An Experimental Determination of Losses in a 3-Port Wave Rotor 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 An Experimental Determination of Losses in a 3-Port Wave Rotor PDF full book. Access full book title An Experimental Determination of Losses in a 3-Port Wave Rotor by Jack Wilson. Download full books in PDF and EPUB format.
Author: Jack Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Get Book Here
Book Description
Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Author: Jack Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Get Book Here
Book Description
Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Author: Jack Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Get Book Here
Book Description
The U.S. Army Research Laboratory, NASA Glenn Research Center, and Rolls-Royce Allison are working collaboratively to demonstrate the benefits and viability of a wave-rotor-topped gas turbine engine. The self-cooled wave rotor is predicted to increase the engine overall pressure ratio and peak temperature by 300% and 25 to 30%, respectively, providing substantial improvements in engine efficiency and specific power. Such performance improvements would significantly reduce engine emissions and the fuel logistics trails of armed forces. Progress towards a planned demonstration of a wave-rotor-topped Rolls-Royce Allison model 250 engine has included completion of the preliminary design and layout of the engine, the aerodynamic design of the wave rotor component and prediction of its aerodynamic performance characteristics in on- and off-design operation and during transients, and the aerodynamic design of transition ducts between the wave rotor and the high pressure turbine. The topping cycle increases the burner entry temperature and poses a design challenge to be met in the development of the demonstrator engine.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 596
Get Book Here
Book Description
Author: Daniel E. Paxson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 16
Get Book Here
Book Description
Author: Jack Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 246
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 598
Get Book Here
Book Description
