Axisymmetric Endwall Contouring in a Four-Stage Turbine: Comparison of Experimental and Numerical Results

2002 ◽  
Author(s):  
Dieter E. Bohn ◽  
Norbert Su¨rken ◽  
Qing Yu ◽  
Franz Kreitmeier
Keyword(s):  
Flow Field ◽  
Positive Influence ◽  
Secondary Flows ◽  
Navier Stokes ◽  
Flow Measurements ◽  
Flow Angle ◽  
Numerical Predictions ◽  
Before And After ◽  
Endwall Contouring ◽  
Aerodynamic Losses

Secondary flows and leakage flows lead to complex vortex structures in the 3-D flow field of a turbine blading. Aerodynamic losses are the consequence. Reducing these aerodynamic losses by axisymmetric endwall contouring is the subject of a current experimental and numerical investigation of the flow field in a 4-stage test turbine with repeating stages. Numerical 4-stage simulations for the reconstructed turbine with an axisymmetric off-set arc endwall contour at the casing have been performed and compared to corresponding numerical investigations of the original machine without endwall modifications. The 3-D flow fields have been calculated by application of a steady 3-D Navier-Stokes code. Based on these results the experimental setup is modified to the off-set arc endwall design. The characteristics of the reconstructed machine are measured and compared to the original test rig. Special emphasis is put on the determination of the aerodynamic efficiencies over the four stages. For a detailed assessment of the radial and spanwise flow field properties inside the blading, 5-hole pressure probes are used for steady flow measurements in the narrow axial gaps before and after the 3rd stage. Finally, the measured radial distributions of the flow field properties and the machine characteristics are compared to the corresponding numerical predictions. All results show a significant positive influence of the endwall contouring on the radial distribution of the flow angle, the pressure field and the aerodynamic efficiency.

Influence of Endwall Contouring in Axial Gaps on the Flow Field in a Four-Stage Turbine

2000 ◽  
Author(s):  
Dieter E. Bohn ◽  
Karsten Kusterer ◽  
Norbert Sürken ◽  
Franz Kreitmeier
Keyword(s):  
Flow Field ◽  
Flow Analysis ◽  
Numerical Data ◽  
Positive Influence ◽  
Secondary Flows ◽  
Maximum Deviation ◽  
Leakage Flows ◽  
Endwall Contouring ◽  
D Values ◽  
Aerodynamic Losses

Secondary flows and leakage flows are leading to complex vortex structures in the 3-D flow field of a turbine blading. Aerodynamic losses are the consequence. Reducing the aerodynamic losses related to tip leakage flows by endwall contouring is subject of an actual numerical investigation of the flow field in a 4-stage test turbine with repeating stages. The 3-D flow field for various geometric configurations with endwall contouring is calculated by application of a 3-D Navier-Stokes code. Here, the numerical results of configurations with arc-like and wave-like contours (bumps) at the shaft and the casing with a maximum deviation from the reference contour in the axial gap between stator and rotor are presented. Furthermore, the results are compared to the experimental and numerical data of the test turbine with a reference contour without endwall contouring. The results show a significant influence of the bumps on the radial velocity distribution in the flow field and the static pressure field. By application of a subtraction method where the reference flow field is subtracted from the flow fields of the bump-configurations, it can be shown that the leakage flows are reduced. A detailed flow analysis shows the presence of a leakage vortex. For a measure of the flow field inhomogeneity and for reducing the complex 3-D data to 2-D and 1-D values a balance-based averaging method is used. The method is based on a hypothetical equilibration process between two infinitesimal neighbouring control surfaces. During this physically based averaging process, equilibration coefficients can be derived which are a measure for the flow inhomogeneity. It can be shown that arc-like and wave-like endwall contouring has a positive influence on the homogeneity of the flow field. Thus, this effect leads to higher aerodynamic stage efficiencies for repeating stages.

Numerical and Experimental Investigations on Endwall Contouring in a Four-Stage Turbine

2001 ◽  
Author(s):  
Dieter E. Bonn ◽  
Harald Funke ◽  
Norbert Sürken ◽  
Franz Kreitmeier
Keyword(s):  
Flow Field ◽  
Flow Analysis ◽  
Numerical Results ◽  
Secondary Flows ◽  
Experimental Investigations ◽  
Maximum Deviation ◽  
Reference Case ◽  
Geometric Configurations ◽  
Endwall Contouring ◽  
Aerodynamic Losses

