Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2: ; Simulation Results PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2: ; Simulation Results PDF full book. Access full book title Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2: ; Simulation Results by National Aeronautics and Space Adm Nasa. Download full books in PDF and EPUB format.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724093950
Category : Science
Languages : en
Pages : 28
Get Book Here
Book Description
A combined experimental and numerical study to investigate the heat transfer distribution in a complex blade trailing edge passage was conducted. The geometry consists of a two pass serpentine passage with taper toward the trailing edge, as well as from hub to tip. The upflow channel has an average aspect ratio of roughly 14:1, while the exit passage aspect ratio is about 5:1. The upflow channel is split in an interrupted way and is smooth on the trailing edge side of the split and turbulated on the other side. A turning vane is placed near the tip of the upflow channel. Reynolds numbers in the range of 31,000 to 61,000, based on inlet conditions, were simulated numerically. The simulation was performed using the Glenn-HT code, a full three-dimensional Navier-Stokes solver using the Wilcox k-omega turbulence model. A structured multi-block grid is used with approximately 4.5 million cells and average y+ values on the order of unity. Pressure and heat transfer distributions are presented with comparison to the experimental data. While there are some regions with discrepancies, in general the agreement is very good for both pressure and heat transfer. Rigby, David L. and Bunker, Ronald S. Glenn Research Center NASA/CR-2002-211701, NAS 1.26:211701, ASME-2002-GT-30213, E-13430
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724093950
Category : Science
Languages : en
Pages : 28
Get Book Here
Book Description
A combined experimental and numerical study to investigate the heat transfer distribution in a complex blade trailing edge passage was conducted. The geometry consists of a two pass serpentine passage with taper toward the trailing edge, as well as from hub to tip. The upflow channel has an average aspect ratio of roughly 14:1, while the exit passage aspect ratio is about 5:1. The upflow channel is split in an interrupted way and is smooth on the trailing edge side of the split and turbulated on the other side. A turning vane is placed near the tip of the upflow channel. Reynolds numbers in the range of 31,000 to 61,000, based on inlet conditions, were simulated numerically. The simulation was performed using the Glenn-HT code, a full three-dimensional Navier-Stokes solver using the Wilcox k-omega turbulence model. A structured multi-block grid is used with approximately 4.5 million cells and average y+ values on the order of unity. Pressure and heat transfer distributions are presented with comparison to the experimental data. While there are some regions with discrepancies, in general the agreement is very good for both pressure and heat transfer. Rigby, David L. and Bunker, Ronald S. Glenn Research Center NASA/CR-2002-211701, NAS 1.26:211701, ASME-2002-GT-30213, E-13430
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Je-Chin Han
Publisher: Taylor & Francis
ISBN: 1466564903
Category : Science
Languages : en
Pages : 865
Get Book Here
Book Description
A comprehensive reference for engineers and researchers, this second edition focuses on gas turbine heat transfer issues and their associated cooling technologies for aircraft and land-based gas turbines. It provides information on state-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling schemes. The book also offers updated experimental methods for gas turbine heat transfer and cooling research, as well as advanced computational models for gas turbine heat transfer and cooling performance predictions. The authors provide suggestions for future research within this technology and includes 800 illustrations to help clarify concepts and instruction.
Author:
Publisher: DIANE Publishing
ISBN: 1428918205
Category :
Languages : en
Pages : 274
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 726
Get Book Here
Book Description
Annotation This is Volume 1 of five volumes that comprise the proceedings of the June 2002 conference, sponsored by the International Gas Turbine Institute (IGTI), a technical institute of the American Society of Mechanical Engineers. The purpose of the conference was to facilitate international exchange and development of educational and technical information related to the design, application, manufacture, operation, maintenance, and environmental impact of all types of gas engines. With an emphasis upon the need for more efficient, cleaner, and more reliable gas turbines, the approximately 130 articles cover various technical aspects of aircraft engines; coal, biomass, and alternative fuels; combustion and fuels; education; electric power; and vehicular and small turbomachines. There is no subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author:
Publisher:
ISBN:
Category : Legal deposit of books, etc
Languages : en
Pages : 538
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 590
Get Book Here
Book Description
Annotation Volumes 3A and 3B are part of a five-volume set comprising the proceedings of the June 2002 conference held in the Netherlands. Approximately 125 articles address heat transfer, and manufacturing materials and metallurgy. A sampling of topics: the effect of freestream turbulence on film cooling adiabatic effectiveness; the influence of periodic unsteady inflow conditions on leading edge film cooling; and fluid dynamcis of a pre-swirl rotor-stator system. No subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 276
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 958
Get Book Here
Book Description
Author: Bengt Sundén
Publisher: Witpress
ISBN:
Category : Medical
Languages : en
Pages : 544
Get Book Here
Book Description
This title presents and reflects current active research on various heat transfer topics and related phenomena in gas turbine systems. It begins with a general introduction to gas turbine heat transfer, before moving on to specific areas.
