Abstract: In the development of 1700 degree gas turbines, the innovation of turbine cooling technology is important. Film cooling is widely used in order to reduce the metal temperature and thermal stress. In this paper, the novel film hole configurations are proposed. The adiabatic effectiveness of those configurations is measured using PSP (pressure sensitive paint). The adiabatic effectiveness of those configurations is higher than cylindrical film hole. The shaped hole was applied to the vane/blade of low speed rotating test facility. It is found that the rotating blade platform is difficult to cool by film cooling technique compared to stationary vane shroud.
The H-IIB launch vehicle is an upgraded version of the current H-IIA launch capacity, which has two liquid rocket engines (LE-7A) in the first-stage, instead of one for the H-IIA. It has four SRB-As attached to the body, while the standard version of H-IIA had two SRB-As. One of the major design issue of H-IIB launch vehicle is increased prume heating due to clustering two LE-7A engines and four SRB-As, especially the interaction of engine prumes at high altitude. This paper describes the prume analysys method of H-IIB launch vehicle which is based on the flight proven method of the current H-IIA launch.