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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Banjac, Milan Milan, V. Petrovic |
| Copyright Year | 2018 |
| Abstract | An axial compressor loss and deviation model that was developed and presented during previous research has now been used to develop a computer program for multistage compressor design. A set of input data including overall parameters such as pressure ratio and mass flow rate and the first-stage parameters such as inlet flow coefficient and rotor tip Mach number are used to determine a number of stages and their geometry, speed and relevant flow properties. Then a subsequent redistribution of parameters for separate stages can be carried out in order to increase the stability indicators and efficiency over a desired operating range. A selected stage vortex law determines velocity triangles and blading geometry for hub and tip sections, which allows the generation of a realistic flow path shape. The developed program is considered to be a flexible and stable tool useful for tasks of manual or automated optimization when combined with an external optimization algorithm. This paper presents a basic mathematical model and the level of accuracy achieved. This is demonstrated through examples of manual design and redesign cases, while automated optimization will be included in future research. |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791851012 |
| DOI | 10.1115/GT2018-75410 |
| Volume Number | Volume 2C: Turbomachinery |
| Conference Proceedings | ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition |
| Language | English |
| Publisher Date | 2018-06-11 |
| Publisher Place | Oslo, Norway |
| Access Restriction | Subscribed |
| Subject Keyword | Stability Computer software Rotors Optimization algorithms Compressors Flow (dynamics) Pressure Optimization Design Geometry Vortices Shapes Mach number |
| Content Type | Text |
| Resource Type | Article |
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