Internal Crossflow Effects on Turbine Airfoil Film Cooling Adiabatic Effectiveness with Compound Angle Round Holes

Download Internal Crossflow Effects on Turbine Airfoil Film Cooling Adiabatic Effectiveness with Compound Angle Round Holes PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 230 pages
Book Rating : 4.:/5 (892 download)

DOWNLOAD NOW!


Book Synopsis Internal Crossflow Effects on Turbine Airfoil Film Cooling Adiabatic Effectiveness with Compound Angle Round Holes by : Sean Robert Klavetter

Download or read book Internal Crossflow Effects on Turbine Airfoil Film Cooling Adiabatic Effectiveness with Compound Angle Round Holes written by Sean Robert Klavetter and published by . This book was released on 2014 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt: Internal crossflow is an important element to actual gas turbine blade cooling; however, there are very few studies in open literature that have documented its effects on turbine blade film cooling. Experiments measuring adiabatic effectiveness were conducted to investigate the effects of perpendicular crossflow on a row of 45 degree compound angle, cylindrical film cooling holes. Tests included a standard plenum condition, a baseline crossflow case consisting of a smooth-walled channel, and various crossflow configurations with ribs. The ribs were angled to the direction of prevailing internal crossflow at 45 and 135 degrees and were positioned at different locations. Experiments were conducted at a density ratio of DR=1.5 for a range of blowing ratios including M=0.5, 0.75, 1.0, 1.5, and 2.0. Results showed that internal crossflow can significantly influence adiabatic effectiveness when compared to the standard plenum condition. The implementation of ribs generally decreased the adiabatic effectiveness when compared to the smooth-walled crossflow case. The highest adiabatic effectiveness measurements were recorded for the smooth-walled case in which crossflow was directed against the spanwise hole orientation angle. Tests indicated that the direction of perpendicular crossflow in relation to the hole orientation can significantly influence the adiabatic effectiveness. Among the rib crossflow tests, rib configurations that directed the coolant forward in the direction of the mainstream resulted in higher adiabatic effectiveness measurements. However, no other parameters could consistently be identified correlating to increased film cooling performance. It is likely that a combination of factors are responsible for influencing performance, including internal local pressure caused by the ribs, the internal channel flow field, jet exit velocity profiles, and in-hole vortices.

Diffused-exit Film Cooling Holes Fed by an Internal Crossflow

Download Diffused-exit Film Cooling Holes Fed by an Internal Crossflow PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 434 pages
Book Rating : 4.:/5 (111 download)

DOWNLOAD NOW!


Book Synopsis Diffused-exit Film Cooling Holes Fed by an Internal Crossflow by : John W. McClintic

Download or read book Diffused-exit Film Cooling Holes Fed by an Internal Crossflow written by John W. McClintic and published by . This book was released on 2017 with total page 434 pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling is an essential technology to the operation of modern gas turbine engines, allowing for greater efficiency and part durability. Due to film cooling’s complexity, laboratory studies of film cooling isolate various effects by intentionally simplifying or neglecting various aspects of the film cooling problem. One such aspect that had been consistently neglected by film cooling studies is how the internal flow within the turbine blade affects film cooling performance. Studies have found that feeding the holes with an internal crossflow, directed perpendicular to the mainstream flow, can cause up to a 50% reduction in film cooling effectiveness. This result is of concern because internal crossflow is a common internal flow condition in gas turbine engines. However, none of the former studies have made a concerted effort to examine the important scaling parameters governing this effect. Nor have they provided experimental evidence showing the cause of this reduction in effectiveness due to internal crossflow. In this study, a wide range of flow conditions was studied for two common film cooling hole geometry types: axial and compound angle diffused-exit film cooling holes. Internal crossflow-to-mainstream velocity ratios of VR [subscript c] = 0.2-0.6 were tested along with jet-to-mainstream velocity ratios of VR = 0.2-1.7. Film cooling effectiveness and discharge coefficients were measured for this full range of flow conditions for both geometries in order to produce a sufficiently large data set to observe important trends in the data. It was found that the discharge coefficients, centerline effectiveness, and centerline location all scaled with the crossflow-to-jet velocity ratio, VR [subscript i] for the axial holes. Temperature and velocity fields showed that VR [subscript i] also scaled the in-hole temperature and velocity fields. A swirling flow within the hole was shown to cause ingestion of mainstream into the diffused exit of the hole and biasing of the issuing jet in the outlet diffuser, which reduced film cooling effectiveness. The direction of bias at the exit resulted from the direction of the internal crossflow and was critical for compound angle holes. Crossflow directed counter to the lateral direction of coolant injection caused improved film cooling effectiveness relative to the in-line crossflow direction

