title: Ð¡Ð¾Ð²ÐµÑÑÐµÐ½ÑÑÐ²Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸ Ð¼Ð¾Ð´ÐµÐ»ÑÐ½Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸ 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° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: Improvement the passage of the model stage of an axial compressor
Creators: name: ÐÐ°ÑÐ¼Ð°Ð½, ÐÑÑÐµÐ¼Ð¸Ð¹
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: ÑÑÑÐ±Ð¾ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÑ
ansys
Ð²ÐµÑÐ¸ÑÐ¸ÐºÐ°ÑÐ¸Ñ
Ð¾ÑÐµÐ²Ð¾Ð¹ ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾Ñ
sst
cfd Ð°Ð½Ð°Ð»Ð¸Ð·
Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð°Ñ ÑÐ°ÑÑÑ
cfx
nasa
ÑÐºÑÐ¸
turbo-compressor
solidworks
verification
axial compressor
cfd analysis
tskti
passage

description: Ð Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ñ ÑÐ¸ÑÐ»ÐµÐ½Ð½ÑÐµ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ Ð¼Ð¾Ð´ÐµÐ»ÑÐ½ÑÑ ÑÑÑÐ¿ÐµÐ½ÐµÐ¹ Nasa 37 Ð¸ Ð¦ÐÐ¢Ð Ð-50-1. ÐÑÐ»Ð¸ Ð¿Ð¾ÑÑÑÐ¾ÐµÐ½Ñ Ð¿ÑÐ¾ÑÐ¸Ð»Ð¸ Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½ÑÑ ÑÐµÑÐµÑÐ¾Ðº Ð´Ð»Ñ ÐºÐ°Ð¶Ð´Ð¾Ð¹ Ð¸Ð· Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð´Ð»Ñ Ð´Ð°Ð»ÑÐ½ÐµÐ¹ÑÐµÐ¹ ÑÐ±Ð¾ÑÐºÐ¸ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸. ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð° Ð²ÐµÑÐ¸ÑÐ¸ÐºÐ°ÑÐ¸Ñ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ Ð´Ð°Ð½Ð½ÑÑ Ð¸ Ð²Ð°Ð»Ð¸Ð´Ð°ÑÐ¸Ñ Ð¿Ð¾ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ°Ð¼ Ð½Ð°ÑÑÑÐ½ÑÑ ÑÐºÑÐ¿ÐµÑÐ¸Ð¼ÐµÐ½ÑÐ¾Ð² Ð¿ÑÐ¸ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ Ð·Ð½Ð°ÑÐµÐ½Ð¸ÑÑ Ð¼Ð°ÑÑÐ¾Ð²Ð¾Ð³Ð¾ ÑÐ°ÑÑÐ¾Ð´Ð°. Ð Ð°ÑÑÐµÑÑ Ð²ÐµÐ»Ð¸ÑÑ Ð½Ð° SST Ð¼Ð¾Ð´ÐµÐ»Ð¸ ÑÑÑÐ±ÑÐ»ÐµÐ½ÑÐ½Ð¾ÑÑÐ¸. ÐÐ°Ð½Ð½ÑÐ¹ ÑÑÐ°Ð¿ ÑÐ°Ð±Ð¾ÑÑ Ð½ÐµÐ¾Ð±ÑÐ¾Ð´Ð¸Ð¼, ÑÑÐ¾Ð±Ñ ÑÐ¸ÑÐ»ÐµÐ½Ð½Ð°Ñ Ð¼Ð¾Ð´ÐµÐ»Ñ ÑÐ¾Ð¾ÑÐ²ÐµÑÑÑÐ²Ð¾Ð²Ð°Ð»Ð° ÑÐ°Ð±Ð¾ÑÐµ Ð½Ð°ÑÑÑÐ½Ð¾Ð¹ ÑÑÑÐ¿ÐµÐ½Ð¸. ÐÐ¾ÑÐ»Ðµ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¸Ñ Ð²ÐµÑÐ¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸ Ð±ÑÐ»Ð¸ Ð¿ÑÐµÐ´Ð¿ÑÐ¸Ð½ÑÑÑ Ð¿Ð¾Ð¿ÑÑÐºÐ¸ ÑÐ¾Ð²ÐµÑÑÐµÐ½ÑÑÐ²Ð¾Ð²Ð°Ð½Ð¸Ñ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸. ÐÐ»Ñ ÑÑÐ¾Ð³Ð¾ Ð¸Ð·Ð¼ÐµÐ½ÑÐ»Ð¸ÑÑ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¸Ðµ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÑ Ð¿ÑÐ¾ÑÐ¸Ð»Ñ Ð¸ Ð¿ÑÐ¾ÑÐ¾ÑÐ½Ð¾Ð¹ ÑÐ°ÑÑÐ¸, ÑÐ°ÐºÐ¸Ðµ ÐºÐ°Ðº Ð¾ÑÐµÐ²Ð¾Ð¹ Ð¸Ð»Ð¸ ÑÐ°Ð´Ð¸Ð°Ð»ÑÐ½ÑÐ¹ Ð·Ð°Ð·Ð¾Ñ. ÐÑÐµ ÑÑÐ¸ Ð¾Ð¿ÐµÑÐ°ÑÐ¸Ð¹ Ð¿ÑÐ¾Ð²Ð¾Ð´Ð¸Ð»Ð¸ÑÑ Ð´Ð»Ñ ÑÐ²ÐµÐ»Ð¸ÑÐµÐ½Ð¸Ñ ÐÐÐ ÑÑÑÐ¿ÐµÐ½Ð¸ Ð¸Ð»Ð¸ Ð¾ÑÐ½Ð¾ÑÐµÐ½Ð¸Ñ Ð´Ð°Ð²Ð»ÐµÐ½Ð¸Ð¹. Ð Ð·Ð°ÐºÐ»ÑÑÐµÐ½Ð¸Ð¸ Ð±ÑÐ»Ð¸ ÑÐ´ÐµÐ»Ð°Ð½Ñ Ð²ÑÐ²Ð¾Ð´Ñ Ð¾ÑÐ½Ð¾ÑÐ¸ÑÐµÐ»ÑÐ½Ð¾ ÑÑÐ¿ÐµÑÐ½Ð¾ÑÑÐ¸ Ð²ÐµÑÐ¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸, ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ñ Ð¼Ð¾Ð´ÐµÐ»ÐµÐ¹ ÑÑÑÐ±ÑÐ»ÐµÐ½ÑÐ½Ð¾ÑÑÐ¸, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÑÐ¿ÐµÑÐ½Ð¾ÑÑÐ¸ ÐºÐ¾ÑÑÐµÐºÑÐ¸ÑÐ¾Ð²ÐºÐ¸ Ð»Ð¾Ð¿Ð°ÑÐ¾ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ° ÐºÐ¾Ð¼Ð¿ÑÐµÑÑÐ¾ÑÐ°.
description: In this work, numerical studies of the model stages of Nasa 37 and TsKTI K-50-1 are carried out. The profiles of blade gratings were constructed for each of the models for further assembly of the passage. Next, the obtained data were verified with the results of experiments with changes in the mass flow rate. Calculations were carried out on the SST model of turbulence. This stage of the work is necessary for the numerical model to correspond to the work of the full-scale stage. After verification, attempts were made to improve the flow path. To do this, the geometric parameters of the profile and the passage, such as the axial or radial clearance, were changed. All these operations were carried out to increase the efficiency of the stage or the pressure ratio. To sum up, conclusions were made regarding the success of the verification, the comparison of turbulence models and the success of adjusting the compressor blade unit.