The comparative analysis of the selected construction types of axial compressor stage including the modal analysis

• Autorzy: Kozakiewicz A. , Grzejszczak O. , Lacki T.

Identyfikatory

DOI

10.5604/01.3001.0010.7008

• Języki publikacji: EN

Abstrakty

EN

The article concerns the issues of the scope of optimization of the gas turbine jet engine. These issues include limiting the weight and number of engine parts. One way to reduce the weight and number of components, including the compressor assembly, is to use the BLISK's replacement construction. The replacement construction should meet the strength requirement and the vibration spectrum as well. The paper presents a comparative analysis of the influence of rotational speed on the characters and the vibration frequency of the single rotor stage of the high pressure compressor. The analysis was carried out for two different design solutions of the blade-disk connection: the classical and integral. The comparative analysis focused on three important from the point of view of operation, the engine operating ranges: work on the ground (idle) and work during take-off and climb the aircraft.

Słowa kluczowe

EN

modal analysis; jet engine rotating parts; BLISK; optimisation

• Wydawca: Wydawnictwo Wrocławskiej Rady FSNT NOT
• Czasopismo: Journal of Machine Engineering
• Rocznik: 2017
• Tom: Vol. 17, No. 4
• Strony: 91--97
• Opis fizyczny: Bibliogr. 12 poz., rys., tab.

Twórcy

autor

Kozakiewicz A.

• Military University of Technology, Faculty of Mechatronics and Aviation, Warsaw, Poland

autor

Grzejszczak O.

• Military University of Technology, Faculty of Mechatronics and Aviation, Warsaw, Poland

autor

Lacki T.

• Military University of Technology, Faculty of Mechatronics and Aviation, Warsaw, Poland

Bibliografia

• [1] CHROMEK L., 2016, Design of the blisk of an aircraft turbojet engine and verification of its resonance free operation, Applied and Computational Mechanics, 10, 17-26.
• [2] FRISCHBIER J., SCHULZE G., 1996, Blade vibrations of a high speed compressor blisk-rotor- Numerical resonance tuning and optical measurements, International Gas Turbine and Aeroengine Congress and Exhibition, Birmingham, UK.
• [3] JAMROZ T., HAD J., 2015, Structural analysis of bladed disk, International Scientific Conference Modern Safety Technologies in Transportation.
• [4] KLAUKE T., 2007, Schaufelschwingungen realer integraler Verdichterräder im Hinblick auf Verstimmung und Lokalisierung, Dissertation, Brandenburgische Technische Universität Cottbus –Senftenberg.
• [5] KOSING O., SCHARL R., SCHMUHL H.J., 2001, Design improvements of the EJ200 HP compressor. From design verification engine to a future all blisk version, Nowy Orlean.
• [6] KOZAKIEWICZ A., GRZEJSZCZAK O., 2016, Influence of blades operation damages on work of the single stage of axial compressor, Conference papers, WPP, Poznań, (in Polish).
• [7] LIPKA J., 1967, Robustness of rotary machines, WNT, (in Polish).
• [8] SALUNKE NILESH P., CHANNIWALA S.A., JUNED A.R.A., 2014, Design optimization of an axial flow compressor for industrial gas turbine, IJRET, 03.
• [9] VRBKA D., POSPÍŠIL R., Operational reliability of rotor blades in extreme operating conditions, Ekol, Brno.
• [10] ZALECKI W., ŁAPCZYŃSKI Z., 2013, High temperature properties of Inconel 625 and Inconel 718 alloys, Prace IMŻ 3, 35-41, (in Polish).
• [11] www.specialmetals.com
• [12] https://www.cfmaeroengines.com