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Fuel and oxidizer turbine loss analysis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Haas, J. E. |
| Copyright Year | 1985 |
| Description | The turbine losses for the fuel and oxidizer turbines at the FPL condition were assessed by a quasi-3D loss analysis method. This loss analysis method uses two flow codes - MERIDL and TSONIC - to calculate the flow velocities along the blade surfaces and endwalls. The velocities are then used as input to the boundary layer code - BLAYER - to calculate the friction losses due to incidence, secondary flow, and tip clearance. The loss analysis for the fuel turbine indicated an overall two-stage efficiency of about 90%. The largest loss was due to rotor tip clearance. The loss analysis for the oxidizer turbine is nearly completed. Results for the first stage of the two-stage design indicates an efficiency of about 80%, with high losses due to rotor incidence and blade and endwall friction. |
| File Size | 473671 |
| Page Count | 11 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850018589 |
| Archival Resource Key | ark:/13960/t93827m2n |
| Language | English |
| Publisher Date | 1985-04-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Method of Characteristics Losses Three Dimensional Flow Flow Distribution Flow Characteristics Flow Velocity Design Analysis Turbines Boundary Layer Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
