4 edition of Heat transfer on a film-cooled rotating blade found in the catalog.
Heat transfer on a film-cooled rotating blade
Published
1999
by National Aeronautics and Space Administration, Glenn Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va
.
Written in
Edition Notes
| Other titles | Heat transfer on a film cooled rotating blade. |
| Statement | Vijay K. Garg. |
| Series | [NASA contractor report] -- NASA/CR-1999-209301., NASA contractor report -- NASA CR-209301. |
| Contributions | NASA Glenn Research Center. |
| The Physical Object | |
|---|---|
| Format | Microform |
| Pagination | 1 v. |
| ID Numbers | |
| Open Library | OL17592138M |
| OCLC/WorldCa | 43248912 |
Heat transfer in gas turbine systems. --Numerical investigation of film cooling flow induced by cylindrical and shaped holes --Numerical investigation of heat transfer on film-cooled turbine blades --Comparison between two models of cooling Analyses of heat transfer in stationary and rotating ribbed blade cooling passages using. "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, 6 .
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. I. 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 .
An Experimental Study on the Aerodynamics and the Heat Transfer of a Suction Side Film Cooled Large Scale Turbine Cascade. Wolfgang Ganzert, Leonhard Fottner. Heat Transfer on a Film-Cooled Rotating Blade. Vijay K. Garg. GT ; VT01A doi: https: Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade. This article provides an overview of gas turbine blade tip external cooling technologies. It is not the intention to comprehensively review all the publications from past to present. Instead, selected reports, which represent the most recent progress in tip cooling technology in open publications, are reviewed. The cooling performance on flat tip and squealer tip blades from reports are Cited by: 1.
Longman Reading World
world too near
Evaluation fundamentals
Labor availability
Preparing for emergencies and disasters
Something important
The declassified documents reference system 2002
Introduction to development economics
The Lake Superior Agate, One Mans Journey
CONNECTICUT
Congressional Directory.
Catalogue of the sixty-sixth annual exhibition [held] November 19th to December 19th, 1959 [at] the Royal Institute Galleries.
Nursing educations accreditation program
information history of the elevator from the Pyramids to the present
The legend of Dagad Trikon
A multi-block, three-dimensional Navier–Stokes code has been used to compute heat transfer coefficient on the blade, hub and shroud for a rotating high-pressure turbine blade with film-cooling holes in eight by: HEAT TRANSFER ON A FILM-COOLED ROTATING BLADE Vijay K.
Garg AYT Corporation ABSTRACT A multi-block, three-dimensional Navier-Stokes code has been used to compute heat transfer coefficient on the blade, hub and shroud for a rotating high-pressure turbine blade with film-cooling holes in eight rows.
Film cooling effectiveness is also computed. Get this from a library. Heat transfer on a film-cooled rotating blade. [Vijay K Garg; NASA Glenn Research Center.]. A multi-block, three-dimensional Navier-Stokes code has been used to compute heat transfer coefficient on the blade, hub and shroud for a rotating high-pressure turbine blade with film-cooling holes in eight rows.
Film cooling effectiveness is also computed on the adiabatic blade. Wilcox’s k-ω model is used for modeling the by: 4. 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.
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 reduce the heat transfer rates directly from the hot clearance flow to Cited by: A three-dimensional Navier–Stokes code has been used to compare the heat transfer coefficient on a film-cooled, rotating turbine blade.
The blade chosen is the ACE rotor with five rows containing 93 film cooling holes covering the entire span. This is the only filmcooled rotating blade over which experimental data is available for comparison.
The above survey indicates that the interaction between the film coolant flow and the mainstream over an actual blade surface is not well understood even though it is known to have a large influence on the heat transfer characteristics of film-cooled blades (Garg and Gaugler, b).
We need to model this interaction in order to incorporate Cited by: used to study the within-hole and near-hole physics in relation to heat transfer on a film-cooled blade.
The flow domain consists of the coolant flow through the plenum and hole-pipes for the three staggered rows of shower-head holes on the VKI rotor, and the main flow over the blade.
A multi-block grid is generated that is nearly orthogonal to. @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. 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.
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.
The influence of the unsteady wakes and shock waves on the heat transfer to a film cooled rotor blade was studied for five film cooling configurations using a rotating bar apparatus in front of a 2-D cascade. Heat transfer measurements were made using thin film gauges placed at the mid-span of the test blade.
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 for Gas Turbines & Power 4, Oct., –Cited by: 1.
leading edge film-cooling effects on turbine blade heat transfer Vijay K. Garg AYT Corporation, NASA Lewis Research Center, Cleveland, Ohio,USA & Raymond E. Gaugler Turbomachinery Flow Physics Branch, Internal Fluid Mechanics Division, NASA Lewis Research Center, Cleveland, Ohio,USACited by: Computations are performed to simulate the flow and heat transfer characteristics of film-cooled rotating turbine blade models under different operating conditions.
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.
Town, J, Straub, D, Black, J, Thole, K & Shih, TState-of-the-art cooling technology for a turbine rotor blade. in Heat Transfer. Proceedings of the ASME Turbo Expo, vol.
5A, American Society of Mechanical Engineers (ASME), ASME Turbo Expo Turbomachinery Technical Conference and Exposition, GTCharlotte, United States, 6 Author: Jason Town, Doug Straub, James Black, Karen Thole, Tom Shih.
heat transfer rates with favorable agreement (Bunker et al. and Ameri et al. y+ y+ yv * ν = η A NUMERICAL ANALYSIS OF HEAT TRANSFER AND EFFECTIVENESS ON FILM COOLED TURBINE BLADE TIP MODELS A.A.
Ameri Senior Research Engineer, AYT Corporation Brook Park, OH, USA D. Rigby* Senior Research Engineer, Dynacs Inc. Brook. > Gas Turbine Heat Transfer and Cooling Technology Second Edition By JeChin Han Sandip Dutta and Srinath Ekkad.
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).Turbine Aero-Heat Transfer Studies in Rotating Research Facilities The most significant parameters to simulate in a rotating aero-heat transfer facility can be listed as Reynolds number based on the blade chord, Mach number for compressibility and shock wave ef-fects, tip speed, intensity and scale of free-stream turbulence, Strouhal.A NUMERICAL ANALYSIS OF HEAT TRANSFER AND EFFECTIVENESS ON FILM COOLED TURBINE BLADE TIP MODELS A.A.
Ameri Senior Research Engineer, AYT Corporation Brook Park, OH, USA D. L. Rigby* Senior Research Engineer, Dynacs Inc. Brook Park, OH, USA =_= ABSTRACT A computational study has been performed to predict the distribution of Cited by:
