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Turbine disk cavity aerodynamics and heat transfer
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Daniels, W. A. Johnson, B. V. |
| Copyright Year | 1992 |
| Description | Experiments were conducted to define the nature of the aerodynamics and heat transfer for the flow within the disk cavities and blade attachments of a large-scale model, simulating the Space Shuttle Main Engine (SSME) turbopump drive turbines. These experiments of the aerodynamic driving mechanisms explored the following: (1) flow between the main gas path and the disk cavities; (2) coolant flow injected into the disk cavities; (3) coolant density; (4) leakage flows through the seal between blades; and (5) the role that each of these various flows has in determining the adiabatic recovery temperature at all of the critical locations within the cavities. The model and the test apparatus provide close geometrical and aerodynamic simulation of all the two-stage cavity flow regions for the SSME High Pressure Fuel Turbopump and the ability to simulate the sources and sinks for each cavity flow. |
| File Size | 472483 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920023021 |
| Archival Resource Key | ark:/13960/t9c58hr8c |
| Language | English |
| Publisher Date | 1992-07-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Leakage Cavities Turbine Pumps Stagnation Temperature Rotating Disks Turbine Wheels Space Shuttle Main Engine Flow Distribution Coolants Aerodynamic Characteristics Cavity Flow Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