A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole

Download A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (13 download)

DOWNLOAD NOW!


Book Synopsis A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole by : Shane Haydt

Download or read book A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole written by Shane Haydt and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbines are used around the world to provide thrust for airplanes and to generate electricity. Designers and operators are constantly chasing higher thermal efficiency, and even an incremental increase is considered an achievement. Higher thermal efficiency begets higher turbine inlet temperatures, and the parts that are exposed to these temperatures require sophisticated cooling technologies. One such cooling method is shaped film cooling, which ejects low momentum coolant with the goal of it staying attached to the wall, spreading laterally, and providing a lower driving temperature for convection.In some film cooling manufacturing processes, the meter and diffuser are created in separate steps with separate machines, and an offset can occur in that process. A study was designed to quantify the change in adiabatic effectiveness for five offset directions: fore, fore-left, left, aft-left, and aft. All offset directions caused a detriment to film cooling performance, except for the fore offset, which improved adiabatic effectiveness relative to a no offset case. CFD helped show that the fore offset created a separation in the region of the film cooling metering section where jetting occurs, which decreased the high momentum and made the cooling jet more likely to remain attached to the surface. This study resulted in a patent.A large range of area ratios and blowing ratios were examined in a study designed to isolate the effect of area ratio by lengthening the diffuser of a shaped hole. Very high area ratios were generated that resulted in significant cooling potential. It was shown that at each area ratio there is an optimal blowing ratio beyond which the effectiveness will decrease or plateau. This was reduced to an optimal effective blowing ratio, M/AR, which was shown through CFD to be the condition when the coolant jet core has similar velocity magnitude to the mainstream flow. This results in a weak shear layer and a weak counter-rotating vortex pair.In an axially oriented hole, the mainstream flows over the top of a cooling jet and around the sides, in equal measure, creating a symmetric flowfield. In a compound angled shaped hole, the mainstream flows primarily around the leeward side, creating a strong shear layer and an asymmetric streamwise vortex. Compound angled shaped holes are used commonly in gas turbines, but there has been no work examining the adiabatic effectiveness and heat transfer coefficient augmentation at a range of compound angles, and there are no flowfield measurements. A comprehensive study of the flowfield, cooling effectiveness, and heat transfer coefficient were obtained for compound angled shaped holes for compound angles ranging from 0-60 in 15 increments. It is shown that asymmetry and vorticity magnitude increase with increasing compound angle and increasing blowing ratio. Holes with high compound angles can maintain jet attachment at high blowing ratios because the streamwise component of blowing ratio is reduced, which leads to high effectiveness. The most important contribution of this work was showing that the streamwise vortex increases heat transfer coefficient in a region adjacent to the jet, where very little coolant coverage exists. For this reason, compound angled shaped holes can cause local regions of increased heat flux relative to an uncooled surface, which may be an issue for some designs if not properly accounted for. Heat transfer coefficient augmentation increases as compound angle and blowing ratio increase. Designs that promote jet interaction, such as holes with a smaller pitchwise spacing or holes with significant lateral motion, cover the entire endwall in coolant and lessen the negative effects of high heat transfer coefficient augmentation.

Gas Turbine Heat Transfer and Cooling Technology, Second Edition

Download Gas Turbine Heat Transfer and Cooling Technology, Second Edition PDF Online Free

Author :
Publisher : CRC Press
ISBN 13 : 1439855684
Total Pages : 892 pages
Book Rating : 4.4/5 (398 download)

DOWNLOAD NOW!


