Unstable operation of the turbine aircraft engine

• Autorzy: Kozakiewicz A. , Kowalski M.
• Języki publikacji: EN

Abstrakty

EN

The article presents reasons for generating a non-uniform field of parameters in the compressor inlet of a turbine aircraft engine and its influence on the air jet kinematics at lowering fatigue strength of the compressor blade. Analysis of the engine torque in function of the engine operation time has been performed. Courses of the basic turbine engine operations parameters during compressor stall have been presented. The significant role of changes of the first torque derivative in relation to variation of the rotor acceleration in that assessment has been determined, which may be an important signal of the compressor surge occurring in the compressor. That parameter may be a signal for the control system to eliminate the negative phenomenon. The engine dynamics during the compressor surge has also been presented by developing the phase images of the engine operation basic parameters. The article includes analysis of dynamical changes in temperature of the combustion gases.

Słowa kluczowe

EN

turbine engine; engine dynamics; compressor stall

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2013
• Tom: Vol. 51 nr 3
• Strony: 719--727
• Opis fizyczny: Bibliogr. 10 poz., rys.

Twórcy

autor

Kozakiewicz A.

• Military University of Technology (WAT), Warsaw, Poland

autor

Kowalski M.

• Air Force Institute of Technology, Warsaw, Poland

Bibliografia

• 1. Balicki W., Chachurski R., Kawalec K., Kozakiewicz A., Szczeciński S., 2009, Unstable operation of turbine engines – causes of the occurrence and methods of prevention, Transacations of the Institute of Aviation. Scientific Quarterly, 4 (199) [in Polish]
• 2. Kotlarz W., 1973, Perekhodnye procesy v gazotiurbinnykh ustanovkakh, Mashinostroenie, Leningrad
• 3. Kowalski M., Pietraszek M., Szymczak J., Winczura Z., 2010, Report on “Analysis of the compressor stall occurence during firing NLPR-70 missiles from W-3W helicopter”, ITWL No. V 5786, Warszawa [in Polish]
• 4. Kozakiewicz A., 2011, Theoretical fundamentals of the origination of unstable regions of operation of aircraft turbine engines, Mechanik, 7, 421-432 [in Polish]
• 5. Kozakiewicz A., Frant M., 2011, Construction of anairintake system model for F-100-PW-229 engine in F-16 aircraft for intake vortex development analysis, Transcations of the Institute of Aviation. Scientific Quarterly, 4 (210) [in Polish]
• 6. Movikov A.C., 2007, Kontrol i diagnostyka tekhnicheskovo sostayaniya gazoturbinykh dvigateleĭ, Nauka, Moscow
• 7. Orkisz M., 1990, Operational Characteristics of Jet Turbine Engines Versus Stability of Working of the Compressor, WOSL, Dęblin [in Polish]
• 8. Szczeciński S., 1955, Stall phenomenon in jet engines with centrifugal compressors, Wojskowy Przegląd Lotniczy, VIII [in Polish]
• 9. Szczepanik R. et al., 2003, Report on “Analysis of dn/dt=f/n diagrams of the 89 engines for identification of characteristic points in the phase portrait”, ITWL No. V 1209, Warszawa [in Polish]
• 10. Szlachtenko C.M., 1987, Teoria i raschot wozdushno-reaktivnykh dvigateleĭ, Mashinostroenie, Moscow