Development of Ceramic Gas Turbine Components for CGT301 in Moonlight Project

Hattori, Mitsuru; Masuda, Masaaki; Ozawa, Tadao

doi:10.1115/93-gt-065

Cited by 1 publication

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“…Development of fabrication technologies of high temperature parts with refractory and high-strength ceramics has been carried out, and ceramic parts with high-quality and precise geometry have been successfully fabricated. (6) Development of engine component, i.e.. compressor, combustor, turbine and heat exchanger, has been carried out to attain the required structural reliability and efficiency of the components. The target efficiency of each components (Phase 2) shown in Table 2, were attained in the component rig tests.…”

Section: Component Developmentmentioning

confidence: 99%

Development of 300kW-Class Ceramic Gas Turbine (CGT301) Engine System

Tatsuzawa

Taoka

Sakida

et al. 1995

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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CGT301 is a recuperated, single-shaft ceramic gas turbine for co-generation use. Ceramic parts are used in the hot section of the engine, such as turbine blades, nozzle vanes, combustor liners, heat exchanger elements and gas path parts. These ceramic parts are designed axi-symmetrically to reduce their sizes and thermal stresses and to avoid their unexpected deformations. The turbine is a two-stage axial flow type. As a primary feature of this turbine, the rotors are composed of ceramic blades inserted into metallic disks. The ceramic parts of the engine system have been tested before installing them in the engine to assure their reliability in the following manner. The ceramic blades have been examined by hot-spin test with the gas temperature of 1100°C and up to 110% of the engine rated speed. The ceramic stationary parts such as nozzle vanes, combustor liners and gas path parts, have been assembled and installed in a test rig with almost the same constraint and thermal conditions as the engine, and thermal fatigue tests of 100 cycles between 1200°C and 300°C have been conducted. After the proof tests of ceramic parts, they have been installed in the engine, step by step. Finally, the engine has been operated with a TIT of 1200°C at the engine rated speed of 56000 rpm. The present paper describes the development process and shows test results of the ceramic gas turbine at a TIT of 1200°C.

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Section: Component Developmentmentioning

confidence: 99%