Method and appliance for cooling a gas turbine combustion chamber
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Apr 1, 1997
Grant Date -
N/A
app pub date -
Oct 17, 1994
filing date -
Oct 18, 1993
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Advertisement
Advertisement
Advertisement
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully