Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry

Strazisar, A. J.

doi:10.1115/1.3239743

Cited by 51 publications

(10 citation statements)

References 1 publication

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“…With the exception of the model of Wennerstrom and Puterbaugh [17] this is normally neglected in even the most sophisticated shock loss models, e.g. that of Kö nig et al [18], constructed from purely two-dimensional considerations in the blade-toblade plane, but was demonstrated, among others by Strazisar [19] and by Wood et al [20], to have decisive influence on the shock strength. Preliminary experience seems to indicate, however, that the structure and upstream Mach number of shocks captured in analysis mode are difficult to control.…”

Section: The Relevance Of Captured Throughflow Shocksmentioning

confidence: 99%

Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver

Sturmayr

Hirsch

1999

Proceedings of the Institution of Mechanical Engineers, Part A:

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A multiblock multigrid Navier-Stokes solver has been extended to include a throughflow model for the design and analysis of turbomachines. The presence of the blades in the inviscid axisymmetric flow is modelled in the classical way through a distributed blade force to produce the desired turning, a blockage factor that accounts for the reduced area due to blade thickness, and a distributed frictional force representing the entropy increase due to viscous stresses and heat conduction. The exact blade geometry is not required. All features of the three-dimensional code concerning the physical fluid model, boundary conditions, spatial and time discretization, convergence acceleration techniques and data visualization are available to the throughflow module. This includes the capability to treat the entire range of relevant Mach numbers, from strictly incompressible (through a preconditioning technique) to supersonic, as well as any number of blade rows in any configuration, including, for example, bypass engines. Selected elements comprising the throughflow model are discussed, with special emphasis on the blade force and its discretization. The properties of analysis and design mode with respect to shocks and the associated losses are investigated. The methodology is demonstrated on a transonic compressor rotor and a four-stage low-speed turbine.

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Section: The Relevance Of Captured Throughflow Shocksmentioning

confidence: 99%

Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver

Sturmayr

Hirsch

1999

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Shaft encoder information was used to develop blade-to-blade velocity profiles. Strazisar (1985) used a laser velocimeter and a variable clock that was phase locked to the shaft to investigate the flow field between the blades in a transonic fan. An oscillating shock was seen.…”

Section: Previous Research Of Unsteady Flows In Turbo Machinesmentioning

confidence: 99%

Laser Velocimeter Measurements in the Turbine of an Automotive Torque Converter: Part II — Unsteady Measurements

Bran

Flack

1995

Volume 1: Turbomachinery

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The unsteady velocity field found in the turbine of an automotive torque converter was measured using laser velocimetry. Velocities in the inlet, quarter, mid, and exit planes of the turbine were investigated at two significantly different operating conditions: turbine/pump rotational speed ratios of 0.065, and 0.800. A data organization method was developed to visualize the three-dimensional, periodic unsteady velocity field in the rotating frame. For this method, the acquired data is assumed to be periodic at synchronous and blade interaction frequencies. Two shaft encoders were employed to obtain the instantaneous angular position of the torque converter pump and turbine at the instant of laser velocimeter data acquisition. By proper “registration” of the velocity data, visualizing the transient interaction effects between the turbine, pump, and stator was possible. Results showed strong cyclic velocity fluctuations in the turbine inlet plane as a function of the relative turbine-pump position. These fluctuations are due to the passing of upstream pump blades by the slower rotating turbine blades. Typical fluctuations in the through flow velocity were 3.6 m/s. Quarter and mid plane velocity fluctuations were seen to be lower; typical values were 1.5 m/s and 0.8 m/s, respectively. The flow field in the turbine exit plane was seen to be relatively steady with negligible fluctuations of less than 0.03 m/s. From the velocity data, the fluctuations of turbine performance parameters such as flow inlet angles, root-mean-square unsteadiness, and output torque per blade passage were calculated. Incidence angles were seen to vary by 3° and 6° for the 0.800 and 0.065 speed ratios, respectively, while the exit angles remained steady. The turbine output torque per blade passage fluctuated by 0.05 Nm for the 0.800 speed ratio and 0.13 Nm for the 0.065 speed ratio.

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“…Earlier investigations (11) have demonstrated the periodicity of the flow field between the rotor passages of this research fan. Present measurements confirm periodicity.…”

Section: Data Reductionmentioning

confidence: 67%

Measurements of the Unsteady Flow Field Within the Stator Row of a Transonic Axial-Flow Fan: I — Measurement and Analysis Technique

Suder

Okiishi

Hathaway

et al. 1987

Volume 1: Turbomachinery

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This two-part paper presents detailed laser anemometer measurements of the unsteady velocity field within the stator row of a transonic axial-flow fan. The objective of this study was to provide additional insight into unsteady blade-row interactions within high speed compressors which affect stage efficiency, energy transfer, and other design considerations. Part I of this paper describes the measurement and analysis techniques used for resolving the unsteady flow field features. The ensemble-average and variance of the measured velocities are used to identify the “rotor-wake-generated” and “unresolved” unsteadiness, respectively. The term “rotor-wake-generated” unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and the term “unresolved” unsteadiness refers to all remaining contributions to unsteadiness such as vortex shedding, turbulence, mass flow fluctuations, etc. A procedure for calculating auto and cross correlations of the rotor-wake-generated and unresolved unsteady velocity fluctuations is described. These unsteady-velocity correlations have significance since they also result from a decomposition of the Navier-Stokes equations. This decomposition of the Navier-Stokes equations resulting in the velocity correlations used to describe the unsteady velocity field will also be outlined in this paper.

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Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry

Cited by 51 publications

References 1 publication

Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver

Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver

Laser Velocimeter Measurements in the Turbine of an Automotive Torque Converter: Part II — Unsteady Measurements

Measurements of the Unsteady Flow Field Within the Stator Row of a Transonic Axial-Flow Fan: I — Measurement and Analysis Technique

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