Flow Effects in a Vertical CVD Reactor

1992 ◽  
Vol 52 (6) ◽  
pp. 1509-1532 ◽  
Author(s):  
G. W. Young ◽  
S. I. Hariharan ◽  
R. Carnahan
Keyword(s):  
Flow Effects ◽  
Vertical Cvd Reactor

FLOW EFFECTS AND MODELING IN GAS-COOLED QUENCHING

1998 ◽  
Author(s):  
Mats Lind ◽  
Noam Lior ◽  
Fritz H. Bark ◽  
Farid Alavyoon
Keyword(s):  
Flow Effects

Numerical Investigation on the Effect of Vortex Generator on Axial Compressor Performance

2014 ◽  
Author(s):  
Ruchika Agarwal ◽  
Anand Dhamarla ◽  
Sridharan R. Narayanan ◽  
Shraman N. Goswami ◽  
Balamurugan Srinivasan
Keyword(s):  
Cross Flow ◽  
Axial Compressor ◽  
Vortex Generator ◽  
Side Surface ◽  
Suction Side ◽  
Test Case ◽  
Stall Margin ◽  
Layer Flow ◽  
Flow Effects ◽  
End Wall

The performance of the compressor blade is considerably influenced by secondary flow effects, like the cross flow on the end wall as well as corner flow separation between the wall and the blade. The present work is focused on the studying the effects of Vortex Generator (VG) on NASA Rotor 37 test case using Computational Fluid Dynamics (CFD). VG helps in controlling the inception of the stall by generating vortices and energizes the low momentum boundary layer flow which enhances the rotor performance. Three design configuration namely, Counter-rotating, Co-rotating and Plow configuration VG are selected based on the improved aerodynamic performance discussed in reference [1]. These VG are located at 90% span and 42% chord on suction side surface of the blade. Among the three configurations, the first configuration has greater impact on the end wall cross flow and flow deflection which resulted in enhanced numerical stall margin of 5.4% from baseline. The reasons for this numerical stall margin improvement are discussed in detail.

Dynamic Simulation of Blood Flow Effects on Flexible Manipulators During Intra-Cardiac Procedures on the Beating Heart

2011 ◽  
Author(s):  
A. Salimi ◽  
J. Mohammadpour ◽  
K. Grigoriadis ◽  
N. V. Tsekos
Keyword(s):  
Blood Flow ◽  
Degrees Of Freedom ◽  
Beating Heart ◽  
Flexible Manipulator ◽  
External Disturbances ◽  
Actuation System ◽  
Cardiac Procedures ◽  
Rigid Body Model ◽  
Flow Effects ◽  
Valve Implantation

In this paper, we develop a numerical mixed flexible-rigid body model to take into account the effects of the external disturbances acting on a flexible manipulator secondary to the oscillatory transmitral blood flow in the left ventricle. The manipulator is made of a flexible rubber-like material to further extend the surgical robotic-based catheters’ degrees of freedom and steer-ability in beating-heart prosthetic aortic valve implantation procedure. Along with the developed numerical model, a detailed description of the catheter’s mechanical architecture and the actuation system is also provided. Necessity of employing such a model for the designed system is clearly justified using simulation studies.

End-Wall Film Cooling Through Fan-Shaped Holes With Different Area Ratios

2006 ◽  
Vol 129 (2) ◽  
pp. 212-220 ◽  
Author(s):  
Giovanna Barigozzi ◽  
Giuseppe Franchini ◽  
Antonio Perdichizzi
Keyword(s):  
Secondary Flow ◽  
Mass Flow ◽  
Film Cooling ◽  
Three Dimensional ◽  
Wide Band ◽  
Lateral Spreading ◽  
Area Ratio ◽  
Adiabatic Effectiveness ◽  
Flow Effects ◽  
End Wall

The present paper reports on the aerothermal performance of a nozzle vane cascade, with film-cooled end walls. The coolant is injected through four rows of cylindrical holes with conical expanded exits. Two end-wall geometries with different area ratios have been compared. Tests have been carried out at low speed (M=0.2), with coolant to mainstream mass flow ratio varied in the range 0.5–2.5%. Secondary flow assessment has been performed through three-dimensional (3D) aerodynamic measurements, by means of a miniaturized five-hole probe. Adiabatic effectiveness distributions have been determined by using the wide-band thermochromic liquid crystals technique. For both configurations and for all the blowing conditions, the coolant share among the four rows has been determined. The aerothermal performances of the cooled vane have been analyzed on the basis of secondary flow effects and laterally averaged effectiveness distributions; this analysis was carried out for different coolant mass flow ratios. It was found that the smaller area ratio provides better results in terms of 3D losses and secondary flow effects; the reason is that the higher momentum of the coolant flow is going to better reduce the secondary flow development. The increase of the fan-shaped hole area ratio gives rise to a better coolant lateral spreading, but appreciable improvements of the adiabatic effectiveness were detected only in some regions and for large injection rates.

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