scholarly journals Closure to “Discussion of ‘Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 1—Experiment’” (1991, ASME J. Turbomach., 113, p. 226)

1991 ◽  
Vol 113 (2) ◽  
pp. 226-226 ◽  
Author(s):  
R. C. Stauter ◽  
R. P. Dring ◽  
F. O. Carta
Keyword(s):  
Axial Compressor ◽  
Two Stage ◽  
Spatially Resolved

Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 1—Experiment

1991 ◽  
Vol 113 (2) ◽  
pp. 219-225 ◽  
Author(s):  
R. C. Stauter ◽  
R. P. Dring ◽  
F. O. Carta
Keyword(s):  
Fluid Dynamics ◽  
Fluid Dynamic ◽  
Axial Compressor ◽  
Spatial Variations ◽  
Navier Stokes ◽  
Dense Matrix ◽  
Two Stage ◽  
Data Set ◽  
Spatially Resolved ◽  
Interactive Nature

The fluid dynamics of turbomachines are extremely complex, due in part to the aerodynamic interactions between rotors and stators. It is necessary to acquire fluid dynamic data that reflect the interactive nature of a turbomachine to correlate with the fluid dynamics predicted from modern analyses. The temporal and spatial variations in the midspan aerodynamics of the second stage of a two-stage compressor have been studied with a two-component LDV system. Spatial variations were examined by traversing the LDV probe volume through a dense matrix of both axial and circumferential positions, while temporal resolution was achieved by acquiring all data as a function of the instantaneous rotor position. Hence, the data set reveals rotor and stator wake structure and decay in both the stationary and rotating frames of reference. The data also compared very favorably with extensive pneumatic measurements previously acquired in this compressor. In Part 2 of the paper, the data are used in the assessment of a prediction of the flow in the compressor using a time-accurate, thin-layer, two-dimensional Navier–Stokes analysis.

scholarly journals Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 1 — Experiment

1990 ◽  
Author(s):  
R. Charles Stauter ◽  
Robert P. Dring ◽  
Franklin O. Carta
Keyword(s):  
Fluid Dynamics ◽  
Fluid Dynamic ◽  
Axial Compressor ◽  
Spatial Variations ◽  
Navier Stokes ◽  
Dense Matrix ◽  
Two Stage ◽  
Data Set ◽  
Spatially Resolved ◽  
Interactive Nature

The fluid dynamics of turbomachines are extremely complex, due in part to the aerodynamic interactions between rotors and Stators. It is necessary to acquire fluid dynamic data that reflect the interactive nature of a turbomachine to correlate with the fluid dynamics predicted from modern analyses. The temporal and spatial variations in the midspan aerodynamics of the second stage of a two-stage compressor have been studied with a two-component LDV system. Spatial variations were examined by traversing the LDV probe volume through a dense matrix of both axial and circumferential positions while temporal resolution was achieved by acquiring all data as a function of the instantaneous rotor position. Hence, the data set reveals rotor and Stator wake structure and decay in both the stationary and rotating frames of reference. The data also compared very favorably with extensive pneumatic measurements previously acquired in this compressor. In Part 2 of the paper, the data are used in the assessment of a prediction of the flow in the compressor using a time-accurate, thin-layer, two-dimensional Navier-Stokes analysis.

Structure and Propagation of Rotating Stall in a Single- and a Multi-Stage Axial Compressor

1999 ◽  
Author(s):  
H. M. Saxer-Felici ◽  
A. P. Saxer ◽  
F. Ginter ◽  
A. Inderbitzin ◽  
G. Gyarmathy
Keyword(s):  
Numerical Solutions ◽  
Equations Of Motion ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Water Model ◽  
Two Stage ◽  
Additional Information ◽  
Driving Mechanisms ◽  
Multi Stage ◽  
Stall Cells

The structure and propagation of rotating stall cells in a single- and a two-stage subsonic axial compressor is addressed in this paper using computational and experimental analysis. Unsteady solutions of the 2-D inviscid compressible (Euler) equations of motion are presented for one operating point in the fully-developed rotating stall regime for both a single- and a two-stage compressor. The inviscid assumption is verified by comparing the single-stage 2-D in viscid/compressible solution with an equivalent 2-D viscous (Navier-Stokes) result for incompressible flow. The structure of the rotating stall cell is analyzed and compared for the single- and two-stage cases. The numerical solutions are validated against experimental data consisting of flow visualization and unsteady row-by-row static pressure measurements obtained in a four-stage water model of a subsonic compressor. The CFD solutions supply a link between the observed experimental features and provide additional information on the structure of the stall flow. Based on this study. supporting assumptions regarding the driving mechanisms for the propagation of fully-developed rotating stall cells and their structure are postulated. In methodical respect the results suggest that the inviscid model is able to reproduce the essentials of the flow physics associated with the propagation of fully-developed, full-span rotating stall in a subsonic axial compressor.

