title: Ð Ð°ÑÑÐµÑ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ° Ð¾ÑÐµÐ²Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð¼Ð°Ð³Ð¸ÑÑÑÐ°
titleType: Subtitle
title: Calculation of the flow part of the axial compressor vanes
Creators: name: Ð¨ÑÐ°Ð¿Ð°ÑÐº, ÐÐ»ÐµÐºÑÐ°Ð½Ð´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: ÐÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÑ Ð¾ÑÐµÐ²ÑÐµ
Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð°Ñ ÑÐ°ÑÑÑ
ÑÑÐ°ÑÐ¸ÑÐµÑÐºÐ¾Ðµ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ðµ
Ð¿Ð¾Ð¿ÑÐ°Ð²Ð¾ÑÐ½ÑÐ¹ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½Ñ
flow part
static pressure
correction factor

description: Ð Ð°ÑÑÐµÑ Ð±ÑÐ´ÐµÑ ÑÐ¾ÑÑÐ¾ÑÑÑ Ð¸Ð· Ð²Ð°ÑÐ¸Ð°Ð½ÑÐ½Ð¾Ð³Ð¾ ÑÐ°ÑÑÐµÑÐ° Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ°, Ð² ÐºÐ¾ÑÐ¾ÑÐ¾Ð¼ Ð±ÑÐ´ÐµÑ: Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð¿Ð¾ÑÐµÑÑ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ñ Ð²Ð¾ Ð²ÑÐ°ÑÑÐ²Ð°ÑÑÐµÐ¼ Ð¸ Ð½Ð°Ð³Ð½ÐµÑÐ°ÑÐµÐ»ÑÐ½Ð¾Ð¼ Ð¿Ð°ÑÑÑÐ±ÐºÐµ, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð°Ð´Ð¸Ð°Ð±Ð°ÑÐ½Ð¾Ð³Ð¾ Ð½Ð°Ð¿Ð¾ÑÐ° Ð² Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð¼ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐµ, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð½Ð°ÑÑÐ¶Ð½Ð¾Ð³Ð¾ Ð´Ð¸Ð°Ð¼ÐµÑÑÐ° ÐÐ Ð¸ Ð¾ÐºÑÑÐ¶Ð½Ð¾Ð¹ ÑÐºÐ¾ÑÐ¾ÑÑÐ¸ ÑÐ¾ÑÐ¾ÑÐ°, Ð²ÑÐ±Ð¾Ñ ÑÑÐµÐ¿ÐµÐ½Ð¸ ÑÐµÐ°ÐºÑÐ¸Ð²Ð½Ð¾ÑÑÐ¸, Ð²ÑÐ±Ð¾Ñ ÑÐ¸Ð¿Ð° Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ ÑÐ¸ÑÐ»Ð° ÑÑÑÐ¿ÐµÐ½ÐµÐ¹, Ð¿ÑÐµÐ´Ð²Ð°ÑÐ¸ÑÐµÐ»ÑÐ½Ð¾Ðµ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½ÑÐ° Ð¿Ð¾Ð»ÐµÐ·Ð½Ð¾Ð³Ð¾ Ð´ÐµÐ¹ÑÑÐ²Ð¸Ñ ÐÐ. ÐÐ°Ð·Ð¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ°ÑÑÐµÑ: Ð¿ÐµÑÐ²ÑÐ¹ Ð¿Ð¾ÑÑÑÐ¿ÐµÐ½ÑÐ°ÑÑÐ¹ ÑÐ°ÑÑÐµÑ Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ°, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð¿Ð¾Ð¿ÑÐ°Ð²Ð¾ÑÐ½ÑÑ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½ÑÐ¾Ð², Ð¿ÑÐ¸Ð¼ÐµÑ ÑÐ¸ÑÐ»ÐµÐ½Ð½Ð¾Ð³Ð¾ ÑÐ°ÑÑÐµÑÐ° Ð¿ÐµÑÐ²Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸, Ð·Ð°ÑÐµÐ¼ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ðµ ÑÑÐºÐ¸Ð·Ð° Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ°, Ð²ÑÐ¾ÑÐ¾Ð¹ Ð¿Ð¾ÑÑÑÐ¿ÐµÐ½ÑÐ°ÑÑ ÑÐ°ÑÑÐµÑ Ð´Ð»Ñ ÐºÐ¾ÑÐ¾ÑÐ¾Ð³Ð¾ Ð¿Ð¾ÑÑÐµÐ±ÑÐµÑÑÑ Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¸Ðµ Ð¿Ð¾Ð¿ÑÐ°Ð²Ð¾Ðº Ð´Ð»Ñ ÐºÐ¾ÑÑÑÐ¸ÑÐ¸ÐµÐ½ÑÐ¾Ð². ÐÐ¿ÑÐµÐ´ÐµÐ»Ð¸Ð¼ Ð¾ÐºÐ¾Ð½ÑÐ°ÑÐµÐ»ÑÐ½ÑÐµ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÑ Ð´Ð»Ñ Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ° Ð¸ Ð¾Ð¿ÑÐµÐ´ÐµÐ»Ð¸Ð¼ ÑÑÐ°ÑÐ¸ÑÐµÑÐºÐ¾Ðµ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ðµ Ð¸ ÑÑÐ°ÑÐ¸ÑÐµÑÐºÑÑ ÑÐµÐ¼Ð¿ÐµÑÐ°ÑÑÑÑ Ð¿ÐµÑÐµÐ´ ÑÐ°Ð±Ð¾ÑÐ¸Ð¼ ÐºÐ¾Ð»ÐµÑÐ¾Ð¼ Ð¸ Ð·Ð° ÑÐ°Ð±Ð¾ÑÐ¸Ð¼ ÐºÐ¾Ð»ÐµÑÐ¾Ð¼ Ð´Ð²ÑÐ¼Ñ Ð¿ÑÐµÐ´ÑÑÐ°Ð²Ð»ÐµÐ½Ð½ÑÐ¼Ð¸ Ð¼ÐµÑÐ¾Ð´Ð°Ð¼Ð¸ Ð¼ÐµÑÐ¾Ð´Ð¸ÐºÐ¸.
description: The calculation will consist of a variant calculation of the blade apparatus, which will be: determination of pressure losses in the suction and discharge nozzles, determination of the adiabatic pressure in the blade apparatus, determination of the outer diameter of the aircraft and the peripheral speed of the rotor, selection of the degree of reactivity, selection of the type of flow part, determination of the number of stages , preliminary determination of the efficiency of an aircraft. Gas-dynamic calculation: the first stepwise calculation of the blade apparatus, the determination of correction factors, an example of the numerical calculation of the first stage, then a sketch of the blade apparatus, the second step is the calculation for which it will be necessary to determine corrections for the coefficients. We will determine the final parameters for the blade apparatus and determine the static pressure and static temperature in front of the impeller and behind the impeller using the two methods presented.