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Author: Jacob Ward Harral Publisher: ISBN: Category : Gas-turbine industry Languages : en Pages : 248
Book Description
Abstract: Increasing the efficiency in gas turbine engines requires constant improvement in the design tools currently available to the industry. One area for potential increases in efficiency deals with the film-cooling effectiveness in the high-pressure turbine section of the engine and the push to increase the temperature at the inlet of the turbine. Modeling of film-cooling effectiveness for incorporation into advanced CFD codes to be used for film effectiveness predictions and subsequent design of advanced engines is currently a major activity within the engine community. For the codes to be implemented as design tools one must gain confidence in their validity. One method that has been used for this purpose is to compare predictions obtained using these codes with experimental results obtained under as realistic conditions as is possible within the confines of controlled laboratory experiments. Under support of the NASA/DoD URETI, the OSU GTL has undertaken the task of performing detailed surface-pressure and surface heat-transfer measurements on the vane surfaces, on the blade surfaces, and on the stationary shroud of a fully cooled high-pressure turbine stage operating at design corrected conditions. Several significant changes have been made to the OSU Gas Turbine Laboratory blowdown turbine facility and to the operating mode of that facility in order to make film effectiveness measurements. One of the major facility changes was the incorporation of a coolant gas supply system (LCF) into the facility. The major changes in operating mode involved operating in blowdown mode instead of shock tube mode. In order to achieve this major change in operating procedure, it was necessary to incorporate a resistance heater into the rig just ahead of the high-pressure turbine vane inlet so that a resistance heater instead of the reflected shock could heat the test gas. The next major task was to sequence the main test gas flow with the coolant gas flow so that one could achieve the proper flow physics. This thesis will focus on the operation and integration of the LCF into the blowdown facility and on the experimental results acquired during the initial film-cooling experiment. Operation of the LCF is divided into three distinct areas: fast acting valve operation and sequencing with the main facility fast acting valve, cooling cycles, and facility controls. Successful integration of the LCF has been achieved and will be illustrated by the results of the initial film-cooling experiment. Through these experimental results and accompanying uncertainty analysis conducted as part of this thesis significant knowledge has been gained and will be applied to future film-cooling measurement programs. With the demonstrated successful operation of the OSU turbine test facility in conjunction with the LCF, the OSU GTL is capable of conducting the critical experiments necessary to provide critical verification information for ongoing film effectiveness modeling and CFD code development.
Author: Jacob Ward Harral Publisher: ISBN: Category : Gas-turbine industry Languages : en Pages : 248
Book Description
Abstract: Increasing the efficiency in gas turbine engines requires constant improvement in the design tools currently available to the industry. One area for potential increases in efficiency deals with the film-cooling effectiveness in the high-pressure turbine section of the engine and the push to increase the temperature at the inlet of the turbine. Modeling of film-cooling effectiveness for incorporation into advanced CFD codes to be used for film effectiveness predictions and subsequent design of advanced engines is currently a major activity within the engine community. For the codes to be implemented as design tools one must gain confidence in their validity. One method that has been used for this purpose is to compare predictions obtained using these codes with experimental results obtained under as realistic conditions as is possible within the confines of controlled laboratory experiments. Under support of the NASA/DoD URETI, the OSU GTL has undertaken the task of performing detailed surface-pressure and surface heat-transfer measurements on the vane surfaces, on the blade surfaces, and on the stationary shroud of a fully cooled high-pressure turbine stage operating at design corrected conditions. Several significant changes have been made to the OSU Gas Turbine Laboratory blowdown turbine facility and to the operating mode of that facility in order to make film effectiveness measurements. One of the major facility changes was the incorporation of a coolant gas supply system (LCF) into the facility. The major changes in operating mode involved operating in blowdown mode instead of shock tube mode. In order to achieve this major change in operating procedure, it was necessary to incorporate a resistance heater into the rig just ahead of the high-pressure turbine vane inlet so that a resistance heater instead of the reflected shock could heat the test gas. The next major task was to sequence the main test gas flow with the coolant gas flow so that one could achieve the proper flow physics. This thesis will focus on the operation and integration of the LCF into the blowdown facility and on the experimental results acquired during the initial film-cooling experiment. Operation of the LCF is divided into three distinct areas: fast acting valve operation and sequencing with the main facility fast acting valve, cooling cycles, and facility controls. Successful integration of the LCF has been achieved and will be illustrated by the results of the initial film-cooling experiment. Through these experimental results and accompanying uncertainty analysis conducted as part of this thesis significant knowledge has been gained and will be applied to future film-cooling measurement programs. With the demonstrated successful operation of the OSU turbine test facility in conjunction with the LCF, the OSU GTL is capable of conducting the critical experiments necessary to provide critical verification information for ongoing film effectiveness modeling and CFD code development.
