Development of mathematical model and computer program for primary design of transonic axial compressor
The mathematical model underlying the program for calculating and designing axial compressors is presented. The process of calculating the pressure loss in the elements of the axial compressor stage flow path is described. The loss coefficient consists of losses on the limiting surfaces, secondary...
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| Format: | Article |
| Language: | English |
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Omsk State Technical University, Federal State Autonomous Educational Institution of Higher Education
2020-12-01
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| Series: | Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" |
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| Online Access: | https://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2020/%D0%A2.%204,%20%E2%84%96%204%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/16-27%20%D0%91%D0%BE%D1%80%D0%BE%D0%B2%D0%BA%D0%BE%D0%B2%20%D0%90.%20%D0%98.,%20%D0%93%D0%B0%D0%BB%D0%B5%D1%80%D0%BA%D0%B8%D0%BD%20%D0%AE.%20%D0%91.,%20%D0%A1%D0%BE%D0%BB%D0%BE%D0%B2%D1%8C%D1%91%D0%B2%D0%B0%20%D0%9E.%20%D0%90.%20%D0%B8%20%D0%B4%D1%80..pdf |
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| author | A. I. Borovkov Yu. B. Galerkin O. A. Solovieva A. A. Drozdov A. F. Rekstin V. B. Semenovsky P. N. Brodnev |
| author_facet | A. I. Borovkov Yu. B. Galerkin O. A. Solovieva A. A. Drozdov A. F. Rekstin V. B. Semenovsky P. N. Brodnev |
| author_sort | A. I. Borovkov |
| collection | DOAJ |
| description | The mathematical model underlying the program for calculating and designing axial compressors is
presented. The process of calculating the pressure loss in the elements of the axial compressor stage
flow path is described. The loss coefficient consists of losses on the limiting surfaces, secondary losses
and profile losses. The effect of roughness on the pressure loss is taken into account by introducing the
corresponding empirical coefficient. An algorithm for calculating the blades and vanes angles of the
impeller and the guide apparatus is presented by calculating the incidence angle and the lag angle of
the flow. The flow lag angle is the sum of the lag angle of the flow on the profile and the lag angle due
to viscous flow on the limiting surfaces |
| format | Article |
| id | doaj-art-05540d79ad1647558c088ac6eb0b9502 |
| institution | Kabale University |
| issn | 2588-0373 2587-764X |
| language | English |
| publishDate | 2020-12-01 |
| publisher | Omsk State Technical University, Federal State Autonomous Educational Institution of Higher Education |
| record_format | Article |
| series | Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" |
| spelling | doaj-art-05540d79ad1647558c088ac6eb0b95022025-02-02T18:56:42ZengOmsk State Technical University, Federal State Autonomous Educational Institution of Higher EducationОмский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение"2588-03732587-764X2020-12-0144162710.25206/2588-0373-2020-4-4-16-27Development of mathematical model and computer program for primary design of transonic axial compressorA. I. Borovkov0Yu. B. Galerkin1O. A. Solovieva2A. A. Drozdov3A. F. Rekstin4V. B. Semenovsky5P. N. Brodnev6Peter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityPeter the Great St. Petersburg Polytechnic UniversityThe mathematical model underlying the program for calculating and designing axial compressors is presented. The process of calculating the pressure loss in the elements of the axial compressor stage flow path is described. The loss coefficient consists of losses on the limiting surfaces, secondary losses and profile losses. The effect of roughness on the pressure loss is taken into account by introducing the corresponding empirical coefficient. An algorithm for calculating the blades and vanes angles of the impeller and the guide apparatus is presented by calculating the incidence angle and the lag angle of the flow. The flow lag angle is the sum of the lag angle of the flow on the profile and the lag angle due to viscous flow on the limiting surfaceshttps://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2020/%D0%A2.%204,%20%E2%84%96%204%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/16-27%20%D0%91%D0%BE%D1%80%D0%BE%D0%B2%D0%BA%D0%BE%D0%B2%20%D0%90.%20%D0%98.,%20%D0%93%D0%B0%D0%BB%D0%B5%D1%80%D0%BA%D0%B8%D0%BD%20%D0%AE.%20%D0%91.,%20%D0%A1%D0%BE%D0%BB%D0%BE%D0%B2%D1%8C%D1%91%D0%B2%D0%B0%20%D0%9E.%20%D0%90.%20%D0%B8%20%D0%B4%D1%80..pdfaxial compressorimpellerreturn channeflow rateradial equilibriumhead loss |
| spellingShingle | A. I. Borovkov Yu. B. Galerkin O. A. Solovieva A. A. Drozdov A. F. Rekstin V. B. Semenovsky P. N. Brodnev Development of mathematical model and computer program for primary design of transonic axial compressor Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение" axial compressor impeller return channe flow rate radial equilibrium head loss |
| title | Development of mathematical model and computer program for primary design of transonic axial compressor |
| title_full | Development of mathematical model and computer program for primary design of transonic axial compressor |
| title_fullStr | Development of mathematical model and computer program for primary design of transonic axial compressor |
| title_full_unstemmed | Development of mathematical model and computer program for primary design of transonic axial compressor |
| title_short | Development of mathematical model and computer program for primary design of transonic axial compressor |
| title_sort | development of mathematical model and computer program for primary design of transonic axial compressor |
| topic | axial compressor impeller return channe flow rate radial equilibrium head loss |
| url | https://www.omgtu.ru/general_information/media_omgtu/journal_of_omsk_research_journal/files/arhiv/2020/%D0%A2.%204,%20%E2%84%96%204%20(%D0%90%D0%A0%D0%B8%D0%AD%D0%9C)/16-27%20%D0%91%D0%BE%D1%80%D0%BE%D0%B2%D0%BA%D0%BE%D0%B2%20%D0%90.%20%D0%98.,%20%D0%93%D0%B0%D0%BB%D0%B5%D1%80%D0%BA%D0%B8%D0%BD%20%D0%AE.%20%D0%91.,%20%D0%A1%D0%BE%D0%BB%D0%BE%D0%B2%D1%8C%D1%91%D0%B2%D0%B0%20%D0%9E.%20%D0%90.%20%D0%B8%20%D0%B4%D1%80..pdf |
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