Mainstream Ingress Suppression in Gas Turbine Disk CavitiesSource: Journal of Turbomachinery:;1994:;volume( 116 ):;issue: 002::page 339Author:V. I. Khilnani
,
J. Waggott
,
L. C. Tsai
,
S. H. Bhavnani
,
J. M. Khodadadi
,
J. S. Goodling
DOI: 10.1115/1.2928370Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The sealing characteristics of an air-cooled gas turbine disk cavity have been studied using laser sheet flow visualization. Experiments were performed on a simplified half-scale model of an actual gas turbine disk cavity. This type of rotor–stator geometry with a double-toothed-rim (DTR) seal at the outer periphery and a labyrinth seal at the inner periphery of the cavity has been tested for its ability in preventing ingress of hot mainstream gases. The results show good agreement with previously esimated design data. Experiments were conducted for various labyrinth seal flow rates and rotational Reynolds numbers up to 1.52 × 106 . The effects of rotor eccentricity on minimum purge flows have also been discussed.
keyword(s): Disks , Cavities , Gas turbines , Rotors , Flow (Dynamics) , Gases , Lasers , Reynolds number , Sealing (Process) , Flow visualization , Design , Geometry AND Stators ,
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| contributor author | V. I. Khilnani | |
| contributor author | J. Waggott | |
| contributor author | L. C. Tsai | |
| contributor author | S. H. Bhavnani | |
| contributor author | J. M. Khodadadi | |
| contributor author | J. S. Goodling | |
| date accessioned | 2017-05-08T23:45:53Z | |
| date available | 2017-05-08T23:45:53Z | |
| date copyright | April, 1994 | |
| date issued | 1994 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28636#339_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/114579 | |
| description abstract | The sealing characteristics of an air-cooled gas turbine disk cavity have been studied using laser sheet flow visualization. Experiments were performed on a simplified half-scale model of an actual gas turbine disk cavity. This type of rotor–stator geometry with a double-toothed-rim (DTR) seal at the outer periphery and a labyrinth seal at the inner periphery of the cavity has been tested for its ability in preventing ingress of hot mainstream gases. The results show good agreement with previously esimated design data. Experiments were conducted for various labyrinth seal flow rates and rotational Reynolds numbers up to 1.52 × 106 . The effects of rotor eccentricity on minimum purge flows have also been discussed. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Mainstream Ingress Suppression in Gas Turbine Disk Cavities | |
| type | Journal Paper | |
| journal volume | 116 | |
| journal issue | 2 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.2928370 | |
| journal fristpage | 339 | |
| journal lastpage | 346 | |
| identifier eissn | 1528-8900 | |
| keywords | Disks | |
| keywords | Cavities | |
| keywords | Gas turbines | |
| keywords | Rotors | |
| keywords | Flow (Dynamics) | |
| keywords | Gases | |
| keywords | Lasers | |
| keywords | Reynolds number | |
| keywords | Sealing (Process) | |
| keywords | Flow visualization | |
| keywords | Design | |
| keywords | Geometry AND Stators | |
| tree | Journal of Turbomachinery:;1994:;volume( 116 ):;issue: 002 | |
| contenttype | Fulltext |