DEVELOPMENT OF A BOUNDARY CONDITION DRIVEN MODEL FOR ANALYZING STALL MARGIN ENHANCEMENT THROUGH PASSIVE FLOW CONTROL IN TURBOMACHINERY
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Authors
Isakov, Daniel
Subjects
turbomachinery
transonic
compressor
turbine
design tool
endwall treatment
casing treatment
Naval Postgraduate School
NPS
Naval Postgraduate School Military Fan
NPSMF
military fan
computational fluid dynamics
CFD
CFX
stall
stall margin
passive flow control
flow recirculation passage.
transonic
compressor
turbine
design tool
endwall treatment
casing treatment
Naval Postgraduate School
NPS
Naval Postgraduate School Military Fan
NPSMF
military fan
computational fluid dynamics
CFD
CFX
stall
stall margin
passive flow control
flow recirculation passage.
Advisors
Gannon, Anthony J.
Smith, Walter C.
Date of Issue
2025-03
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Jet engines, particularly those in military aircraft, are vulnerable to stall, which can severely damage the engine and potentially lead to catastrophic failure. One method to mitigate stall and enhance engine performance is to extend the operational limits by employing a flow recirculation passage over the compressor rotor. This passage helps re-energize low-momentum flow regions, thereby increasing the compressor's stability range. This study develops a computational design tool to facilitate the rapid optimization of a proposed passive flow control mechanism for the Naval Postgraduate School Military Fan (NPSMF). Parametric studies were conducted on key flow recirculation passage parameters, including re-injection angles and area ratios, to determine optimal design values. The results largely align with computational analysis of the full passage and experimental test data. Future research should explore additional design parameters under various flow conditions and incorporate a loss parameter to further refine flow control optimization. Additionally, a detailed design analysis and an upgrade of a compressor drive turbine was conducted to enable operation at its maximum design speed. The upgraded drive turbine configuration achieved up to a 20% power increase.
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Thesis
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Distribution Statement
Distribution Statement A. Approved for public release: Distribution is unlimited.
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