Author: Luis Tord Gomis Publisher: ISBN: Category : Languages : en Pages :
Book Description
Film cooling is widely used to protect gas turbine blades and vanes from the extremelly hot gases leaving the combustion chamber. Over the past decades, film cooling on blades, vanes and end-wall has been widely studied. In order to understand and define the process several measurement techniques have been developed. Given that numerical simulations are yet not accurate enough, as they are not able to take into account all the parameters that affect such process, the interest in experimental measurements has grown. Several measurement techniques have been used in order to calculate the film cooling effectiveness and being able to understand how the different variables affect to the overall efficiency of the process. Trying to determine film cooling efectiveness, Pressure Sensitive Paints (PSP) have been recently adapted and used. PSP have been developed since 1980s for different fluid mechanics and aerodynamic testing expermients. Since 1990s the technique is mature enough to be used and achieve high quality results in industrial wind tunnels. PSP is an absolute transducer able to convert units of surface pressure into units of light. PSP systems are able to give high precision measurements with full-surface coberture and high resolution. As PSP is a non-intrusive measurement technique, once it is designed it can be relatively easy adapted to new systems. This Master Thesis focuses on PSP technique, and aims to give a global explanation of the technique as well as a clear and precise definition of each part of the process. The main goal for this project is to design, build and test a PSP system. In order to test the PSP system, a test setup has been design, consisting in a flat test plate with cooling holes. The design of the process has been thought to be tested in the small Wind tunnel owned by the department Gasturbinen, Luft- und Raumfahrtantriebe (GLR) in the Technische Universität am Darmstadt (TUD). Although the long term objective is to adapt such system to other facilites owned by the same department such as the High Reynold Number Turbine (HiReNT) or the Large Scale Turbine Rig (LSTR).
Author: D. Granser Publisher: ISBN: Category : Cooling Languages : en Pages : 0
Book Description
After compressor discharge air has initially been used to cool the heat shields of the hot gas inlet casing, it can subsequently be employed for film cooling of the first-stage vane shrouds. Since the flow field near these shrouds is three-dimensional, the film cooling effectiveness cannot be predicted correctly by common two-dimensional codes. The secondary flow transports the film from the pressure side to the suction side where it can even climb up the airfoil to cool its trailing section. Such film cooling effectiveness was first investigated experimentally in a linear vane cascade at atmospheric pressure. The temperatures and static pressure levels at the adiabatic shrouds, as well as the temperature measurements within the vane cascade, are reported for different cooling film blowing rates. In addition, the secondary flow was analysed numerically using a partially-parabolic computer code for 3D viscous flows. It involves mutual interaction of the boundary layer with the mainstream. The secondary flow can also be modelled with this algorithm, which requires less numerical effort than solving the fully 3D elliptic flow equations. The numerical results of the experiment and numerical predictions are compared. In addition, the application of these results to a high-temperature gas turbine is presented.
Author: Aragona Patty Publisher: CRC Press ISBN: 1351851950 Category : Science Languages : en Pages : 473
Book Description
The 2016 International Conference on Materials Science, Energy Technology and Environmental Engineering (MSETEE 2016) took place May 28-29, 2016 in Zhuhai City, China. MSETEE 2016 brought together academics and industrial experts in the field of materials science, energy technology and environmental engineering. The primary goal of the conference was to promote research and developmental activities in these research areas and to promote scientific information interchange between researchers, developers, engineers, students, and practitioners working around the world. The conference will be held every year serving as platform for researchers to share views and experience in materials science, energy technology and environmental engineering and related areas.
Author: Thomas Earl Dyson Publisher: ISBN: Category : Languages : en Pages : 576
Book Description
This study focused on the improvement of film cooling for gas turbine vanes using both computational and experimental techniques. The experimental component used a matched Biot number model to measure scaled surface temperature (overall effectiveness) distributions representative of engine conditions for two new configurations. One configuration consisted of a single row of holes on the pressure surface while the other used numerous film cooling holes over the entire vane including a showerhead. Both configurations used internal impingement cooling representative of a 1st vane. Adiabatic effectiveness was also measured. No previous studies had shown the effect of injection on the mean and fluctuating velocity profiles for the suction surface, so measurements were made at two locations immediately upstream of film cooling holes from the fully cooled cooling configuration. Different blowing conditions were evaluated. Computational tools are increasingly important in the design of advanced gas turbine engines and validation of these tools is required prior to integration into the design process. Two film cooling configurations were simulated and compared to past experimental work. Data from matched Biot number experiments was used to validate the overall effectiveness from conjugate simulations in addition to adiabatic effectiveness. A simulation of a single row of cooling holes on the suction side also gave additional insight into the interaction of film cooling jets with the thermal boundary layer. A showerhead configuration was also simulated. The final portion of this study sought to evaluate the performance of six RANS models (standard, realizable, and renormalization group k-[epsilon]; standard k-[omega]; k-[omega] SST; and Transition SST) with respect to the prediction of thermal boundary layers. The turbulent Prandtl number was varied to test a simple method for improvement of the thermal boundary layer predictions.
Author: Isabella Gayoso Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
In this experiment, measurements of the overall cooling effectiveness for a film cooled turbine vane airfoil in a high-speed cascade were obtained using infrared thermography. The vane used was the NASA C3X with impingement holes (showerhead cooling) and convective cooling holes on both the suction and pressure side. This work was done in the Mechanical Engineering Department's Experimental and Computational Convection Lab and used the high-speed cascade capability of the lab. The rationale for conducting this work was to obtain experimental data on film cooling effectiveness in a turbine vane in engine-like conditions at transonic speeds. Previous work has been done at subsonic speeds, but few pieces of literature examine this parameter at transonic speeds. The data can then be used to validate or compare to CFD models and to better understand what happens to the vane temperature distribution during engine operation. This understanding could inform the design of film cooling holes to reduce thermal strain "hot spots" which lead to failure of the vane. The results showed that trends for values of overall film effectiveness were as expected in this experiment, such as increases in blowing ratio correlating to increases in overall film effectiveness. However, the blowing ratios used in this study were not as high as values studied previously, indicating a need for more data on overall film effectiveness at transonic speeds.
Author: Jacob Ward Harral
Author: Jacob Ward Harral
Author: Luis Tord Gomis
Author: D. Granser
Author: Aragona Patty
Author: Thomas Earl Dyson
Author: 
Author: Isabella Gayoso
Author: Marcus Damian Polanka
Author: Douglas Neal Barlow
Author: S. Stephen Papell