This poster depicts the design venture of a single-bladed stator for a tandem bladed rotor. The application of tandem-blading for highly loaded axial compressors is a promising design strategy to maximize the stage loading with acceptable losses. With few exceptions, the investigations in the field of tandem blade configuration pertain primarily to cascade studies aimed at the development of stators. The aerodynamic advantage offered by a tandem arrangement can be harnessed more appropriately by utilizing it in rotor configuration. The feasibility of a tandem bladed compressor stage depends on the performance of the rotor as well as the stator. A Stator operating downstream of a tandem bladed rotor has to deal with severe three dimensionalities due to dual rotor wakes each shed respectively from the highly loaded blades. Additionally, the inherent high aerodynamic loading of the rotor (a necessity for tandem configuration) results in additional concerns in the form of blockage. Often the aforesaid effects combine with each other making the stator design as challenging as the rotor itself. The challenges associated with stator design are confronted only when a tandem bladed rotor-single stator stage is attempted. The poster aims to highlight one of the least explored aspects of tandem bladed compressor stages with a primary focus on stator in the light of the rotor flow field.


Quantification of Variation in Combustion Instability Amplitude in a Multi-Nozzle Can Combustor

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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