A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage
V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev
Institute of Physics (IOP)
Published 2018
Institute of Physics (IOP)
Published 2018
| Publication Date: |
2018-02-09
|
|---|---|
| Publisher: |
Institute of Physics (IOP)
|
| Print ISSN: |
1757-8981
|
| Electronic ISSN: |
1757-899X
|
| Topics: |
Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
|
| Published by: |
| _version_ | 1836398785743290369 |
|---|---|
| autor | V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev |
| beschreibung | In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability. |
| citation_standardnr | 6160117 |
| datenlieferant | ipn_articles |
| feed_id | 123476 |
| feed_publisher | Institute of Physics (IOP) |
| feed_publisher_url | http://www.iop.org/ |
| insertion_date | 2018-02-09 |
| journaleissn | 1757-899X |
| journalissn | 1757-8981 |
| publikationsjahr_anzeige | 2018 |
| publikationsjahr_facette | 2018 |
| publikationsjahr_intervall | 7984:2015-2019 |
| publikationsjahr_sort | 2018 |
| publisher | Institute of Physics (IOP) |
| quelle | IOP Conference Series: Materials Science and Engineering |
| relation | http://iopscience.iop.org/1757-899X/302/1/012079 |
| search_space | articles |
| shingle_author_1 | V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev |
| shingle_author_2 | V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev |
| shingle_author_3 | V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev |
| shingle_author_4 | V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev |
| shingle_catch_all_1 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability. V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev Institute of Physics (IOP) 1757-8981 17578981 1757-899X 1757899X |
| shingle_catch_all_2 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability. V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev Institute of Physics (IOP) 1757-8981 17578981 1757-899X 1757899X |
| shingle_catch_all_3 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability. V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev Institute of Physics (IOP) 1757-8981 17578981 1757-899X 1757899X |
| shingle_catch_all_4 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability. V V Vedeneev, M E Kolotnikov, P A Mossakovskii, L A Kostyreva, F A Abdukhakimov, P V Makarov, A A Pyhalov and M A Dudaev Institute of Physics (IOP) 1757-8981 17578981 1757-899X 1757899X |
| shingle_title_1 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| shingle_title_2 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| shingle_title_3 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| shingle_title_4 | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| timestamp | 2025-06-30T23:32:36.512Z |
| titel | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| titel_suche | A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage |
| topic | ZL |
| uid | ipn_articles_6160117 |