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Advanced radial inflow turbine rotor program: design and dynamic testing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rodgers, C. |
| Copyright Year | 1976 |
| Description | The advancement of small, cooled, radial inflow turbine technology in the area of operation at higher turbine inlet temperature is discussed. The first step was accomplished by designing, fabricating, and subjecting to limited mechanical testing an advanced gas generator rotating assembly comprising a radial inflow turbine and two-stage centrifugal compressor. The radial inflow turbine and second-stage compressor were designed as an integrally machined monorotor with turbine cooling taking place basically by conduction to the compressor. Design turbine inlet rotor gas temperature, rotational speed, and overall gas generator compressor pressure ratio were 1422 K (2560 R), 71,222 rpm, and 10/1 respectively. Mechanical testing on a fabricated rotating assembly and bearing system covered 1,000 cold start/stop cycles and three spins to 120 percent design speed (85,466 rpm). |
| File Size | 6743712 |
| Page Count | 100 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770009119 |
| Archival Resource Key | ark:/13960/t9w13vf8v |
| Language | English |
| Publisher Date | 1976-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Dynamic Tests Gas Turbines Centrifugal Compressors Systems Engineering Radial Flow Inlet Flow Gas Temperature Mechanical Engineering 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 |
