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Showing 1 to 18 of 18 for “"Adiabatic effectiveness"”.
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Heat Transfer Coefficient and Adiabatic Effectiveness Measurements for an Internal Turbine Vane Cooling Feature
… pin fin design within the microcircuit. Adiabatic effectiveness levels were found to be optimum for the slot design at a blowing ratio of 0.37. The pin fin arrangement along with the impingement cooling at the microcircuit entrance increased the area-averaged heat transfer by a factor of …
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Adiabatic Effectiveness Measurements of Leakage Flows along the Hub Region of Gas Turbine Engines
… blades were tested in a low speed wind tunnel. Adiabatic effectiveness measurements were made with infrared thermography of the entire hub region for a range of leakage flow conditions. For the computations, a commercially available computational fluid dynamics (CFD) code, FLUENT 6.0, was used …
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Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer
… One way to increase the power output and effectiveness of the engine is to increase the hot gas temperature inside the combustion chamber. The hot gas can reach a temperature that exceeds the physical limitations of parts inside the engine, causing the parts to fail prematurely. One …
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Effects on Heat Transfer Coefficient and Adiabatic Effectiveness in Combined Backside and Film Cooling with Short-Hole Geometry
… of internal counter-flow backside cooling on adiabatic film cooling effectiveness and heat transfer coefficient. In addition, the effects of density ratio (DR), blowing ratio (BR), diagonal length over diameter (L/D) ratio, and Reynolds number were studied using this new configuration. The …
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Multi-Row Film Cooling Boundary Layers
… into a flat plate turbulent boundary layer. Adiabatic effectiveness distributions are measured for several multi-row film cooling geometries. The geometries are designed with two different hole spacings and two different hole types to yield four total geometries. One of the four geometries …
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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
… coefficient, in terms of Nusselt number, and adiabatic effectiveness are provided in the results. Present research work also numerically investigates the shock/film cooling interaction. A detailed analysis on the physics of the shock/film cooling interaction in the blade cascade is provided. …
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Analysis of film cooling performance of tripod hole
… cooling performance was quantified by measuring adiabatic effectiveness and heat transfer coefficient ratio. In order to gauge the performance, other standard hole geometries were also tested and compared with. Following the results from the flat plate test rig, film cooling performance was also …
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Large Eddy Simulation of Leading Edge Film Cooling: Flow Physics, Heat Transfer, and Syngas Ash Deposition
… As a result, the turbulent jet decreases adiabatic effectiveness but does not have a substantial effect on the heat transfer coefficient. At B.R.=0.4, three types of coherent structures are identified which consist of a primary entrainment vortex at the leeward aft-side of the coolant …
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The Influence of Pressure Ratio on Film Cooling Performance of a Turbine Blade
… of both the heat transfer coefficient and the adiabatic effectiveness were made on the suction side of the center blade in a linear transonic cascade. Entrance and exit Mach numbers were 0.3 and 1.2 respectively. Reynolds number based on chord and exit conditions is 3 x 10⁶. The blade contour …
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Internal Heat Transfer and External Effectiveness Measurements for a Novel Turbine Blade Cooling Design
… internal heat transfer coefficients and external adiabatic effectiveness, using thermal liquid crystallography and infrared thermography. This test facility is unique in that it can be used to test the effects of internal cooling features on external film cooling. Results show that the highest …
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Syngas ash deposition for a three row film cooled leading edge turbine vane
… mechanisms increases with blowing ratio. The adiabatic effectiveness in the stagnation region initially increases with blowing ratio but then generally decreases as the blowing ratio increases further. Immediately downstream of off-stagnation injection, the adiabatic effectiveness is highest …
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Design and Benchmarking of a Combustor Simulator Relevant to Gas Turbine Engines
… in the variation of total pressure and velocity. Adiabatic effectiveness levels were significantly reduced for the case with dilution flow in both the near combustor exit region and along the axial length of the straight exit test section.
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Comparison of the Thermal Performance of Several Tip Cooling Designs for a Turbine Blade
… effectively these designs cool the tip through adiabatic effectiveness measurements and convective heat transfer measurements. Tip gap size and blowing ratio are varied for the different tip cooling configurations. Results from these studies show that coolant injection from either the tip …
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Experimental investigation of overall effectiveness and coolant jet interactions on a fully cooled C3X turbine vane
… internal impingement cooling to overall cooling effectiveness. Overall effectiveness was experimentally measured using a thermally scaled, matched Biot number vane model featuring a realistic internal impingement scheme and had normalized surface temperatures that were representative of those …
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Effects of Realistic First-Stage Turbine Endwall Features
… were varied and the variation in endwall cooling effectiveness was evaluated. Results from these studies show that realistic features, such as surface roughness, can reduce the effectiveness of endwall cooling designs while other realistic features, such as varying the combustor-to-turbine gap …
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Effects of Surface Conditions on Endwall Film-Cooling
… camera was used to obtain measurements of adiabatic effectiveness levels and a laser Doppler velocimeter was used for flowfield measurements. This study was done on a large scale, low-speed, recirculating wind tunnel operating at a Reynolds number of 2.1e+5 and an inlet mainstream …
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Experiments and simulation of shaped film cooling holes fed by crossflow with rib turbulators
… 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 …
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Showerhead Film Cooling Performance of a Turbine Vane at High Freestream Turbulence in a Transonic Cascade
… injected reduces the driving temperature (adiabatic wall temperature) of convective heat transfer—reducing heat load to the airfoil, but coolant injection also disturbs boundary layer and augments convective heat transfer coefficient due to local increase in freestream turbulence. Accurate …