Blade row interaction effects on compressor measurements

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.

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.

Blade-Row Interaction Effects on Unsteady Stator Loading in an Embedded Compressor Stage

Journal of Propulsion and Power ◽

10.2514/1.b35981 ◽

2017 ◽

Vol 33 (1) ◽

pp. 248-255 ◽

Cited By ~ 2

Author(s):

Natalie R. Smith ◽

Nicole L. Key

Keyword(s):

Interaction Effects ◽

Compressor Stage ◽

Blade Row ◽

Blade Row Interaction

Blade row interaction effects on flutter and forced response

10.2514/6.1993-2084 ◽

1993 ◽

Cited By ~ 4

Author(s):

DANIEL BUFFUM

Keyword(s):

Interaction Effects ◽

Forced Response ◽

Blade Row ◽

Blade Row Interaction

Non-Axisymmetric Blade Row Interaction in Axial Turbomachines

Volume 1B: General ◽

10.1115/80-gt-133 ◽

1980 ◽

Cited By ~ 1

Author(s):

N. A. Mitchell

Keyword(s):

Three Dimensional ◽

Interaction Effects ◽

Numerical Calculations ◽

Relative Importance ◽

Streamwise Vorticity ◽

Wake Interaction ◽

Blade Row ◽

Blade Row Interaction

A three-dimensional non-axisymmetric theory is presented to analyze the interaction effects due to wakes between two blade rows in an axial turbomachine. The relative importance of potential and wake interaction with varying row separations and the contribution to the flow of shed radial and shed streamwise vorticity from the first row are examined. Numerical calculations of turbine and compressor stages are presented to illustrate the theory.

Blade Row Interaction Effects on Flutter and Forced Response

Journal of Propulsion and Power ◽

10.2514/3.51412 ◽

1995 ◽

Vol 11 (2) ◽

pp. 205-212 ◽

Cited By ~ 10

Author(s):

Daniel H. Buffurn

Keyword(s):

Interaction Effects ◽

Forced Response ◽

Blade Row ◽

Blade Row Interaction

Nonaxisymmetric Blade Row Interaction in Axial Turbomachines

Journal of Engineering for Power ◽

10.1115/1.3230698 ◽

1981 ◽

Vol 103 (1) ◽

pp. 201-209

Author(s):

N. A. Mitchell

Keyword(s):

Three Dimensional ◽

Interaction Effects ◽

Numerical Calculations ◽

Relative Importance ◽

Streamwise Vorticity ◽

Wake Interaction ◽

Blade Row ◽

Blade Row Interaction

A three-dimensional nonaxisymmetric theory is presented to analyze the interaction effects due to wakes between two blade rows in an axial turbomachine. The relative importance of potential and wake interaction with varying row separations and the contribution to the flow of shed radial and shed streamwise vorticity from the first row are examined. Numerical calculations of turbine and compressor stages are presented to illustrate the theory.

Analysis of Unsteady Blade Row Interaction Using Nonlinear Harmonic Approach

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

10.1115/2000-gt-0431 ◽

2000 ◽

Cited By ~ 4

Author(s):

T. Chen ◽

P. Vasanthakumar ◽

L. He

Keyword(s):

Stokes Equations ◽

Linear Time ◽

Three Dimensional ◽

Axial Flow ◽

Interaction Effects ◽

Navier Stokes ◽

Linear Interaction ◽

Blade Row ◽

Non Linear ◽

Blade Row Interaction

An efficient non-linear harmonic methodology has been developed for predicting unsteady blade row interaction effects in multistage axial flow compressors. Flow variables are decomposed into time averaged variables and unsteady perturbations, resulting in time averaged equations with deterministic stress terms depending on the unsteady perturbation. The non-linear interaction between the time averaged flow field and the unsteady perturbations are included by a simultaneous pseudotime integration approach, leading to a strongly coupled solution. The stator/rotor interface treatment follows a flux averaged characteristic based mixing plane approach and includes the deterministic stress terms due to upstream running potential disturbances and downstream running wakes, resulting in the continuous nature of all parameters across the interface. The basic computational methodology is applied to the three-dimensional Navier-Stokes equations and validated against several cases. Results show that this method is much more efficient than the non-linear time-marching methods while still modeling the nonlinear unsteady blade row interaction effects.

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

Volume 5: Turbo Expo 2002, Parts A and B ◽

10.1115/gt2002-30575 ◽

2002 ◽

Cited By ~ 5

Author(s):

Dale E. Van Zante ◽

Wai-Ming To ◽

Jen-Ping Chen

Keyword(s):

Experimental Data ◽

Velocity Field ◽

Interaction Effects ◽

Operating Conditions ◽

Laser Doppler Velocimeter ◽

Compressor Stage ◽

Peak Efficiency ◽

Transonic Compressor ◽

Blade Row ◽

Blade Row Interaction

Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect of the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

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