Investigation of flow separation in a transonic-fan linear cascade using visualization methods

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National Aeronautics and Space Administration, Glenn Research Center, National Technical Information Service, distributor , [Cleveland, Ohio], Springfield, VA
Transonic flutter., Flow visualization., Supersonic flow., Boundary layer separa
StatementJan Lepicovsky ... [et al.].
Series[NASA technical memorandum] -- NASA/TM-2000-210521., NASA technical memorandum -- 210521.
ContributionsLepicovsky, Jan., NASA Glenn Research Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17717459M

Lepicovsky J, Chima RV, Jett TA, Bencic TJ, Weiland KE () Investigation of flow separation in a transonic-fan linear cascade using visualization methods, NASA TM– Google Scholar Shaw LM, Boldman DR, Buggele AE () Unsteady pressure measurements on a biconvex airfoil in a transonic oscillating cascade, NASA TM Google Cited by: Investigation of flow separation in a transonic-fan linear cascade using visualization methods (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Jan Lepicovsky; NASA Glenn Research Center.

Investigation of flow separation in a transonic-fan linear cascade using visualization methods (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: Jan Lepicovsky; NASA Glenn Research Center.

Complex Flow Separation Pattern on Transonic Fan Airfoils Revealed by Flow Visualization Modern turbofan engines employ a highly loaded fan stage with transonic or low-supersonic velocities in the blade-tip region. The fan blades are often prone to flutter at off-design conditions.

Vol Issue 6, June ISSN: (Print) Investigation of flow separation in a transonic-fan linear cascade using visualization methods. a series of cascade wind tunnel tests to provide the data for blade flutter research. An extensive experimental study on the nature of the separated flows of a modern transonic fan airfoil at high incidence has been reported[7].

In their re-search, visualization methods were used to investigate the flow separation. Steady and unsteady. The resulting conclusion of this study is that the use of scale-resolving methods such as LES or the application of DNS is necessary to correctly predict unsteadiness of the transonic cascade flow.

Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry Anthony J. Sti'azisar - "Lewis Research Center ' Cleveland, Ohio _.L • Prepared for the Twenty-ninth Annual International Gas Turbine Conference sponsored by the American Society of Mechanical Engineers Amsterdam, The Netherlands, JuneCited by: The six cascade Investigation of flow separation in a transonic-fan linear cascade using visualization methods book are supported by side walls made of acrylic (perspex) which provide optical access to the entire test section (see Fig.

Cascade parameter under design conditions can be found in Tab. Visualization and PIV measurements are carried out in the passage between the third and forth airfoil.

Fig. 1 Datum geometry (a).

Details Investigation of flow separation in a transonic-fan linear cascade using visualization methods FB2

Request PDF | Axisymmetric hub-endwall profile optimization for a transonic fan to improve aerodynamic performance based on an integrated design optimization method | This paper investigates an.

vibration is modeled with an aeroelasticity model in which blade motion is computed by linear combination of responses of each mode under unsteady loads. The code is validated in prediction of the unsteady flow flutter behavior of an oscillating cascade and is applied to flutter analysis of a.

Inlet distortion often occurs under off-design conditions when a flow separates within an intake and this unsteady phenomenon can seriously impact fan performance. Fan–distortion interaction is a highly unsteady aerodynamic process into which high-fidelity simulations can provide detailed by: 2.

Active Flow Separation Control Using Endwall Vortex Generator Jets in Highly Loaded Compressor Cascades. Investigation of Corner Separation in a Linear Compressor Cascade Using DDES.

Yangwei Liu, Hao Yan, Measured Heat Transfer in a Transonic Fan Rig at Casing With Implications on Performance. Mark G. Turner. Tucker, PG and Liu, Y and Chung, M and Jouvray, A () Computation of an unsteady complex geometry flow using novel non-linear turbulence models. International Journal for Numerical Methods in Fluids, pp.

ISSN Tucker, PG () Novel multigrid orientated solution adaptive time-step approaches. This investigation extends the study of fan-distortion interactions to an actual turbofan engine with a total pressure distortion profile representative of a boundary-layer ingesting (BLI) embedded engine.

