Characteristics of fluid exciting force due to blade row interaction of a propeller turbine

Ryosuke. Mori; Kazushi. Ajiro; Kazuyoshi. Miyagawa

doi:10.1088/1742-6596/1909/1/012037

Active control of wake/blade-row interaction noise

AIAA Journal ◽

10.2514/3.12238 ◽

1994 ◽

Vol 32 (10) ◽

pp. 1953-1960 ◽

Cited By ~ 14

Author(s):

Kenneth A. Kousen ◽

Joseph M. Verdon

Keyword(s):

Active Control ◽

Blade Row ◽

Blade Row Interaction

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Navier-Stokes and Potential Calculations of Axial Spacing Effect on Vortical and Potential Disturbances and Gust Response in an Axial Compressor

Volume 1: Turbomachinery ◽

10.1115/95-gt-301 ◽

1995 ◽

Author(s):

Meng-Hsuan Chung ◽

Andrew M. Wo

Keyword(s):

Lower Order ◽

Spacing Effect ◽

Axial Compressor ◽

Interaction Effects ◽

Moving Frame ◽

Navier Stokes ◽

Blade Row ◽

Vortical Disturbance ◽

Blade Row Interaction ◽

Gust Response

The effect of blade row axial spacing on vortical and potential disturbances and gust response is studied for a compressor stator/rotor configuration near design and at high loadings using 2D incompressible Navier-Stokes and potential codes, both written for multistage calculations. First, vortical and potential disturbances downstream of the isolated stator in the moving frame are defined; these disturbances exclude blade row interaction effects. Then, vortical and potential disturbances for the stator/rotor configuration are calculated for axial gaps of 10%, 20%, and 30% chord. Results show that the potential disturbance is uncoupled; the potential disturbance calculated from the isolated stator configuration is a good approximation for that from the stator/rotor configuration for all three axial gaps. The vortical disturbance depends strongly on blade row interactions. Low order modes of vortical disturbance are of substantial magnitude and decay much more slowly downstream than do those of potential disturbance. Vortical disturbance decays linearly with increasing mode except very close to the stator trailing edge. For a small axial gap, lower order modes of both vortical and potential disturbances must be included to determine the rotor gust response.

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Simulation of noise generation due to blade row interaction in a high speed compressor

Aerospace Science and Technology ◽

10.1016/j.ast.2004.02.001 ◽

2004 ◽

Vol 8 (4) ◽

pp. 299-306 ◽

Cited By ~ 1

Author(s):

Sitki Uslu ◽

Thomas Hüttl ◽

Klaus Heinig

Keyword(s):

High Speed ◽

Noise Generation ◽

Blade Row ◽

Blade Row Interaction

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Effects of Off-Design Operating Conditions on the Blade Row Interaction in a HP Turbine Stage

Volume 6: Turbo Expo 2007, Parts A and B ◽

10.1115/gt2007-27185 ◽

2007 ◽

Cited By ~ 2

Author(s):

G. Persico ◽

P. Gaetani ◽

C. Osnaghi

Keyword(s):

Flow Field ◽

Strong Dependence ◽

Secondary Flows ◽

Operating Conditions ◽

Pressure Probe ◽

Turbine Stage ◽

Mixing Rate ◽

Aerodynamic Pressure ◽

Blade Row ◽

Blade Row Interaction

An extensive experimental analysis on the subject of the unsteady periodic flow in a highly subsonic HP turbine stage has been carried out at the Laboratorio di Fluidodinamica delle Macchine (LFM) of the Politecnico di Milano (Italy). In this paper the blade row interaction is progressively enforced by increasing the stator and rotor blade loading and by reducing the stator-rotor axial gap from 100% (very large to smooth the rotor inlet unsteadiness) to 35% (design configuration) of the stator axial chord. The time-averaged three-dimensional flow field in the stator-rotor gap was investigated by means of a conventional five-hole probe for the nominal (0°) and an highly positive (+22°) stator incidences. The evolution of the viscous flow structures downstream of the stator is presented to characterize the rotor incoming flow. The blade row interaction was evaluated on the basis of unsteady aerodynamic measurements at the rotor exit, performed with a fast-response aerodynamic pressure probe. Results show a strong dependence of the time-averaged and phase-resolved flow field and of the stage performance on the stator incidence. The structure of the vortex-blade interaction changes significantly as the magnitude of the rotor inlet vortices increases, and very different residual traces of the stator secondary flows are found downstream of the rotor. On the contrary, the increase of rotor loading enhances the unsteadiness in the rotor secondary flows but has a little effect on the vortex-vortex interaction. For the large axial gap, a reduction of stator-related effects at the rotor exit is encountered when the stator incidence is increased as a result of the different mixing rate within the cascade gap.

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Evaluation of Unsteady CFD Methods by Their Application to a Transonic Propfan Stage

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery ◽

10.1115/2001-gt-0310 ◽

2001 ◽

Cited By ~ 7

Author(s):

S. Schmitt ◽

F. Eulitz ◽

L. Wallscheid ◽

A. Arnone ◽

M. Marconcini

Keyword(s):

Numerical Methods ◽

Navier Stokes ◽

Test Case ◽

Flow Angle ◽

Laser Measurements ◽

General Flow ◽

Blade Row ◽

Flow Features ◽

Blade Row Interaction ◽

Good Agreement

The accuracy in predicting the unsteady aerodynamic blade-row-interaction of two state-of-the-art Navier-Stokes codes is evaluated within the current paper. The general flow features of the test case — a transonic research propfan stage — are described in brief as far as necessary to understand the detailed comparisons. The calculated unsteady velocity and flow angle distributions at various axial planes of the stage are compared to data from unsteady laser measurements. The general flow features of the propfan are very well reproduced by the numerical methods and a good agreement is also obtained in comparison to the measured data. One important outcome of the comparison is the good agreement of both numerical methods with the unsteady fluctuations measured in the experiment.

