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Fundamental mechanisms that influence the estimate of heat transfer to gas turbine blades
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Graham, R. W. |
| Copyright Year | 1979 |
| Description | Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major uncertainty due to the complexity of the heat transfer processes. The gas flow through these blade rows is three dimensional with complex secondary viscous flow patterns that interact with the endwalls and blade surfaces. In addition, upstream disturbances, stagnation flow, curvature effects, and flow acceleration complicate the thermal transport mechanisms in the boundary layers. Some of these fundamental heat transfer effects are discussed. The chief purpose of the discussion is to acquaint those in the heat transfer community, not directly involved in gas turbines, of the seriousness of the problem and to recommend some basic research that would improve the capability for predicting gas-side heat transfer on turbine blades and vanes. |
| File Size | 1644427 |
| Page Count | 15 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790012175 |
| Archival Resource Key | ark:/13960/t2t48h32q |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Temperature Measurement Accuracy Gas Turbines Turbulent Flow Turbine Blades Three Dimensional Flow Gas Dynamics Predictions Estimates Heat Transfer Viscous Flow 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 |
