| Autor: |
Balaji Sankar, Tahzeeb Hassan Danish |
| Rok vydání: |
2020 |
| Předmět: |
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| Zdroj: |
Proceedings of the National Aerospace Propulsion Conference ISBN: 9789811550386 |
| Popis: |
Small gas turbine engines are increasingly used in cruise missile applications. In the design stage of these engines, aero-thermodynamic models are used to evaluate the expected performance of the engine for a given set of component characteristics. The throttle characteristics and altitude-Mach number characteristics of the engine are iteratively analyzed using this model. This paper describes the use of such a model to show the expected performance of a set of design choices at different altitudes and Mach numbers. These small engines are operated at maximum possible Turbine Inlet Temperatures (TIT) for maximum thrust. Theoretical relations that give the slope of the operating line for constant turbine inlet temperature operation is derived. Using these expressions, the reduction of stability at high altitude and low Mach number is shown. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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