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Interaction Effects in a Transonic Turbine Stage

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

10.1115/2000-gt-0376 ◽

2000 ◽

Cited By ~ 13

Author(s):

J. W. Barter ◽

P. H. Vitt ◽

J. P. Chen

Keyword(s):

Analytical Techniques ◽

Interaction Effects ◽

Phase Lag ◽

Turbine Stage ◽

Reflected Waves ◽

Blade Row ◽

Transonic Turbine ◽

Unsteady Loading ◽

Unsteady Pressure Measurements ◽

Blade Row Interaction

A 3D, viscous, time-accurate code has been used to predict the time-dependent flowfield in a transonic turbine stage. Two analytical techniques are used to understand the unsteady physics. One technique takes into account interaction effects associated with reflected waves bouncing between blade rows while the other neglects them. Both techniques model the exact blade counts using phase-lag boundary conditions. The analytical techniques are validated by comparing to unsteady pressure measurements which have been made on the vane and blade surfaces at midspan. The analytical results are then used to understand the importance of interaction effects when the blade rows are close-coupled and when they are more widely spaced. The results show that interaction effects must be taken into account in order to accurately predict the unsteady loading on the upstream blade row. However, for the downstream blade row, interaction effects are second order and do not routinely need to be taken into account in the design process.

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Blade-Row Interaction in a High-Pressure Turbine

Journal of Propulsion and Power ◽

10.2514/2.5821 ◽

2001 ◽

Vol 17 (4) ◽

pp. 892-901 ◽

Cited By ~ 38

Author(s):

V. S. P. Chaluvadi ◽

A. I. Kalfas ◽

M. R. Banieghbal ◽

H. P. Hodson ◽

J. D. Denton

Keyword(s):

High Pressure ◽

High Pressure Turbine ◽

Blade Row ◽

Blade Row Interaction

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Dipole Active Control of Wake-Blade Row Interaction Noise

Journal of Propulsion and Power ◽

10.2514/2.5414 ◽

1999 ◽

Vol 15 (1) ◽

pp. 31-37 ◽

Cited By ~ 2

Author(s):

Stacey Myers ◽

Sanford Fleeter

Keyword(s):

Active Control ◽

Blade Row ◽

Blade Row Interaction

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Aerodynamic Origin of Rotor-Rotor Interaction Noise From Unducted Propulsors

Volume 6C: Turbomachinery ◽

10.1115/gt2013-95572 ◽

2013 ◽

Cited By ~ 2

Author(s):

Florian Danner ◽

Christofer Kendall-Torry ◽

Hans-Peter Kau

Keyword(s):

Stokes Equations ◽

Navier Stokes ◽

Propagation Characteristics ◽

Propulsion Systems ◽

Navier Stokes Equations ◽

Pressure Distributions ◽

Blade Row ◽

Open Rotor ◽

Blade Row Interaction ◽

Insight Into

The sound arising from blade row interaction in open rotor propulsion systems is known to significantly contribute to overall noise emissions. The present paper therefore addresses the origination of rotor-rotor interaction noise from a pair of unducted counter-rotating fans. The focus is on the aerodynamic mechanisms that involve sound generation, in order to provide the physical understanding required to find noise-reducing means. Detailed insight into the underlying phenomena is provided on the basis of numerical simulations applying the unsteady Reynolds-averaged Navier-Stokes equations. The interaction mechanisms are identified by extracting the time-dependent disturbances of the flow field in the respective rotor relative frame of reference. Conclusions on the sources of interaction noise and potential noise-reducing means are drawn by evaluating polar directivities, blade surface pressure distributions and propagation characteristics.

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Experimental and Numerical Verification of the Core-Flow in a New Low-Pressure Turbine

Volume 2B: Turbomachinery ◽

10.1115/gt2016-57101 ◽

2016 ◽

Author(s):

Michael Henke ◽

Lars Wein ◽

Tim Kluge ◽

Yavuz Guendogdu ◽

Marc Heinz-Otto Biester ◽

...

Keyword(s):

Flow Field ◽

Low Pressure ◽

Numerical Verification ◽

Two Dimensional ◽

Core Flow ◽

Low Pressure Turbine ◽

The Core ◽

Blade Row ◽

Unsteady Effects ◽

Blade Row Interaction

The flow field in modern axial turbines is non-trivial and highly unsteady due to secondary flow and blade row interaction. In recent years, existing design-tools like two-dimensional flow solvers as well as fully three-dimensional CFD methods have been validated for the assumption of a quasi-steady flow field. Since the inevitable unsteadiness of the flow field has a direct impact on unsteady loss generation and work transfer, existing design methods stand in need of validation for local unsteady effects within the flow field. In order to clearly separate end-wall losses from those generated by blade row interaction within the blade passage, a two-dimensional core-flow is essential for the investigation. Hence, a new 1.5-stage high aspect ratio low pressure turbine has been designed to determine the intensity of core-flow blade row interaction for different axial gaps. First, inlet and outlet conditions of the test rig are evaluated with regard to homogeneity of the flow parameters in their radial and circumferential distributions. Secondly, the measurement data gained from rig tests have been applied as boundary conditions to time-averaged numerical computations. The flow field analysis for two different axial gaps focuses on the verification of the core flow. The authors show that the new turbine has been successfully verified using both test data and the numerical predictions, serving as a precondition for the validation of the numerical model for unsteady effects within the core-flow.

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