ð¸Ð½Ñ). ÐÑÑÑÐ´Ð° Ð¸ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ: ÐÐ°Ð¼ÐµÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ (ÐÐ¡) â Ð¾Ð´Ð¸Ð½ Ð¸Ð· Ð¾ÑÐ½Ð¾Ð²Ð½ÑÑ ÑÐ·Ð»Ð¾Ð² Ð³Ð°Ð·Ð¾ÑÑÑÐ±Ð¸Ð½Ð½ÑÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»ÐµÐ¹ (ÐÐ¢Ð). ÐÐµ Ð½Ð°Ð·Ð½Ð°ÑÐµÐ½Ð¸Ðµ â ÑÐ¶Ð¸Ð³Ð°Ð½Ð¸Ðµ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð° Ð¸ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð¸Ðµ Ð²ÑÑÐ¾ÐºÐ¾-Ð½Ð°Ð³ÑÐµÑÐ¾Ð³Ð¾ ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÑÐ°Ð»Ð°. Ð ÐµÐ°Ð»ÑÐ½ÑÐ¹ Ð¿ÑÐ¾ÑÐµÑÑ Ð² ÐÐ¡ Ð¾ÑÐ»Ð¸ÑÐ°ÐµÑÑÑ Ð¾Ñ Ð¸Ð´ÐµÐ°Ð»ÑÐ½Ð¾Ð³Ð¾ Ð½Ð°Ð»Ð¸ÑÐ¸ÐµÐ¼ Ð¿Ð¾ÑÐµÑÑ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ. ÐÐ¾ÑÐµÑÐ¸ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð² ÐÐ¡ ÑÐºÐ»Ð°Ð´ÑÐ²Ð°ÑÑÑÑ Ð¸Ð· Ð³Ð¸Ð´ÑÐ°Ð²Ð»Ð¸ÑÐµÑÐºÐ¸Ñ Ð¿Ð¾ÑÐµÑÑ (Ð¿Ð¾ÑÐµÑÑ ÑÑÐµÐ½Ð¸Ñ) Ð¸ Ð¿Ð¾ÑÐµÑÑ Ð¾Ñ Ð¿Ð¾Ð´Ð²Ð¾Ð´Ð° ÑÐµÐ¿Ð»Ð° Ðº Ð¿Ð¾ÑÐ¾ÐºÑ ÑÐ°Ð±Ð¾ÑÐµÐ³Ð¾ ÑÐµÐ»Ð°. ÐÐ¸Ð´ÑÐ°Ð²Ð»Ð¸ÑÐµÑÐºÐ¸Ðµ Ð¿Ð¾ÑÐµÑÐ¸, Ð² ÑÐ²Ð¾Ñ Ð¾ÑÐµÑÐµÐ´Ñ, Ð¼Ð¾Ð¶Ð½Ð¾ ÑÐ°Ð·Ð´ÐµÐ»Ð¸ÑÑ Ð½Ð° ÑÐ¾ÑÑÐ°Ð²Ð»ÑÑÑÐ¸Ðµ Ð¿Ð¾ÑÐµÑÐ¸: â Ð² Ð´Ð¸ÑÑÑÐ·Ð¾ÑÐµ; â Ð² ÐºÐ¾Ð»ÑÑÐµÐ²ÑÑ ÐºÐ°Ð½Ð°Ð»Ð°Ñ; â Ð½Ð° Ð²ÑÐµÐºÐ°Ð½Ð¸Ðµ Ð²Ð¾Ð·Ð´ÑÑÐ° Ð² Ð¾ÑÐ²ÐµÑÑÑÐ¸Ñ Ð¶Ð°ÑÐ¾Ð²Ð¾Ð¹ ÑÑÑÐ±Ñ Ð¸ ÑÐ»ÐµÐ¼ÐµÐ½ÑÑ ÑÑÐ¾Ð½ÑÐ¾Ð²Ð¾Ð³Ð¾ ÑÑÑÑÐ¾Ð¹ÑÑÐ²Ð° (Ð¤Ð£); â Ð½Ð° ÑÐ¼ÐµÑÐµÐ½Ð¸Ðµ ÑÑÑÑÐ¹. ÐÑÐ¾Ð¼Ðµ Ð¿Ð¾ÑÐµÑÑ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð¿ÑÐ¾ÑÐµÑÑÑ Ð² ÐÐ¡ ÑÐ¾Ð¿ÑÐ¾Ð²Ð¾Ð¶Ð´Ð°ÑÑÑÑ Ð¿Ð¾ÑÐµÑÑÐ¼Ð¸ ÑÐµÐ¿Ð»Ð° Ð·Ð° ÑÑÐµÑ ÐµÐ³Ð¾ ÑÐ°ÑÑÐµÐ¸Ð²Ð°Ð½Ð¸Ñ Ð² Ð¾ÐºÑÑÐ¶Ð°ÑÑÐµÐµ Ð¿ÑÐ¾ÑÑÑÐ°Ð½ÑÑÐ²Ð¾ Ð¸ Ð·Ð° ÑÑÐµÑ Ð½ÐµÐ¿Ð¾Ð»Ð½Ð¾Ð³Ð¾ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð°. ÐÐ¾ÑÐµÑÐ¸ ÑÐµÐ¿Ð»Ð° Ð² Ð¾ÐºÑÑÐ¶Ð°ÑÑÐµÐµ Ð¿ÑÐ¾ÑÑÑÐ°Ð½ÑÑÐ²Ð¾ Ð¿Ð¾ ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ñ Ñ ÐºÐ¾Ð»Ð¸ÑÐµÑÑÐ²Ð¾Ð¼ ÑÐµÐ¿Ð»Ð°, Ð¿Ð¾Ð´Ð²Ð¾Ð´Ð¸Ð¼ÑÐ¼ Ðº ÑÐ°Ð±Ð¾ÑÐµÐ¼Ñ ÑÐµÐ»Ñ, Ð² ÐÐ¡ Ð¢Ð Ð ÑÐ¾ÑÑÐ°Ð²Ð»ÑÑÑ 0,005 â 0,01 %. Ð­ÐºÐ¾Ð½Ð¾Ð¼Ð¸ÑÐ½Ð¾ÑÑÑ Ð´Ð²Ð¸Ð³Ð°ÑÐµÐ»Ñ Ð½Ð°ÑÐ¾Ð´Ð¸ÑÑÑ Ð² Ð¿ÑÑÐ¼Ð¾Ð¹ Ð·Ð°Ð²Ð¸ÑÐ¸Ð¼Ð¾ÑÑÐ¸ Ð¾Ñ Ð¿Ð¾Ð»Ð½Ð¾ÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð°. Ð ÑÐ¾Ð²ÑÐµÐ¼ÐµÐ½Ð½ÑÑ ÐÐ¢Ð Ð¿ÑÐ¾ÑÐµÑÑ ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð° Ð² ÐÐ¡ Ð´Ð¾ÑÑÐ°ÑÐ¾ÑÐ½Ð¾ ÑÐ¾ÑÐ¾ÑÐ¾ Ð¾ÑÐ³Ð°Ð½Ð¸Ð·Ð¾Ð²Ð°Ð½, Ð¿Ð¾ÑÑÐ¾Ð¼Ñ Ð¿Ð¾Ð»Ð½Ð¾ÑÐ° ÑÐ³Ð¾ÑÐ°Ð½Ð¸Ñ ÑÐ¾Ð¿Ð»Ð¸Ð²Ð° Ð² Ð½Ð¸Ñ Ð´Ð¾ÑÑÐ¸Ð³Ð°ÐµÑ Ð²ÐµÐ»Ð¸ÑÐ¸Ð½Ñ 0,995 â 0,993.
