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Preliminary investigation of several root designs for cermet turbine blades in turbojet engine iii : curved-root design
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1955 |
| Description | Stresses om tje root fastenings of turbine blades were appreciably reduced by redesign of the root. The redesign consisted in curving the root to approximately conform to the camber of the airfoil and elimination of the blade platform. Full-scale jet-engine tests at rated speed using cermet blades of the design confirmed the improvement. |
| File Size | 9036084 |
| Page Count | 19 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088975 |
| Archival Resource Key | ark:/13960/t3130m56j |
| Language | English |
| Publisher Date | 1955-12-28 |
| Access Restriction | Open |
| Subject Keyword | 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 |