Aerodynamic instability performance of an advanced high-pressure-ratio compression component

Hosny, W. M.; Steenken, William

doi:10.2514/6.1986-1619

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…This table indicates that the close coupled data included measurements at compressor inlet, interstage and exit locations. The data obtained were similar to those defined by Hosny [6] while performing an in stall test on the NASA Energy Efficient Engine compressor. In the test described by Hosny, measurements were made with inlet transient airflow rakes, exit transient air flow rakes and static pressure taps at the inlet, exit and interstage of the compressor.…”

Section: Close Coupled Pressure Measurementsupporting

confidence: 77%

“…This information is essential to the characterization of the unsteady pressures that occur within a compressor while operating in rotating stall. Greitzer [6] indicated the need for total pressure measurements to accurately determine the characteristics of a rotating stall cell. In addition, the total pressure measurements obtained at different immersions and inside diameter (I.D.)…”

Section: Close Coupled Pressure Measurementmentioning

confidence: 99%

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Acquisition of Unsteady Pressure Measurements From a High Speed Multi-Stage Compressor

Copenhaver

Worland

1988

Volume 1: Turbomachinery

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Two methods for acquiring transient pressure measurements from a high speed multi-stage compressor are presented. Data were obtained from upstream, inter-stage and downstream measurement locations on the compressor during unsteady operation. The two methods of data acquisition were real time digital conversion of close coupled pressures and frequency modulated (FM) analog recording of high response measurements. The close coupled measurements provide for a nominal frequency response of 70 Hz while the high response measurements provided 200 Hz nominal response. A description of both acquisition systems is provided with discussion of the limitations involved in both methods. Examples and comparisons of data obtained by both methods are presented.

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Section: Close Coupled Pressure Measurementsupporting

confidence: 77%

Section: Close Coupled Pressure Measurementmentioning

confidence: 99%

Acquisition of Unsteady Pressure Measurements From a High Speed Multi-Stage Compressor

Copenhaver

Worland

1988

Volume 1: Turbomachinery

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“…With the advent of advanced gas turbines, jet engines, combined-cycle plants, industrial compressor plants, etc, being operated at high level of pressure ratios in complicated flow-path conditions, further studies are being demanded for security of the operational safety. In the situations, a number of studies on the detailed behaviors of flows and performance characteristics in surge in the compressor systems have been conducted (for example, Gamache and Greitzer [4], Day, Greitzer and Cumpsty [5], Hosny and Steenken [6], Boyer and O'Brien [7], Copenhaver and Okiishi [8], etc. ).…”

Section: Introductionmentioning

confidence: 99%

A Study on the Fundamental Surge Frequencies in Multi-Stage Axial Flow Compressor Systems

Yamaguchi¹

2014

International Journal of Fluid Machinery and Systems

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Surge phenomena in multi-stage axial flow compressors were studied with attention to the frequency behaviors. A new parameter "volume-modified reduced surge frequency" was introduced, which took into consideration the essential surge process, i.e., emptying and filling of the working gas in the delivery plenum. The behaviors of the relative surge frequencies at the stall stagnation boundaries, compared with the corresponding duct resonance frequencies, have demonstrated the existence of two types of surges; i.e., a near-resonant surge and a subharmonic surge. The former, which has fundamentally a near-resonance frequency, occurs predominantly at the stall stagnation boundary for the short -and-fat plenum delivery flow-path and the long-and-narrow delivery duct flow-path, and possibly in the intermediate conditions. The latter, which has a subharmonic frequency of the fundamental near-resonant one and occurs mainly in the inter-mediate zone, is considered to be caused by the reduced frequency restricted to a limited range. In relation with those dimensionless frequencies at the stall stagnation boundary, the surge frequency behaviors in more general situations away from the boundaries could be estimated, though very roughly.

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“…Experimental testing of surge, or compressor stall in general, is very rare on high-speed multi-stage machines representative of real engines [1][2][3]. Compressor stall experimental testing is extremely expensive and often limited to avoid damage to the rig [4,5].…”

Section: Introductionmentioning

confidence: 99%

Experimental validation of a three-dimensional through-flow model for high-speed compressor surge

Righi

Pachidis²,

Könözsy³

et al. 2022

Aerospace Science and Technology

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Aerodynamic instability performance of an advanced high-pressure-ratio compression component

Cited by 6 publications

References 2 publications

Acquisition of Unsteady Pressure Measurements From a High Speed Multi-Stage Compressor

Acquisition of Unsteady Pressure Measurements From a High Speed Multi-Stage Compressor

A Study on the Fundamental Surge Frequencies in Multi-Stage Axial Flow Compressor Systems

Experimental validation of a three-dimensional through-flow model for high-speed compressor surge

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