Heat transfer on a film-cooled blade effect of hole physics : prepared under contract NAS3-27571

Cover of: Heat transfer on a film-cooled blade |

Published by National Aeronautics and Space Administration, Lewis Research Center, National Technical Information Service, [distributor in [Cleveland, Ohio], Springfield, VA .

Written in English

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  • Film cooling.,
  • Coolants.,
  • Heat transfer.,
  • Heat transfer coefficients.

Edition Notes

Book details

Other titlesHeat transfer on a film cooled blade., Effect of hole physics.
StatementVijay K. Garg, David L. Rigby.
Series[NASA contractor report] -- NASA/CR--1998-206609., NASA contractor report -- NASA CR-206609.
ContributionsRigby, David L., Lewis Research Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15543586M

Download Heat transfer on a film-cooled blade

The formation of kidney vortices can significantly be reduced for shaped holes instead of cylindrical holes. For the determination of the film cooling heat transfer, the design of a turbine blade relies on the conventional determination of the adiabatic film cooling effectiveness and Cited by:   This paper presents results of a study of the conjugate heat transfer (CHT) to calculate the metal temperature for a film-cooled gas turbine blade.

ANSYS CFX code was selected as the computational fluid dynamic (CFD) tool to perform the CHT simulation. The two-equation SST turbulence model with automatic wall treatment was by: 4.

@article{osti_, title = {Impact of rotor-stator interaction on turbine blade film cooling}, author = {Abhari, R.S.}, abstractNote = {The goal of this study is to quantify the impact of rotor-stator interaction on surface heat transfer of film cooled turbine blades.

In Section 1, a steady-state injection model of the film cooling is incorporated into a two-dimensional, thin shear layer. The effect of unsteady wakes with trailing edge coolant ejection on surface heat transfer coefficients and film cooling effectiveness is presented for a downstream film-cooled turbine blade.

The detailed heat transfer coefficient and film effectiveness distributions on the blade surface are obtained using a transient liquid crystal technique.

Get this from a library. Heat transfer on a film-cooled rotating blade. [Vijay K Garg; NASA Glenn Research Center.]. The blade tip region, particularly near the trailing edge, is often very difficult to cool adequately with blade internal coolant flow, and film cooling injection directly onto the blade tip region can be used in an attempt to directly reduce the heat transfer rates from the hot clearance flow to the blade tip.

Get this from a library. Heat transfer on a film-cooled blade: effect of hole physics: prepared under contract NAS [Vijay K Garg; D L Rigby; Lewis Research Center.].

This paper deals with an experimental convective heat transfer investigation around a high pressure gas turbine film cooled rotor blade.

The measurements were performed in the von Karman Institute short duration isentropic light piston compression tube facility allowing a correct simulation of Mach and Reynolds number as well as free stream to. Book. Gas Turbine Heat Transfer and Cooling Technology Authors: J.C. Han, S. Dutta and S.V.

Ekkad. Publishers: Taylor & Francis, New York, A comprehensive compilation of the available cooling techniques used in the Gas Turbine industry has been encapsulated in this book. The heat transfer of a film-cooled turbine blade shall be influenced more by radiation. Its characteristic of conjugate heat transfer is studied experimentally and numerically in the paper by considering radiation heat transfer, multicomposition gas, and thermal barrier coating (TBC).

The Weighted Sum of Gray Gases Spectral Model and the. Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim.

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 Heat transfer on a film-cooled blade book ReferencesTurbine Heat TransferIntroductionTurbine-Stage Heat TransferCascade Vane Heat-Transfer ExperimentsCascade Blade Heat TransferAirfoil Endwall.

blade and the rotor passageway, higher heat transfer occurs over the blade tip due to the tip leakage flow, while there is a noticeably lower value of heat transfer in the rotor passageway.

> Gas Turbine Heat Transfer and Cooling Technology Second Edition By JeChin Han Sandip Dutta and Srinath Ekkad. Camci, C., and Arts, T., a, Experimental Heat Transfer Investigation Around the Film Cooled Leading Edge of a High Pressure Gas Turbine Rotor Blade.

