Unsteady Numerical Simulations of Radial Temperature Profile Redistribution in a Single-Stage Turbine

1996 ◽  
Vol 118 (4) ◽  
pp. 783-791 ◽  
Author(s):  
D. J. Dorney ◽  
J. R. Schwab
Keyword(s):  
Experimental Data ◽  
Temperature Profile ◽  
Total Pressure ◽  
Three Dimensional ◽  
Temperature Gradients ◽  
Single Stage ◽  
Angle Distribution ◽  
Pressure Gradients ◽  
Flow Angle ◽  
Radial Temperature

Experimental data taken from gas turbine combustors indicate that the flow exiting the combustor can contain both circumferential and radial temperature gradients. A significant amount of research recently has been devoted to studying turbine flows with inlet temperature gradients, but no total pressure gradients. Less attention has been given to flows containing both temperature and total pressure gradients at the inlet. The significance of the total pressure gradients is that the secondary flows and the temperature redistribution process in the vane blade row can be significantly altered. Experimental data previously obtained in a single-stage turbine with inlet total temperature and total pressure gradients indicated a redistribution of the warmer fluid to the pressure surface of the airfoils, and a severe underturning of the flow at the exit of the stage. In a concurrent numerical simulation, a steady, inviscid, three-dimensional flow angle distribution, In the current research program, a series of unsteady two-and three-dimensional Navier–Stokes simulations have been performed to study the redistribution of the radial temperature profile in the turbine stage. The three-dimensional analysis predicts both the temperature redistribution and the flow underturning observed in the experiments.

scholarly journals Unsteady Numerical Simulations of Radial Temperature Profile Redistribution in a Single-Stage Turbine

1995 ◽  
Author(s):  
Daniel J. Dorney ◽  
John R. Schwab
Keyword(s):  
Experimental Data ◽  
Temperature Profile ◽  
Total Pressure ◽  
Three Dimensional ◽  
Temperature Gradients ◽  
Single Stage ◽  
Angle Distribution ◽  
Pressure Gradients ◽  
Flow Angle ◽  
Radial Temperature

Experimental data taken from gas turbine combustors indicate that the flow exiting the combustor can contain both circumferential and radial temperature gradients. A significant amount of research recently has been devoted to studying turbine flows with inlet temperature gradients, but no total pressure gradients. Less attention has been given to flows containing both temperature and total pressure gradients at the inlet. The significance of the total pressure gradients is that the secondary flows and the temperature redistribution process in the vane blade row can be significantly altered. Experimental data previously obtained in a single-stage turbine with inlet total temperature and total pressure gradients indicated a redistribution of the warmer fluid to the pressure surface of the airfoils, and a severe underturning of the flow at the exit of the stage. In a concurrent numerical simulation, a steady, inviscid, three-dimensional flow analysis was able to capture the redistribution process, but not the exit flow angle distribution. In the current research program, a series of unsteady two- and three-dimensional Navier-Stokes simulations have been performed to study the redistribution of the radial temperature profile in the turbine stage. The three-dimensional analysis predicts both the temperature redistribution and the flow underturning observed in the experiments.

Effects of Tip Clearance on Hot Streak Migration in a High-Subsonic Single-Stage Turbine

2000 ◽  
Author(s):  
Daniel J. Dorney ◽  
Douglas L. Sondak
Keyword(s):  
Experimental Data ◽  
Three Dimensional ◽  
Single Stage ◽  
Rotor Blades ◽  
Tip Clearance ◽  
Navier Stokes ◽  
Radial Spreading ◽  
Rotor Surface ◽  
Hot Streak ◽  
Turbine Airfoils

Experimental data have shown that combustor temperature non-uniformities can lead to the excessive heating of first-stage rotor blades in turbines. This heating of the rotor blades can lead to thermal fatigue and degrade turbine performance. The results of recent studies have shown that variations in the circumferential location, or clocking, of the first-stage vane airfoils can be used to minimize the adverse effects of the hot streaks due to the hot fluid mixing with the cooler fluid contained in the vane wake. In addition, the effects of the hot streak/airfoil count ratio on the heating patterns of turbine airfoils have been quantified. In the present investigation, three-dimensional unsteady Navier-Stokes simulations have been performed for a single-stage high-pressure turbine geometry operating in high subsonic flow to study the effects of tip clearance on hot streak migration. Baseline simulations were initially performed without hot streaks to compare with the experimental data. Two simulations were then performed with a superimposed combustor hot streak; in the first the tip clearance was set at the experimental value, while in the second the rotor was allowed to scrape along the outer case (i.e., the limit as the tip clearance goes to zero). The predicted results for the baseline simulations show good agreement with the available experimental data. The simulations with the hot streak indicate that the tip clearance increases the radial spreading of the hot fluid, and increases the integrated rotor surface temperature compared to the case without tip clearance.

