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Film Cooling Heat Transfer And Aerodynamic Measurements In A Three Stage Research Gas Turbine
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Book Synopsis Film Cooling, Heat Transfer and Aerodynamic Measurements in a Three Stage Research Gas Turbine by : Arun Suryanarayanan
Download or read book Film Cooling, Heat Transfer and Aerodynamic Measurements in a Three Stage Research Gas Turbine written by Arun Suryanarayanan and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The existing 3-stage turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A and M University, is re-designed and newly installed to enable coolant gas injection on the first stage rotor platform to study the effects of rotation on film cooling and heat transfer. Pressure and temperature sensitive paint techniques are used to measure film cooling effectiveness and heat transfer on the rotor platform respectively. Experiments are conducted at three turbine rotational speeds namely, 2400rpm, 2550rpm and 3000rpm. Interstage aerodynamic measurements with miniature five hole probes are also acquired at these speeds. The aerodynamic data characterizes the flow along the first stage rotor exit, second stage stator exit and second stage rotor exit. For each rotor speed, film cooling effectiveness is determined on the first stage rotor platform for upstream stator-rotor gap ejection, downstream discrete hole ejection and a combination of upstream gap and downstream hole ejection. Upstream coolant ejection experiments are conducted for coolant to mainstream mass flow ratios of MFR=0.5%, 1.0%, 1.5% and 2.0% and downstream discrete hole injection tests corresponding to average hole blowing ratios of M = 0.5, 0.75, 1.0, 1.25, 1.5, 1.75 and 2.0 for each turbine speed. To provide a complete picture of hub cooling under rotating conditions, experiments with simultaneous injection of coolant gas through upstream and downstream injection are conducted for an of MFR=1% and Mholes=0.75, 1.0 and 1.25 for the three turbine speeds. Heat transfer coefficients are determined on the rotor platform for similar upstream and downstream coolant injection. Rotation is found to significantly affect the distribution of coolant on the platform. The measured effectiveness magnitudes are lower than that obtained with numerical simulations. Coolant streams from both upstream and downstream injection orient themselves towards the blade suction side. Passage vortex cuts-off the coolant film for the lower MFR for upstream injection. As the MFR increases, the passage vortex effects are diminished. Effectiveness was maximum when Mholes was closer to one as the coolant ejection velocity is approximately equal to the mainstream relative velocity for this blowing ratio. Heat transfer coefficient and film cooling effectiveness increase with increasing rotational speed for upstream rotor stator gap injection while for downstream hole injection the maximum effectiveness and heat transfer coefficients occur at the reference speed of 2550rpm.
Book Synopsis Gas Turbine Heat Transfer and Cooling Technology, Second Edition by : Je-Chin Han
Download or read book Gas Turbine Heat Transfer and Cooling Technology, Second Edition written by Je-Chin Han and published by CRC Press. This book was released on 2012-11-27 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.
Book Synopsis The Influence of Film Cooling and Inlet Temperature Profile on Heat Transfer for the Vane Row of a 1-1/2 Stage Transonic High-pressure Turbine by : Harika Senem Kahveci
Download or read book The Influence of Film Cooling and Inlet Temperature Profile on Heat Transfer for the Vane Row of a 1-1/2 Stage Transonic High-pressure Turbine written by Harika Senem Kahveci and published by . This book was released on 2010 with total page 269 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The goal of this research was to establish an extensive database for typical engine hardware with a film-cooled first stage vane, which represents the foundation for future turbomachinery film cooling modeling and component heat transfer studies. Until this time, such a database was not available within the gas turbine industry. Accordingly, the study focuses on determination of the local heat flux for the airfoil and endwall surfaces of the vane row of a fully-cooled turbine stage. The measurements were performed at the Ohio State University Gas Turbine Laboratory using the Turbine Test Facility. The full-scale rotating 1 and 1/2 turbine stage is operated at the proper corrected engine design conditions: Flow Function (FF), corrected speed, stage Pressure Ratio (PR), and temperature ratios of gas to wall and gas to coolant. The primary measurements of temperature, pressure, and heat flux are repeated for different vane inlet temperature profiles and different vane cooling flows to establish an understanding of the influence of film cooling on local heat transfer. Double-sided Kapton heat-flux gauges are used for heat-flux measurements at different span locations along the airfoil surfaces and along the inner endwall. The cooling scheme consists of numerous cooling holes located on the endwalls, at the airfoil leading edge, on the airfoil pressure and suction surfaces, and at the trailing edge, resulting in a fully cooled first stage vane. The unique film-cooled endwall heat transfer data demonstrated in contour plots reveals insight to the complex flow behavior that is dominant in this region, which becomes even more complicated with the addition of coolant. Varying profile shapes resulted in significant heat transfer variations in a growing fashion towards the trailing edge region, which increased in magnitude when there is no coolant supply. The largest cooling effect is observed on 5% span pressure surface and at the inner endwall region. Heat transfer decreases from tip towards hub with addition of cooling. However, a similar decrease is not observed at the inner endwall region by doing so, which suggests excess coolant once beyond an optimum blowing ratio. Cooling flow rate and temperature profile shape affect the distributions on the airfoil surface very similarly, the latter observed more clearly at the endwall region. The vane outer cooling effect is comparable to the combined coolant effect at all surfaces, while no impact of purge flow is observed. Aligning the hot streaks with the vane leading edge lowered heat transfer compared to mid-passage alignment at the mid-span suction surface and through the endwall passage, and increased it at the endwall exit, while the pressure surface is found to be insensitive to this switch. Comparison with a previous research program with the un-cooled version of the vane gave good agreement on the pressure surface and at the endwall, but significantly lower heat transfer on the suction surface due to ingestion of the hot flow through the cooling holes when there is no cooling.
Book Synopsis Film Cooling and End Wall Heat Transfer in Small Turbine Blade Passages by :
Download or read book Film Cooling and End Wall Heat Transfer in Small Turbine Blade Passages written by and published by . This book was released on 1978 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two topics have been studied related to the cooling of the end wall of a turbine passage. The first concerns the development of a method for measuring the adiabatic wall effectiveness and heat transfer coefficient of a film cooling system for protecting a surface from high heating derived from a hot compressible flow. The second concerns the measurement of the heat transfer rate distribution to a turbine cascade end wall in order to choose an appropriate film cooling system. These are related to providing the background to the final phase of the study in which the effectiveness of a film cooling system to cool a turbine end wall will be made combined with the measurement of the aerodynamic losses incurred by such a system. (Author).
Book Synopsis Experimental Study of Film Cooling and Heat Transfer on a Gas Turbine Vane with Shaped Holes by : Tarek Elnady
Download or read book Experimental Study of Film Cooling and Heat Transfer on a Gas Turbine Vane with Shaped Holes written by Tarek Elnady and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer in Gas Turbines by : Bengt Sundén
Download or read book Heat Transfer in Gas Turbines written by Bengt Sundén and published by Witpress. This book was released on 2001 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt: This title presents and reflects current active research on various heat transfer topics and related phenomena in gas turbine systems. It begins with a general introduction to gas turbine heat transfer, before moving on to specific areas.
Book Synopsis Particle Image Velocimetry by : Andreas Schröder
Download or read book Particle Image Velocimetry written by Andreas Schröder and published by Springer Science & Business Media. This book was released on 2008-01-14 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book summarizes the main results reached using the EC-funded network PivNet 2. It also presents a survey of the state of the art of scientific research using PIV techniques. You get a clear introduction to the basics of these techniques. The authors then guide you through current and possible future applications for flow analysis, including combustion and supersonic flow. Hundreds of illustrations, many in full color, are provided.
Book Synopsis Heat Transfer Due to Unsteady Effects as Investigated in a High-speed, Full-scale, Fully-cooled Turbine Vane and Rotor Stage by : Jonathan R. Mason
Download or read book Heat Transfer Due to Unsteady Effects as Investigated in a High-speed, Full-scale, Fully-cooled Turbine Vane and Rotor Stage written by Jonathan R. Mason and published by . This book was released on 2008 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Conjugate Heat Transfer Effects on Gas Turbine Film Cooling by : William Robb Stewart
Download or read book Conjugate Heat Transfer Effects on Gas Turbine Film Cooling written by William Robb Stewart and published by . This book was released on 2014 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt: The efficiency of natural gas turbines is directly linked to the turbine inlet temperature, or the combustor exit temperature. Further increasing the turbine inlet temperature damages the turbine components and limits their durability. Advances in turbine vane cooling schemes protect the turbine components. This thesis studies the conjugate effects of internal cooling, film cooling and thermal barrier coatings (TBC) on turbine vane metal temperatures. Two-dimensional thermal profiles were experimentally measured downstream of a single row of film cooling holes on both an adiabatic and a matched Biot number model turbine vane. The measurements were taken as a comparison to computational simulations of the same model and flow conditions. To improve computational models of the evolution of a film cooling jet as it propagates downstream, the thermal field above the vane, not just the footprint on the vane surface must be analyzed. This study expands these data to include 2-D thermal fields above the vane at 0, 5 and 10 hole diameters downstream of the film cooling holes. In each case the computational jets remained colder than the experimental jets because they did not disperse into the mainstream as quickly. Finally, in comparing results above adiabatic and matched Biot number models, these thermal field measurements allow for an accurate analysis of whether or not the adiabatic wall temperature was a reasonable estimate of the driving temperature for heat transfer. In some cases the adiabatic wall temperature did give a good indication of the driving temperature for heat transfer while in other cases it did not. Previous tests simulating the effects of TBC on an internally and film cooled model turbine vane showed that the insulating effects of TBC dominate over variations in film cooling geometry and blowing ratio. In this study overall and external effectiveness were measured using a matched Biot number model vane simulating a TBC of thickness 0.6d, where d is the film cooing hole diameter. This new model was a 35% reduction in thermal resistance from previous tests. Overall effectiveness measurements were taken for an internal cooling only configuration, as well as for three rows of showerhead holes with a single row of holes on the pressure side of the vane. This pressure side row of holes was tested both as round holes and as round holes embedded in a realistic trench with a depth of 0.6 hole diameters. Even in the case of this thinner TBC, the insulating effects dominate over film cooling. In addition, using measurements of the convective heat transfer coefficient above the vane surface, and the thermal conductivities of the vane wall and simulated TBC material, a prediction technique of the overall effectiveness with TBC was evaluated.
