Development of micro ceramic gas turbine based on mini jet engine

• Autorzy: Yoshida H. , Sodeoka S. , Iki N. , Matsunuma T. , Inoue T. , Suzuki M. , Ebara T. , Lee Y.
• Konferencja: Problemy Badawcze Energetyki Cieplnej. PBEC/sympozjum (VII ;06-09.12.2005; Warszawa, Polska)
• Języki publikacji: EN

Abstrakty

EN

Ceramic Gas Turbine can achieve high thermal efficiency without cooling system of turbine blades. However, ceramic elements are too expensive for development and introduction stage. Thus a hybrid type gas turbine of ceramic parts and metal parts are designed and manufactured. The hottest parts i.e., a turbine nozzle and rotor are replaced to ceramic type. But its combustor is still made of metal. The baseline machine is a small single-shaft turbojet engine (J-850, Sophia Precision, Co., Ltd.) with a centrifugal compressor and a radial turbine. An Inconel 713C alloy turbine rotor was replaced into a ceramic rotor (SN-235, Kyocera Corporation). The Inconel turbine nozzle and casing were replaced into the ceramic parts (SN-01, Otsuka Ceramics Co., Ltd.). The ceramic nozzle and case is supported by metal parts. As a first step, only turbine rotor was replaced with a ceramic rotor. A test operation was conducted at rotating speeds of up to 140,000 rpm in atmospheric air. As a second step, the Inconel turbine nozzle and turbine nozzle casing were replaced with ceramic parts. The ceramic nozzle and case were supported by metal parts. Through tests with the ceramic nozzle, it became evident that one of the key technologies for the development of ceramic gas turbines is the design of the interface between the ceramic components and the metallic components, because the difference between the coefficients of linear thermal expansion of the ceramic and metal produces large thermal stress at their interface in the high-temperature condition. Therefore a buffer material made of alumina fiber was inserted at the interface between the ceramic and metal. However alumina fiber is not tough enough for repeat of assembly and disassembly. The metallic spring ring seal can be applied instead of the alumina fiber, because the wall temperature of the combustor is not as high as the turbine inlet temperature due to the cooling effect of the combustion air. This metallic seal and the ceramic rotor were assembled into the gas turbine. This engine could operate for 1 hour in the condition that the estimated turbine inlet temperature was over 1000 °C.

Słowa kluczowe

EN

ceramic gas turbine; cooling systems; gas turbine

PL

turbiny gazowe; chłodzenie; układy chłodzenia

• Wydawca: Oficyna Wydawnicza Politechniki Warszawskiej
• Czasopismo: Prace Naukowe Politechniki Warszawskiej. Konferencje
• Rocznik: 2005
• Tom: z. 24
• Strony: 365--374
• Opis fizyczny: Bibliogr. 6 poz., rys., tab., wykr.

Twórcy

autor

Yoshida H.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Sodeoka S.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Iki N.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Matsunuma T.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Inoue T.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Suzuki M.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Ebara T.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

autor

Lee Y.

• National Institute of Advanced Industrial Science and Technology (AIST), Tsukuba, Japan

Bibliografia

• [1] Roode, M.V., Ferber, M.K. and Richerson, D.W., Ceramic Gas Turbine Design and Test Experience, ASME Press 2002
• [2] Hartsock, D.L., „Ford's development of the 820 high temperature ceramic gas turbine”, Ceramic Gas Turbine Design and Test Experience, ASME Press 2002
• [3] Arakawa, H., Suzuki, T., Saito, K., Tamura, S., and Kishi, S., 1997, „Research and Development of 300 kW Class Ceramic Gas Turbine Project in Japan”, ASME Paper No. 97-GT-87.
• [4] Yoshida, H., Matsunuma, T., Iki, N., Akimune, Y. and Hoya, H., 2004, „Micro Gas Turbine with Ceramic Rotor”, ASME Paper GT-2004-53493.
• [5] Matsunuma, T., Yoshida, H., Iki, N., Ebara, T., Sodeoka, S., Inoue, T. and Suzuki, M., 2005, „Micro Gas Turbine with Ceramic Nozzle and Rotor”, ASME Paper GT-2005-68711.
• [6] Shimizu, D., lki, N. and Ebara, T., 2004, „The Atomization of the Liquid Fuel by the Pressure Injector for Small Jet Engines”, Proc. 32nd Gas Turbine Conference, pp. 113-118., (in Japanese)