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3 edition of Predicted turbine heat transfer for a range of test conditions found in the catalog.

Predicted turbine heat transfer for a range of test conditions

Predicted turbine heat transfer for a range of test conditions

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  • 6 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va .
Written in English

    Subjects:
  • Aerodynamic characteristics.,
  • Heat transfer.,
  • Turbulence models.,
  • Turbine blades.,
  • Wall flow.,
  • Navier-Stokes equation.

  • Edition Notes

    StatementR.J. Boyle and B.L. Lucci.
    SeriesNASA technical memorandum -- 107374.
    ContributionsLucci, B. L., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15497542M

    •A variety of high-intensity heat transfer processes are involved with combustion and chemical reaction in the gasifier unit itself. •The gas goes through various cleanup and pipe-delivery processes to get to our heat transfer processes involved in these stages are generally less intense. the heat transfer characteristics of fluid flowing in a ribbed rectangular duct (simulating an internal cooling passage of the gas turbine blade), and thus to provide validation for the fur-.

    turbulence condition had Tu = %. The test facility was adjusted so that the pressure distribution around the model airfoil matched the pressure distribution predicted by an aerodynamic CFD model. IR thermography and an airfoil model equipped with a constant heat flux surface were used to measure the heat transfer coefficient. Turbine generators operate with complex cooling systems due to the challenge in controlling the peak temperature of the stator bar caused by Ohm loss, which is unavoidable. Therefore, it is important to characterize and quantify the thermal performance of the cooling system. The focus of the present research is to investigate the heat transfer and pressure loss characteristics of a typical.

    Varying heat transfer rate by a few percent relative to some baseline establishes a range of conditions for which turbine performance is to be predicted. Establishing ad-hoc conditions in this manner provides no guarantee that the parametric combination of variables provides a physically possible state for system operation. The blade heat transfer is more two dimensional in ha- entire turbine stages. Boyle and Giel(), and Ameri ture. Blair(), and Boyle and Russell() pre- and Amone() showed comparisons with the exper-sented endwall heat transfer distributions obtained in imental heat transfer .


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Predicted turbine heat transfer for a range of test conditions Download PDF EPUB FB2

Boyle, R. J., and Lucci, B. "Predicted Turbine Heat Transfer for a Range of Test Conditions." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and by: 3.

Additional Physical Format: Online version: Boyle, Robert J. Predicted turbine heat transfer for a range of test conditions (OCoLC) Material Type. Predicted Turbine Heat Transfer for a Range of Test Conditions.

Comparisons are shown between predictions and experimental data for blade and endwall heat transfer. The comparisons of computational domain parisons are given for both vane and rotor geometries over an extensive range of Reynolds and Mach numbers. of an investigation to Author: R. Boyle and B.

Lucci. ple of the predicted metal temperature on a turbine vane based on a conjugate heat transfer model and compared to measured metal temperatures from a test engine [ 2, 10]. : Shailendra Naik. Figure 9(b) shows a typical example of the predicted metal temperature on a turbine vane based on a conjugate heat transfer model and compared to measured metal temperatures from a test engine [2, 10].Cited by: 2.

Predicted turbine vane heat transfer for a rough surface over a wide range of test conditions was compared with experimental data. Inlet pressures varied between and 1 atm., and exit Mach numbers ranged between and Comparisons of the predicted and measured heat transfer are presented for each airfoil at three locations, as well as on the various endwalls and rotor tip.

The measurements were performed using the Ohio State University Gas Turbine Laboratory Test Facility (TTF). The research program utilized an uncooled turbine stage at a range of operating.

Vane endwall heat transfer distributions are documented for a mock aeroderivative combustion system and for a low turbulence condition in a large-scale low speed linear cascade facility. Inlet turbulence levels range from below % for the low turbulence condition to 14% for the mock combustor system.

HT-7 ∂ ∂−() = −= f TT kA L 2 AB TA TB 0. () In equation (), k is a proportionality factor that is a function of the material and the temperature, A is the cross-sectional area and L is the length of the bar. In the limit for any temperature difference ∆T across a length ∆x as both L, T A. Measurements were taken on the vane suction side, and on the pressure side leading edge region.

The designs for both the vane and test facility are discussed. The approach used to account for conduction within the vane is described. Midspan heat transfer distributions are given for the range of test conditions. ASME PTC Steam generating units performance test code.

• ASME PTC Gas turbine heat recovery steam generators performance test code. expensive to measure accurate data over a wide range of conditions. formulas for predicting heat transfer for laminar and turbulent flow conditions.

The results of the heat transfer formulas are. Heat transfer and life through typical turbine blade are predicted and the computational results are fully analyzed. The heat transfer results show that maximum blade temperature at the reference case is ˚C and because of inlet temperature.

The endwall heat transfer measurements, with and without a three-dimensional contoured endwall, were obtained in a newly constructed test section containing seven scaled-up turbine blades. the life prediction of turbine cooled vanes and blades is strongly dependent on the metal temperature.

The problem of metal temperature prediction is essentially equal to obtaining the convective heat transfer boundary conditions on external and internal surfaces of the cooled vane and blade. Combustion and Heat Transfer in Gas Turbine Systems Gas turbine conditions are most nearly simulated by a pressurized passage in which typically contaminated fuel and air are burned in a gas turbine combustor.

Specimens of candidate superalloys are exposed in the gas stream at characteristic turbine pressures, temperatures, and flow. In this article, a new heat transfer model for solar receivers with metal foam is developed for design optimization. The proposed model facilitates analysis of heat transfer processes in terms of forced convection, natural convection, heat conduction and radiation, accurately predicting the energy efficiency and percentage contribution of each form of heat loss.

The measured and predicted results show, that for all cases investigated, the local internal heat transfer coefficient, which is driven by the highly three dimensional passage flows, is highly non.

predictions were shown to be between 1% and 3% higher across a range of conditions. A level of confidence in temperature prediction was demonstrated at compressed cold or hot air to power the turbine.

Heat transfer effects can be of on whether engine or test cell conditions are of interest, local ambient conditions. for the internal and external heat transfer, which are necessary for the conventional design process.

Here, analysis of turbine blade cooling and heat transfer consists of three areas (Patankar, [1]): (a) prediction of the heat transfer coefficients on the external surface of the airfoil (Kays and Crawford, [2]), (b) prediction of heat.

FundamentalsNeed for Turbine Blade CoolingTurbine-Cooling TechnologyTurbine Heat Transfer and Cooling IssuesStructure of the BookReview Articles and Book Chapters on Turbine Cooling and Heat TransferNew Information from to ReferencesTurbine Heat TransferIntroductionTurbine-Stage Heat TransferCascade Vane Heat-Transfer ExperimentsCascade Blade Heat TransferAirfoil Endwall Heat.

ASME PTC Performance Test Code on Overall Plant Performance, Published January 1, Object and Scope Performance Test Code on Gas Turbines ASME Published ASME Measurement of Exhaust Emissions from Stationary Gas Turbine Engines B, Published ASME PTC 36 Measurement of Industrial Sound (ASME B).Experimental results are presented from testing in the Rotating Heat Transfer Rig at the Massachusetts Institute of Technology.

An infrared detector capable of high scan rates was used to fully map the temperature distribution of a single, heated, rotating turbine blade.Gland leakoff system—These systems are used with all turbines in order to minimize outward leakage of steam from HP, LP packing to atmosphere and toward bearing s often include a gland condenser and steam ejector in order.

Negative pressure is obtained in packing drains in order to encourage flow toward gland condenser, as shown in Fig. of a typical system for a.