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.

Computational Film Cooling Methods for Gas Turbine Airfoils

Download Computational Film Cooling Methods for Gas Turbine Airfoils PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)

DOWNLOAD NOW!


Book Synopsis Computational Film Cooling Methods for Gas Turbine Airfoils by :

Download or read book Computational Film Cooling Methods for Gas Turbine Airfoils written by and published by . This book was released on 2002 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A previously documented CFD methodology is further generalized and applied to realistic turbine airfoil film cooling test cases. First, a series of fundamental test cases are examined in order to document the ability of the robust and practical CFD methodology to deal with the effects of the individually isolated key physics mechanisms on film cooling. These include: (1) favorable and adverse pressure gradients; (2) convex curvature; (3) horseshoe vortex; (4) profile losses with and without coolant jets; (5) laminar-to-turbulent boundary layer transition; and (6) discontinuities. Second, in addition to the fundamental flow test cases, two turbine airfoil cascade, one low subsonic and another transonic, configurations were modeled. The subsonic cascade case was designed to study the aerodynamics losses with and without film cooling jets, as well as, the adiabatic effectiveness for a range of parameters. The transonic turbine cascade represents a truly modern design at realistic engine conditions. A total of 18 test configurations, corresponding to compound-round, axial-shaped, and compound-shaped film holes, are simulated in order to document in detail the current state of the readily available robust and practical CFD technology for use by the gas turbine design community.

Journal of Heat Transfer

Download Journal of Heat Transfer PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 484 pages
Book Rating : 4.:/5 (318 download)

DOWNLOAD NOW!


Book Synopsis Journal of Heat Transfer by :

Download or read book Journal of Heat Transfer written by and published by . This book was released on 2005 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Variable Incidence Angle Film Cooling Experiments on a Scaled Up Turbine Airfoil Model

Download Variable Incidence Angle Film Cooling Experiments on a Scaled Up Turbine Airfoil Model PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 546 pages
Book Rating : 4.:/5 (15 download)

DOWNLOAD NOW!


Book Synopsis Variable Incidence Angle Film Cooling Experiments on a Scaled Up Turbine Airfoil Model by : Kyle Feliciano Chavez

Download or read book Variable Incidence Angle Film Cooling Experiments on a Scaled Up Turbine Airfoil Model written by Kyle Feliciano Chavez and published by . This book was released on 2016 with total page 546 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study focused on three main areas of research - the development of a new type of low-speed, closed-loop wind tunnel design to test at varying incidence angles, the investigation of film cooling for gas turbine components at varying incidence angles, and the analysis of the heat transfer and flow field predictive capability of RANS models. In order to develop the closed loop wind tunnel, a rigorous design and validation process was followed. This validated design is unique for low-speed closed-loop facilities. The development of this wind tunnel enabled measurements of adiabatic and overall effectiveness of two highly realistic airfoil models with shaped holes at varying incidence angles. This was accomplished through application of the appropriate aerodynamic and heat transfer scaling parameters for all measurements. Among other results, it was found that the shaped holes at the stagnation row of holes significantly enhanced film cooling effectiveness in the high curvature region of the showerhead depending on the incidence angle tested, and that the incidence angle effect persisted on the matched Biot number model. No previous studies had experimentally investigated the effects of incidence angle effects on overall effectiveness of a full-coverage airfoil. Furthermore, no previous studies had investigated the effect of shaped holes in the showerhead region of a realistic airfoil model such as the one used in this study. Finally, the computational predictive capability of various RANS turbulence models were analyzed by predicting the heat transfer coefficient of the model as well as the turbulence production and turning angle of a vertical array of rods used to generate turbulence in the tunnel. It was found that the computational predictions of leading-edge heat transfer were under-predicted due to the shape of the model leading edge. It was also found that the SST-Transition model appropriately predicted downstream turbulence and turning angle of the vertical rod array when compared to experimental results and empirical correlations in the literature. This is the first study to experimentally and computationally investigate the turning angle of a vertical grid array over a range of zero and non-zero inlet flow angles.

