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Self-acting seals for helicopter engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lynwander, P. |
| Copyright Year | 1975 |
| Description | An experimental evaluation was conducted with NASA-designed self-acting face and circumferential seals for use in the main shaft positions of advanced gas turbine engines. The seals featured Rayleigh step pads (self-acting geometry) for lift augmentation. The tested seals incorporated design improvements over previous self-acting configurations. Self-acting face seals were tested to speeds of 214 m/s (700 ft/sec, 63700 rpm), air pressures of 216.8 N/sq cm abs (314.7 psia), and air temperatures of 688K (778 F). Self-acting circumferential seals were tested to speeds of 183 m/s (600 ft/sec, 47700 rpm), air pressures of 61.8 N/sq cm abs (89.7 psia), and air temperatures of 711 K (820 F). Self-acting face-seals are capable of operating at conditions exceeding conventional seal capability. The limit on speed capability was found to be the flatness of the seal-seat. The self-acting circumferential seal design tested requires further development for use in advanced engines. |
| File Size | 3948731 |
| Page Count | 119 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760011035 |
| Archival Resource Key | ark:/13960/t2896036f |
| Language | English |
| Publisher Date | 1975-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Seals Stoppers Helicopter Engines Shafts Machine Elements Gas Turbine Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
