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Cold-air performance of compressor-drive turbine of department of energy upgraded automobile gas turbine engine. 3: performance of redesigned turbine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Haas, J. E. Roelke, R. J. |
| Copyright Year | 1984 |
| Description | The aerodynamic performance of a redesigned compressor drive turbine of the gas turbine engine is determined in air at nominal inlet conditions of 325 K and 0.8 bar absolute. The turbine is designed with a lower flow factor, higher rotor reaction and a redesigned inlet volute compared to the first turbine. Comparisons between this turbine and the originally designed turbine show about 2.3 percentage points improvement in efficiency at the same rotor tip clearance. Two versions of the same rotor are tested: (1) an as cast rotor, and (2) the same rotor with reduced surface roughness. The effect of reducing surface roughness is about one half percentage point improvement in efficiency. Tests made to determine the effect of Reynolds number on the turbine performance show no effect for the range from 100,000 to 500,000. |
| File Size | 3656351 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840017576 |
| Archival Resource Key | ark:/13960/t29932q13 |
| Language | English |
| Publisher Date | 1984-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turbocompressors Performance Tests Engine Design Propulsion System Performance Flow Measurement Gas Turbine Engines Rotor Aerodynamics Propulsive Efficiency Clearances Inlet Flow Surface Roughness Engine Tests Axial Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
