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Tytuł artykułu

Considerations od stages of aviation turbine engine test program

Wybrane pełne teksty z tego czasopisma
Identyfikatory
Warianty tytułu
PL
Rozważania dotyczące etapów programu prób lotniczego silnika turbinowego
Języki publikacji
EN
Abstrakty
EN
Detailed course and systematization of an aircraft turbine engine test program are presented. Types, groups, sorts and particular variations of tests are described on the basis of a literature review and the experience of two research centers: Institute of Aviation, Warsaw and Research & Development Center of WSK PZL-Rzesz6w S.A. The inference is exemplified by turbine engine test results costs.
PL
W artykule przedstawiono szczegółowo podział i przebieg badań eksperymentalnych lotniczego silnika turbinowego. Opisano typy, grupy, rodzaje i poszczególne odmiany prób w oparciu o przegląd literatury i doświadczenie dwóch ośrodków: Instytutu Lotnictwa w Warszawie oraz Zakładu Badawczo-Rozwojowego WSK PZL Rzeszów S.A. Uwagi końcowe zilustrowano przykładami kosztów badań silników turbinowych.
Rocznik
Strony
78--88
Opis fizyczny
Bibliogr. 32 poz., rys., tab.
Twórcy
autor
  • WSK PZL- Rzeszów
  • Ministry of Infrastructure
Bibliografia
  • [1] Antas S.: Stages of Realization of Aviation Gas Turbine Engine General Considerations. Transactions of the Institute of Aviation. Vol. 141, No 2, 1995, pp. 79-87 (in Polish).
  • [2] Antas S., Bucior J.: Chosen Aspects of Estimating of Operational Reliability of Aircraft Turbine Engines During of Manufacturing. VII Scientific-Technical Conference of Turbomachines, Rzeszów. November 1993, Part II. pp. 287-298 (in Polish).
  • [3] Antas S., Gnot A.: The Conformity Chart of PZL – 10W Engine to the Requirements of USA Airworthiness Regulations (FAR part 33). Doc. No. 19.0.263, Issue V, WSK ..PZL-Rzeszów", 1991 (in English, not published).
  • [4] Code of Federal Regulations. Aeronautics and Space. Parts I to 59. U.S. Government Printing Office. Washington 1990.
  • [5] Dorofyeyev V. M., Levin B. Ya.: Ispytanya Vozdushnoreaktivnych Dvigatetei {Jet Engines Testing - in Russian). Oborongiz. Moscow 1961.
  • [6] Flight Testing Gas Turbines on the Ground. Engineering. October 3, 1958, pp. 443-475, October 10. 1958, pp. 476-478.
  • [7] Description of Modifications of Universal Stand No 2 for Testing Aggregates of PZL- WW Engine, (collective work). Institute of Aviation Report No 8.12.18, Warsaw 1978. (in Polish).
  • [8] Fuhs A. E., Kingery M. (ed.): Instrumentation for Airbreathing Propulsion. Progress in Astronautics and Aeronautics. Vol. 34. MIT Press. Cambridge 1974.
  • [9] Giadrosich D.: Operation Research Analysis in Test and Evaluation. AIAA Textbook. 1995.
  • [10] Hartley R. M. BoaU.: Use of an Attitude Test Facility in Engine Development. The Aeronautical Journal. Vol. 74, No 712, 1970, pp. 307-314.
  • [11] Jachimowicz J.. Zygarek K.: Maximum Load and Low Cyclic Fatigue Tests of Jet Engine Rotor Elements (to be published in Machine Dynamics Problems).
  • [12] Japan to develop XF 3-400 engine. Flight International, 1-7 November 1995, p. 13.
  • [13] Joint Aviation Requirements. JAR-E. Engines. Civil Aviation Authority, Printing and Publication Services. Chaltenham 1990.
  • [14] Joint Aviation Requirements. JAR-23. Normal. Utility, Acrobatic and Commuter Category Airplane. Civil Aviation Authority, Printing and Publication Services. Chaltenham 1994.
  • [15] Joint Aviation Requirements. JAR-27. Small Rotocraft. Civil Aviation Authority, Printing and Publication Services. Chaltenham 1993.
  • [16] Joint Aviation Requirements. JAR-29. Large Rotocraft. Civil Aviation Authority, Printing and Publication Services. Chaltenham 1993.
  • [17] Macioce E.: The Further Application of Generalized Parameter to Turbojet Performance Relationship, in Morley A. W., Fabri J. (ed.): Advanced Aero Engine Testing. Pergamon. ondon 1959.
  • [18] MIL-E-5007C. Military Specification. Engines, Aircraft. Turbojet and Turbofan. General Specification For. Defense Supply Agency. Wright Patterson Airforce Space 1975.
  • [19] Murthy S. N. B., Curran E. T. (ed.): Developments in ' High-Speed-Vehicle Propulsion Systems. Progress in Astronautics and Aeronautics. AIAA 1996.
  • [20] Norris G.: ACCORD Rolls on with New UK MoD Founding. Flight International. Vol. 139, No 4261, 1991, p. 16.
  • [21] Report from the Second Stage of Endurance Test of PZL-10W Engine Till Total Service Time 3000 Hours. Report No BP/401.19/79/96. WSK PZL-Rzeszow, 1996
  • [22] Ropelewski R.: High Stakes in High-thrust Engine Race. Interavia. Vol. 49. No 579, 1994, pp. 34-37.
  • [23] Rosen R., Bawditch D. N.: The Future Challenge for Aeropropulsion. NASA Technical Memorandum No. 105613, 1992.
  • [24] Saravanamuttoo H. I. H.: Recommended Practices for Measurement of Gas Path Pressures and Temperatures for Performance Assessment of Aircraft Turbine Engines and Components. AGARD Advisory Report No. 245, 1990.
  • [25] Schench H. (jr): Theories of Engineering Experimentation. Second Edition. McGrow-Hill. New York 1968.
  • [26] Schuring D. J.: Scale Models in Engineering. Fundamentals and Applications. Pergamon Press. Oxford 1977.
  • [27] Service Manual of PZL-10S (TWD-10B) Engine Test Bed. (collective work). Report H-2480. WSK PZL-Rzeszów, 1978. (in Polish).
  • [28] Sweetman B.: IHPTET Spawns Engines for 21st Century. Interavia. Vol. 44, No. 11, I989, pp. 1113-1115.
  • [29] Tests of an Anti-icing System of Product 150 on the Test Stand, (collective work). Institute of Aviation Report No K 15.9.17. Warsaw 1982. (in Polish).
  • [30] Tests of the Aircraft Intake of Product 300 and Trade-off Studies of Lemniscate Intake and Aircraft Intake of the Aircraft TS-11 Iskra. (collective work). Report RKB-1/401, 17/3/81/WSK PZL-Rzeszów, 1981. (in Polish).
  • [31] Thermal and Gasdynamical Tests of Research Combustion Chamber in a Rig. (collective work). Institute of Aviation Report No K15.5.12. Warsaw 1983. (in Polish).
  • [32] Yaffe M. L.: GEI Engine Spawns Numerous Derivatives. Aviation Week. Vol. 93, No. 8, 1970, p. 27.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BSW1-0007-0010
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