description: In the "simple" thermodynamic cycle of a gas turbine engine, heat is supplied to the flow of the working fluid. In a gas turbine engine, this process is carried out in a combustion chamber (CS). Heat is supplied due to fuel combustion, i.e. the conversion of chemical fuel energy into thermal energy, while the temperature of the working fluid increases from a value of 2 (behind the compressor) to 3 (at the turbine inlet). Hence the definition: The combustion chamber (CS) is one of the main components of gas turbine engines (GTE). Its purpose is to burn fuel and obtain a highly heated working hoist. The real process in CS differs from the ideal one by the presence of pressure losses. Pressure losses in the CS consist of hydraulic losses (friction losses) and losses from heat supply to the working fluid flow. Hydraulic losses, in turn, can be divided into component losses: â in the diffuser; â in the ring channels; â for air to flow into the openings of the heat pipe and the elements of the front device (FU); â to mix the jets. In addition to pressure losses, processes in CS are accompanied by heat losses due to its dispersion into the surrounding space and due to incomplete combustion of fuel. The heat loss to the surrounding space in comparison with the amount of heat supplied to the working fluid in the CS turbofan is 0.005 â 0.01%. The efficiency of the engine is directly dependent on the completeness of fuel combustion. In modern gas turbine engines, the process of fuel combustion in The CS is quite well organized, so the completeness of fuel combustion in them reaches a value of 0.995 â 0.993.