ENHANCED FILM COOLING SLOT FOR TURBINE BLADE OUTER AIR SEALS
Assignee
UNITED TECHNOLOGIES CORPORATION
Filed
Nov 22, 1993
Granted
Jul 22, 1997
Location
JUPITER FL US
Abstract
This disclosure describes a cooling enhancement for gas turbine engine outer air seals. The invention provides heat transfer using impingement cooling and convective cooling through the use of tortuous cooling air passages, and film effective film cooling through the use of cooling air discharge slots that are oriented so as to discharge coolant into the working fluid flowpath with a minimum of momentum exchange between the cooling air and the working fluid.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Sep 28, 1994
Rescinded
Apr 9, 1997
Duration
2 years, 6 months
Inventor
- 1JOSEPH A. SCRICCA
Record Details
- Patent number
- US 5649806
- Application
- 08155989
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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