TURBINE COMBUSTOR COOLING SYSTEM
Assignee
ALLIED-SIGNAL INC., A CORP. OF DE.
Filed
Aug 31, 1989
Granted
Jul 19, 1994
Location
PHOENIX AZ US
Abstract
A gas turbine engine has a low cost combustor liner cooling system combining the benefits of high internal heat removal with improved film cooling by employing a large number of strategically positioned, laser-drilled cooling passages. Cooling air flows through these specially tailored passages to absorb heat from the liner prior to injection as a protective film on the interior surface. The passages are set in staggered rows on a thickened portion of the liner and have a rough internal heat transfer surface and an exit with a steep injection angle to evenly distribute the cooling film along the interior surface of the liner.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 4, 1990
Rescinded
Nov 9, 1993
Duration
3 years, 6 months
Inventor
- 1GEOFFREY D. MYERS
Technology Domains
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Record Details
- Patent number
- US 5329773
- Application
- 07401366
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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