Relevant bibliographies by topics / Film cooled nozzle

Academic literature on the topic 'Film cooled nozzle'

Author: Grafiati
Published: 10 March 2023

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Journal articles on the topic "Film cooled nozzle"

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Stark, Ralf, Chloé Génin, Christian Mader, Dietmar Maier, Dirk Schneider, and Michael Wohlhüter. "Design of a film cooled dual-bell nozzle." Acta Astronautica 158 (May 2019): 342–50. http://dx.doi.org/10.1016/j.actaastro.2018.05.056.

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Pereselkov, A., and O. Kruglyakova. "EXPERIMENTAL STUDY OF ELEMENTARY ACTS OF HYDRODYNAMICS AND HEAT TRANSFER DURING THE INTERACTION BETWEEN WATER DROPS AND FILM AND CASTING ROLLER SURFACE." Integrated Technologies and Energy Saving, no. 4 (December 12, 2022): 3–12. http://dx.doi.org/10.20998/2078-5364.2022.4.01.

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Experimental studies of the boundary conditions of heat transfer for the thermally stressed state of casting rollers while are spraying with flat-jet nozzles in a thermal preconditioning unit have been carried out. It is shown that the hydrodynamic conditions on the sprinkling surface are formed as a result of both the influx of "primary" dispersed water from the flat jet nozzle, and the "secondary" liquid coming from neighboring areas in the form of reflected drops and films. The heat transfer effecting individual factors that form the hydrodynamic conditions on the sprinkling surface was studied separately. The heat transfer intensity was studied depending on the spraying density, the injection-pressure drop and the temperature of the cooled surface when the "primary" drop flow runs in the heat exchange surface. The local sprinkling density of droplets on the surface under the flat-jet nozzle spray were measured using a sampling tube moved by a coordinator. At the same time, the ingress of “secondary” liquid into it was excluded. The specific heat flux and heat transfer coefficient were determined using a heat meter made of a nichrome tape heated by direct current. In this case, the isothermality of the surface of the measuring section was ensured. Thermocouples measured the temperature of the lower surface of the tape, and then the stationary temperature of the upper surface of the heat meter sprinkled with drops is calculated. As a result of the multivariate analysis of the experimental data, the correlation dependence of the heat transfer coefficient in dependance on the local spraying conditions of the heat meter surface was obtained. Also, studies of the heat transfer during water film flow over the heat meter surface were carried out. A similar situation takes place when water spreads between the adjacent nozzles sprinkling zones of the roller surface. The correlation dependence between the heat transfer coefficient, the water film speed and the cooled surface temperature was obtained. Studies of heat transfer during combined influence of moving water film and a flat-jet nozzle drop flow on the heat exchange surface showed that the heat transfer rate is approximately 80–90 % of the arithmetic sum of the coefficients obtained by separate cooling the heat meter with drops and a water film.
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Kukutla, Pol Reddy, and B. V. S. S. S. Prasad. "Numerical Study on the Secondary Air Performance of the Film Holes for the Combined Impingement and Film Cooled First Stage of High Pressure Gas Turbine Nozzle Guide Vane." International Journal of Turbo & Jet-Engines 37, no. 3 (August 27, 2020): 221–40. http://dx.doi.org/10.1515/tjj-2017-0022.

