TURBINE AIRFOIL SUCTION AIDED FILM COOLING MEANS
Assignee
UNITED TECHNOLOGIES CORPORATION
Filed
Nov 20, 1992
Granted
Oct 10, 2000
Location
TEQUESTA FL US
Abstract
Film cooling effectiveness for internally air cooled turbine blades of gas turbine engines is enhanced by including an interconnecting passage to the film cooling hole that is in communication with a lower internal pressure in the blade to create a suction at the exit end of the film hole to limit penetration into the gas stream.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 27, 1993
Rescinded
Dec 29, 1999
Duration
6 years, 8 months
Inventor
- 1FRIEDRICH O. SOECHTING
Record Details
- Patent number
- US 6129515
- Application
- 07979718
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
UNITED TECHNOLOGIES CORPORATIONMore from this assignee
COOLED AIRFOILS FOR A GAS TURBINE ENGINE
UNITED TECHNOLOGIES CORPORATION
ENHANCED FILM COOLING SLOT FOR TURBINE BLADE OUTER AIR SEALS
UNITED TECHNOLOGIES CORPORATION
AIRFOIL HAVING EXPANDED WALL PORTIONS TO ACCOMMODATE FILM COOLING HOLES
UNITED TECHNOLOGIES CORPORATION
LOW OBSERVABLE ENGINE AIR INLET SYSTEM
UNITED TECHNOLOGIES CORPORATION
DUCTILE TITANIUM ALLOY MATRIX FIBER REINFORCED COMPOSITES
UNITED TECHNOLOGIES CORPORATION
TIP SEAL AND ANTI-CONTAMINATION FOR TURBINE BLADES
UNITED TECHNOLOGIES CORPORATION
Related by domain
NEURAL NETWORK CONTROLLER FOR A PULSED ROCKET MOTOR TACTICAL MISSILE SYSTEM
Raytheon
VTOL AIRCRAFT NOZZLE
ROLLS-ROYCE PLC
MISSILE JET VANE CONTROL SYSTEM AND METHOD
HUGHES MISSILE SYSTEMS COMPANY
AIRCRAFT INFRARED GUIDED DEFENSE MISSILE SYSTEM
VECTORABLE NOZZLE FOR AIRCRAFT
ROLLS-ROYCE PLC
METHOD OF MAKING AN AIR COOLED VANE WITH FILM COOLING POCKET CONSTRUCTION