In order to achieve higher gas turbine efficiency, the main gas temperature at turbine inlet has been steadily increased from approximately 900°C to about 1500°C over the last few decades. This temperature is higher than the maximum acceptable temperature for turbine internals. The hot main gas may get ingested into the space between rotor and stator, the rotor-stator disk cavity in a stage because of the pressure differential between main gas annulus and the disk cavity.
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- Partial requirement for: M.S., Arizona State University, 2014Note typethesis
- Includes bibliographical references (p. 72-75)Note typebibliography
- Field of study: Mechanical engineering