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    Effect of Leading Edge Erosion on the Tip Leakage Flow in a Compressor Cascade

    Source: Journal of Turbomachinery:;2025:;volume( 147 ):;issue: 008::page 81015-1
    Author:
    Stein, Thomas
    ,
    Leitner, Markus W.
    ,
    Staudacher, Stephan
    DOI: 10.1115/1.4067462
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The interaction between tip leakage flow and passage flow in axial compressor blade rows creates complex flow mechanisms that impair flow stability. Caused by erosion of the compressor blades, these flow mechanisms become time-dependent. Especially, the compressor tip regions experience erosion-related surface loss owing to the particle-laden flow inside the engine. The corresponding reduction in chord length varies in height and leads to varying shapes of eroded compressor blades. It is likely that these impact the engine’s operability. The optical accessibility of flow structures in water was exploited by analyzing four blade tip geometries at different angles of incidence in a linear compressor cascade. The impact of these geometries on the tip flow structures is analyzed by observing the movement of inked fluid elements in space and time. Particle tracking velocimetry is used to obtain 3D trajectories of both stable and unstable flows. Whilst the non-eroded blade geometry shows stable vortex formation, a notable change in the flow characteristics is observed for particular erosion patterns. In these cases, the tip leakage flow exhibits unsteadiness, featuring fluctuations and unstable flow phenomena. A large blockage of the flow passage occurs due to a vortex breakdown.
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      Effect of Leading Edge Erosion on the Tip Leakage Flow in a Compressor Cascade

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4306021
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    contributor authorStein, Thomas
    contributor authorLeitner, Markus W.
    contributor authorStaudacher, Stephan
    date accessioned2025-04-21T10:21:40Z
    date available2025-04-21T10:21:40Z
    date copyright1/30/2025 12:00:00 AM
    date issued2025
    identifier issn0889-504X
    identifier otherturbo_147_8_081015.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4306021
    description abstractThe interaction between tip leakage flow and passage flow in axial compressor blade rows creates complex flow mechanisms that impair flow stability. Caused by erosion of the compressor blades, these flow mechanisms become time-dependent. Especially, the compressor tip regions experience erosion-related surface loss owing to the particle-laden flow inside the engine. The corresponding reduction in chord length varies in height and leads to varying shapes of eroded compressor blades. It is likely that these impact the engine’s operability. The optical accessibility of flow structures in water was exploited by analyzing four blade tip geometries at different angles of incidence in a linear compressor cascade. The impact of these geometries on the tip flow structures is analyzed by observing the movement of inked fluid elements in space and time. Particle tracking velocimetry is used to obtain 3D trajectories of both stable and unstable flows. Whilst the non-eroded blade geometry shows stable vortex formation, a notable change in the flow characteristics is observed for particular erosion patterns. In these cases, the tip leakage flow exhibits unsteadiness, featuring fluctuations and unstable flow phenomena. A large blockage of the flow passage occurs due to a vortex breakdown.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEffect of Leading Edge Erosion on the Tip Leakage Flow in a Compressor Cascade
    typeJournal Paper
    journal volume147
    journal issue8
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4067462
    journal fristpage81015-1
    journal lastpage81015-9
    page9
    treeJournal of Turbomachinery:;2025:;volume( 147 ):;issue: 008
    contenttypeFulltext
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