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Labyrinth seal testing for lift fan engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dobek, L. J. |
| Copyright Year | 1973 |
| Description | An abradable buffered labyrinth seal for the control of turbine gas path leakage in a tip-turbine driven lift fan was designed, tested, and analyzed. The seal configuration was not designed to operate in any specific location but was sized to be evaluated in an existing test rig. The final sealing diameter selected was 28 inches. Results of testing indicate that the flow equations predicted seal air flows consistent with measured values. Excellent sealing characteristics of the abradable coating on the stator land were demonstrated when a substantial seal penetration of .030 inch into the land surface was encountered without appreciable wear on the labyrinth knife edges. |
| File Size | 5103740 |
| Page Count | 78 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730007797 |
| Archival Resource Key | ark:/13960/t46q6qm5f |
| Language | English |
| Publisher Date | 1973-02-01 |
| Access Restriction | Open |
| Subject Keyword | Machine Elements And Processes Leakage Gases Temperature Distribution Seals Stoppers Air Flow Stators Lift Fans Turbine Engines Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |