Forcing function generator fluid dynamic effects on compressor blade gust response

1994 ◽  
Vol 10 (2) ◽  
pp. 204-216 ◽  
Author(s):  
Kuk H. Kim ◽  
Sanford Fleeter
Keyword(s):  
Fluid Dynamic ◽  
Compressor Blade ◽  
Dynamic Effects ◽  
Function Generator ◽  
Forcing Function ◽  
Gust Response

Forcing Function Effects on Unsteady Aerodynamic Gust Response: Part 2—Low Solidity Airfoil Row Response

1993 ◽  
Vol 115 (4) ◽  
pp. 751-759 ◽  
Author(s):  
G. H. Henderson ◽  
S. Fleeter
Keyword(s):  
Linear Theory ◽  
Perforated Plate ◽  
Function Generator ◽  
Pressure Transducers ◽  
Response Characteristics ◽  
Unsteady Aerodynamic ◽  
Forcing Function ◽  
Annular Cascade ◽  
Airfoil Cascade ◽  
Gust Response

The fundamental gust modeling assumption is investigated by means of a series of experiments performed in the Purdue Annular Cascade Research Facility. The unsteady periodic flow field is generated by rotating rows of perforated plates and airfoil cascades, with the resulting unsteady periodic chordwise pressure response of a downstream low-solidity stator row determined by miniature pressure transducers embedded within selected airfoils. When the forcing function exhibited the characteristics of a linear-theory vortical gust, as was the case for the perforated-plate wake generators, the resulting response on the downstream stator airfoils was in excellent agreement with the linear-theory models. In contrast, when the forcing function did not exhibit linear-theory vortical gust characteristics, i.e., for the airfoil wake generators, the resulting unsteady aerodynamic responses of the downstream stators were much more complex and correlated poorly with the linear-theory gust predictions. Thus, this investigation has quantitatively shown that the forcing function generator significantly affects the resulting gust response, with the complexity of the response characteristics increasing from the perforated-plate to the airfoil-cascade forcing functions.

scholarly journals Forcing Function Effects on Unsteady Aerodynamic Gust Response: Part 2 — Low Solidity Airfoil Row Response

1992 ◽  
Author(s):  
Gregory H. Henderson ◽  
Sanford Fleeter
Keyword(s):  
Linear Theory ◽  
Perforated Plate ◽  
Function Generator ◽  
Pressure Transducers ◽  
Response Characteristics ◽  
Unsteady Aerodynamic ◽  
Forcing Function ◽  
Annular Cascade ◽  
Airfoil Cascade ◽  
Gust Response

The fundamental gust modeling assumption is investigated by means of a series of experiments performed in the Purdue Annular Cascade Research Facility. The unsteady periodic flow field is generated by rotating rows of perforated plates and airfoil cascades, with the resulting unsteady periodic chordwise pressure response of a downstream low solidity stator row determined by miniature pressure transducers embedded within selected airfoils. When the forcing function exhibited the characteristics of a linear-theory gust, as was the case for the perforated-plate wake generators, the resulting response on the downstream stator airfoils was in excellent agreement with the linear-theory models. In contrast, when the forcing function did not exhibit linear-theory gust characteristics, i.e., for the airfoil wake generators, the resulting unsteady aerodynamic response of the downstream stators were much more complex and correlated poorly with the linear-theory gust predictions. Thus, this investigation has quantitatively shown that the forcing function generator significantly affects the resulting gust response, with the complexity of the response characteristics increasing from the perforated-plate to the airfoil-cascade forcing functions.

Fluid dynamic effects of grooves on circular cylinder surface

AIAA Journal ◽  
1991 ◽  
Vol 29 (12) ◽  
pp. 2062-2068 ◽  
Author(s):  
Takeyoshi Kimura ◽  
Michihisa Tsutahara
Keyword(s):  
Circular Cylinder ◽  
Fluid Dynamic ◽  
Cylinder Surface ◽  
Dynamic Effects

scholarly journals PC206. A Novel Computation Model of the Carotid Artery to Determine Fluid Dynamic Effects on Plaque Instability

2016 ◽  
Vol 63 (6) ◽  
pp. 217S
Author(s):  
Kristy Cosgrove ◽  
Scott J. Hymel ◽  
T. Cooper Woods ◽  
Damir B. Khismatullin ◽  
Hernan Bazan
Keyword(s):  
Carotid Artery ◽  
Fluid Dynamic ◽  
Dynamic Effects ◽  
Computation Model ◽  
Plaque Instability

Fluid Dynamic Effects in the Fuel Element Top Nozzle Area during Refilling and Reflooding

1984 ◽  
Vol 88 (3) ◽  
pp. 376-385 ◽  
Author(s):  
A. Hawighorst ◽  
H. Kröning ◽  
F. Mayinger
Keyword(s):  
Fuel Element ◽  
Fluid Dynamic ◽  
Dynamic Effects

Forcing Function Effects on Unsteady Aerodynamic Gust Response: Part 1 — Forcing Functions

1992 ◽  
Author(s):  
Gregory H. Henderson ◽  
Sanford Fleeter
Keyword(s):  
Linear Theory ◽  
Static Pressure ◽  
Pressure Fluctuations ◽  
Perforated Plate ◽  
Flow Angle ◽  
Unsteady Aerodynamic ◽  
Forcing Function ◽  
Forcing Functions ◽  
Relative Flow ◽  
Gust Response

The fundamental gust modeling assumption is investigated by means of a series of experiments performed in the Purdue Annular Cascade Research Facility. The unsteady periodic flow field is generated by rotating rows of perforated plates and airfoil cascades. In this paper, the measured unsteady flow fields are compared to linear-theory gust requirements, with the resulting unsteady gust response of a downstream stator cascade correlated with linear theory predictions in an accompanying paper. The perforated-plate forcing functions closely resemble linear-theory forcing functions, with the static pressure fluctuations small and the periodic velocity vectors parallel to the downstream mean-relative flow angle over the entire periodic cycle. In contrast, the airfoil forcing functions exhibit characteristics far from linear-theory gusts, with the alignment of the velocity vectors and the static pressure fluctuation amplitudes dependent on the rotor-loading condition, rotor solidity and the inlet mean-relative flow angle. Thus, these unique data clearly show that airfoil wakes, both compressor and turbine, are not able to be modeled with the boundary conditions of current state-of-the-art linear unsteady aerodynamic theory.

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