Download or read book Heat Transfer in Gas Turbines written by and published by . This book was released on 2001 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fundamental Heat Transfer Research for Gas Turbine Engines by :
Download or read book Fundamental Heat Transfer Research for Gas Turbine Engines written by and published by . This book was released on 1980 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Gas Turbine Film Cooling and Heat Transfer Measurements Using a Transient Liquid Crystal Technique by : Srinath Varadarajan Ekkad
Download or read book Gas Turbine Film Cooling and Heat Transfer Measurements Using a Transient Liquid Crystal Technique written by Srinath Varadarajan Ekkad and published by . This book was released on 1995 with total page 366 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Cooling in Gas Turbines by :
Download or read book Heat Transfer and Cooling in Gas Turbines written by and published by . This book was released on 1985 with total page 530 pages. Available in PDF, EPUB and Kindle. Book excerpt: Partial Contents: Rotating Heat Transfer on a Multipass Cooling Geometry; Pressure Drop and Heat Transfer Characteristics of Circular and Oblong Low Aspect Ratio Pin Fins; External Heat Transfer Study on a HP Turbine Rotor Blade; Effects of Wakes on the Heat Transfer in Gas Turbine Cascades; Effect of Hole Geometry, Wall Curvature and Pressure Gradient on Film Cooling Downstream of a Single Row; The Effect of Density Ratio on the Film-Cooling of a Flat Plate; Shroud Segments for Unshrouded Blade Turbines; Heat Transfer Test Evaluation of the Shell-Spar Blade Cooling Concept Applied to Industrial Gas Turbines; Heat-Flux Measurements and Analysis for a Rotating Turbine Stage; Calculation of Laminar-Turbulent Boundary Layer Transition on Turbine Blades; A Model for Correlating Flat Plate Film Cooling Effectiveness for Rows of Round Holes; Heat Transfer in Gas Turbine Combustors; Effectiveness Measurements for a Cooling Film Disrupted by a Single Jet with Wall Plunging; Full Coverage Impingement Heat Transfer: The Variation in Pitch to Diameter Ratio at a Constant Gap; The Measurement of Local Heat Transfer Coefficients in Blade Cooling Geometries; High Frequency Response Heat Flux Gauge for Metal Blading; Transient Thermal Behavior of a Compressor Rotor with Ventilation - Test Results under Simulated Engine Conditions; Heat Exchangers in Regenerative Gas Turbine Cycles.
Book Synopsis Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film Cooled Transonic Turbine Blade by : Cengiz Camci
Download or read book Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film Cooled Transonic Turbine Blade written by Cengiz Camci and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study investigates the influence of incidence on convective heat transfer to highly curved surfaces of a film-cooled turbine rotor blade. A computational study of free-stream inviscid aerodynamics without cooling at various incidences is followed by well-documented measured heat transfer data sets. The heat transfer experiments are discussed for cases with and without film cooling, performed under realistic gas turbine flow conditions in the short-duration heat transfer facility of the von Karman Institute for Fluid Dynamics. The precise location of the stagnation point and the iso-Mach number contours in the passage for each incidence (−10, 0, 10, +15 deg) are presented for a nominal exit Mach number of 0.94. The free-stream mass flow rate was kept constant for each experiment at different incidence levels. Three rows of compound angled discrete cooling holes are located near the leading edge in a showerhead configuration. Two rows of staggered discrete cooling holes are located on the suction side and a single row of cooling holes is located on the pressure side. The short-duration measurements of quantitative wall heat fluxes on nearly isothermal blade surfaces both in the presence and absence of coolant ejection are presented. The study indicated that the change of the position of the stagnation point strongly altered the aerodynamic behavior and convective heat transfer to the blade in approximately the first 30 percent of both the pressure side and the suction side in the presence and absence of film cooling. The immediate vicinity of the stagnation point was not significantly affected by changing incidence without cooling. Transitional behavior both on the suction surface and on the pressure surface was significantly influenced by the changes in approaching flow direction. Flow separation associated with incidence variations was also observed. Extremely low levels of the convective heat transfer coefficients were experienced near the regions where small separation bubbles are located.
