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Improved Design of Compressor Transition Ducts for Gas Turbine Engines"

Cecilia Ortiz

2:30 PM on 2008-03-07


The transmission system in a multi-spool commercial aircraft engine is a complicated system of support structures. One of these support structures is the intermediate case which provides housings for the thrust bearings for all shafts as well as incorporating an S-shaped duct that is used to transmit the core engine airflow from the larger radius LP or IP compressor to the smaller radius HP compressor. Improving the design of compressor transition S-shaped ducts to be shorter in length and have an axial inlet mean line could lead to significant benefits in weight and in component performance. An experimental and numerical investigation into the flow aerodynamics that determine the performance of these ducts was carried out and a new design methodology which allows for more aggressive designs (25% shorter in length) whilst maintaining current levels of performance is presented. Duct performance was quantified using the loss in stagnation pressure.


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