Effects of Film Injection Angle on Turbine Vane Cooling

Download Effects of Film Injection Angle on Turbine Vane Cooling PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)

DOWNLOAD NOW!


Book Synopsis Effects of Film Injection Angle on Turbine Vane Cooling by : James W. Guantner

Download or read book Effects of Film Injection Angle on Turbine Vane Cooling written by James W. Guantner and published by . This book was released on 1977 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Experiments and Simulation of Shaped Film Cooling Holes Fed by Crossflow with Rib Turbulators

Download Experiments and Simulation of Shaped Film Cooling Holes Fed by Crossflow with Rib Turbulators PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 172 pages
Book Rating : 4.:/5 (18 download)

DOWNLOAD NOW!


Book Synopsis Experiments and Simulation of Shaped Film Cooling Holes Fed by Crossflow with Rib Turbulators by : Dale Wilson Fox (III)

Download or read book Experiments and Simulation of Shaped Film Cooling Holes Fed by Crossflow with Rib Turbulators written by Dale Wilson Fox (III) and published by . This book was released on 2018 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: Most studies of turbine airfoil film cooling in laboratories have used relatively large plenums to feed flow into the coolant holes. A more realistic inlet condition for the film cooling holes is an internal crossflow channel. In this study, angled rib turbulators were installed in two geometric configurations inside the internal crossflow channel, at 45° and 135°, to assess the impact on film cooling effectiveness. Film cooling hole inlets positioned in both pre-rib and post-rib locations tested the effect of hole inlet position relative to the rib turbulators. Experiments were performed varying channel velocity ratio and jet to mainstream velocity ratio. These results were compared to the film cooling performance of previously measured shaped holes fed by a smooth internal channel, as well as RANS simulations performed for select cases. The film cooling hole discharge coefficients and channel friction factors were measured for both rib configurations. Spatially-averaged film cooling effectiveness behaves similarly to holes fed by a smooth internal crossflow channel, but hole-to-hole variation due to the obstruction by the ribs was observed.

Evaluation of Additively Manufactured Internal Cooling Channels and Film Cooling Holes for Cooling Effectiveness

Download Evaluation of Additively Manufactured Internal Cooling Channels and Film Cooling Holes for Cooling Effectiveness PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (14 download)

DOWNLOAD NOW!


Book Synopsis Evaluation of Additively Manufactured Internal Cooling Channels and Film Cooling Holes for Cooling Effectiveness by : Emma Veley

