An Experimental Investigation Into the Effect of Wakes on the Unsteady Turbine Rotor Flow

Binder, A.; Förster, Wolfgang; Kruse, H.; Rogge, H.

doi:10.1115/1.3239749

Cited by 59 publications

(37 citation statements)

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“…They detected considerable variations of flow angles, velocity and pressure distributions for different rotor-stator positions. Binder et al (1985) measured a sudden increase of turbulence energy when the rotor cuts off the passage vortices of the upstream stator row. Extensive studies of the unsteady rotor flow were carried out by Zeschky and Gallus (1993).…”

Section: Introductionmentioning

confidence: 99%

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Walraevens

Gallus

Jung

et al. 1998

Volume 1: Turbomachinery

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A study of the unsteady flow in an axial flow turbine stage with a second stator blade row is presented. The low aspect ratio blades give way to a highly three-dimensional flow which is dominated by secondary flow structures. Detailed steady and unsteady measurements throughout the machine and unsteady flow simulations which include all blade rows have been carried out. The presented results focus on the second stator flow. Secondary flow structures and their origins are identified and tracked on their way through the passage. The results of the time-dependent secondary velocity vectors as well as flow angles and Mach number distributions as perturbation from the time-mean flow field are shown in cross-flow sections and azimuthal cuts throughout the domain of the second stator. At each location the experimental and numerical results are compared and discussed. A good overall agreement in the time-dependent flow behaviour as well as in the secondary flow structures is stated. ' fluctuation

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Section: Introductionmentioning

confidence: 99%

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Walraevens

Gallus

Jung

et al. 1998

Volume 1: Turbomachinery

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“…Due to the high aspect ratio of the rotor blade, the region between 15% and 80% passage height is characterized by velocity defects related to the blade wakes. In particular, the flowfield at the stage exit is the result of two dimensional interaction mechanisms like vane wake blade interaction, which has been largely documented since the mid of the 80s [1,2]. Furthermore, since the number of vanes and blades of the turbine is unequal, adjacent rotor blades face different flow structures from the stator and, then, the outlet flow of adjacent blade passages is not uniform along the circumference.…”

Section: Resultsmentioning

confidence: 98%

“…In the last decades, since Binder et al [1] and Hodson [2], many studies have been performed in turbine research facilities in order to increase the knowledge of the unsteady flow inside a turbine and improve the efficiency of highly loaded profiles. The sources of unsteadiness are numerous: secondary flows, potential flow fields and wakes, they are among the main that may be encountered in subsonic turbines.…”

Section: Introductionmentioning

confidence: 99%

A method for the determination of turbulence intensity by means of a fast response pressure probe and its application in a LP turbine

2012

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This paper describes the measurements and the post-processing procedure adopted for the determination of the turbulence intensity in a low pressure turbine (LPT) by means of a single sensor fast response aerodynamic pressure probe. The rig was designed in cooperation with MTU Aero Engines and considerable efforts were put into the adjustment of all relevant model parameters. Blade count ratio, airfoil aspect ratio, reduced massflow, reduced speed, inlet turbulence intensity and Reynolds numbers were chosen to reproduce the full scale LP turbine. Measurements were performed adopting a phase-locked acquisition technique in order to provide the time resolved\ud flow field downstream of the turbine rotor. The total pressure random fluctuations are obtained by selectively filtering, in the frequency domain, the deterministic unsteadiness due to the rotor blades and coherent structures.\ud The turbulence intensity is derived from the inverse Fourier transform and the correlations between total pressure and velocity fluctuations. The determination of the turbulence intensity allows the discussion of the interaction processes between the stator and rotor for engine-representative operating conditions of the turbine

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“…These blade wakes interact with the stator flow field as described in e.g. [22] [23]. Due to the uneven blade/vane count, the shape and velocity/pressure defect of the wake are not circumferentially constant.…”

Section: Rotor Exit Flow Fieldmentioning

confidence: 99%

“…According to Binder et al [22] the wane wakes leave the rotor on fixed positions relative to the upstream vane position, allowing the identification of the upstream stators. The resulting width of the blade wake is wider when superimposing with the regions of low , the supposed wake avenues of the upstream stator.…”

Section: Rotor Exit Flow Fieldmentioning

confidence: 99%

Comparison of a State of the Art and a High Stage Loading Rotor

Selic

Lengani

Schönleitner

et al. 2014

Volume 2C: Turbomachinery

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This paper presents measurement results of a 1½ stage LPT test rig at Graz University of Technology incorporating two different rotor geometries: one with a regular blade loading and a second rotor with a highly loaded blade geometry. The test rig was designed in cooperation with MTU Aero Engines and represents the last 1.5 stages of a commercial aero engine. Considerable efforts were put on the adjustment of all relevant model parameters (Mach number, blade count ratio, airfoil aspect ratio, blade loading, etc.) to reproduce the full scale LPT situation. The rig diameter is approximately half of that of a commercial aero engine LPT. The number of blades and vanes for the two investigated stages as well as the pressure ratio and power output are identical, resulting in a decrease in rotational speed of the HSL rotor. Measurement data from a fast response pressure probe (FRAPP) is used to compare the flow fields of the two different stages.The effect of the different stage designs can be seen when comparing the exit flow fields. The highly loaded stage shows a more pronounced tip leakage vortex compared to the datum stage. The highly loaded stage shows wider wakes with a lower total pressure deficit. The fluctuations of total pressure within the flow field are directly related to the upstream wake. If the measurement position is located within a stator wake, the fluctuations are significantly smaller than out of the wake.

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An Experimental Investigation Into the Effect of Wakes on the Unsteady Turbine Rotor Flow

Cited by 59 publications

References 0 publications

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

Experimental and Computational Study of the Unsteady Flow in a 1.5 Stage Axial Turbine With Emphasis on the Secondary Flow in the Second Stator

A method for the determination of turbulence intensity by means of a fast response pressure probe and its application in a LP turbine

Comparison of a State of the Art and a High Stage Loading Rotor

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