Loading...
Please wait, while we are loading the content...
Similar Documents
Effect of reduced stator-blade trailing-edge thickness on over-all performance of a transonic turbine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1955 |
| Description | A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement was largely due to a reduced amount of low-velocity fluids entering the rotor and the interference effect of these fluids whth the mainstream flow. |
| File Size | 9304812 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089089 |
| Archival Resource Key | ark:/13960/t48q0r70v |
| Language | English |
| Publisher Date | 1955-11-01 |
| Access Restriction | Open |
| Subject Keyword | 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 |
