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Heat Transfer Effects Of Non Traditional Film Cooling Hole Geometries On Cooling Effectiveness
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Book Synopsis HEAT TRANSFER EFFECTS OF NON-TRADITIONAL FILM COOLING HOLE GEOMETRIES ON COOLING EFFECTIVENESS. by : Emily J Sun
Download or read book HEAT TRANSFER EFFECTS OF NON-TRADITIONAL FILM COOLING HOLE GEOMETRIES ON COOLING EFFECTIVENESS. written by Emily J Sun and published by . This book was released on 2019 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A gas turbine is a device that harnesses energy from the manipulation of air. In pursuit of greater efficiencies, the temperatures of the combustors are being increased. Given these conditions, certain design steps and materials selection are vital for the performance of the components. On the design side, internal and external cooling features can be designed to control the heat transfer to and from a part. Film cooling is a mechanism by which some of the internal cooling flow is allowed to flow over the surface of the airfoil of a turbine blade via holes in the wall of the turbine blade. Currently film cooling hole geometry designs are usually drilled through the walls of the airfoil through laser drilling or electro discharge machining (EDM). With this method of creating the film cooling holes, the designs for these holes needs to fall along a linear axis and tool-paths must be considered. However, with the development of additive manufacturing, turbine blades can be constructed with film cooling holes already embedded in the designs. As a result, the designs for film cooling holes have a greater complexity tolerance, which can be used to optimize the internal fluid dynamics. In order to explore the effects of the complex film cooling geometries, various film cooling hole geometries have been designed. The major designs were different modification of the 7-7-7 hole. The two types of design modifications were to the cross section or the curvature of the meter. The four major designs were: the Square hole, the Half Circle hole, the 60 Turn hole, and the 90 Turn hole. An experiment was conducted to determine the effect of the different changes on film cooling effectiveness in comparison to the 7-7-7 hole.
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.
Book Synopsis Effects of Hole Length, Supply Plenum Geometry, and Freestream Turbulence on Film Cooling Performance by :
Download or read book Effects of Hole Length, Supply Plenum Geometry, and Freestream Turbulence on Film Cooling Performance written by and published by . This book was released on 2000 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Full Coverage Film Cooling Study by : Justin Hodges
Download or read book A Full Coverage Film Cooling Study written by Justin Hodges and published by . This book was released on 2015 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis is an experimental and numerical full-coverage film cooling study. The objective of this work is the quantification of local heat transfer augmentation and adiabatic film cooling effectiveness for two full-coverage film cooling geometries. Experimental data was acquired with a scientific grade CCD camera, where images are taken over the heat transfer surface, which is painted with a temperature sensitive paint. The CFD component of this study served to evaluate how well the v2-f turbulence model predicted film cooling effectiveness throughout the array, as compared with experimental data. The two staggered arrays tested are different from one another through a compound angle shift after 12 rows of holes. The compound angle shifts from [beta]=-45° to [beta]=+45° at row 13. Each geometry had 22 rows of cylindrical film cooling holes with identical axial and lateral spacing (X/D=P/D=23). Levels of laterally averaged film cooling effectiveness for the superior geometry approach 0.20, where the compound angle shift causes a decrease in film cooling effectiveness. Levels of heat transfer augmentation maintain values of nearly h/h0=1.2. There is no effect of compound angle shift on heat transfer augmentation observed. The CFD results are used to investigate the detrimental effect of the compound angle shift, while the SST k-[omega] turbulence model shows to provide the best agreement with experimental results.
Book Synopsis Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery by : S. Stephen Papell
Download or read book Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery written by S. Stephen Papell and published by . This book was released on 1979 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery by : S. Stephen Papell
Download or read book Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery written by S. Stephen Papell and published by . This book was released on 1979 with total page 24 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 Shaped Hole Effects on Film Cooling Effectiveness and a Comparison of Multiple Effectiveness Measurement Techniques by : Trent Alan Varvel
Download or read book Shaped Hole Effects on Film Cooling Effectiveness and a Comparison of Multiple Effectiveness Measurement Techniques written by Trent Alan Varvel and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: This experimental study consists of two parts. For the first part, the film cooling effectiveness for a single row of seven cylindrical holes with a compound angle is measured on a flat surface using five different measurement techniques: steady-state liquid crystal thermography, transient liquid crystal thermography, pressure sensitive paint (PSP), thermocouples, and infrared thermography. A comparison of the film cooling effectiveness from each of the measurement techniques is presented. All methods show a good comparison, especially for the higher blowing ratios. The PSP technique shows the most accurate measurements and has more advantages for measuring film cooling effectiveness. Also, the effect of blowing ratio on the film cooling effectiveness is investigated for each of the measurement techniques. The second part of the study investigates the effect of hole geometries on the film cooling effectiveness using pressure sensitive paint. Nitrogen is injected as the coolant air so that the oxygen concentration levels can be obtained for the test surface. The film effectiveness is then obtained by the mass transfer analogy. Five total hole geometries are tested: fan-shaped laidback with a compound angle, fan-shaped laidback with a simple angle, a conical configuration with a compound angle, a conical configuration with a simple angle, and the reference geometry (cylindrical holes) used in part one. The effect of blowing ratio on film cooling effectiveness is presented for each hole geometry. The spanwise averaged effectiveness for each geometry is also presented to compare the geometry effect on film cooling effectiveness. The geometry of the holes has little effect on the effectiveness at low blowing ratios. The laterally expanded holes show improved effectiveness at higher blowing ratios. All experiments are performed in a low speed wind tunnel with a mainstream velocity of 34 m/s. The coolant air is injected through the coolant holes at four different coolant-to-mainstream velocity ratios: 0.3, 0.6, 1.2, and 1.8.