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AbstractThe present numerical investigation of Leading Edge (LE) Nozzle Guide Vane (NGV) is considered with five rows of impingement holes combined with five rows of film cooled for the secondary coolant flow path analysis. The coolant mass flow rate variations in all the LE rows of the film holes externally subjected to the hot main stream were obtained by making a three-dimensional computational analysis of NGV with a staggered array of film cooled rows. The experiments were carried out for the same NGV using Particle Image Velocimetry technique to determine the effused coolant jet exit velocity at the stagnation row of film holes as mentioned in reference [Kukutla PR, Prasad BVSSS. Secondary flow visualization on stagnation row of a combined impingement and film cooled high pressure gas turbine nozzle guide vane using PIV technique, J Visualization, 2017; DOI: 10.1007/s12650-017-0434-6]. In this paper, results are presented for three different mass flow rates ranges from 0.0037 kg/s to 0.0075 kg/s supplied at the Front Impingement Tube (FIT) plenum. And the mainstream velocity 6 m/s was maintained for all the three coolant mass flow rates. The secondary coolant flow distribution was performed from SH1 to SH5 row of film holes. Each row of a showerhead film hole exit coolant mass flow rate varied in proportion to the amount of coolant mass rates supplied at the FIT cooling channel. The corresponding minimum and maximum values and their film hole locations were altered. The same behaviour was continued for the coolant pressure drop and temperature rise from SH1 to SH5 row of film holes. Owing to the interaction between hot main stream and the coolant that effuses out of the film holes, occasional presence of hot gas ingestion was noticed for certain flow rates. This caused nonlinear distribution in mass flow, pressure drop and temperature rise. The minimum flow rate results estimate oxidation of NGV material near the film cooled hole. And the effect of hot gas ingestion on the ejected film cooled jet which would recommends effective oxidation resistant material which in turn leads to better durability of the NGV surface.
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Wang, Ten-See, and Mike Guidos. "Transient Three-Dimensional Side-Load Analysis of a Film-Cooled Nozzle." Journal of Propulsion and Power 25, no. 6 (November 2009): 1272–80. http://dx.doi.org/10.2514/1.41025.

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Yang, R. J. "Assessment of turbulence and chemistry models for film-cooled nozzle flows." Journal of Thermophysics and Heat Transfer 10, no. 2 (April 1996): 284–89. http://dx.doi.org/10.2514/3.785.

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Sellam, Mohamed, and Amer Chpoun. "Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling." International Journal of Aerospace Engineering 2015 (2015): 1–15. http://dx.doi.org/10.1155/2015/252404.

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Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynamic and chemical mechanisms that are at the origin of these processes. This paper is a numerical contribution which reports results from CFD analysis carried out for supersonic reactive flows in a planar nozzle cooled with GH2film. Like the experimental observations, CFD simulations showed their ability to highlight these phenomena for the same nozzle flow conditions. Induced thermal load are also analyzed in terms of cooling efficiency and the results already give an idea on their magnitude. It was also shown that slightly increasing the film injection pressure can avoid the reignition phenomena by moving the separation shock towards the nozzle exit section.
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Wang, Ten-See, Jeff Lin, and Mike Guidos. "Transient Side-Load Analysis of Out-of-Round Film-Cooled Nozzle Extensions." Journal of Propulsion and Power 29, no. 4 (July 2013): 855–66. http://dx.doi.org/10.2514/1.b34812.

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Kozyulin, N. N., M. S. Bobrov, and M. Y. Hrebtov. "Adjoint shape optimization of a duct for a wall jet film cooling setup." Journal of Physics: Conference Series 2119, no. 1 (December 1, 2021): 012018. http://dx.doi.org/10.1088/1742-6596/2119/1/012018.

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Abstract The paper presents the results of optimization of the geometric parameters of the simplified wall jet cooling system using a modified Adjoint Shape optimization method for algebraic systems of equations (Discrete Adjoint Optimization). The modification consists in using a linearized discrete system of equations with the replacement of derivatives by their finite-volume approximations. The jet flowed through a duct and out from a nozzle. The duct was inclined at an angle of 35 degrees to the cooled wall. The mean velocity ratio between the jet and the main flow was set to 2. The total heat flux on the cooled wall was taken as a cost function. The problem was considered in a two-dimensional stationary turbulent formulation (RANS). As a result of optimization, the shape of the duct changed significantly, affecting the flow inside it. The optimization led to the disappearance of the recirculation zone and reattaching of the jet to the cooled wall. As a result of the optimization performed, the heat flux at the wall increased by 20%.
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Day, C. R. B., M. L. G. Oldfield, and G. D. Lock. "The Influence of Film Cooling on the Efficiency of an Annular Nozzle Guide Vane Cascade." Journal of Turbomachinery 121, no. 1 (January 1, 1999): 145–51. http://dx.doi.org/10.1115/1.2841223.

