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A survey of instabilities within centrifugal pumps and concepts for improving the flow range of pumps in rocket engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Veres, Joseph P. |
| Copyright Year | 1992 |
| Description | Design features and concepts that have primary influence on the stable operating flow range of propellant-feed centrifugal turbopumps in a rocket engine are discussed. One of the throttling limitations of a pump-fed rocket engine is the stable operating range of the pump. Several varieties of pump hydraulic instabilities are mentioned. Some pump design criteria are summarized and a qualitative correlation of key parameters to pump stall and surge are referenced. Some of the design criteria were taken from the literature on high pressure ratio centrifugal compressors. Therefore, these have yet to be validated for extending the stable operating flow range of high-head pumps. Casing treatment devices, dynamic fluid-damping plenums, backflow-stabilizing vanes and flow-reinjection techniques are summarized. A planned program was undertaken at LeRC to validate these concepts. Technologies developed by this program will be available for the design of turbopumps for advanced space rocket engines for use by NASA in future space missions where throttling is essential. |
| File Size | 847830 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920009038 |
| Archival Resource Key | ark:/13960/t3dz55b9s |
| Language | English |
| Publisher Date | 1992-02-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Throttling Systems Stability Turbine Pumps Centrifugal Compressors Vanes Centrifugal Pumps Rocket Engines Hydraulic Equipment Rocket Engine Design Design Analysis Surges Spacecraft Propulsion Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |