Aero-Thermal Performance of a Rotor Blade Cascade With Stator-Rotor Seal Purge Flow

2012 ◽  
Author(s):  
G. Barigozzi ◽  
F. Fontaneto ◽  
G. Franchini ◽  
A. Perdichizzi ◽  
M. Maritano ◽  
...  
Keyword(s):  
Secondary Flow ◽  
Thermal Performance ◽  
Flow Injection ◽  
Rotor Blade ◽  
Thermal Protection ◽  
Leading Edge ◽  
Pressure Probe ◽  
Blade Cascade ◽  
Purge Flow ◽  
End Wall

The present paper investigates the effects of purge flow from a stator-rotor seal gap on the aerodynamic and thermal performance of a rotor blade cascade. Particular attention is paid to thermal results in the leading edge area that is typically difficult to protect. Experimental tests have been performed on a seven-blade cascade of a high-pressure rotor stage of a real gas turbine at low Mach number (Ma2is = 0.3). To simulate the rotational effect in a linear cascade environment, a number of inclined fins have been installed inside the stator-rotor gap, making the coolant flow to exit with the right tangential velocity component. Tests have been carried out at different blowing conditions, with mass flow rate ratios up to 2.0%. Aerodynamic effects of purge flow on secondary flow structures were surveyed by traversing a 5-hole miniaturized pressure probe in a plane 0.08cax downstream of the trailing edge. Film cooling effectiveness distributions on the end wall platform were obtained by using Thermochromic Liquid Crystals technique. Results allowed to investigate the effect of purge flow injection from the upstream gap on the secondary flows development and on the thermal protection capability. Purge flow injection of 1.0% reduced secondary flow losses and was found to effectively protect the front end wall region, up to about 0.5cax downstream of the leading edge. Increasing the purge flow up to 1.5%–2.0% provided a better thermal protection not only stream wise, but also in the region close to the leading edge because of the weakened washing activity of the horseshoe vortex.

Influence of Purge Flow Injection Angle on the Aero-Thermal Performance of a Rotor Blade Cascade

2013 ◽  
Author(s):  
G. Barigozzi ◽  
G. Franchini ◽  
A. Perdichizzi ◽  
M. Maritano ◽  
R. Abram
Keyword(s):  
Thermal Performance ◽  
Flow Injection ◽  
Rotor Blade ◽  
Thermal Protection ◽  
Secondary Flows ◽  
Pressure Probe ◽  
Injection Angle ◽  
Blade Cascade ◽  
Purge Flow ◽  
End Wall

This paper is focused on the influence of stator-rotor purge flow injection angle on the aerodynamic and thermal performance of a rotor blade cascade. Tests were performed in a seven-blade cascade of a high-pressure gas turbine rotor at low Mach number (Ma2is = 0.3) under different blowing conditions. A number of fins were installed inside the upstream slot to simulate the effect of rotation on the seal flow exiting the gap in a linear cascade environment. The resulting coolant flow is ejected with the correct angle in the tangential direction. Purge flow injection angle and blowing conditions were changed in order to identify the best configuration in terms of end wall thermal protection and secondary flows reduction. The 3D flow field was surveyed by traversing a 5-hole miniaturized pressure probe in a downstream plane. Secondary flow velocities, loss coefficient and vorticity distributions are presented for the most significant test conditions. Film cooling effectiveness distributions on the platform were obtained by Thermochromic Liquid Crystals technique. Results show that purge flow injection angle has an impact on secondary flows development and thus on the end wall thermal protection, especially at high injection rates. Passage vortex is enhanced by a negative injection angle, which simulates the real counter rotating purge flow direction.

Influence of Purge Flow Injection Angle on the Aerothermal Performance of a Rotor Blade Cascade

2013 ◽  
Vol 136 (4) ◽  
Author(s):  
G. Barigozzi ◽  
G. Franchini ◽  
A. Perdichizzi ◽  
M. Maritano ◽  
R. Abram
Keyword(s):  
Flow Injection ◽  
Rotor Blade ◽  
Thermal Protection ◽  
Secondary Flows ◽  
Pressure Probe ◽  
Film Cooling Effectiveness ◽  
Injection Angle ◽  
Blade Cascade ◽  
Purge Flow ◽  
End Wall

This paper is focused on the influence of stator-rotor purge flow injection angle on the aerodynamic and thermal performance of a rotor blade cascade. Tests were performed in a seven-blade cascade of a high-pressure gas turbine rotor at low Mach number (Ma2is = 0.3) under different blowing conditions. A number of fins were installed inside the upstream slot to simulate the effect of rotation on the seal flow exiting the gap in a linear cascade environment. The resulting coolant flow is ejected with the correct angle in the tangential direction. Purge flow injection angle and blowing conditions were changed in order to identify the best configuration in terms of end wall thermal protection and secondary flows reduction. The 3D flow field was surveyed by traversing a five-hole miniaturized pressure probe in a downstream plane. Secondary flow velocities, loss coefficient, and vorticity distributions are presented for the most significant test conditions. Film cooling effectiveness distributions on the platform were obtained by thermochromic liquid crystals (TLC) technique. Results show that purge flow injection angle has an impact on secondary flows development and, thus, on the end wall thermal protection, especially at high injection rates. Passage vortex is enhanced by a negative injection angle, which simulates the real counter rotating purge flow direction.

