AerospaceAdverse pressure gradients are intrinsic to compressor flow behavior and are further intensified by secondary effects associated with rotor tip clearance flow interactions. Tip clearance generates leakage flow, which leads to the formation of tip leakage
Pedro Seiti Endo +4 more
doaj +1 more source
Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05 [PDF]
The overall and blade-element performances of a low-aspect-ratio transonic compressor stage are presented over the stable operating flow range for speeds from 50 to 100 percent of design.
Moore, R. D., Reid, L.
core +1 more source
Sliding Mode Control in Aerospace Applications: A Survey
International Journal of Robust and Nonlinear Control, EarlyView.ABSTRACT Sliding mode control (SMC) enjoys robustness to matched and unmatched (in the case of minimum phase input‐output dynamics) bounded perturbations, and finite time convergence. Second‐order and higher‐order sliding mode control systems (2‐SMC/HOSMC) retain all the advantages of sliding mode control, but in addition can be applied to systems of ...
Yuri Shtessel, Christopher Edwards
wiley +1 more source
High-tip-speed, low-loading transonic fan stage. Part 3: Final report [PDF]
Tests were conducted on a high-tip-speed, low-loading transonic fan stage to determine the performance and inlet flow distortion tolerance of the design.
Jackson, R. J. +2 more
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Using Fine Sediment Monitoring to Quantify Sand Loading Over Time
River Research and Applications, EarlyView.ABSTRACT Riverine sand loading can lead to geomorphic change, impacting river processes like lateral migration and vertical aggradation or degradation. Yet many sediment monitoring programs track only fine sediment measurable as total suspended solids (TSS). Here, we assess the ability for TSS data to be used to determine sand loading.
Andrew P. Kasun, Karen B. Gran
wiley +1 more source
Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82 [PDF]
The overall and blade-element performance of a transonic compressor stage is presented over the stable operating flow range for speeds from 50 to 100 percent of design.
Moore, R. D., Reid, L.
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Steady and Unsteady Flow Effects of Circumferential Grooves Casing Treatment in a Transonic Compressor Rotor [PDF]
, 2011 The current paper reports on an investigation of steady and unsteady flow effects of circumferential grooves casing treatment in a transonic compressor rotor.
Hah, Chunill
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International Journal of Satellite Communications and Networking, EarlyView.ABSTRACT The integration of low Earth orbit (LEO) satellite constellations with commercial aircraft communication systems presents critical challenges in maintaining continuous connectivity during dynamic flight conditions. Current geostationary satellite systems suffer from high round‐trip latency (>$$ > $$ 500 ms) and inadequate coverage at high ...
Raúl Parada +4 more
wiley +1 more source
Dynamic System Stability Modeling Approach with Sparrow-Inspired Meta-Heuristic Optimization Algorithm. [PDF]
Biomimetics (Basel), 2023 Xia T, Zhang M, Wang S.
europepmc +1 more source
Performance with and without inlet radial distortion of a transonic fan stage designed for reduced loading in the tip region [PDF]
A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades was tested with and without inlet radial distortion. The rotor was 50 cm in diameter and designed for an operating tip speed of 420 m/sec.
Ruggeri, R. S., Schmidt, J. F.
core +1 more source