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Heat Transfer In The Blade Row And Tip Region Of A Modern Transonic High Pressure Turbine With And Without Forward Cavity Purge Flow
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Book Synopsis Heat Transfer in the Blade Row and Tip Region of a Modern Transonic High Pressure Turbine with and Without Forward Cavity Purge Flow by : Stephen M. Molter
Download or read book Heat Transfer in the Blade Row and Tip Region of a Modern Transonic High Pressure Turbine with and Without Forward Cavity Purge Flow written by Stephen M. Molter and published by . This book was released on 2006 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: A full scale rotating turbine rig operated at design corrected conditions has been used to study the heat transfer mechanisms affecting the flowpath surfaces within a modem single stage high-pressure (HP) turbine. The experimental rig was first run completely un-cooled and is currently being re-constructed to accommodate HP vane airfoil and endwall cooling and inner-stage cavity purge flow injection. Heat flux and pressure data were measured for both a flat and recessed, or squealer, HP blade tip and the stationary shroud above. The measurements indicate that the recessed tip, used in the majority of modem turbines to minimize blade damage from rubs, increases the blade heat load overall, and creates several hot spots on the floor of the recess for an un-cooled airfoil. The tip data also showed there were significant unsteady variations in the heat load at the vane passing frequency. Steady state CFD calculations were completed for both flat and squealer tip configurations to examine if the analysis could capture the details that were measured. The CFD, while not capable of estimating the unsteady heat load component and generally over predicting the overall heat flux by 10-25%, did capture the measured heat flux trends in the recessed tip. The steady state CFD prediction did show good agreement with the time-accurate data along the stationary shroud. These results show that steady-state CFD analysis can be useful in predicting the complex flow field and heat load distribution in turbine blade tips to help guide future blade designs. Pre-test CFD predictions were also performed for the upcoming series of experiments that include replacing the un-cooled vane row with a fully cooled HP vane row and the introduction of HP blade forward cavity purge flow, while leaving the HP blade un-cooled. The focus of the steady state predictions for the HP blade row was two fold; to assist in guiding the placement of new heat flux and pressure instrumentation and to study the cold flow migration through the HP blade row. Adiabatic wall temperature and Nusselt number predictions along the blade surface showed large radial, or spanwise, gradients, mostly along the suction side of the blade. Surface visualization on the suction side of the blade revealed two bands of cooler regions located at the upper and lower spans, with the middle spans being hotter, comparable to the pressure side. The lower band of cool flow is a result of the forward cavity purge flow, which mostly migrates to the suction side of the blade passage. By the trailing edge of the blade the purge flow has migrated upwards to an extent of approximately 20% of the blade span surface. The upper band of cool flow is a result of the cooling flow from the HP vane outer endwall. Blade tip secondary flows and the tip leakage vortex act to entrain this cool flow into the tip gap, resulting in its migration to the suction side of the blade. Due to a downward migration of the tip vortex along the suction side through the blade row, this cool band along the airfoil surface affects the upper 20% of the blade span. Results from the pre-test CFD predictions were also analyzed along the blade platform and rim seal surfaces. Migration of the forward cavity purge flow towards the suction side increases the Nusselt number along the rim seal and platform in these areas. Adiabatic wall temperatures on the platform surface were reasonably constant and lower than those on the blade surface, an effect of a portion of the purge flow being entrained into the platform boundary layer. Pressure asymmetries along the rim seal created circumferential variations in the local purge mass flow rates, with the leading edge of blade being the location of highest pressure and thus lower purge injection. Results also indicate the possibility of hot gas ingestion into the upper region of the rim seal at the leading edge. When data is available from the updated turbine rig, the comparisons will help to further validate this code as a useful design tool.
