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Descripción
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| The use of compact architectures on aircraft turbine engines challenges the design and management of structural and thermal load requirements. Even operating in subsonic conditions, supersonic regimes may develop at the high-pressure turbine passages, experiencing complex compression and expansion wave systems that interact with adjacent stages of the turbine. When the cooling flow is ejected through the blade trailing edge slots, non-symmetrical configurations can appear due to the interaction of the injected flow with the surrounding flow field, leading to undesired loads and efficiency loses. In this work, a combination of RANS simulations, global stability and sensitivity analysis is employed to identify and explain the physical mechanisms of this phenomenon. A global mode associated with the geometrical expansion of the trailing edge slot is identified and linked to the non-symmetrical configurations. To conclude, the regions where the flow would be more sensitive to flow modifications to excite or damp this phenomenon are identified throughout an adjoint approximation. | |
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Internacional
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Si |
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ISSN o ISBN
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978-84-947311-6-7 |
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Entidad relacionada
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ECCOMAS |
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Nacionalidad Entidad
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Sin nacionalidad |
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Lugar del congreso
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Gasglow |