Turbine inlet temperature of gas turbine engines have been increased in order to improve engine efficiency but is closing in on the upper limit of capacity for current casting materials and thermal barrier coating systems. To cope with such situations, it is necessary to develop new material applications which have superior heat resistant properties than current casting superalloys, ODS alloys are one of the candidate materials. In this study, optimum HIP (Hot Isostatic Pressing) diffusion bonding parameters and a manufacturing process for turbine vanes of Ni base ODS (Oxide Dispersion Strengthened) alloy, MA754, were developed for the purpose of introducing advanced internal cooling structures. By using these parameters and process, HIP diffusion bonded MA754 turbine vanes were manufactured experimentally. As another application of the bonding process, MA754 turbine vanes HIP diffusion bonded with pure Cu internal cooling structure which has high thermal conductivity were also manufactured.

A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of three-dimensional-woven ceramic-matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723K and 1623K respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m 3 /Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse–flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.

Research Institute of Advanced Materials Gas-Generator (AMG), a joint effort by the Japan Key Technology Center and 14 companies in Japan, has, since 1993, been conducting technological studies on an innovative gas generator that will use 20% less fuel, weigh 50% less, and emit 70% less NOx than the conventional gas generator through the use of advanced materials[1]. In the course of R&D, the feasibility of applying a gradient composite material with ceramic matrix composite (CMC) and glass matrix composite (GMC), which is expected to reduce the thermal stress of actual parts with temperature distribution, was evaluated based on its mechanical and thermal properties, productivity and stress analysis for an actual part as a combustor liner with 500 mm diameter, and non-cooled combustion tests for the liner outlet temperature of 1873 K. Through our studies we have confirmed the applicability of the selected CMC/GMC hybrid composite as a combustor liner.