Secondary flows and leakage flows create complex vortex structures in the 3-D flow field of a turbine stage. Aerodynamic losses are the consequence. Reducing the aerodynamic losses by endwall contouring is subject of an actual investigation of the flow field in a 4-stage test turbine with repeating stages. Numerical 4-stage simulations are performed for a reference case of a turbine without endwall modifications and two different geometric configurations with endwall contouring. The numerical results for the reference case are compared to corresponding experimental investigations. Both, the experiment and the CFD focus on the stage exit flow field of the second, the third and the fourth stage of the actual four stage turbine. The 3-D flow field is calculated by application of a steady 3-D Navier-Stokes code. The numerical results of an arc-like endwall contouring at the casing are presented a) with a maximum deviation from the reference contour in the axial gap within the stages (“arc contour”) and b) with a maximum deviation in the axial gap between the stages (“off-set arc contour”). The results show a significant influence of the bumps on the blade’s profile pressure distribution near the radial gap, the leakage flow and the radial pressure field. A detailed secondary flow analysis shows the influence of the different endwall contours on the leakage vortex development. Finally, the aerodynamic efficiencies of the geometric configurations are compared. It is predicted that the off-set arc contour has a remarkable positive influence on the machine’s performance.

Flow Measurements in a First Stage Nozzle Cascade Having Endwall Contouring, Leakage and Assembly Features

2005 ◽  
Author(s):  
J. D. Piggush ◽  
T. W. Simon
Keyword(s):  
Secondary Flows ◽  
Flow Measurements ◽  
Leakage Flows ◽  
Assembly Features ◽  
Transition Piece ◽  
Endwall Contouring ◽  
Improved Performance ◽  
Flow Effects ◽  
Work Supports ◽  
Aerodynamic Losses

This work supports new gas turbine designs for improved performance by evaluating the use of endwall contouring in a cascade that is representative of a first stage stator passage. Contouring accelerates the flow, reducing the thickness of the endwall inlet boundary layer to the turbine stage and reducing the strength of secondary flows within the passage. Reduction in secondary flows leads to less mixing in the endwall region. This allows improved cooling of the endwall and airfoil surfaces with injected and leakage flows. The present paper documents component misalignment and leakage flow effects on the aerodynamic losses within a passage having one contoured and one straight endwall. Steps on the endwall and leakage flows through the endwall can lead to thicker endwall boundary layers, stronger secondary flows and possibly additional vortex structures in the passage. The paper compares losses with steps of various geometries and leakage of various flow rates to assess their importance on aerodynamic losses in this contoured passage. In particular, features associated with the combustor-to-turbine transition piece and the slashface gap, a gap between two vane segments on the vane platform, are addressed. An n-factorial study is used to quantify the importance of such effects on aerodynamic losses.

Flow Measurements in a First Stage Nozzle Cascade Having Endwall Contouring, Leakage, and Assembly Features

2012 ◽  
Vol 135 (1) ◽  
Author(s):  
J. D. Piggush ◽  
T. W. Simon
Keyword(s):  
Secondary Flows ◽  
Flow Measurements ◽  
Leakage Flows ◽  
Assembly Features ◽  
Transition Piece ◽  
Endwall Contouring ◽  
Improved Performance ◽  
Flow Effects ◽  
Work Supports ◽  
Aerodynamic Losses

This work supports new gas turbine designs for improved performance by evaluating the use of endwall contouring in a cascade that is representative of a first stage stator passage. Contouring accelerates the flow, reducing the thickness of the endwall inlet boundary layer to the turbine stage and reducing the strength of secondary flows within the passage. The reduction in secondary flows leads to less mixing in the endwall region. This allows for an improved cooling of the endwall and airfoil surfaces with injected and leakage flows. The present paper documents the component misalignment and injected and leakage flow effects on the aerodynamic losses within a passage that has one contoured and one straight endwall. Steps and injected flows within the passage can lead to thicker endwall boundary layers, stronger secondary flows, and possibly additional vortex structures in the passage. The paper compares losses with various steps, gaps, and leakage flows to assess their importance in this contoured passage. In particular, features associated with the combustor-to-turbine transition piece and the slashface on the vane platform are addressed. An n-factorial study is used to quantify the importance of such effects on aerodynamic losses.

scholarly journals The Secondary Flow Field of a Turbine Cascade With 3D Airfoil Design and Endwall Contouring at Off-Design Incidence

1999 ◽  
Author(s):  
Arno Duden ◽  
Leonhard Fottner
Keyword(s):  
Flow Field ◽  
Secondary Flow ◽  
High Speed ◽  
Secondary Flows ◽  
Turbine Cascade ◽  
Flow Angle ◽  
Radial Extent ◽  
Endwall Contouring ◽  
End Wall ◽  
Secondary Flow Field