Purge flow and interface gap geometry influence on the aero-thermal performance of a rotor blade cascade

2013 ◽  
Vol 44 ◽  
pp. 563-575 ◽  
Author(s):  
Giovanna Barigozzi ◽  
Giuseppe Franchini ◽  
Antonio Perdichizzi ◽  
Massimiliano Maritano ◽  
Roberto Abram
Keyword(s):  
Thermal Performance ◽  
Rotor Blade ◽  
Blade Cascade ◽  
Purge Flow

Effects of an Upstream Cavity on the Secondary Flow in a Transonic Turbine Cascade

2010 ◽  
Author(s):  
H. M. Abo El Ella ◽  
S. A. Sjolander ◽  
T. J. Praisner
Keyword(s):  
Mach Number ◽  
Secondary Flow ◽  
Ultra Violet ◽  
Leading Edge ◽  
Reactive Dye ◽  
Surface Flow ◽  
Flow Structures ◽  
Pressure Probe ◽  
Turbine Cascade ◽  
Blow Down

This paper examines experimentally the effects of an upstream cavity on the flow structures and secondary losses in a transonic linear turbine cascade. The cavity approximates the endwall geometry resulting from the platform overlap at the interface between stationary and rotating turbine blade rows. Previous investigations of the effects of upstream cavity geometries have been conducted mainly at low-speed conditions. The present work aims to extend such research into the transonic regime with a more engine representative upstream platform geometry. The investigations were carried out in a blow-down type wind tunnel. The cavity is located at 30% of axial-chord from the leading edge, extends 17% of axial-chord in depth, and is followed by a smooth ramp to return the endwall to its nominal height. Two cascades are examined for the same blade geometry: the baseline cascade with a flat endwall and the cascade with the cavity endwall. Measurements were made at the design incidence and the outlet design Mach number of 0.80. At this condition, the Reynolds number based on outlet velocity is about 600,000. Off-design outlet Mach numbers of 0.69, and 0.89 were also investigated. Flowfield measurements were carried out at 40% axial-chord downstream of the trailing edge, using a seven-hole pressure probe, to quantify losses and identify the flow structures. Additionally, surface flow visualization using an ultra-violet reactive dye was employed at the design Mach number, on the endwall and blade surfaces, to help in the interpretation of the flow physics. The experimental results also include blade-loading distributions, and the probe measurements were processed to obtain total-pressure loss coefficients, and stream-wise vorticity distributions. It was found that the presence of the upstream cavity noticeably altered the structure and the strength of the secondary flow. Some effect on the secondary losses was also evident, with the cavity having a larger effect at the higher Mach number.

A Low Pressure Turbine With Profiled End Walls and Purge Flow Operating With a Pressure Side Bubble

2011 ◽  
Author(s):  
P. Jenny ◽  
R. S. Abhari ◽  
M. G. Rose ◽  
M. Brettschneider ◽  
J. Gier
Keyword(s):  
Computational Study ◽  
Leading Edge ◽  
Low Pressure ◽  
Fast Response ◽  
Turbine Rotor ◽  
Operating Point ◽  
Pressure Side ◽  
Low Pressure Turbine ◽  
Purge Flow ◽  
End Wall

This paper presents an experimental and computational study of non-axisymmetric rotor end wall profiling in a low pressure turbine. End wall profiling has been proven to be an effective technique to reduce both turbine blade row losses and the required purge flow. For this work a rotor with profiled end walls on both hub and shroud is considered. The rotor tip and hub end walls have been designed using an automatic numerical optimisation that is implemented in an in-house MTU code. The end wall shape is modified up to the platform leading edge. Several levels of purge flow are considered in order to analyze the combined effects of end wall profiling and purge flow. The non-dimensional parameters match real engine conditions. The 2-sensor Fast Response Aerodynamic Probe (FRAP) technique system developed at ETH Zurich is used in this experimental campaign. Time-resolved measurements of the unsteady pressure, temperature and entropy fields between the rotor and stator blade rows are made. For the operating point under investigation the turbine rotor blades have pressure side separations. The unsteady behavior of the pressure side bubble is studied. Furthermore, the results of unsteady RANS simulations are compared to the measurements and the computations are also used to detail the flow field with particular emphasis on the unsteady purge flow migration and transport mechanisms in the turbine main flow containing a rotor pressure side separation. The profiled end walls show the beneficial effects of improved measured efficiency at this operating point, together with a reduced sensitivity to purge flow.

