Turbine engine with detonation combustion chamber in institute of aviation

• Autorzy: Kalina P.

Identyfikatory

DOI

10.5604/12314005.1134060

• Języki publikacji: EN

Abstrakty

EN

In Institute of Aviation from 2010 is realized a project POIG 2007-2014 “Turbine engine with detonation chamber.” The main target is to develop a turbine engine using a rotating detonation effect in the process of combustion the fuel. This article presents the most important stages leading to achieve the goals. As a facility test, we have chosen a turbo shaft engine GTD-350 characterized by the location of combustion chamber, which is outside the engine. This feature has helped in modernization the combustion chamber to adjust it to the detonation combustion. Works over the project has been started from the attempts to obtain a rotating detonation in the combustion chamber with a diameter of 500 mm powered by hydrogen. These researches have allowed the team to master the method of detonation initiation and methods for identifying the process of spinning detonation. In the same time works over the kerosene injection on the visualization bench has been begun. On this bench, we have mainly evaluated the extent and location of the fuel stream and the quality of the spray. Simultaneously the program to simulate the injection and the process of spinning detonation in actual geometries of different combustion chambers has been created. The process of initiation the detonation is discussed in the article on the example of detonator using ammo tutorial. Researches about combustion detonation with simultaneously reinforcement the combustion chamber with hydrogen and liquid fuel JET-A1 has also been discussed in this article. Presented research results includes pressure fuel waveforms in supply manifold along with the measurements of combustion pressure correlated with Air-Fuel Equivalence Ratio – lambda. Currently we are working over the integration of the combustion chamber of the engine GTD-350.

Słowa kluczowe

EN

turbine engine; rotating detonation; combustion

• 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: 2014
• Tom: Vol. 21, No. 1
• Strony: 119--124
• Opis fizyczny: Bibliogr. 3 poz., rys.

Twórcy

autor

Kalina P.

• Institute of Aviation, Department of Aviation Propulsion Krakowska Av. 110/114, 02-256 Warszawa, Poland tel.: [phone]

Bibliografia

• [1] Kindracki, J., Fujiwara, T., Wolanski, P., An experimental study of small rotating detonation engine, in: Pulsed and continuous detonation, Torus Press, pp. 332-338, 2006.
• [2] Wolanski, P., Development of the continuous rotating detonation engines, in “Progress in Pulsed and Continuous Detonations, edited by G. D. Roy and S. M. Frolov, Torus Press, pp. 395-406, Moscow 2010.
• [3] Wolanski, P., Detonative propulsion, Proceedings of the Combustion Institute 34, pp. 125-158, 2013.