Now showing items 1-10 of 10
Reduction of Unsteady Stator-Rotor Interaction by Trailing Edge Blowing Using MEMS Based Microvalves
(Virginia Tech, 1999-04-16)
This research performs an experimental study of a trailing edge blowing system that can adapt to variations in flow parameters and reduce the unsteady stator-rotor interaction at all engine operating conditions. The fan ...
Noise Reduction in an Axisymmetric Supersonic Aircraft Inlet using Trailing Edge Blowing
(Virginia Tech, 1998-01-21)
Acoustic experiments were conducted in an anechoic chamber with a 1/14th scale model of a supersonic aircraft engine inlet using Trailing Edge Blowing (TEB) to reduce the engine fan noise from a turbofan propulsion simulator ...
Effects of Mach Number and Flow Incidence on Aerodynamic Losses of Steam Turbine Blades
(Virginia Tech, 1997-04-15)
An experiment was conducted to investigate the aerodynamic losses of two high-pressure steam turbine nozzles (526A, 525B) subjected to a large range of incident angle and exit Mach number. The blades were tested in a 2D ...
The correlation of randomness with high tip losses in an axial flow fan stage
(Virginia Tech, 1991-04-19)
<p>The results of a test program incorporating a dual hot wire aspirating probe to radially survey the by-pass duct downstream of an axial flow fan stage are presented. The probe measures time resolved total temperature ...
A modified Baldwin-Lomax turbulence model for turbomachinery wakes
(Virginia Tech, 1991-01-08)
A critical evaluation of the Baldwin-lomax (Bl) turbulence model for shock/shear layer interactions, reversed flow, and curved, asymmetric wakes is made. No general definition for reference line is available for wakes, ...
Reduced fan noise radiation from a supersonic inlet
(Virginia Tech, 1993-04-15)
Reduction of Unsteady Rotor-Stator Interaction Using Trailing Edge Blowing
(Virginia Tech, 1997-01-16)
An aeroacoustic investigation was performed to assess the effects of adding mass flow at the trailing edges of four stators upstream of an aircraft engine simulator. By using trailing edge blowing to minimize the shed wakes ...
3-D flow calculations of a bifurcated 2D supersonic engine inlet at takeoff
(Virginia Tech, 1995-08-05)
<p>An internal, 3-D, viscous numerical flow simulation was performed on the rectangular-to-circular transition, bifurcated, 2D high speed civil transport engine inlet at takeoff. The objective of the study was to obtain ...
Aspirating probes for measurement of mean concentration and fluctuating quantities in supersonic air/helium shear layer
(Virginia Tech, 1990-12-31)
Two aspirating hot-film probes are developed to make measurements in supersonic air/helium shear layers. The first probe is designed to measure local mean gas composition and is referred to as the mean concentration probe. ...
Preliminary experiment and analysis of supersonic inlet buzz
(Virginia Tech, 1996-12-05)
<p>The inlet buzz phenomenon was investigated experimentally and analytically. An external-compression axisymmetric inlet model, having 74 mm in cowl lip diameter, was tested in the 229x229 sq mm blowdown wind tunnel at ...