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This paper examines the effect of aerofoil surface film cooling on the aerodynamic efficiency of an annular cascade of transonic nozzle guide vanes. A dense foreign gas (SF6/Ar mixture) is used to simulate engine representative coolant-to-mainstream density ratios under ambient conditions. The flowfield measurements have been obtained using a four-hole pyramid probe in a short duration blowdown facility that correctly models engine Reynolds and Mach numbers, as well as the inlet turbulence intensity. The use of foreign gas coolant poses specific challenges not present in an air-cooled cascade, and this paper addresses two. First, a novel method for the determination of mass flow from pneumatic probe data in a heterogeneous gas environment is presented that eliminates the need to measure concentration in order to determine loss. Second, the authors argue on the grounds of dimensionless similarity that momentum flux ratio is to be preferred to blowing rate for the correct parameterization of film cooling studies with varying coolant densities. Experimental results are presented as area traverse maps, from which values for loss have been calculated. It is shown that air and foreign gas at the same momentum flux ratio give very similar results, and that the main difference between cooled and uncooled configurations is an increase in wake width. Interestingly, it is shown that an increase in the momentum flux ratio above the design value with foreign gas coolant reduces the overall loss compared with the design value. The data have been obtained both for purposes of design and for CFD code Validation.
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Reddy Kukutla, Pol, and BVSSS Prasad. "Network analysis of a coolant flow performance for the combined impingement and film cooled first-stage of high pressure gas turbine nozzle guide vane." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 6 (April 16, 2018): 1977–89. http://dx.doi.org/10.1177/0954410018767290.

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The present paper describes a system-level thermo-fluid network analysis for the secondary air system analysis of a typically film-cooled nozzle guide vane with multiple actions of jet impingement. The one-dimensional simulation was done with the help of the commercially available Flownex 2015 software. The system-level thermo-fluid network results were validated with both the computational fluid dynamics results and experimentally available literature. The entire nozzle guide vane geometry was first mapped to a thermo-fluid network model and the pressure conditions at different nodes. The discharge and heat transfer coefficients obtained from the Ansys FLUENT were specified as inputs to the thermo-fluid network model. The results show that the one-dimensional simulation of the coolant mass flow rates and jet Nusselt number values are in good agreement with the three-dimensional computational fluid dynamics results.
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Dissertations / Theses on the topic "Film cooled nozzle"

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Lai, Cheng-Chyuan. "Fully film cooled nozzle guide vane heat transfer measurement and prediction." Thesis, University of Oxford, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.312115.

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Vogel, Gregory. "Experimental study on a heavy film cooled nozzle guide vane with contoured platforms /." Lausanne, 2002. http://library.epfl.ch/theses/?nr=2602.

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Thèse sciences techniques, EPF Lausanne, no 2602 (2002), Faculté Sciences et techniques de l'ingénieur, Domaine du génie mécanique. Directeur: A. Bölcs ; rapporteurs: M. Gritsch, J. Thome, B. Weigand.
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Luehr, Luke Emerson. "Step Misaligned and Film Cooled Nozzle Guide Vanes at Transonic Conditions: Heat Transfer." Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/83237.

