One Dimensional Calculation Of Flow In A Rotating Passage With Ejection Through A Porous Wall
Download One Dimensional Calculation Of Flow In A Rotating Passage With Ejection Through A Porous Wall full books in PDF, epub, and Kindle. Read online free One Dimensional Calculation Of Flow In A Rotating Passage With Ejection Through A Porous Wall ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author | : Ernst Rudolf Georg Eckert |
Publisher | : |
Total Pages | : 738 |
Release | : 1955 |
Genre | : Cooling |
ISBN | : |
In transpiration cooling of various structural elements in gas turbines, the coolant has to be ducted within passages to the porous walls through which it is ejected into the gas stream. The passages, often arranged in rotating parts, have to be designed in such a way as to ensure the proper local distribution of the coolant. In this report, a method is presented by which either the local permeability can be predicted. The method is based on a one-dimensional treatment of the gas flow through a rotating channel with varying cross section and partially porous walls. The inlet pressure into the channel and the outside pressure along it are assumed prescribed. It is also stipulated that the passage ends blindly. However, the method can easily be extended to cover the situation where a certain mass flow leaves the open end of the passage.
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 956 |
Release | : 1955 |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 386 |
Release | : 1955 |
Genre | : Aeronautics |
ISBN | : |
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 508 |
Release | : 1954 |
Genre | : Aeronautics |
ISBN | : |
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 442 |
Release | : |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 48 |
Release | : 1955 |
Genre | : Science |
ISBN | : |
Author | : United States. Dept. of Commerce. Office of Technical Services |
Publisher | : |
Total Pages | : 850 |
Release | : |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 1558 |
Release | : |
Genre | : Government publications |
ISBN | : |
Author | : Defense Documentation Center (U.S.) |
Publisher | : |
Total Pages | : 308 |
Release | : 1960 |
Genre | : Science |
ISBN | : |
Author | : Chaitanya D Ghodke |
Publisher | : SAE International |
Total Pages | : 238 |
Release | : 2018-12-10 |
Genre | : Technology & Engineering |
ISBN | : 0768095034 |
Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.