Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-321T
In order to investigate air-Cooled turbines for application to high-temperature engines, a single stage turbine with a 0.56-m (22 inch) tip diameter was designed. The aerodynamical design procedures of the turbine are presented herein. The stator and rotor blades are characterized by low blade solidity, thick blade section, blunt leading edge and trailing edge, and low blade aspect ratio. A cold air test without supply of cooling air was conducted to determine the turbine aerodynamic performance. The highest efficiency obtained over the range of conditions investigated was 0.865. The turbine satisfied the equivalent design Value of specific work output at the design condition (i.e. at equivalent design speed and equivalent design pressure ratio) with an efficiency of 0.856. Detailed surveys of rotor-outlet gas flow were made with Pitot tubes and temperature sensors and the results are also presented. From these results, it can be concluded that the present airfoil shapes designed for an air cooled turbine by application of conventional technical design procedures worked well from an aerodynamical point of view and that the compromise, which was necessary in designing the aerofoil shapes because of cooling considerations, did not noticeably impair the turbine's overall performance.
An Aerodynamic Design and the Overall Stage Performance of an Air-cooled Axial-flow Turbine
naltr0321t.pdf
(3.17MB)