Book Synopsis The Effect of Injection Hole Geometry on Flat Plate Film Cooling and Heat Transfer by : Eric Perry Madsen
Download or read book The Effect of Injection Hole Geometry on Flat Plate Film Cooling and Heat Transfer written by Eric Perry Madsen and published by . This book was released on 1994 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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.
Book Synopsis Dependence of Film Cooling Effectiveness on 3D Printed Cooling Holes by : Paul P. Aghasi
Download or read book Dependence of Film Cooling Effectiveness on 3D Printed Cooling Holes written by Paul P. Aghasi and published by . This book was released on 2016 with total page 189 pages. Available in PDF, EPUB and Kindle. Book excerpt: To investigate the viability of using additive manufacturing technology for flat plate film cooling experiments a new experiential facility was constructed using gas analysis and oxygen sensitive paint as a method of measuring and characterizing film cooling effectiveness for various additive manufacturing technologies as well as aluminum. The ultimate objective of this work is to assess whether these technologies can be a replacement for traditional aluminum CNC machining. Film Cooling Effectiveness is closely dependent on the geometry of the hole emitting the cooling film. These holes are sometimes quite expensive to machine by traditional methods so 3D printed test pieces have the potential to greatly reduce the cost of film cooling tests. What is unknown is the degree to which parameters like layer resolution and the choice of 3D printing technologies influence the results of a film cooling test. A new flat-plate film cooling facility employing the mass transfer analogy (introduction of foreign gas as coolant, not to be confused with the sublimation method) and measurements both by gas sample analysis and oxygen-sensitive paint is first validated using gas analysis and oxygen sensitive paint cross correlation. The same facility is then used to characterize the film cooling effectiveness of a diffuser shaped film cooling hole geometry. These diffuser holes (film hole diameter, D of 0.1 inches) are then produced by a variety of different manufacturing technologies, including traditional machined aluminum, Fused Deposition Modeling (FDM), Stereo Lithography Apparatus (SLA) and PolyJet with layer thicknesses from 0.001D (25 [micro]m) to 0.12D (300 [micro]m). Tests are carried out at mainstream flow Mach number of 0.30 and blowing ratios from 1.0 to 3.5. The coolant gas used is CO2 yielding a density ratio of 1.5. Surface quality is characterized by an Optical Microscope that calculates surface roughness. Test coupons with rougher surface topology generally showed delayed film hole blow off and higher film cooling effectiveness at increased blowing ratios compared to the geometries with lower measured surface roughness.
Book Synopsis Film Cooling on a Convex Wall by : Kokichi Furuhama
Download or read book Film Cooling on a Convex Wall written by Kokichi Furuhama and published by . This book was released on 1983 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Film Cooling on the Heat Transfer Between a Shrouded Rotating Disk and a Radially Inward Flow by : Darryl E. Metzger
Download or read book The Effect of Film Cooling on the Heat Transfer Between a Shrouded Rotating Disk and a Radially Inward Flow written by Darryl E. Metzger and published by . This book was released on 1963 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Freestream Conditions on Effectiveness and Heat Transfer Coefficient in Turbine Film Cooling Geometries by :
Download or read book Influence of Freestream Conditions on Effectiveness and Heat Transfer Coefficient in Turbine Film Cooling Geometries written by and published by . This book was released on 2004 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Numerical Study of Discrete-hole Film Cooling by : Mulugeta K. Berhe
Download or read book A Numerical Study of Discrete-hole Film Cooling written by Mulugeta K. Berhe and published by . This book was released on 1997 with total page 314 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer in Gas Turbine Systems by : Richard J. Goldstein
Download or read book Heat Transfer in Gas Turbine Systems written by Richard J. Goldstein and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Explores recent developments in heat transfer and thermal control applied to modern high-temperature gas turbine systems. It examines experimental results and techniques computational studies and methods and design recommendations. Aspects of heat transfer in rotating machinery are studied as well as thermal aspects of other sections of the turbine (e.g. the compressor). Proceedings of an August 2000 conference.