Book Synopsis Blade-to-coolant Heat-transfer Results and Operating Data from a Natural-convection Water-cooled Single-stage Turbine by : Anthony J. Diaguila
Download or read book Blade-to-coolant Heat-transfer Results and Operating Data from a Natural-convection Water-cooled Single-stage Turbine written by Anthony J. Diaguila and published by . This book was released on 1951 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Navier-Stokes Heat Transfer Predictions for Turbine Blade Rows by : Robert J. Boyle
Download or read book Three-dimensional Navier-Stokes Heat Transfer Predictions for Turbine Blade Rows written by Robert J. Boyle and published by . This book was released on 1992 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Determination of Gas-to-blade Convection Heat-transfer Coefficients on a Forced-convection, Water-cooled Single-stage Aluminum Turbine by : John C. Freche
Download or read book Determination of Gas-to-blade Convection Heat-transfer Coefficients on a Forced-convection, Water-cooled Single-stage Aluminum Turbine written by John C. Freche and published by . This book was released on 1951 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Blade Heat Transfer Measurements and Prediction in a Transonic Turbine Cascade by :
Download or read book Blade Heat Transfer Measurements and Prediction in a Transonic Turbine Cascade written by and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Blade Tip Heat Transfer Measurements in a Shroudless, Transonic, High Pressure Turbine by : Adam James Jackson
Download or read book Blade Tip Heat Transfer Measurements in a Shroudless, Transonic, High Pressure Turbine written by Adam James Jackson and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: To improve the performance of aero-engines manufacturers strive to increase the inlet temperature to the high pressure turbine. The components that are exposed to the hot gas - particularly the over-tip casing and blade tips of shroud less turbines - are vulnerable to heat damage. A previous investigation using the Oxford Rotor Facility demonstrated that a backwards facing casing step - located 20 % of high pressure blade axial chord upstream of the leading edge of the rotor - could mitigate the significant convective heat loads that the over-tip casing must withstand. This thesis describes an investigation into the effect ofthe aforementioned casing step on blade tip heat transfer rates. A second investigation, to determine the effect of the tip gap size on blade tip heat transfer rates, is also reported. These investigations necessitated the acquisition of two sets of experimental measurements. In both instances the casing step was present. The time resolved heat transfer rate data was obtained using thirty- five thin film gauges distributed over three blade tips. A small number of blade relative aerodynamic measurements were also performed. The aerodynamic measurements were valuable in helping to elucidate the mechanisms responsible for the measured changes of heat transfer rate. In order to investigate the effect of the tip gap size it was necessary to modify the over-tip casing before the second set of measurements were made. Detailed measurements of the over-tip casing were made before and after the modifications. It was shown that the mod- ifications reduced the mean tip gap to approximately two thirds ofthe baseline size. Computational fluid dynamics calculations were performed to complement the predomi- nantlyexperimental investigations. The predictive work was undertaken in order to obtain further insight into the mechanisms underpinning the changes of heat transfer rate that were observed in the experiments.
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine by :
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine written by and published by . This book was released on 1999 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Determination of Blade-to-coolant Heat-transfer Coefficients on a Forced-convection, Water-cooled, Single-stage Turbine by : John C. Freche
Download or read book Determination of Blade-to-coolant Heat-transfer Coefficients on a Forced-convection, Water-cooled, Single-stage Turbine written by John C. Freche and published by . This book was released on 1951 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer by : Ali A. Ameri
Download or read book Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer written by Ali A. Ameri and published by . This book was released on 1996 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Book Synopsis Prediction of Unshsrouded Rotor Blade Tip Heat Transfer by :
Download or read book Prediction of Unshsrouded Rotor Blade Tip Heat Transfer written by and published by . This book was released on 1994 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Inlet Geometry on the Turbine Blade Tip Region Heat Transfer Coefficient and Effectiveness by :
Download or read book Effect of Inlet Geometry on the Turbine Blade Tip Region Heat Transfer Coefficient and Effectiveness written by and published by . This book was released on 2002 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the local film cooling effectiveness and heat transfer coefficient downstream of a row of elongated holes in a simulated axial turbine blade tip is presented. Film cooling is needed to protect the turbine blade tip region from high heat transfer rates, especially when cooling by convection is insufficient to keep the temperature distribution of the blade within the limits required. Accurate heat transfer predictions in this region of the blade are particularly difficult given the dimensionality of the flow and the narrow passage typical of turbine blades. The effect of inlet geometry film cooling injection point and blowing ratio are examined for an injection on the blade tip itself close to the pressure surface corner. Additionally the corner radii between the pressure surface and the tip were varied. The experimental method uses the steady state liquid crystal technique. Film cooling injection provides the tip with a blanket of protection from the hot leakage flow. This extends far downstream of the holes at higher blowing ratios. Inlet curvature provides greater local film cooling effectiveness but it lacks streamwise film cooling coverage. It is important to have direct injection onto the separation bubble for greater lateral film cooling coverage.