The goal was to make a series of flow measurements that contribute to the overall physical understanding of this complex flow situation. Experimental Investigation of a Single Stage Axial Flow Compressor With Controlled Diffusion Airfoils.

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S Part 1 — Linear Cascade Experiment. GT Cascades (Fluid dynamics), Turbines, Unsteady flow, Bubbles, Flow separation, Blades, Turbulence, Boundary layers, Computation, Computational methods. Inlet Distortion. Aerodynamic Design and Testing of an Imbedded Forward Swept Rotor in a Two-Stage Transonic Fan.

R on the Applicability of Using a Curved Blade to Optimize the Flow Loss Weight Distribution of a Linear Compressor Cascade With Different Flow Separation Types. Numerical Investigation of Passive Flow Control Using Wavy Blades in a Highly.

Investigation of the 3-D Flow Structure in a High-Speed Annular Compressor Cascade for Tip Clearance Effects Boundary layers, Pressure gradient, Turbulence, Flow visualization, Separation (Technology) External Heat Transfer Predictions in a Highly-Loaded Transonic Linear Turbine Guide Vane Cascade Using an Upwind Biased Navier.

Flow over the Onera M6 wing is transonic and compressible. The wing flow experiences supersonic conditions, a shock and boundary layer separation. There is no wing twist, with all chords being in the same plane.

Therefore, the angle of attack is simply the angle between the free stream and the chord line. There is no side-slip in the simulation. This banner text can have markup.

web; books; video; audio; software; images; Toggle navigation. International Journal of Turbomachinery, Propulsion and Power (ISSN X) is an international peer-reviewed open access journal on turbomachinery, propulsion and power. It is the journal of the EUROTURBO European turbomachinery society and is published online quarterly by MDPI.

Open Access - free for readers, with article processing charges (APC) paid by authors or their institutions. Close Drawer Menu Close Drawer Menu Menu.

Description Investigation of flow separation in a transonic-fan linear cascade using visualization methods PDF

Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of. Experimental Investigation of the Flow in a Forward Swept Transonic Compressor Rotor at Stall Inception Optimization of the Gas Turbine Engine Parts Using Methods of Numerical Simulation.

LRotors, Diffusers, Flow (Dynamics), Pressure, Design, Flow separation, Lasers, Optical measurement. A New Slip Factor Correlation for. Investigation of 3D Unsteady Flows in a Two-Stage Shrouded Axial Turbine Using Stereoscopic PIV and FRAP: Part II — Kinematics of Shroud Cavity Flow Y.

Yun. Turbomachinery has been widely used in the energy systems as an energy conversion device, such as gas turbine and aero-engine. The losses in the turbomachinery, especially in the multi-stage conditions, restrict the energy conversion efficiency and corresponding fuel economy.

Previous studies show that non-axisymmetric endwall could be used to decrease the losses in compressors, but the real. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The mixing of the cooling flow with the main flow alters the aerodynamics of the flow within the turbine cascade.

The cooling flow that is injected into the main flow needs to be optimized, not only in terms of thermodynamic parameters, but also in terms of the locations to ensure the turbine vanes and blade surfaces are maintained well below. Advances in Gas Turbine Technology inlet flow field occurred after optimization but the flow field structure in the duct is clearly different.

The negative curvature of the blade upstream of the shock led to the reduction of the upstream relative Mach number from to With this curvature change, the velocity slowdown is better driven.

Masi, A and Cui, J and Tucker, PG () Numerical investigation of flow separation from aircraft tail surfaces. In: UNSPECIFIED. Nagabhushana Rao, V and Tucker, PG () Intake lip separation control using plasma actuators.

In: 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, to The Joint Propulsion Conference focuses on identifying and highlighting how innovative aerospace propulsion technologies powering both new and evolving systems are being designed.

Part 5: Flow instabilities-Analysis of unsteady casing-Core compressor rotating stall simulation with a multi-bladerow model-Parametric study of surface roughness and wake unsteadiness on a flat plate with large pressure gradient-Bypass flow pattern changes at turbo-ram transient operation of combined cycle engine-Experimental investigation of.Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, " See other formats.Full text of "Aeronautical engineering: A special bibliography with indexes (supplement 8)" See other formats.