A new method of determining the transport coefficients for high pressure arcs from experimental data

1969 ◽  
Vol 3 (2) ◽  
pp. 269-280 ◽  
Author(s):  
L. B. Kapp ◽  
P. H. Richards
Keyword(s):  
Experimental Data ◽  
High Pressure ◽  
Computer Program ◽  
Numerical Method ◽  
Temperature Profile ◽  
Transport Coefficients ◽  
New Method ◽  
Radial Temperature ◽  
Current Voltage ◽  
Current Voltage Characteristics

The problem is to determine the electrical and thermal conductivities of high pressure are plasmas from measurements of the current—voltage characteristics of the are and a single radial temperature profile. A new numerical method is described together with the corresponding computer program. The latter is applied to some recent measurements on wall-stabilized nitrogen ares, covering the temperature range 4500—11,000 °K, for which radiation can be neglected, and the results are compared with those of other workers.

Modelling Non-Uniform Bleed in Axial Compressors

2015 ◽  
Author(s):  
S. D. Grimshaw ◽  
G. Pullan ◽  
T. P. Hynes
Keyword(s):  
Experimental Data ◽  
Computational Cost ◽  
Three Dimensional ◽  
Flow Coefficient ◽  
Axial Distance ◽  
Two Dimensional ◽  
Flow Angle ◽  
Axial Compressors ◽  
Two Dimensional Flow ◽  
Satisfactory Prediction

The coupling between the bleed system and the flowfield of a downstream compressor stage is studied using two approaches. In the first, three-dimensional, full annulus, unsteady computations simulate the flow in a low speed research compressor with non-uniform bleed extraction. Comparisons with experimental data show that the flow prediction in the main annulus is accurate to within 0.005 of flow coefficient and 0.5° of flow angle. The CFD is then used to provide a description of flow within the bleed system itself. In the second approach, a two-dimensional mean radius model, similar to that adopted by Hynes and Greitzer in previous work on compressor stability, is used to simulate the response of the compressor to non-uniform bleed. This model is validated against experimental data for a single stage compressor and despite the inherent assumptions (two dimensional flow and simplified compressor response) provides a satisfactory prediction of the flow for preliminary design purposes with orders of magnitude less computational cost than full 3D CFD. The model is then used to investigate the effect of different levels of bleed non-uniformity and of varying the axial distance between the bleed and the downstream stage. Reducing bleed non-uniformity and moving the stage away from the bleed slot are predicted to reduce the circumferential non-uniformity of the flow entering the stage.

scholarly journals Flow Development Through Inter-Turbine Diffusers

1996 ◽  
Author(s):  
Robert G. Dominy ◽  
David A. Kirkham ◽  
Andrew D. Smith
Keyword(s):  
Experimental Data ◽  
Three Dimensional ◽  
Secondary Flows ◽  
Flow Coefficient ◽  
Experimental Measurements ◽  
Good Prediction ◽  
Pressure Gradients ◽  
Computational Simulations ◽  
Flow Development ◽  
Inlet Swirl

Inter-turbine diffusers offer the potential advantage of reducing the flow coefficient in the following stages leading to increased efficiency. The flows associated with these ducts differ from those in simple annular diffusers both as a consequence of their high-curvature S-shaped geometry and of the presence of wakes created by the upstream turbine. Experimental data and numerical simulations clearly reveal the generation of significant secondary flows as the flow develops through the diffuser in the presence of cross-passage pressure gradients. The further influence of inlet swirl is also demonstrated. Data from experimental measurements with and without an upstream turbine are discussed and computational simulations are shown not only to give a good prediction of the flow development within the diffuser but also to demonstrate the importance of modelling the fully three-dimensional nature of the flow.

A three-dimensional law of the wall for turbulent shear flows

1975 ◽  
Vol 70 (1) ◽  
pp. 149-160 ◽  
Author(s):  
B. Van Den Berg
Keyword(s):  
Experimental Data ◽  
Pressure Gradient ◽  
Velocity Vector ◽  
Shear Flows ◽  
Three Dimensional ◽  
Turbulent Shear ◽  
Inertial Forces ◽  
Flow Angle ◽  
Law Of The Wall ◽  
Good Agreement

An extended law of the wall is derived for three-dimensional flows. It describes the variation of the magnitude and direction of velocity close to the wall. The effects of both the pressure gradient and the inertial forces have been taken into account. The derived wall law is valid only when the deviations from the simple law of the wall are not large. The most important feature of a three-dimensional wall law is the prediction of the rotation of the velocity vector near the wall. Comparison of the flow angle variations predicted by the present wall law with the few available experimental data shows good agreement.