Book Synopsis Three-Dimensional Aero-Thermal Optimization of Film Cooling in a High Pressure Turbine by : Carole El Ayoubi
Download or read book Three-Dimensional Aero-Thermal Optimization of Film Cooling in a High Pressure Turbine written by Carole El Ayoubi and published by . This book was released on 2014 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Fully-integrated Approach to Gas Turbine Cooling System Research by : Salvador G. Luque Martinez
Download or read book A Fully-integrated Approach to Gas Turbine Cooling System Research written by Salvador G. Luque Martinez and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A novel experimental facility for the testing of modern high pressure nozzle guide vanes, the Annular Sector Heat Transfer Facility, is described in this thesis. Non- dimensionally similar conditions to a thermal paint test are reproduced, in a warm flow field, by the use of actual engine hardware, contoured sidewalls, and an innova- tive system of deswirl vanes in a five-passage annular sector cascade. External Mach and Reynolds numbers, inlet turbulence intensity, and coolant-to-mainstream pres- sure ratio are all matched to engine conditions. The test vanes are heavily cooled both internally (by convection and impingement) and externally (by film cooling). Detailed aerodynamic measurements are discussed, which demonstrate that a peri- odic, transonic, and highly engine-realistic flow is established in the cascade. High resolution full coverage maps of overall cooling effectiveness are presented, acquired on the vane surfaces at steady state conditions by wide-band liquid crys- tals and infrared thermography. Experimental measurements are then scaled to en- gine conditions by a new theoretical procedure, argued from first principles, which extends the principle of superposition to fully-cooled compressible flows. A newly- defined recovery temperature is proposed, which accounts for the redistribution of heat between the internal and external vane flows in a fully-integrated manner. This technique makes the results analogous to those of a thermal paint test, but allows for fundamental research and early and inexpensive cooling system validation. Overall cooling effectiveness measurements are complemented by those of the re- quired cooling flow capacity to achieve them, conducted in a second test rig commis- sioned during this research: the Flow Testing Facility. To conclude, the approach developed is applied to the global thermal assessment of the dendritic geometry, an innovative turbine cooling system. Experimental results show promising benefits over the baseline vane, especially in regions of low coolant-to-mainstream pressure margin.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781790127511 Total Pages :178 pages Book Rating :4.1/5 (275 download)
Book Synopsis The Effects of Leading Edge and Downstream Film Cooling on Turbine Vane Heat Transfer by : National Aeronautics and Space Adm Nasa
Download or read book The Effects of Leading Edge and Downstream Film Cooling on Turbine Vane Heat Transfer written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-23 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt: The progress under contract NAS3-24619 toward the goal of establishing a relevant data base for use in improving the predictive design capabilities for external heat transfer to turbine vanes, including the effect of downstream film cooling with and without leading edge showerhead film cooling. Experimental measurements were made in a two-dimensional cascade previously used to obtain vane surface heat transfer distributions on nonfilm cooled airfoils under contract NAS3-22761 and leading edge showerhead film cooled airfoils under contract NAS3-23695. The principal independent parameters (Mach number, Reynolds number, turbulence, wall-to-gas temperature ratio, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio) were maintained over ranges consistent with actual engine conditions and the test matrix was structured to provide an assessment of the independent influence of parameters of interest, namely, exit Mach number, exit Reynolds number, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio. Data provide a data base for downstream film cooled turbine vanes and extends the data bases generated in the two previous studies. The vane external heat transfer obtained indicate that considerable cooling benefits can be achieved by utilizing downstream film cooling. The data obtained and presented illustrate the interaction of the variables and should provide the airfoil designer and computational analyst the information required to improve heat transfer design capabilities for film cooled turbine airfoils. Hylton, L. D. and Nirmalan, V. and Sultanian, B. K. and Kaufman, R. M. EQUIPMENT SPECIFICATIONS; FILM COOLING; HEAT TRANSFER; LEADING EDGES; STRUCTURAL DESIGN; VANES; AIRCRAFT ENGINES; CASCADE FLOW; DATA PROCESSING; GAS TURBINES; HIGH TEMPERATURE; PARAMETERIZATION; TWO DIMENSIONAL FLOW...
