The influence of the blades leading edge anti-erosion protection on main rotor performances

• Autorzy: Wojtas M. , Czajkowski Ł. , Sobieszek A.

Identyfikatory

DOI

10.5604/01.3001.0012.2866

• Języki publikacji: EN

Abstrakty

EN

This article presents the influence of rotor blade airfoil shape on main rotor performances. In this case, we analysed the influence of anti-erosion tape, which is applied to the leading edge of the blade to protect the blades from environmental conditions. In Gyro-Tech Innovation an Aviation Company and Institute of Aviation the independent tests of helicopter and gyroplane main rotors were performed. Research includes: bench tests, on the test stand for dynamic testing of insulated rotors and tests on two flying constructions, gyroplane Cavalon produced by AutoGyro GmbH Company and ultralight helicopter Dynali H3. On the test bench, a two-blade rotor, used in ultralight and unmanned helicopters, was tested. In article, the authors present importance of the proper selection and application of anti-erosion coatings on rotor blades. Discuss the behaviour of the above-mentioned constructions with main rotor blades leading edge covered anti-erosion tape, during flight tests. The results of bench tests, including the comparison of polar curves of the main rotor with anti-erosion coating and without were also presented and discussed. In the summary of this article among others the solution of technological pocked introduced in the rotor blade, corresponding to the thickness of the anti-erosion tapes, in such way that after tape is applied it does not change the contour of the blade airfoil were presented.

Słowa kluczowe

EN

airfoil; rotor blades; flight tests; light rotorcrafts; ultra-light rotorcrafts

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2018
• Tom: Vol. 25, No. 2
• Strony: 409--414
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Wojtas M.

• Institute of Aviation, Department of Transport and Energy Conversion Division Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone], ext. 224, fax: [phone]

autor

Czajkowski Ł.

• Institute of Aviation, Department of Transport and Energy Conversion Division Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone], ext. 224, fax: [phone]

autor

Sobieszek A.

• Institute of Aviation, Department of Transport and Energy Conversion Division Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.:[phone], ext. 224, fax: [phone]

Bibliografia

• [1] Collins, P., Moore, C., Solutions to helicopter blade erosion improving aircraft availability and reducing costs, 40th European Rotorcraft Forum, 2014.
• [2] Czechyra, T., Experimental Investigation of the Influence of Blade Airfoil Shape Deformation on Helicopter Main Rotor Model Loads in Hover, Transaction of the Institute of Aviation, No. 2-3 (177-178), pp. 86-92, 2004.
• [3] Sobieszek, A. Wojtas, M., Composite rotor blades tests essential before mounting on gyroplane, Journal of KONES, 1231-4005, 2354-0133, pp. 487-494, 2016.
• [4] Thomas, W., Shek, C. H., Chin-Jye, M., Rosenzweig, E. I., Enhanced erosion protection for rotor blades, American Helicopter Society 65th Annual Forum, Grapevine, Texas 2009.
• [5] Wojtas, M., Wyznaczanie podstawowych własności wirnika – biegunowe wirnika dwułopatowego wykonanego w technologii prepregowej, No. 0221/58/ZTET/2017/RAP, 2017.
• [6] Żurawski, R., Bezpieczne wykonywanie prób prototypów obiektów wirujących, Bezpieczeństwo na lądzie, morzu i w powietrzu w XXI wieku, CNBOP-PIB, Józefów 2014.
• [7] www.solutions.3m.com.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).