Performance Evaluation of an S-Duct Diffuser of a Flight-Vehicle Inlet in High-Subsonic Flow

2015 ◽  
Author(s):  
Asad Asghar ◽  
Robert A. Stowe ◽  
William D. E. Allan ◽  
Derrick Alexander
Keyword(s):  
Performance Evaluation ◽  
Total Pressure ◽  
Three Dimensional ◽  
Pressure Gradients ◽  
Exit Plane ◽  
Three Dimensional Flow ◽  
Pressure Losses ◽  
Parametric Investigation ◽  
Air Vehicle ◽  
Aero Engines

The characteristic aerodynamics of inlets in a fuselage-embedded propulsion system of an air-vehicle vary from one configuration to other, making it necessary to document the performance of each and every type of inlet in various flight conditions. This paper focuses on the internal performance evaluation of a baseline S-duct diffuser for a future parametric investigation of a generic S-duct inlet. The generic baseline was a rectangular-entrance, transitioning S-duct diffuser in high subsonic (Mach number > 0.8) flow. The test section was manufactured using rapid prototyping for facilitating a future parametric investigation of geometry. Streamwise static pressure and exit-plane total pressure were measured in a test-rig using surface pressure taps and a 5-probe rotating rake, respectively and was simulated through computational fluid dynamics. The investigation indicated the presence of streamwise and circumferential pressure gradients leading to three dimensional flow in the S-duct diffuser and distortion at the exit plane. Total pressure losses and circumferential and radial distortions at the exit plane were higher than that of the podded nacelle type of inlet. The work represents the beginning of the development of a database for the performance of a particular type of generic inlet. This database will be useful for predicting the performance of aero-engines and air vehicles in high subsonic flight.

Flow Development Through Interturbine Diffusers

1998 ◽  
Vol 120 (2) ◽  
pp. 298-304 ◽  
Author(s):  
R. G. Dominy ◽  
D. A. Kirkham ◽  
A. D. Smith
Keyword(s):  
Experimental Data ◽  
Three Dimensional ◽  
Secondary Flows ◽  
Flow Coefficient ◽  
Experimental Measurements ◽  
Good Prediction ◽  
Pressure Gradients ◽  
Computational Simulations ◽  
Flow Development ◽  
Inlet Swirl

Interturbine diffusers offer the potential advantage of reducing the flow coefficient in the following stages, leading to increased efficiency. The flows associated with these ducts differ from those in simple annular diffusers both as a consequence of their high-curvature S-shaped geometry and of the presence of wakes created by the upstream turbine. Experimental data and numerical simulations clearly reveal the generation of significant secondary flows as the flow develops through the diffuser in the presence of cross-passage pressure gradients. The further influence of inlet swirl is also demonstrated. Data from experimental measurements with and without an upstream turbine are discussed and computational simulations are shown not only to give a good prediction of the flow development within the diffuser but also to demonstrate the importance of modeling the fully three-dimensional nature of the flow.

Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes

2007 ◽  
Author(s):  
M. D. Barringer ◽  
M. D. Polanka ◽  
J. P. Clark ◽  
P. J. Koch ◽  
K. A. Thole
Keyword(s):  
High Pressure ◽  
Secondary Flow ◽  
Total Pressure ◽  
Secondary Flows ◽  
Working Fluid ◽  
Outer Diameter ◽  
High Pressure Turbine ◽  
Flow Angle ◽  
Radial Temperature ◽  
Turbine Vane

The high pressure turbine stage within gas turbine engines is exposed to combustor exit flows that are nonuniform in both stagnation pressure and temperature. These highly turbulent flows typically enter the first stage vanes with significant spatial gradients near the inner and outer diameter endwalls. These gradients can result in secondary flow development within the vane passage that is different than what classical secondary flow models predict. The heat transfer between the working fluid and the turbine vane surface and endwalls is directly related to the secondary flows. The goal of the current study was to examine the migration of different inlet radial temperature and pressure profiles through the high turbine vane of a modern turbine engine. The tests were performed using an inlet profile generator located in the Turbine Research Facility (TRF) at the Air Force Research Laboratory (AFRL). Comparisons of area-averaged radial exit profiles are reported as well as profiles at three vane pitch locations to document the circumferential variation in the profiles. The results show that the shape of the total pressure profile near the endwalls at the inlet of the vane can alter the redistribution of stagnation enthalpy through the airfoil passage significantly. Total pressure loss and exit flow angle variations are also examined for the different inlet profiles.

A Trace Gas Technique to Study Mixing in a Turbine Stage

1988 ◽  
Vol 110 (1) ◽  
pp. 38-43 ◽  
Author(s):  
H. D. Joslyn ◽  
R. P. Dring
Keyword(s):  
Temperature Profile ◽  
Large Scale ◽  
Three Dimensional ◽  
Axial Flow ◽  
Surface Flow ◽  
Trace Gas ◽  
Inlet Temperature ◽  
Turbine Stage ◽  
Radial Temperature ◽  
Gas Concentration

An experimental technique to study mixing in a turbine stage is demonstrated. An axisymmetric, radial temperature profile at the inlet to the first stator of a large-scale, low-speed, single-stage, axial flow turbine model is simulated with a radial trace gas concentration distribution. Mixing or redistribution of the inlet profile by three-dimensional aerodynamic mechanisms (other than temperature-driven mechanisms) is determined from trace gas concentration measurements made in both the stationary and rotating frames of reference at various locations through the turbine. The trace gas concentration contours generated are consistent with flow pitch angle measurements made downstream of the first stator and with surface flow visualization on the rotor airfoil and the hub endwall. It is demonstrated that this trace gas technique is well suited to quantify many aspects of the redistribution and diffusion of an inlet temperature profile as it is convected through a turbine stage.

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