A highly loaded turbine cascade with prismatic airfoils and straight endwalls was redesigned with the objective of reducing the secondary flow by applying end wall contouring and 3D airfoil design in the endwall regions. When tested at design conditions the flow field showed distinct improvements. The radial extent of the secondary flows was reduced and a decrease in secondary losses was observed (Duden et al., 1998). As an extension of this investigation, the effects of positive and negative incidence on the performance of the redesigned cascade have been evaluated and compared to the original cascade. The investigations were carried out in a high speed cascade wind tunnel. At negative incidence the redesigned cascade was observed to reduce the radial variation of the circumferential exit flow angle but to increase the magnitude of the secondary losses. At positive incidence, in comparison to the flowfield in the reference cascade, the radial extent of the secondary flows and the magnitude of the secondary losses were greatly reduced. The benefits provided by the 3D airfoil design and endwall contouring were even more obvious at positive incidence than at the design conditions.

Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing-Jets—Part I: Flow Field Analysis

2009 ◽  
Vol 132 (1) ◽  
Author(s):  
Alessandro Armellini ◽  
Filippo Coletti ◽  
Tony Arts ◽  
Christophe Scholtes
Keyword(s):  
Flow Field ◽  
Three Dimensional ◽  
Side Wall ◽  
Field Analysis ◽  
Navier Stokes ◽  
Trailing Edge ◽  
Present Contribution ◽  
Cross Sectional ◽  
Numerical Predictions ◽  
Rib Roughened

The present contribution addresses the aerothermal, experimental, and computational studies of a trapezoidal cross-sectional model simulating a trailing edge cooling cavity with one rib-roughened wall. The flow is fed through tilted slots on one side wall and exits through straight slots on the opposite side wall. The flow field aerodynamics is investigated in Part I of the paper. The reference Reynolds number is defined at the entrance of the test section and set at 67,500 for all the experiments. A qualitative flow model is deduced from surface-streamline flow visualizations. Two-dimensional particle image velocimetry measurements are performed in several planes around midspan of the channel and recombined to visualize and quantify three-dimensional flow features. The crossing-jets issued from the tilted slots are characterized and the jet-rib interaction is analyzed. Attention is drawn to the motion of the flow deflected by the rib-roughened wall and impinging on the opposite smooth wall. The experimental results are compared with the numerical predictions obtained from the finite volume Reynolds-averaged Navier–Stokes solver, CEDRE.

Flow Measurements in a Nozzle Guide Vane Passage With a Low Aspect Ratio and Endwall Contouring

2000 ◽  
Author(s):  
Steven W. Burd ◽  
Terrence W. Simon
Keyword(s):  
Aspect Ratio ◽  
Flow Field ◽  
Guide Vane ◽  
Flow Measurements ◽  
Vast Number ◽  
Aspect Ratios ◽  
Nozzle Guide Vane ◽  
Endwall Contouring ◽  
Nozzle Guide

The vast number of turbine cascade studies in the literature has been performed in straight-endwall, high-aspect-ratio, linear cascades. As a result, there has been little appreciation for the role of, and added complexity imposed by, reduced aspect ratios. There also has been little documentation of endwall profiling at these reduced spans. To examine the role of these factors on cascade hydrodynamics, a large-scale nozzle guide vane simulator was constructed at the Heat Transfer Laboratory of the University of Minnesota. This cascade is comprised of three airfoils between one contoured and one flat endwall. The geometries of the airfoils and endwalls, as well as the experimental conditions in the simulator, are representative of those in commercial operation. Measurements with hot-wire anemometry were taken to characterize the flow approaching the cascade. These measurements show that the flow field in this cascade is highly elliptic and influenced by pressure gradients that are established within the cascade. Exit flow field measurements with triple-sensor anemometry and pressure measurements within the cascade indicate that the acceleration imposed by endwall contouring and airfoil turning is able to suppress the size and strength of key secondary flow features. In addition, the flow field near the contoured endwall differs significantly from that adjacent to the straight endwall.