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine by : Ali A. Ameri
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine written by Ali A. Ameri and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Studies on Transonic Turbines with Film-Cooled Blades by :
Download or read book Studies on Transonic Turbines with Film-Cooled Blades written by and published by . This book was released on 1976 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the third year of the contract, further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled, highly-loaded, transonic turbine blading. The MIT cascade blowdown facility now fully operational was used in evaluating the heat transfer performance of the four blade profiles designed in the first year of the program. The results show that the level of turbulence is an important parameter in determining heat transfer in transonic cascades. It also shows that the heat transfer to the trailing edge of the blades is very high being about 75% of the heat transfer to the leading edge. A comparison of the Nusselt number calculated from heat transfer measurements with the Nusselt number obtained by a prediction method using the pressure distribution shows good correspondence. The variation of average Stanton number over a range of Mach numbers shows that the reference blade has the most superior heat transfer performance. Preliminary data has been obtained on the off-design performance of the blades and full scale tests are underway. Comparative studies show that about 21% less heat needs to be taken out by internal cooling if one stage of a transonic turbine is used to replace two moderately loaded subsonic stages which produce the same output, have the same inlet stagnation conditions, have the same mass flow and the same tip speed. This demonstrates one of the potential advantages of transonic turbines.
Book Synopsis Navier-Stokes Analysis of Flow and Heat Transfer Inside High-pressure-ratio Turbine Blade Rows by : C. Hah
Download or read book Navier-Stokes Analysis of Flow and Heat Transfer Inside High-pressure-ratio Turbine Blade Rows written by C. Hah and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721183678 Total Pages :26 pages Book Rating :4.1/5 (836 download)
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 2; Simulation Results by : National Aeronautics and Space Administration (NASA)
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 2; Simulation Results written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines (>1OOMW). This paper is concerned with the numerical prediction of the tip surface heat transfer. Good comparison with the experimental measured distribution was achieved through accurate modeling of the most important features of the blade passage and heating arrangement as well as the details of experimental rig likely to affect the tip heat transfer. A sharp edge and a radiused edge tip were considered. The results using the radiused edge tip agreed better with the experimental data. This improved agreement was attributed to the absence of edge separation on the tip of the radiused edge blade. Ameri, A. A. and Bunker, R. S. Glenn Research Center NASA/CR-1999-209151/PT2, NAS 1.26:209151/PT2, E-11656/PT2, ASME 99-GT-283/PT2
Book Synopsis Heat Transfer Measurements and Predictions on a Power Generation Gas Turbine Blade by :
Download or read book Heat Transfer Measurements and Predictions on a Power Generation Gas Turbine Blade written by and published by . This book was released on 2000 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 129 deg of nominal turning and an axial chord of 137 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the design point of 628,000, -20%, +20%, and +40%. Three ideal exit pressure ratios were examined including the design point of 1.378, -10%, and +10%. Inlet incidence angles of 0 deg and +/-2 deg were also examined. Measurements were made in a linear cascade with highly three-dimensional blade passage flows that resulted from the high flow turning and thick inlet boundary layers. Inlet turbulence was generated with a blown square bar grid. The purpose of the work is the extension of three-dimensional predictive modeling capability for airfoil external heat transfer to engine specific conditions including blade shape, Reynolds numbers, and Mach numbers. Data were obtained by a steady-state technique using a thin-foil heater wrapped around a low thermal conductivity blade. Surface temperatures were measured using calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, and also show good detail in the stagnation region.
Book Synopsis Numerical Analysis of Blade Tip Leakage Flow and Shroud Heat Transfer in Gas Turbine Engines by : Md. Hamidur Rahman
Download or read book Numerical Analysis of Blade Tip Leakage Flow and Shroud Heat Transfer in Gas Turbine Engines written by Md. Hamidur Rahman and published by . This book was released on 2008 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt:
