| contributor author | S. Aoki | |
| contributor author | H. Yamao | |
| contributor author | K. Teshima | |
| contributor author | M. Arai | |
| date accessioned | 2017-05-08T23:27:09Z | |
| date available | 2017-05-08T23:27:09Z | |
| date copyright | April, 1988 | |
| date issued | 1988 | |
| identifier issn | 1528-8919 | |
| identifier other | JETPEZ-26654#251_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/103897 | |
| description abstract | Phase II of the high-temperature turbine test was performed using the H igh-T emperature D eveloping U nit (HTDU). This unit has the same two stages as the high-pressure turbine of the AGTJ-100A reheat system. The purpose of the Phase II test was to investigate the potential of candidate technologies that may be applied to the advanced engine, the AGTJ-100B. Cooling characteristics of several cooling schemes for the first stage blades, and the performance of thermal barrier coating employed on the first stage nozzles and blades, were investigated. This paper presents the Phase II test results. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Results From the Phase II Test Using the High-Temperature Developing Unit (HTDU) | |
| type | Journal Paper | |
| journal volume | 110 | |
| journal issue | 2 | |
| journal title | Journal of Engineering for Gas Turbines and Power | |
| identifier doi | 10.1115/1.3240114 | |
| journal fristpage | 251 | |
| journal lastpage | 258 | |
| identifier eissn | 0742-4795 | |
| keywords | High temperature | |
| keywords | Turbines | |
| keywords | Blades | |
| keywords | Cooling | |
| keywords | Engines | |
| keywords | High pressure (Physics) | |
| keywords | Nozzles AND Thermal barrier coatings | |
| tree | Journal of Engineering for Gas Turbines and Power:;1988:;volume( 110 ):;issue: 002 | |
| contenttype | Fulltext | |
