Compressor blade row unsteady aerodynamic response to attached and separated flow forcing functions

Kim, Kuk; Fleeter, Sanford

doi:10.2514/6.1992-147

Cited by 7 publications

(2 citation statements)

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“…Advanced inviscid flow analyses are being developed which model p density thickness and camber in the responding blade row, thereby distorting the perturbation by linearizing about the non-uniform steady flow overbar steady component around the blade rather than the simpler upstream uniform flow, for A harmonic component example Goldstein and Atassi [1976], Scott and Atassi [1990], Hall and Verdon [1989], and Fang [1991]. u upper surface A number of experiments have been directed at the verification of such mathematical models and the determination of their * Advanced Product Development, Cummins Engine Company applicability and limitations, for example Capece and Fleeter [1989], Columbus, Indiana Kim and Fleeter [1992], , Manwaring…”

Section: Epmentioning

confidence: 99%

Vortical Gust Response of a Low Solidity Vane Row Including Steady Loading and Dynamic Stall Effects

Henderson

Fleeter

1994

Volume 1: Turbomachinery

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The effects of high steady loading and separated flow on the unsteady aerodynamic response of turbomachine blade rows are experimentally investigated. This is accomplished utilizing a unique single stage turbomachine research facility in which the flow is not generated by the blading but rather by an additional fan. Thus, for a particular stator incidence angle, the steady or mean stator aerodynamic performance were determined in a completely steady flow with no rotor and also with unsteady flow generated by a rotor composed of perforated plates at the same mean operating condition, thereby identifying the stator vane row dynamic stall conditions. The unsteady aerodynamic response of the very low solidity stator vane row is then investigated over a range of incidence angle values, including attached and separated flows with dynamic stall.

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Section: Epmentioning

confidence: 99%

Vortical Gust Response of a Low Solidity Vane Row Including Steady Loading and Dynamic Stall Effects

Henderson

Fleeter

1994

Volume 1: Turbomachinery

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“…Some experimental investigations for compression systems have been made into vane/blade interactions. For compressors, initial research was accomplished using low speed rigs (Kim and Fleeter, 1992) or annular cascades (Henderson and Fleeter, 1992). The low speed and large scale of these experimental rigs simplifies the measurements, but transonic flow phenomena, i.e., shock interaction, can not be modeled.…”

Section: Introductionmentioning

confidence: 99%

Transonic Compressor Influences on Upstream Surface Pressures With Axial Spacing

Koch

Probasco

Wolff

et al. 1999

Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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A set of inlet guide vane (IGV) unsteady surface pressure measurements is presented. The unsteady aerodynamic effects of a highly loaded, high speed downstream compression stage on the upstream inlet guide vane stator surface pressures are characterized through experimental and computational analysis. The axial spacing between the IGV and rotor was varied between 12%, 26%, and 56% of the IGV chord for a 105% speed, peak efficiency operating condition, which is transonic. Unsteady IGV surface pressures were acquired for two spanwise locations on both blade surfaces. The largest unsteady surface pressure magnitudes were obtained at the 12% axial spacing configuration and 95% chord location. In general, spanwise variations were found to be important. The upstream bow shock effect is non-linear in character. Comparisons to a twodimensional, non-linear unsteady multi-blade row Navier-Stokes analysis at 50% span show a good agreement with the IGV unsteady surface pressure results and higher harmonic content. The results of the study indicate significant variations in the IGV unsteady loading caused by changes in axial spacing. NOMENCLATURE C -chord length p -pressure t -time x -distance along vane or blade Subscripts n -normalized s -IGV inlet 1 -IGV upper surface 2 -IGV lower surface

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Variations in Upstream Vane Loading With Changes in Back Pressure in a Transonic Compressor

Probasco

Leger

Wolff

et al. 1998

Journal of Turbomachinery

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Dynamic loading of an inlet guide vane (IGV) in a transonic compressor is characterized by unsteady IGV surface pressures. These pressure data were acquired for two spanwise locations at a 105 percent speed operating condition, which produces supersonic relative Mach numbers over the majority of the rotor blade span. The back pressure of the compressor was varied to determine the effects from such changes. Strong bow shock interaction was evident in both experimental and computational results. Variations in the back pressure have significant influence on the magnitude and phase of the upstream pressure fluctuations. The largest unsteady surface pressure magnitude, 40 kPa, was obtained for the near-stall mass flow condition at 75 percent span and 95 percent chord. Radial variation effects caused by the spanwise variation in relative Mach number were measured. Comparisons to a two-dimensional nonlinear unsteady blade/vane Navier–Stokes analysis show good agreement for the 50 percent span results in terms of IGV unsteady surface pressure. The results of the study indicate that significant nonlinear bow shock influences exist on the IGV trailing edge due to the downstream rotor shock system. [S0889-504X(00)00303-2]

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Compressor blade row unsteady aerodynamic response to attached and separated flow forcing functions

Cited by 7 publications

References 0 publications

Vortical Gust Response of a Low Solidity Vane Row Including Steady Loading and Dynamic Stall Effects

Vortical Gust Response of a Low Solidity Vane Row Including Steady Loading and Dynamic Stall Effects

Transonic Compressor Influences on Upstream Surface Pressures With Axial Spacing

Variations in Upstream Vane Loading With Changes in Back Pressure in a Transonic Compressor

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