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This study describes a detailed investigation on the effects that upstream step misalignment and upstream purge film cooling have on the endwall heat transfer for nozzle guide vanes in a land based power generation gas turbine at transonic conditions. Endwall Nusselt Number and adiabatic film cooling effectiveness distributions were experimentally calculated and compared with qualitative data gathered via oil paint flow visualization which also depicts endwall flow physics. Tests were conducted in a transonic linear cascade blowdown facility. Data were gathered at an exit Mach number of 0.85 with a freestream turbulence intensity of 16% at a Re = 1.5 x 106 based on axial chord. Varied upstream purge blowing ratios and a no blowing case were tested for 3 different upstream step geometries, one of which was the baseline (no step). The other two geometries are a backward step geometry and a forward step geometry, which comprised of a span-wise upstream step of +4.86% span and -4.86% span respectively. Experimentation shows that the addition of upstream purge film cooling increases the Nusselt Number at injection upwards of 50% but lowers it in the throat of the passage by approximately 20%. The addition of a backward facing step induces more turbulent mixing between the coolant and mainstream flows, thus reducing film effectiveness coverage and increasing Nusselt number by nearly 40% in the passage throat. In contrast, the presence of a forward step creates a more stable boundary layer for the coolant flow, thus aiding to help keep the film attached to the endwall at higher blowing ratios. Increasing the blowing ratio increases film cooling effectiveness and endwall coverage up to a certain point, beyond which, the high momentum of the coolant results in poor cooling performance due to jet liftoff. Near endwall streamlines without purge cooling generated by Li et al. [1] for the same geometries were compared to the experimental data. It was shown that even with the addition of upstream purge cooling, the near endwall streamlines as they moved downstream matched strikingly well with the experimental data. This discovery indicates that while the coolant flow will likely affect the flow streamlines three dimensionally, they are minimally effected by the coolant flow near the endwall as the flow moves downstream.
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Abdeh, Hamed. "Incidence Effects on Aerodynamic and Thermal Performance of a Film-Cooled Gas Turbine Nozzle Guide Vane." Doctoral thesis, Università degli studi di Bergamo, 2018. http://hdl.handle.net/10446/105183.

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In this study, the influence of inlet flow incidence on the aerodynamic and thermal performance of a film cooled linear nozzle vane cascade is fully assessed. Tests have been carried out on a solid and a cooled cascade. In the cooled cascade, coolant is ejected at the end wall through a slot located upstream of the leading edge plane. Moreover, a vane showerhead cooling system is also realized through 4 rows of cylindrical holes. The cascade was tested at a high inlet turbulence intensity level (Tu1 = 9%) and at a constant inlet Mach number of 0.12 and nominal cooling condition, varying the inlet flow angle. In addition to the reference incidence angle (0°), four other cases were investigated: +20°, +10°, -10° and -20°. The aero-thermal characterization of vane platform was obtained through 5-hole probe, endwall and vane showerhead adiabatic film cooling effectiveness measurements. Vane load distributions and surface flow visualizations supported the discussion of the results. On the vane, a significant movement in stagnation point happened when incidence angle varied, resulted in changing of the coolant distribution pattern between SS and PS of the cooled vane; which adversely affects the efficiency for both negative and positive inlet flow incidence angles. On the platform, however, a relevant negative impact of positive inlet flow incidence on the cooled cascade aerodynamic and endwall thermal performance was detected. A negligible influence was instead observed at negative incidence, even at the lowest tested value of -20°.
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Leung, Pak Wing. "Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane." Thesis, KTH, Kraft- och värmeteknologi, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130.

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Over the last two decades, most developed countries have reached a consensus that greener energy production is necessary for the world, due to the climate changes and limited fossil fuel resources. More efficient turbine is desirable and can be archived by higher turbine-inlet temperature (TIT). However, it is difficult for nozzle guide vane (NGV), which is the first stage after combustion chamber, to withstand a very high temperature. Thus, cooling methods such as film cooling have to be implemented. Film-cooled NGV of an annular sector cascade (ASC) is studied in this thesis, for getting comprehensive calculation of vorticity, and analyzing applicability of existing loss models, namely Hartsel model and Young & Wilcock model. The flow-field calculation methods from previously published studies are reviewed. Literatures focusing on Hartsel model and Young & Wilcock model are studied. Measurement data from previously published studies are analyzed and compared with the loss models. In order to get experience of how measurements take place, participation of a test run experiment is involved. Calculation of flow vector has been evaluated and modified. Actual flow angle is introduced when calculating velocity components. Thus, more exact results are obtained from the new method. Calculation of vorticity has been evaluated and made more comprehensive. Vorticity components as well as magnitude of total streamwise vorticity are calculated and visualized. Vorticity is higher and more extensive for fully cooled case than uncooled case. Highest vorticity is found at regions near the hub, tip and TE. Axial and circumferential vorticities show similar patterns, while the radial vorticity is relatively simpler. Compressibility is introduced as a new method when calculating circumferential and radial vorticities, resulting more extensive and higher vorticities than results from incompressible solutions. Hartsel model and Young & Wilcock model have been evaluated and compared to the ASC to see the applicability of the models. In general, Hartsel model cannot agree with the ASC to a satisfactory level and thus cannot be applied. Coolant velocity is found to be the dominant factor of Hartsel model. Young & Wilcock model may match SS1 and SS2 cases, or even PS and SH4 cases, but cannot match TE case. The applicability of Young & Wilcock model is much dependent on the location of cooling rows.
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Cubeda, Simone. "Impacts of gas-turbine combustors outlet flow on the aero-thermal performance of film-cooled first stage nozzles." Doctoral thesis, 2020. http://hdl.handle.net/2158/1197567.