Investigation of the Flow Field in a HP Turbine Stage for Two Stator-Rotor Axial Gaps: Part II — Unsteady Flow Field

2006 ◽  
Author(s):  
P. Gaetani ◽  
G. Persico ◽  
V. Dossena ◽  
C. Osnaghi
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Dominant Role ◽  
Outer Part ◽  
Secondary Flows ◽  
Pressure Probe ◽  
Turbine Stage ◽  
Mean Flow ◽  
Tip Leakage Flow ◽  
Flow Measurements

An extensive experimental analysis was carried out at Politecnico di Milano on the subject of unsteady flow in high pressure (HP) turbine stages. In this paper the unsteady flow measured downstream of a modern HP turbine stage is discussed. Traverses in two planes downstream of the rotor are considered and, in one of them, the effects of two very different axial gaps are investigated: the maximum axial gap, equal to one stator axial chord, is chosen to “switch off” the rotor inlet unsteadiness, while the nominal gap, equal to 1/3 of the stator axial chord, is representative of actual engines. The experiments were performed by means of a fast-response pressure probe, allowing for two-dimensional phase-resolved flow measurements in a bandwidth of 80 kHz. The main properties of the probe and the data processing are described. The core of the paper is the analysis of the unsteady rotor aerodynamics; for this purpose, instantaneous snapshots of the rotor flow in the relative frame are used. The rotor mean flow and its interaction with the stator wakes and vortices are also described. In the outer part of the channel only the rotor cascade effects can be observed, with a dominant role played by the tip-leakage flow and by the rotor tip passage vortex. In the hub region, where the secondary flows downstream of the stator are stronger, the persistence of stator vortices is slightly visible in the maximum stator-rotor axial gap configuration, while in the minimum stator-rotor axial gap configuration the interaction with the rotor vortices dominates the flow field. A fair agreement with the wakes and vortices transport models has been achieved. A discussion of the interaction process is reported giving particular emphasis to the effects of the different cascade axial gaps. Some final considerations on the effects of the different axial gap over the stage performances are reported.

Three Dimensional Clocking Effects in a One and a Half Stage Transonic Turbine

2009 ◽  
Vol 132 (1) ◽  
Author(s):  
O. Schennach ◽  
J. Woisetschläger ◽  
B. Paradiso ◽  
G. Persico ◽  
P. Gaetani
Keyword(s):  
Flow Field ◽  
Three Dimensional ◽  
Fast Response ◽  
Secondary Flows ◽  
Pressure Probe ◽  
Time Resolved ◽  
Flow Angle ◽  
Aerodynamic Pressure ◽  
Velocity Flow ◽  
Transonic Turbine

This paper presents an experimental investigation of the flow field in a high-pressure transonic turbine with a downstream vane row (1.5 stage machine) concerning the airfoil indexing. The objective is a detailed analysis of the three-dimensional aerodynamics of the second vane for different clocking positions. To give an overview of the time-averaged flow field, five-hole probe measurements were performed upstream and downstream of the second stator. Furthermore in these planes additional unsteady measurements were carried out with laser Doppler velocimetry in order to record rotor phase-resolved velocity, flow angle, and turbulence distributions at two different clocking positions. In the planes upstream of the second vane, the time-resolved pressure field has been measured by means of a fast response aerodynamic pressure probe. This paper shows that the secondary flows of the second vane are significantly modified by the different clocking positions, in connection with the first vane modulation of the rotor secondary flows. An analysis of the performance of the second vane is also carried out, and a 0.6% variation in the second vane loss coefficient has been recorded among the different clocking positions.

Laminarization of Internal Flows Under the Combined Effect of Strong Curvature and Rotation

2008 ◽  
Vol 130 (9) ◽  
Author(s):  
K. M. Guleren ◽  
I. Afgan ◽  
A. Turan
Keyword(s):  
Secondary Flows ◽  
Combined Effect ◽  
Navier Stokes ◽  
Duct Flow ◽  
Internal Flows ◽  
Square Duct ◽  
Eddy Simulation ◽  
Numerical Predictions ◽  
Wide Range ◽  
Strong Curvature

The laminarization phenomenon for the flow under the combined effect of strong curvature and rotation is discussed based on numerical predictions of large-eddy simulation (LES). Initially, the laminarization process is presented for the fully developed flow inside a spanwise rotating straight square duct. LES predictions over a wide range of rotation numbers (Ro=0–5) show that the turbulent kinetic energy decreases monotonically apart from 0.2<Ro<0.5. Subsequently, a spanwise rotating U-duct flow is considered with Ro=±0.2. The interaction of curvature and Coriolis induced secondary flows enhances the turbulence for the negative rotating case, whereas this interaction ensues strong laminarization for the positive rotating case. Finally, the laminarization is presented in the impeller of a typical centrifugal compressor, rotating at a speed of Ω=1862rpm(Ro=0.6). The resulting LES predictions are observed to be better than those of Reynolds-averaged Navier-Stokes (RANS) in the regions where turbulence is significant. However, for the regions dominated by strong laminarization, RANS results are seen to approach those of LES and experiments.

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