Download or read book Evaluation of Additively Manufactured Internal Cooling Channels and Film Cooling Holes for Cooling Effectiveness written by Emma Veley and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Cooling of the high-pressure turbine in a gas turbine engine is essential for durability because the gas temperature entering the turbine exceeds the melting point of the hardware. Both internal and external cooling reduces the temperature of the blades and vanes. Using air that bypassed the combustor as coolant, the convective heat transfer from the hardware to this internal coolant is often augmented by ribs or a serpentine path. To cool the external surface, coolant passes through holes on the outer wall of airfoil. The coolant creates a protective film on the surface. The shape of the cooling hole influences the cooling effectiveness of this film cooling. Additive manufacturing facilitates rapid prototyping compared to traditional manufacturing methods, which can be exploited for designing and evaluating cooling schemes of gas turbine hardware. The work in this dissertation used additive manufacturing to investigate the cooling performance of several internal and external cooling schemes manufactured in at engine scale for the unique objective of determining the impacts of the internal cooling scheme on the external cooling. A variety of cooling hole shapes were investigated for this work: cylindrical hoes, meter-diffuser shaped holes, and novel optimized holes. Once additively manufactured, the as-built cooling hole surfaces were analyzed to determined their roughness and minimum cross-sectional areas. The arithmetic mean roughness of holes built at the optimal build orientation (perpendicular to the build plate) were on the order of 10 [mu]m; whereas those investigated at other build orientations had roughness values up to 75 [mu]m. For the holes built perpendicular to the substrate the minimum cross-sectional area was usually greater than the design intent but within 15%. The additive process also created an overbuilt lip on the leading edge (windward) side of the hole exit for these holes because of the thin wall thickness in the design. Using these cooling holes, the impact of rounding on meter-diffuser shaped holes and optimized holes on overall effectiveness was investigated. The rounding, which came in the form of inlet fillets on the meter-diffuser shaped holes, was found to decrease the required pressure ratio to obtain the same cooling effectiveness. The deviations from the design due to the additive process caused the novel cooling hole shapes designed through adjoint optimization to perform differently than anticipated. For example, the coolant jet from hole designed for co-flow did not bifurcate as the computational simulation showed. The cross-flow optimized hole outperformed the co-flow optimized hole for most of the tested blowing ratio when both holes were tested in a co-flow configuration. These results from the novel optimized holes proved the necessity of experimentally verifying new designs prior to incorporating into final cooling schemes. The effect of supply channel height, number of channels, ribs, and the cross-sectional shape of the supply channel was investigated to determine the impact of each on the overall effectiveness. Designs that had high overall effectiveness from only internal cooling had less augmentation in effectiveness from film cooling than designs with less effective internal cooling. For example, a ribbed channel typically had a lower film-cooling augmentation than the film-cooling augmentation for same supply channel without ribs. However, a highly effective feed channel can obtain a higher overall effectiveness without any film cooling than a poorly performing feed channel can obtain with film cooling. But the features that create a highly effective feed channel can also cause the cooling jet to lift-off the surface and mix with the hot gas path, which was seen with some rib and hole combinations and with the triangle -- vertex down supply channels. Therefore, the hole shape, the supply channel geometry, and the junction between the two all significantly contribute to a cooling scheme's performance and all three must be considered concurrently to create an optimal cooling design.

Journal of Thermophysics and Heat Transfer

Download Journal of Thermophysics and Heat Transfer PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 996 pages
Book Rating : 4.F/5 ( download)

DOWNLOAD NOW!


Book Synopsis Journal of Thermophysics and Heat Transfer by :

Download or read book Journal of Thermophysics and Heat Transfer written by and published by . This book was released on 2006 with total page 996 pages. Available in PDF, EPUB and Kindle. Book excerpt: This journal is devoted to the advancement of the science and technology of thermophysics and heat transfer through the dissemination of original research papers disclosing new technical knowledge and exploratory developments and applications based on new knowledge. It publishes papers that deal with the properties and mechanisms involved in thermal energy transfer and storage in gases, liquids, and solids or combinations thereof. These studies include conductive, convective, and radiative modes alone or in combination and the effects of the environment.

Effects of Film Injection Angle on Turbine Vane Cooling

Download Effects of Film Injection Angle on Turbine Vane Cooling PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (317 download)

DOWNLOAD NOW!


Book Synopsis Effects of Film Injection Angle on Turbine Vane Cooling by : James W. Gauntner

Download or read book Effects of Film Injection Angle on Turbine Vane Cooling written by James W. Gauntner and published by . This book was released on 1977 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements

Download Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 572 pages
Book Rating : 4.:/5 (112 download)

DOWNLOAD NOW!


Book Synopsis Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements by : Joshua Brian Anderson

Download or read book Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements written by Joshua Brian Anderson and published by . This book was released on 2017 with total page 572 pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling is widely used in gas turbine engines to manage temperatures within the hot section of the engine. In this work, several investigations are described, all of which studied how fundamental hydrodynamic and thermal parameters influence the performance of film cooling. The first investigation studied the impact of freestream turbulence, boundary layer thickness, Reynolds number, and Mach number on film cooling performance, using axial shaped film cooling holes. The second study considered a similar set of parameters, and investigated their impact on compound-angle oriented film cooling holes. Both of these studies utilized measurements of adiabatic effectiveness and heat transfer coefficient augmentation. In general, the parameters had effects which were dependent on the coolant flow rate and density ratio. The final study considered methods to reduce the experimental uncertainty which arises from conduction and radiation errors in thermal measurements. A careful evaluation of the thermal boundary layer was used to validate these corrections

Heat Transfer on a Film-Cooled Blade - Effect of Hole Physics

Download Heat Transfer on a Film-Cooled Blade - Effect of Hole Physics PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (317 download)

DOWNLOAD NOW!