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Modern aero-engine and industrial gas turbines typically employ lean-type combustors, which are capable of limiting pollutant emissions thanks to premixed flames, while sustaining high turbine inlet temperatures that increase the single-cycle thermal efficiency. In such technology gas-turbine first stage nozzles are characterised by a highly-swirled and temperature-distorted inlet flow field. However, due to several sources of uncertainty during the design phase, wide safety margins are commonly adopted, which can have a direct impact on the engine performance and efficiency. Therefore, with the aim of increasing the knowledge on combustor-turbine interaction and improving standard design practices, two non-reactive test rigs were assembled at the University of Florence, Italy. The rigs, both accommodating three lean-premix swirlers within a combustion chamber and a first stage film-cooled nozzles cascade, were operated in similitude conditions to mimic an aero-engine and an industrial gas turbine arrangements. The rigs were designed to reproduce the real engine periodic flow field on the central sector, allowing also to perform measurements far enough from the lateral walls. The periodicity condition was enforced by the installation of circular ducts at the injectors outlet section as to preserve the non-reactive swirling flow down to the nozzles inlet plane. For the aero-engine simulator rig and as part of two previous PhD works, of which the present is a continuation, an extensive test campaign was conducted. The flow field within the combustion chamber was investigated via particle-image velocimetry (PIV) and the combustor-turbine interface section was experimentally characterised in terms of velocity, pressure and turbulence fields by means of a five-hole pressure plus thermocouple probe and hot-wire anemometers, mounted on an automatic traverse system. To study the evolution of the combustor outlet flow through the nozzles and its interaction with the film-cooling flow, such measurements have been also replicated slightly downstream of the airfoils' trailing edge. Lastly, the film-cooling adiabatic effectiveness distribution over the airfoils was evaluated via coolant concentration measurements based on pressure sensitive paints (PSP) application. As far as the industrial turbine rig is concerned, the same type of measurements were carried out except for PIV. Within such experimental scenario, the core of the present work is related to numerical analyses. In fact, since the design of industrial high-pressure turbines historically relies on 1D, circumferentially-averaged profiles of pressure, velocity and temperature at the combustor/turbine interface in conjunction with Reynolds-averaged Navier-Stokes (RANS) models, this thesis describes how measurements can be leveraged to improve numerical modelling procedures. Within such context, hybrid scale resolving techniques, such as Scale-Adaptive Simulation (SAS), can suit the purpose, whilst containing computational costs, as also shown in the literature. Furthermore, the investigation of the two components within the same integrated simulation enables the transport of unsteady fluctuations from the combustor down to the first stage nozzles, which can make the difference in the presence of film cooling.
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Books on the topic "Film cooled nozzle"

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National Aeronautics and Space Administration (NASA) Staff. Numerical Simulation of Film-Cooled Ablative Rocket Nozzles. Independently Published, 2018.

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Book chapters on the topic "Film cooled nozzle"

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Génin, Chloé, Dirk Schneider, and Ralf Stark. "Dual-Bell Nozzle Design." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 395–406. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_25.

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Abstract The dual-bell nozzle is an altitude adaptive nozzle concept that offers two operation modes. In the framework of the German Research Foundation Special Research Field SFB TRR40, the last twelve years have been dedicated to study the dual-bell nozzle characteristics, both experimentally and numerically. The obtained understanding on nozzle contour and inflection design, transition behavior and transition prediction enabled various follow-ups like a wind tunnel study on the dual-bell wake flow, a shock generator study on a film cooled wall inflection or, in higher scale, the hot firing test of a thrust chamber featuring a film cooled dual-bell nozzle. A parametrical system study revealed the influence of the nozzle geometry on the flow behavior and the resulting launcher performance increase.
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Raju, Martin, V. V. Ijas Muhammed, Abhilash Suryan, and Heuy Dong Kim. "Computational Study on the Flow Characteristics in a Film Cooled Dual-Bell Nozzle." In Lecture Notes in Mechanical Engineering, 225–32. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-5183-3_24.

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Conference papers on the topic "Film cooled nozzle"

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Stark, Ralf, and Chloé Génin. "Hot Flow Testing of a Film Cooled Dual Bell Nozzle." In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-5614.

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Kukutla, Pol Reddy, and B. V. S. S. S. Prasad. "Fluid Thermal Network Studies on Cooled Nozzle Guide Vane." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2651.

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Abstract The aerothermal analysis is reported with the help of one-dimensional network modeling for the impingement cum film cooled gas turbine vane. The purpose of this one-dimensional simulation is to obtain the optimized film hole diameters of each row by analyzing the coolant flow distribution and overall effectiveness variations. FlownexR2017 commercial code is used to determine the detailed steady-state performance of the cooling vane. The results show that it is a useful simulation tool to obtain improved effectiveness of film cooling rows in a relatively short turn around time.
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Bassi, F., S. Rebay, and M. Savini. "Quasi-3D Numerical Computations on a Film-Cooled Gas Turbine Nozzle." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-536.

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The aim of this work is to assess the accuracy of a “quasi-3d” Navier-Stokes solver equipped with the k-ω turbulence model in the computation of a film-cooled gas turbine blade under a variety of flow conditions. The “quasi-3d” formulation was chosen as a cheap approach to investigate a large number of test conditions for a nozzle of complex geometry (around 400 cooling holes) which would require a large computational effort for a truly 3d simulation. The developed code has been used to investigate the influence of various cooling geometries and blowing conditions (mass flow rate and/or density ratios) on the aerodynamic behaviour of the cascade (in terms of loading, losses and flow angles) and their impact on the mixing process downstream of the trailing edge. The investigated nozzle is an advanced design turbine vane working in high subsonic regime. It is characterized by a marked endwall contouring at the casing and by the presence of 12 rows of holes (including a trailing edge row of slots) so as to obtain full-coverage film-cooling of the solid surfaces. This vane has been extensively tested in the Politecnico di Milano Fluid Dynamics Laboratory (formerly C.N.P.M.) blowdown transonic wind tunnel and a great amount of data are therefore available for validation purposes. The uselfulness of the proposed approach is fully analyzed and discussed throughout the paper and it is shown that the relation between the cascade performance and the variation of the investigated parameters is correctly described. In addition we address and discuss which ejection boundary conditions and which loss definitions are best suited for a meaningful comparison with the experimental measurements. In conclusion, in the case considered the developed code seems to be a valuable tool to determine the impact of film-cooling on the aerodynamic performance of a gas turbine blade.
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Wang, Ten-See, and Michael Guidos. "Transient Three-Dimensional Side Load Analysis of a Film Cooled Nozzle." In 38th Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4297.

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Beard, Robert, D. Landrum, Robert Beard, and D. Landrum. "Numerical simulation of a film-cooled LOX/RP-1 rocket nozzle." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3227.

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Wang, Ten-See, Jeff Lin, and Michael Guidos. "Transient Side Load Analysis of Out-of-Round Film-Cooled Nozzle Extensions." In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-3968.

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Knab, O., C. Weiland, O. Knab, and C. Weiland. "Effect of detailed physical-chemical modeling on film-cooled nozzle flow calculations." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2910.

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Ragab, Kasem E., and Lamyaa El-Gabry. "Heat Transfer Analysis of the Surface of Nonfilm-Cooled and Film-Cooled Nozzle Guide Vanes in Transonic Annular Cascade." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64982.

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One of the approaches adopted to improve turbine efficiency and increase power to weight ratio is reducing vane count. In the current study, numerical analysis was performed for the heat transfer over the surface of nozzle guide vanes under the condition of reduced vane count using three dimensional computational fluid dynamics (CFD) models. The investigation has taken place in two stages: the baseline nonfilm-cooled nozzle guide vane, and the film-cooled nozzle guide vane. A finite volume based commercial code (ANSYS CFX 15) was used to build and analyze the CFD models. The investigated annular cascade has no heat transfer measurements available; hence in order to validate the CFD models against experimental data, two standalone studies were carried out on the NASA C3X vanes, one on the nonfilm-cooled C3X vane and the other on the film-cooled C3X vane. Different modelling parameters were investigated including turbulence models in order to obtain good agreement with the C3X experimental data, the same parameters were used afterwards to model the industrial nozzle guide vanes. Three Shear Stress Transport (SST) turbulence model variations were evaluated, the SST with Gamma-Theta transition model was found to yield the best agreement with the experimental results; model capabilities were demonstrated when the laminar to turbulent transition took place.
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Dahlander, Petter, Hans Abrahamsson, Hans Mårtensson, and Ulf Håll. "Numerical Simulation of a Film Cooled Nozzle Guide Vane Using an Injection Model." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-439.

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Numerical simulations of film cooled nozzle guide vanes (NGV) are difficult since resolving the local flow near each cooling hole requires a very fine computational mesh. In this paper an injection model is used to include the coolant in the main flow by adding the influence of the coolant jets to the source terms in the governing equations. The present method enables simulations of film cooled turbine stages using rather coarse meshes (i.e. not resolving the cooling holes) and gives the possibility to study, for example, the influence of the secondary flows on the coolant distribution. The disadvantage is that some parameters describing the injection need to be determined. The development and validation of the injection model is performed using fully resolved 3D simulations and experimental data from single cooling jets. The present injection model is used to simulate the film cooled NGV of the research turbine stage MT1 at DERA, Pyestock, UK. Predictions of the heat transfer using the injection model show promising results.
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Alqefl, Mahmood H., Kedar P. Nawathe, Pingting Chen, Rui Zhu, Yong W. Kim, and Terrence W. Simon. "Aero-Thermal Aspects of Film Cooled Nozzle Guide Vane Endwalls: Part 1 — Aerodynamics." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15926.

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Abstract:
Abstract The first stage turbine of a modern gas turbine is subjected to high thermal loads which lead to a need for aggressive cooling schemes to protect its components from melting. Endwalls are particularly challenging to cool due to the complex system of secondary flows near them that wash the protective film coolants into the mainstream. This paper shows that without including combustor cooling, the complex secondary flow physics are not representative of modern engines. Aggressive injection of all cooling flows upstream of the passage is expected to interact and change passage aerodynamics and, subsequently, mixing and transport of coolants. This study describes, experimentally, the aero-thermal interaction of cooling flows near the endwall of a first stage nozzle guide vane passage. The test section involves an engine-representative combustor-turbine interface geometry, combustor coolant flow and endwall film cooling flow injected upstream of a linear cascade. The approach flow conditions represent flow exiting a cooled, low-NOx combustor. This first part of this two-part study aims to understand the complex aerodynamics near the endwall through detailed measurements of passage three-dimensional velocity fields with and without endwall film cooling. The aerodynamic measurements reveal a dominant vortex in the passage, named here as the Impingement Vortex, that opposes the passage vortex formed at the airfoil leading edge plane. This Impingement Vortex completely changes our description of flow over a modern film cooled endwall.
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