title: Verifying heat transfer analysis of high pressure cooled turbine blades and disk.
abstract: To demonstrate cooling and heat transfer technology, a core engine test was conducted with a turbine inlet temperature 1700 degrees C. Measurement data were compared with predictions for a vane, a blade, and a disk. Measured cooling effectiveness of the blade and the vane agreed well with predictions. CFD analysis was carried out for verification of the heat transfer coefficient which was adopted from a heat conduction analysis over the disk. The CFD model including bolt heads showed better results than an axisymmetric model.
authors.affiliation: Advanced Technology Department, Aero-Engine & Space Operations, Ishikawajima-Harima Heavy Industries Co., Ltd, 229, Tonogaya, Mizuho-machi, Nishitama-gun, Tokyo, 190-1297, Japan.
authors.forename: S
authors.initials: S
authors.lastname: Yamawaki