Influence of Coolant Flow Rate on Aero-Thermal Performance of a Rotor Blade Cascade With Endwall Film Cooling

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
G. Barigozzi ◽  
F. Fontaneto ◽  
G. Franchini ◽  
A. Perdichizzi ◽  
M. Maritano ◽  
...  
Keyword(s):  
High Pressure ◽  
Thermal Performance ◽  
Film Cooling ◽  
Rotor Blade ◽  
Secondary Flows ◽  
Film Cooling Effectiveness ◽  
Blade Cascade ◽  
Comprehensive Picture ◽  
Cylindrical Holes ◽  
Endwall Film Cooling

This paper investigates the influence of coolant injection on the aerodynamic and thermal performance of a rotor blade cascade with endwall film cooling. A seven blade cascade of a high-pressure-rotor stage of a real gas turbine has been tested in a low speed wind tunnel for linear cascades. Coolant is injected through 10 cylindrical holes distributed along the blade pressure side. Tests have been preliminarily carried out at low Mach number (Ma2is = 0.3). Coolant-to-mainstream mass flow ratio has been varied in a range of values corresponding to inlet blowing ratios M1 = 0–4.0. Secondary flows have been surveyed by traversing a five-hole miniaturized aerodynamic probe in two downstream planes. Local and overall mixed-out secondary loss coefficient and vorticity distributions have been calculated from measured data. The thermal behavior has been also analyzed by using thermochromic liquid crystals technique to obtain film cooling effectiveness distributions. All this information, including overall loss production for variable injection conditions, allows us to draw a comprehensive picture of the aero-thermal flow field in the endwall region of a high pressure rotor blade cascade.

Anisotropic Eddy Viscosity in the Secondary Flow of a Low-Speed Linear Turbine Cascade

2011 ◽  
Author(s):  
G. D. MacIsaac ◽  
S. A. Sjolander
Keyword(s):  
Turbulent Flow ◽  
Secondary Flow ◽  
Eddy Viscosity ◽  
Turbulence Models ◽  
Leading Edge ◽  
Boussinesq Approximation ◽  
Pressure Probe ◽  
Turbine Cascade ◽  
Low Speed ◽  
Sst Turbulence Model

The final losses within a turbulent flow are realized when eddies completely dissipate to internal energy through viscous interactions. The accurate prediction of the turbulence dissipation, and therefore the losses, requires turbulence models which represent, as accurately as possible, the true flow physics. Eddy viscosity turbulence models, commonly used for design level computations, are based on the Boussinesq approximation and inherently assume the eddy viscosity field is isotropic. The current paper compares the computational predictions of the flow downstream of a low-speed linear turbine cascade to the experimentally measured results. Steady-state computational simulations were performed using ANSYS CFX v12.0 and employed the shear stress transport (SST) turbulence model with the γ-Reθ transition model. The experimental data includes measurements of the mean and turbulent flow quantities. Steady pressure measurements were collected using a seven-hole pressure probe and the turbulent flow quantities were measured using a rotatable x-type hotwire probe. Data is presented for two axial locations: 120% and 140% of the axial chord (Cx) downstream of the leading edge. The computed loss distribution and total bladerow losses are compared to the experimental measurements. Differences are noted and a discussion of the flow structures provides insights into the origin of the differences. Contours of the shear eddy viscosity are presented for each axial plane. The secondary flow appears highly anisotropic, demonstrating a fundamental difference between the computed and measured results. This raises questions as to the validity of using two-equation turbulence models, which are based on the Boussinesq approximation, for secondary flow predictions.

Influence of Rotor Blade Fillets on Aerodynamic Performance of Turbine Stage

2010 ◽  
Author(s):  
Yan Shi ◽  
Jun Li ◽  
Zhenping Feng
Keyword(s):  
Secondary Flow ◽  
Rotor Blade ◽  
Stokes Equations ◽  
Leading Edge ◽  
Navier Stokes ◽  
Aerodynamic Load ◽  
Main Stream ◽  
Shape Parameters ◽  
Turbine Stage ◽  
A Minor

