An Experimental Investigation Of A Two Liquid Cooling System For Gas Turbine Blades
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An Experimental Investigation Of A Two Liquid Cooling System For Gas Turbine Blades
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Author : John H. Jones
language : en
Publisher:
Release Date : 1956
An Experimental Investigation Of A Two Liquid Cooling System For Gas Turbine Blades written by John H. Jones and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Gas-turbines categories.
Computational And Experimental Investigation Of Vortex Cooling Of A Gas Turbine Blade Using 3 D Stereo Particle Image Velocimetry And Liquid Crystals
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Author : Daisy Galeana
language : en
Publisher:
Release Date : 2022
Computational And Experimental Investigation Of Vortex Cooling Of A Gas Turbine Blade Using 3 D Stereo Particle Image Velocimetry And Liquid Crystals written by Daisy Galeana and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2022 with categories.
The limiting factor for most gas turbines has been the turbine inlet temperature. Furthermore, higher pressure ratios and turbine inlet temperatures improve the efficiencies on the gas turbine. A big focus has been on new schemes of internal cooling designs of turbine blades, using pressurized air from the engine compressor, and break-through in blade metallurgy, in order to achieve higher turbine inlet temperatures. Significant research has been ongoing for decades to design an internal cooling system for the first stage of the turbine blade consequently higher turbine inlet temperatures can be achieved. The challenging engineering intricacies related to improving the efficiency of a gas turbine engine come with the need to maximize the efficiency of the internal cooling of the turbine blade to withstand the high turbine inlet temperature. Understanding the fluid mechanics and heat transfer of internal blade cooling is therefore of paramount importance. This dissertation presents the impact of swirl flow cooling on the heat transfer of a gas turbine blade cooling passage to understand the mechanics of internal blade cooling. The focus is the continuous cooling flow that must be maintained via nonstop injection of tangential flow, whereby swirl flow is generated. The experimental investigation is presented first with three-dimensional (3-D) Stereo-Particle Image Velocimetry (Stereo-PIV) and second Thermochromic Liquid Crystal (TLC) of a swirl flow that models a gas turbine blade internal cooling configuration. The study is intended to provide an evaluation of the developments of swirl flow cooling methodology utilizing 3-D Stereo-PIV and liquid crystals. The objective of the experimental models is to determine the critical swirl number that has the potential to deliver the maximum axial velocity results with the highest heat transfer at three different Reynolds numbers, 7,000, 14,000, and 21,000. The swirl flow cooling methodology comprises of cooling air channeling through the blade's internal passages lowering the metal temperature, therefore the experimental cylindrical chamber is made of acrylic allowing detailed measurements and includes seven discrete tangential air inlets designed to create the swirl flow. Additionally, a 3D domain fluent setup employing a steady-state pressure-based solver with a standard k-epsilon turbulence model was applied. The energy equations were activated to handle the temperature effect; the gravitational acceleration is accounted for. Important variations of the swirl number are present near the air inlets and decrease with downstream distance as predicted since the second half of the chamber has no more inlets. The axial velocity reaches the maximum downstream in the second half of the chamber. The circumferential velocity decreases downstream distance and reaches the highest towards the center of the chamber. As part of the results relatively low heat transfer rates were observed near the upstream end of the cylindrical chamber, resulting from a low momentum swirl flow as well as crossflow effects. The TLC heat transfer results exemplify how the Nusselt Number (Nu) measured favorably at the midstream of the chamber and values decline downstream. Furthermore, experimental results when compared to the Computational Fluid Dynamics analysis are compatible with each other.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Herman H. Ellerbrock (Jr.)
language : en
Publisher:
Release Date : 1951
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Herman H. Ellerbrock (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aeronautics categories.
An Experimental Investigation Of Turbine Blade Heat Transfer And Turbine Blade Trailing Edge Cooling
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Author : Jungho Choi
language : en
Publisher:
Release Date : 2005
An Experimental Investigation Of Turbine Blade Heat Transfer And Turbine Blade Trailing Edge Cooling written by Jungho Choi and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2005 with categories.
This experimental study contains two points; part 1 - turbine blade heat transfer under low Reynolds number flow conditions, and part 2 - trailing edge cooling and heat transfer. The effect of unsteady wake and free stream turbulence on heat transfer and pressure coefficients of a turbine blade was investigated in low Reynolds number flows. The experiments were performed on a five blade linear cascade in a low speed wind tunnel. A spoked wheel type wake generator and two different turbulence grids were employed to generate different levels of the Strouhal number and turbulence intensity, respectively. The cascade inlet Reynolds number based on blade chord length was varied from 15,700 to 105,000, and the Strouhal number was varied from 0 to 2.96 by changing the rotating wake passing frequency (rod speed) and cascade inlet velocity. A thin foil thermocouple instrumented blade was used to determine the surface heat transfer coefficient. A Liquid crystal technique based on hue value detection was used to measure the heat transfer coefficient on a trailing edge film cooling model and internal model of a gas turbine blade. It was also used to determine the film effectiveness on the trailing edge. For the internal model, Reynolds numbers based on the hydraulic diameter of the exit slot and exit velocity were 5,000, 10,000, 20,000, and 30,000 and corresponding coolant-to-mainstream velocity ratios were 0.3, 0.6, 1.2, and 1.8 for the external models, respectively. The experiments were performed at two different designs and each design has several different models such as staggered / inline exit, straight / tapered entrance, and smooth / rib entrance. The compressed air was used in coolant air. A circular turbulence grid was employed to upstream in the wind tunnel and square ribs were employed in the inlet chamber to generate turbulence intensity externally and internally, respectively.
Index Of Naca Technical Publications
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1959
Index Of Naca Technical Publications written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aeronautics categories.
Analytical And Experimental Investigation Of A Forced Convection Air Cooled Internal Strut Supported Turbine Blade
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Author : Eugene F. Schum
language : en
Publisher:
Release Date : 1954
Analytical And Experimental Investigation Of A Forced Convection Air Cooled Internal Strut Supported Turbine Blade written by Eugene F. Schum and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Air-cooled engines categories.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Robert O. Hickel
language : en
Publisher:
Release Date : 1950
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Robert O. Hickel and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with categories.
Experimental Investigation Of External Water Spray Cooling In A Turbojet Engine Utilizing Several Injection Configurations Including Orifices In The Rotor Blade Bases
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Author : Roy A. McKinnon
language : en
Publisher:
Release Date : 1955
Experimental Investigation Of External Water Spray Cooling In A Turbojet Engine Utilizing Several Injection Configurations Including Orifices In The Rotor Blade Bases written by Roy A. McKinnon and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Airplanes categories.
Circular Of The Bureau Of Standards
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Author :
language : en
Publisher:
Release Date : 1954
Circular Of The Bureau Of Standards written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Weights and measures categories.
Experimental Investigation Of The Cooling Characteristics Of Transpiration Air Cooled Turbine Blades In A High Temperature Gas Cascade
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Author : Ronald Lang
language : en
Publisher:
Release Date : 1958
Experimental Investigation Of The Cooling Characteristics Of Transpiration Air Cooled Turbine Blades In A High Temperature Gas Cascade written by Ronald Lang and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with categories.
An experimental investigation was conducted on a transpiration air cooled stator cascade to evaluate the heat transfer characteristics, to observe the temperature patterns, and to verify the existing transpiration cooling theory for hot gas streams ranging in temperature from 1600 to 2050 F.A total of 49 hours and 55 minutes of cascade testing were logged. Hot gas Reynolds numbers computed at ten span-wise positions on the blade varied between 7800 on the pressure side near the leading edge and 288,000 at the convex side just upstream of the trailing edge. Hot gas weight flows of 2.46 lb/sec and 1.64 lb/sec were directed at the cascade section. A comprehensive analysis of the data accumulated along with detailed descriptions of the test facility, the component test hardware, and the problems associated with instrumentation is presented.