Book Synopsis Heat Transfer on a Film-Cooled Blade - Effect of Hole Physics by :

Download or read book Heat Transfer on a Film-Cooled Blade - Effect of Hole Physics written by and published by . This book was released on 1998 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles

Download Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 265 pages
Book Rating : 4.:/5 (227 download)

DOWNLOAD NOW!


Book Synopsis Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles by :

Download or read book Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles written by and published by . This book was released on 1991 with total page 265 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental results are presented which describe the development and structure of flow downstream of one row and downstream of two staggered rows of film cooling holes with compound angle orientations. Results presented include distributions of iso-energetic Stanton number ratios, and adiabatic film-cooling effectiveness deduced from Stanton numbers using superposition. Also presented are plots showing the streamwise development of injectant distributions and streamwise development of mean velocity distributions. Spanwise averaged values of the adiabatic film-cooling effectiveness are highest for blowing ratio m=0.5 and decrease as blowing ratio increases for x/d less than 20. At farther downstream positions, spanwise averaged effectiveness values increase with blowing ratio, except for data obtained downstream of two rows of holes with a blowing ratio of 3.0 and data obtained downstream of two rows of holes with a blowing ratio of 3.0 and data obtained downstream of one row of holes with a blowing ratio of 4.0, where severe lift-off of injectant occurs. Spanwise averaged iso-energetic Stanton number ratios range between 1.0 and 1.4 and show little variation as x/d increases for each value of blowing ratio, however for each x/d, values increases with increasing blowing ratio. The need for greater efficiency in gas turbine engines has resulted in higher turbine inlet temperatures approaching 2000 K. These extreme temperatures, in combination with the high rotational speeds, result in large stress magnitudes on component materials, especially on the blades of the first turbine stage.

The Effect of Channel Parameters on the Adiabatic Film Cooling Effectiveness of Shaped Holes in Crossflow

Download The Effect of Channel Parameters on the Adiabatic Film Cooling Effectiveness of Shaped Holes in Crossflow PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 168 pages
Book Rating : 4.:/5 (946 download)

DOWNLOAD NOW!


Book Synopsis The Effect of Channel Parameters on the Adiabatic Film Cooling Effectiveness of Shaped Holes in Crossflow by : Ellen Katherine Wilkes

Download or read book The Effect of Channel Parameters on the Adiabatic Film Cooling Effectiveness of Shaped Holes in Crossflow written by Ellen Katherine Wilkes and published by . This book was released on 2015 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: There is limited information in the literature on the behavior of shaped film cooling holes fed by crossflow and even less information on the effect of crossflow parameters on film cooling performance. Here, two scaled film cooling models were used to independently vary the crossflow Reynolds numbers in the range of 36,000 to 57,000 and the crossflow velocity ratio from 0.36 to 0.64. Careful attention was paid to controlling physical parameters between comparisons to isolate the effects of internal velocity ratio or Reynolds number on the performance of shaped holes. In the process of controlling the physical parameters of the system, a novel correction for coolant to mainstream density ratio was proposed. The results of this study showed that channel velocity ratio had a larger effect on the film cooling performance of shaped holes than channel Reynolds number. When the mass flux of fluid through the film cooling holes was at the highest and lowest value, increasing the channel velocity ratio decreased the film cooling effectiveness. At a middle mass flux, the outcome was opposite such that an increase in channel velocity ratio resulted in increased effectiveness.

94-GT-312 Film cooling with compound angle holes: adiabatic effectiveness

Download 94-GT-312 Film cooling with compound angle holes: adiabatic effectiveness PDF Online Free

Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)

DOWNLOAD NOW!


Book Synopsis 94-GT-312 Film cooling with compound angle holes: adiabatic effectiveness by : Donald L. Schmidt

Download or read book 94-GT-312 Film cooling with compound angle holes: adiabatic effectiveness written by Donald L. Schmidt and published by . This book was released on 1994 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: