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Showing 1 to 19 of 19 for “"Nozzle Guide Vane"”.
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Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade
… have effects on turbines performance through the nozzle guide vane passages. The current experimental aerodynamic investigation over the nozzle guide vane passage was concentrated on the backward-facing step of upstream misalignments. The tests were performed using two types of vane endwall …
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Effect of Endwall Fluid Injection on Passage Vortex formation in a First Stage Nozzle Guide Vane Passage
… stresses especially along the first stage nozzle guide vane cascade as the hot combustion products exiting modern day gas turbine combustors generally reach temperatures that could endanger the structural stability of these vanes and greatly reduce the vane life. The highest heat transfer …
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Endwall Heat Transfer and Shear Stress for a Nozzle Guide Vane with Fillets and a Leakage Interface
… The challenge of adequately cooling the nozzle guide vane directly downstream of the combustor is compounded by a complex vortical secondary flow at the junction of the endwall and the airfoil. This flow tends to increase local heat transfer rates and sweep coolant away from component …
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A Detailed Study of Fan-Shaped Film-Cooling for a Nozzle Guide Vane for an Industrial Gas Turbine
… holes on two critical turbine surfaces; the vane and endwall. This research was the first to offer a complete characterization of film-cooling on a turbine vane surface, both in single and multiple row configurations. Infrared thermography was used to measure adiabatic wall temperatures, and …
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An investigation of the effects of nozzle guide vane trailing edge cooling on rotor heat transfer in a transonic turbine stage
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1992.
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The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions
… of misalignment between the combustor exit and nozzle guide vane endwall on the heat transfer distribution across an axisymmetric converging endwall. The axisymmetric converging endwall investigated was representative of that found on the shroud side of a first stage turbine nozzle section. The …
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The Effect of Density Ratio on Steep Injection Angle Purge Jet Cooling for a Converging Nozzle Guide Vane Endwall at Transonic Conditions
… at varying blowing rates for a typical nozzle guide vane platform purge jet cooling scheme. An axisymmetric converging endwall with an upstream doublet staggered cylindrical hole purge jet cooling scheme was employed. Nominal exit flow conditions were engine representative and as …
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Heat Transfer and Film Cooling Performance on a Transonic Converging Nozzle Guide Vane Endwall With Purge Jet Cooling and Dual Cavity Slashface Leakage
… rate on the thermal performance for a 1st stage nozzle guide vane axisymmetric converging endwall. An upstream doublet staggered cylindrical hole jet cooling scheme provides additional purged coolant with consistent conditions throughout the investigation. The effects are measured in engine …
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Turbine tip clearance loss mechanisms
… geometry, and unsteadiness due to an upstream nozzle guide vane. Tip leakage loss changes due to three-dimensional blade stacking (bowing or reverse bowing) are verified to be associated with changes in the magnitude of blade tip loading, which create differences in the leakage flow exit …
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Parametric Investigation of the Combustor-Turbine Interface Leakage Geometry
… in the stagnating flow approaching the inlet nozzle guide vane as well as a strong cross-passage gradient within the passage. These flow structures enhance heat transfer and convect hot core flow gases onto component surfaces. In modern engines it has become critical to cool component surfaces …
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Aerodynamic performance measurements of a fully scaled, film-coated, turbine stage
… a film-cooled configuration. A solid blade and nozzle guide vane set was machined via electro-discharge machining, laser drilling, and laser welding to provide film-cooling holes and manifold channels. The effective area (CdA) of the film-cooling holes was measured and part-to-part variations …
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Predictions and Measurements of Film-Cooling on the Endwall of a First Stage Vane
… such surface is the endwall of the first stage nozzle guide vane. This thesis details the design, prediction, and testing of two endwall film-cooling hole patterns provided by leading gas turbine engine companies. In addition a flush, two-dimensional slot was included to simulate leakage flow …
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Fan-Shaped Hole Film Cooling on Turbine Blade and Vane in a Transonic Cascade with High Freestream Turbulence: Experimental and CFD Studies
… the fan-shaped hole injected turbine blade and vane. The study was operated with high freestream turbulence intensity (12% at the inlet) and large turbulence length scales (0.26 for blade, 0.28 for vane, normalized by the cascade pitch of 58.4mm and 83.3mm respectively). Both convective heat …
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Performance of a Showerhead and Shaped Hole Film Cooled Vane at High Freestream Turbulence and Transonic Conditions
… effectiveness on a film cooled first stage nozzle guide vane using a transient thin film gauge (TFG) technique. The information presented attempts to further characterize the performance of shaped hole film cooling by taking measurements on a row of shaped holes downstream of leading edge …
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Cooling hole geometry and turbulence effects on the early suction side surface of a turbine vane
… cascade of the Mitsubishi F-701 first stage nozzle guide vane. The latter is a flat plate arrangement matching the Reynolds number achieved by the LE-Sim on the early suction side. In this thesis, six cooling designs are tested on the LE-Sim and the impact of the turbulence is analysed on …
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The effect of sintering and CMAS on the stability of plasma-sprayed zirconia thermal barrier coatings
… a borescope. Deposition mainly occurred on the nozzle guide vane and blade platform. A numerical model was used to predict particle acceleration and heating in flight. It was observed that larger particles are more likely to adhere because they have greater inertia, and thus are more likely to …
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Modelling Gas Turbine Degradation
… when the same techniques where applied to an nozzle guide vane (NGV) cascade. A simplified model for oxidation and hot corrosion of elemental nickel is suggested. This model was used to drive a geometry morphing technique, based on a level-set geometry representation, of an NGV cascade. The …
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The Effects of Upstream Boundary Layers on the NGV Endwall Cooling
… inlet temperature raises challenges for the nozzle guide vane cooling. Two typical endwall cooling schemes, jump cooling and louver cooling, result in different interactions between the injected coolant and the mainstream, leading to different cooling effects. This study investigates these …
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Heat Transfer Performance Improvement Technologies for Hot Gas Path Components in Gas Turbines
… One of the commonly used methods for cooling the vanes involves passing coolant air bled from the compressor through serpentine passages inside the airfoils. The walls of the internal cooling passages are usually roughened with turbulence promoters like ribs to enhance heat transfer. Though the …