Engrg Cited by: 1. The thermal analysis is based on a simplified conjugate heat transfer analysis of flow in a cooling passage of a turbine blade as shown in Figure 7 and assumes that the airofoil; (a) metal temperature is the average surface temperature at the airofoil midspan, (b) is exposed to the maximum hot gas temperature profile at the blade inlet, and (c Cited by: 1.

StructureoftheBook 22 ReviewArticles andBookChapters onTurbineCooling andHeatTransfer 23 Flat-BladeTip HeatTransfer 98 Squealer-orGrooved-Blade-TipHeatTransfer 99 Film-Cooled,Heat-TransferCoefficient EffectofBlowingRatio File Size: KB.

Future power equipment tends to take hydrogen or middle/low heat-value syngas as fuel for low emission. The heat transfer of a film-cooled turbine blade shall be influenced more by radiation.

Its characteristic of conjugate heat transfer is studied experimentally and numerically in the paper by considering radiation heat transfer, multicomposition gas, and thermal barrier coating (TBC).Author: Jing Ren, Xueying Li, Hongde Jiang. "Heat Transfer Investigation Around the Film-Cooled Leading Edge of a High-Pressure Gas Turbine Rotor Blade by Artificial Neural Networks,"(with Gumusel and Toprak), GT to be presented at the IGTI ASME International Gas Turbine Conference, Vancouver, Canada, June Multdisciplinary design optimization of film-cooled gas turbine blades.

In American Society of Mechanical Engineers, Heat Transfer Division, (Publication) HTD (4 ed., Vol.pp. ) Multdisciplinary design optimization of film-cooled gas turbine by: Conjugate Heat Transfer Analysis for Gas Turbine Film-Cooled Blade Mr.

Bruno Aguilar Honeywell Aerospace The presentation will cover the heat transfer analysis of a film-cooled blade used in the Honeywell FGA turbofan engine that powers the M advanced jet trainer built by Alenia.

The mid-chord region of the blade contains a three-pass serpentine passage with internal discrete V-shaped trip strips to enhance the internal heat transfer coefficient. The film cooling along the mid-chord of the blade uses multiple rows of shaped diffusion : Jason Town, Doug Straub, James Black, Karen Thole, Tom Shih.

Introduction. Thermal analysis of cooled blades requires the solution of equations describing the heat flow through the blade for given the internal and external distributions of the boundary gas temperature and heat transfer gh analytical solutions are nowadays used for detailed blade design, in earlier years engine companies relied on practical methods for determining Cited by: A turbine blade is the individual component which makes up the turbine section of a gas turbine or steam blades are responsible for extracting energy from the high temperature, high pressure gas produced by the turbine blades are often the limiting component of gas turbines.

To survive in this difficult environment, turbine blades often use exotic materials like. Eryilmaz, S. Inanli, B. Gumusel, S. Toprak and Cengiz Camci,"Heat Transfer Investigation Around the Film-Cooled Leading Edge of a High-Pressure Gas Turbine Rotor Blade by Artificial Neural Networks", ASME International Gas Turbine Congress, ASME/IGTIpp.

GT   Heat flux reductions due to film cooling depend on the ratio of film cooled-to-solid blade heat transfer coefficients. Comparisons are made between published experimental data and published correlations for leading edge heat transfer. Stagnation region heat transfer rates of vanes and blades of high pressure turbines can be nearly double those.

They used this code to study the heat transfer of the middle span section of a film-cooled turbine vane with a few blade materials. The results indicated that the heat transfer in a film-cooled vane was complex and the simple 1D conduction analysis from the vane surface to the plenum surface was no longer by: 3.

AbstractThe effect of conjugate heat transfer is investigated on a first stage nozzle guide vane (NGV) of a high pressure gas turbine which has both impingement and film cooling holes.

