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Turbine blade and endwall heat transfer measured in nasa glenn's transonic turbine blade cascade
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Giel, Paul W. |
| Copyright Year | 2000 |
| Description | Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also degrade internal components. High-pressure turbine blades just downstream of the combustor are particularly susceptible to overheating. Computational fluid dynamics (CFD) computer programs can predict the flow around the blades so that potential hot spots can be identified and appropriate cooling schemes can be designed. Various blade and cooling schemes can be examined computationally before any hardware is built, thus saving time and effort. Often though, the accuracy of these programs has been found to be inadequate for predicting heat transfer. Code and model developers need highly detailed aerodynamic and heat transfer data to validate and improve their analyses. The Transonic Turbine Blade Cascade was built at the NASA Glenn Research Center at Lewis Field to help satisfy the need for this type of data. |
| File Size | 81941 |
| File Format | |
| Language | English |
| Publisher Date | 2000-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Cooling Turbine Blades Computational Fluid Dynamics Aerodynamic Heat Transfer Supersonic Turbines Heat Transfer Computer Programs Operating Temperature High Pressure 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 |