In this paper, steady and unsteady flow simulations were performed to investigate the influence of rotor fillet on the performance of turbine stage, based on 3D compressible Navier-Stokes equations closed with the Spalart-Allmaras turbulence model. The profile of Aachen turbine was employed and the fillet modeled by two shape parameters was placed at the junctions between the rotor blade and the endwalls (at both tip and hub). Based on the comparisons of the efficiency and the flow rate of turbine stage among the cases with different fillet shapes, the roles of two shape parameters were evaluated. To understand the mechanism of the rotor fillet influence on the flow field, the aerodynamic load, secondary flow and loss were analyzed and compared between the cases with and without the rotor fillet. It is found that the fillet is capable of restraining the flow separation near the leading edge of the rotor blade while inducing the displacement of the flow from the endwalls towards the mid-span, which enhances the loss generated by the interaction between the secondary flow and the main stream. Consequently, associated with the distribution of the loss at the outlet of the turbine stage, the best clocking position near the endwalls for the downstream blade moves about 10%∼20% of rotor pitch in the direction of rotor rotation. Therefore, the shape of the fillet in the rotor blade should be especially controlled in the process of the rotor design and manufacture, even though it is a minor part in the turbomachine.

The Behavior of Turbine Center Frames Under the Presence of Purge Flows

2017 ◽  
Author(s):  
S. Zerobin ◽  
A. Peters ◽  
S. Bauinger ◽  
A. Ramesh ◽  
M. Steiner ◽  
...  
Keyword(s):  
High Pressure ◽  
Secondary Flow ◽  
Pressure Loss ◽  
Measurement Data ◽  
Leading Edge ◽  
Turbine Rotor ◽  
High Pressure Turbine ◽  
Oil Flow ◽  
Purge Flow ◽  
Cooling Air

This paper deals with the influence of high-pressure turbine purge flows on the aerodynamic performance of turbine center frames. Measurements were carried out in a product-representative one and a half stage turbine test setup, installed in the Transonic Test Turbine Facility at Graz University of Technology. The rig allows testing at engine-relevant flow conditions, matching Mach, Reynolds, and Strouhal number at the inlet of the turbine center frame. Four individual purge mass flows differing in flow rate, pressure, and temperature were injected through the hub and tip, forward and aft cavities of the unshrouded high-pressure turbine rotor. Two turbine center frame designs (differing in area distribution and inlet-to-exit radial offset), equipped with non-turning struts, were tested and compared. For both configurations, aerodynamic measurements at the duct inlet and outlet as well as oil flow visualizations through the turbine center frame were performed. The acquired measurement data illustrate that the interaction of the ejected purge flow with the main flow enhances the secondary flow structures through the turbine center frame duct. Depending on the purge flow rates, the radial migration of purge air onto the strut surfaces directly impacts the loss behavior of the duct. While the duct loss is demonstrated to be primarily driven by the core flow between two duct struts, the losses associated with the flow close to the struts and in the strut wakes are highly dependent on the relative position between the high-pressure turbine vane and the strut leading edge, as well as the interaction between vane wake and ejected purge flow. Hence, while the turbine center frame duct pressure loss depends on the duct geometric characteristics it is also influenced by the presence and rate of the high-pressure turbine purge flows. This first-time experimental assessment demonstrates that a reduction in the high-pressure turbine purge and cooling air requirement not only benefits the engine system performance by decreasing the secondary flow taken from the high-pressure compressor but also by lowering the turbine center frame total pressure loss.

Swept Blade Aerodynamics Numerical Simulation of Super-Critical HP Stage Static Cascade

2010 ◽  
Vol 29-32 ◽  
pp. 554-559
Author(s):  
Zi Ming Feng ◽  
Zhen Xu Sun ◽  
De Shi Zhang ◽  
Guang Ling Zhou ◽  
Chun Hong Li
Keyword(s):  
Numerical Simulation ◽  
Pressure Distribution ◽  
Secondary Flow ◽  
Low Energy ◽  
Sweep Angle ◽  
Blade Cascade ◽  
Flow Loss ◽  
Simulation Results ◽  
End Wall ◽  
Type Pressure

Super-critical HP steam stage static blade cascade is as the prototype blade to numerical simulations. Different swept blades are made by changing the sweep angle and sweep height in order to study the effect of swept blade on aerodynamics characteristics of turbine static cascade. The numerical simulation sweep angle are made of ±10° and 0°,swept heights are 30% blade height. The turbine aerodynamics characteristics are analyzed by NUMECA software. The numerical simulation results indicate: that aft-sweep blades negative C-type pressure distribution increase the low energy fluid centralizing in end-wall corner and the end-wall secondary flow loss, but the loss is decreased at mid-span, depending on the baseline. But fore-sweep blades C-type pressure distribution decrease the low energy fluid centralizing in endwall corner and the endwall secondary flow loss, but the loss is increased at mid-span, depending on the baseline.

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