The study is carried out computationally by considering a linear cascade domain, having two passages formed between the vanes, with a chord length of mm and spacing of : Arun Kumar Pujari, B. S Prasad, Nekkanti Sitaram. Here, unified multidisciplinary modeling of complex engineering systems is addressed by using the model-based systems engineering (MBSE) methodology.

Following the MBSE principles, this work builds up an integrated hierarchy of geometric, aerodynamics, heat transfer, structure dynamics, and design optimization models, which are used to support Author: Cheng'en Wang.

Detailed heat transfer measurements have been made around a film-cooled transonic gas turbine rotor blade in the Oxford Isentropic Light Piston Tunnel.

Film cooling behaviour for four film cooling configurations has been analysed for a range of blowing rates both without and with simulated nozzle guide vane (NGV) shock wave and wake passing. Conjugate heat transfer analysis of a film cooled high-pressure turbine vane under realistic combustor exit flow conditions.

In Proceedings of the ASME Turbo ExpoVolume 5A: Heat Transfer, Dusseldorf, Germany, June 16–20, pp. V05AT11A (14 pages). doi: /GTCited by: 2. Effect of rotation on leading edge region film cooling of a gas turbine blade with three rows of film cooling holes presented heat transfer coefficients and film effectiveness for a film cooled vane.

The heat transfer coefficient on the pressure surface showed very little effect of Cited by: Turbine Blade Heat Transfer: p. Turbine Blade Internal Cooling: p. Turbine Blade Film Cooling: p. Thermal Barrier Coating and Heat Transfer: p.

Structure of the Book: p. Review Articles and Book Chapters on Turbine Cooling and Heat Transfer: p. New Information from to p. ASME Turbo Expo Conference CDs: p.

Currently, there is a deficit of experimental data for surface heat transfer characteristics and thermal transport processes associated with tip gap flows, and a lack of understanding of performance and behavior of film cooling as applied to blade tip : Michael Sampson, Avery Fairbanks, Jacob Moseley, Phillip M.

Ligrani, Hongzhou Xu, Michael Fox. GT Numerical Prediction of Film Cooling and Heat Transfer With Different Film-Hole Arrangements on the Plane and Squealer Tip of a Gas Turbine Blade Yang, H. The flow simulations of the film-cooled flat plates were conducted using Code Leo, a three-dimensional unsteady Reynolds-averaged Navier-Stokes solver, using the conjugate heat transfer method.

An unstructured meshing approach was selected for the initial calculations due to the difficulty of generating a structured mesh for such a complicated.

Heat transfer to a full-coverage film-cooled surface with 30 ̊slant-hole injection / (Washington: National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, ), by M. Crawford, R. Moffat, W. Kays, Stanford University, and United States National Aeronautics and Space.

Han J.-C. Gas turbine heat transfer and cooling technology / Je-Chin Han, Sandip Dutta, Srinath Ekkad. - 2nd ed. - Boca Raton: CRC Press/Taylor & Francis, TP/HT Aerospace and Aerothermodynamics Heat Transfer • Tuesday, 06 June • hrs.

A0: INTRODUCTION: A1: Alan Epstein, Pratt & Whitney, “Is the Future Electric: Hope, Hype, or Reality?” A2: Ryan M. Chapin, GE Aviation, “Digital Solutions for the 21st Century“ A3: Bruno Aguilar, Honeywell, “Conjugate Heat Transfer Analysis for Gas Turbine Film-Cooled Blade“ A4: Joachim Kurzke, GasTurb, “Engine Families” A5: Boris Glezer, Optimized Turbine Solutions, “Getting.

Topics: Heat transfer, High temperature, Cooling, Heat transfer coefficients, Transients (Dynamics), Coolants, Low temperature, Combustion, Flow (Dynamics), Heating Free.

Efficient thermal design of turbine blade cooling needs to take wall temperature effects on heat transfer into account. This can only be achieved by .An Experimental Study on the Aerodynamics and the Heat Transfer of a Suction Side Film Cooled Large Scale Turbine Cascade. Wolfgang Ganzert, Leonhard Fottner.

Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade. P. W. Giel, G. J. Van Fossen, R.

J. Boyle.

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