Failure mechanism of casing treatment in improving stability of a highly loaded two-stage axial compressor

2020 ◽  
Vol 105 ◽  
pp. 105979
Author(s):  
Wei Wang ◽  
Jin-ling Lu ◽  
Xing-qi Luo ◽  
Rui Huang ◽  
Wu-li Chu
Keyword(s):  
Failure Mechanism ◽  
Axial Compressor ◽  
Two Stage ◽  
Casing Treatment ◽  
Highly Loaded

Experimental Analysis of the Flow in a Two Stage Axial Compressor at Off-Design Conditions

1987 ◽  
Author(s):  
Aristide Massardo ◽  
Antonio Satta
Keyword(s):  
Boundary Layer ◽  
Experimental Analysis ◽  
Energy Flow ◽  
Axial Compressor ◽  
Axial Flow ◽  
Low Energy ◽  
Tip Clearance ◽  
Two Stage ◽  
Local Conditions ◽  
Flow Compressor

The experimental analysis of the flow that develops in a two stage axial flow compressor at off-design conditions is presented. The measurements are performed upstream, between and downstream of the four blade rows of the compressor. The analysis shows the off-design effects on the local conditions of the flow field. Low energy flow zones are identified, and the development of annulus boundary layer, secondary and tip clearance flows, are shown. The tip clearance flows are also present in the stator rows with various outlying conditions (stationary or rotating hub).

scholarly journals Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 2—Computational Assessment

1991 ◽  
Vol 113 (2) ◽  
pp. 227-232 ◽  
Author(s):  
K. L. Gundy-Burlet ◽  
M. M. Rai ◽  
R. C. Stauter ◽  
R. P. Dring
Keyword(s):  
Fluid Dynamics ◽  
Experimental Data ◽  
Thin Layer ◽  
Axial Compressor ◽  
Unsteady Aerodynamics ◽  
Numerical Data ◽  
Navier Stokes ◽  
Grid Refinement ◽  
Spatially Resolved ◽  
Multistage Compressor

Fluid dynamics of turbomachines are complicated because of aerodynamic interactions between rotors and stators. It is necessary to understand the aerodynamics associated with these interactions in order to design turbomachines that are both light and compact as well as reliable and efficient. The current study uses an unsteady, thin-layer Navier–Stokes zonal approach to investigate the unsteady aerodynamics of a multistage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results have been computed for a 2 1/2-stage compressor configuration. The numerical data compare well with experimental data for surface pressures and wakes. In addition, the effect of grid refinement on the solution is studied.

Development of a Control System for a Dual-Shaft Gas Turbine for Rapid Load Acceptance and Rejection

1962 ◽  
Author(s):  
Leo P. McGuire
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Two Stage ◽  
Control Valves ◽  
Air Inlet ◽  
Voltage Variation ◽  
Power Turbine ◽  
Voltage Recovery

The application required large electrical load changes with very limited variations in frequency and voltage. With a dual-shaft gas turbine, nominal rating 8000 kilowatts, instantaneous loads up to 90 per cent rated were successfully accepted and rejected with frequency maintained within a one and one half per cent band. Voltage variation did not exceed four per cent. Frequency and voltage recovery were well within two seconds. The foregoing was accomplished by incorporating a control system which permitted operation of the turbine at other than normal operating conditions when auxiliary control valves were preset in anticipation of the load variation. The auxiliary control valves were air-inlet throttling valves, an inter-turbine bleed valve, and an additional fuel valve. The basic machine consisted of a 15-stage axial compressor, a two-stage, high-pressure turbine, and a two-stage power turbine. The unique requirements necessitated off-design operation and considerable extrapolation from known test data. However, it was possible to program the control-system components so that a conventional pneumatic control system was capable of maintaining speed within the prescribed band even though the applied load varied from that anticipated by as much as 12.5 per cent.

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