Surge margin value controling factors selection of the turbojet engine compressor

• Autorzy: Antas S. , Ćwik A.
• Konferencja: International Symposium SYMKOM Compressor & Turbine Flow Systems, Treory & Application Areas (15-17.09.2008; Łódź; Polska)
• Języki publikacji: EN

Abstrakty

EN

Article presents conditions analysis of compressor turbine matching for aircraft turbojet engine and theoretical research of factors affecting this matching. Recommendations are presented for rational design actions to enable change of the steady state operating line position for compressor and gasifier turbine on the full compressor map. Influence of the throat area change of gasifier turbine nozzle guide vanes (FGV)CT and the throat area change of exhaust nozzle F5 on the parameters and engine compressor surge margin were measured at manufacturing conditions with the value of Πc*/G1cor ratio. Results obtained from experimental tests for exhaust nozzle throat area changes verified this theoretical research.

Słowa kluczowe

EN

surge margin; turbojet engine; compressor

• Wydawca: Wydawnictwo Politechniki Łódzkiej
• Czasopismo: Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka
• Rocznik: 2008
• Tom: nr 133
• Strony: 25--38
• Opis fizyczny: Bibliogr. 9 poz.

Twórcy

autor

Antas S.

• Politechnika Rzeszowska

autor

Ćwik A.

• WSK “PZL Rzeszów” S.A

Bibliografia

• [1] Antas S.,1999,”The Selection of Turbine Critical Parameters For Providing Stable Compressor Operation Range”. The Archive of Mechanical Egineering vol. XLVI. No 3, pp. 273 – 290.
• [2] Antas S., 1996, “The analysis of rational actions changing the positions of C-CT working line for SO-3 and SO-3W engines”. WSK “PZL-Rzeszów” S.A. Doc. No. 17.0.476, pp. 27 (in Polish).
• [3] Antas S., Lesikiewicz A.1987,”Theory of Jet Eng ines. Gasdynamics Functions.” Publishing House of Rzeszów University of Technology, Rzeszów (in Polish).
• [4] Antas S., 2006,”The Estimation of the Influence of Selected Methods of Modifications of Rotary Fluid Flow Machines of Aviation Turboprop and Turboshaft Engines on the Compressor Surge Margin”. Publishing House of Rzeszów University of Technology; Rzeszów (D.Sc. Dissertation in Polish).
• [5] Antas S., Szular A, 2007, “Report from 1-st section experimental tests of SO-3 engine No 39223101, carried out in accordance with 2-nd stage of agreement No U-7157” (Grant No. N509 002 32/0078). WSK “PZL-Rzeszów” S.A. Doc. No. 1/RB/SO-3/2007, pp. 38.
• [6] Antas S., 1996, “The gasdynamics analysis of modifications for K-15 turbojet engine ”. WSK “PZL-Rzeszów” S.A. Doc. No. 15.0.096, pp. 158 (in Polish).
• [7] Akimow W.M., 1981, „Osnowy nadieżnosti gazoturbinnych dwigatielej”. Maszynostrojenije, Moskwa.
• [8] Ćwik A., “Analytical and numerical methods for compressor surge margin value determining for the turbojet engine”. (Ph. D. Disertation under preparation) Rzeszów University of Technology.
• [9] Oakes W., Shook P., McGuire R., Fleeter S., 1997, “Aerodynamic Performance and Instability Initiation of a High Speed Research Centrifugal Compressor”, International Journal of Turbo and Jet Engines. Vol. 14, pp. 187-199.