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NASA-TM-213049
Leakage and Power Loss Test Results for Competing Turbine Engine Seals
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:22:50Z | |
| date available | 2017-09-04T17:22:50Z | |
| date copyright | 01/01/2004 | |
| date issued | 2004 | |
| identifier other | ZXHOEEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/146087 | |
| description abstract | Advanced brush and finger seal technologies offer reduced leakage rates over conventional labyrinth seals used in gas turbine engines. To address engine manufacturers concerns about the heat generation and power loss from these contacting seals, brush, finger, and labyrinth seals were tested in the NASA High Speed, High Temperature Turbine Seal Test Rig. Leakage and power loss test results are compared for these competing seals for operating conditions up to 922 K (1200 F) inlet air temperature, 517 KPa (75 psid) across the seal, and surface velocities up to 366 m/s (1200 ft/s). | |
| language | English | |
| title | NASA-TM-213049 | num |
| title | Leakage and Power Loss Test Results for Competing Turbine Engine Seals | en |
| type | standard | |
| page | 18 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;2004 | |
| contenttype | fulltext | |
| subject keywords | BRUSH SEALS | |
| subject keywords | GAS TURBINE ENGINES | |
| subject keywords | HEAT GENERATION | |
| subject keywords | HIGH SPEED | |
| subject keywords | HIGH TEMPERATURE TESTS | |
| subject keywords | INLET TEMPERATURE | |
| subject keywords | LABYRINTH SEALS | |
| subject keywords | LEAKAGE |
