COOLED AIRFOILS FOR A GAS TURBINE ENGINE
Assignee
UNITED TECHNOLOGIES CORPORATION
Filed
Dec 13, 1994
Granted
Dec 30, 1997
Location
TEQUESTA FL US
Abstract
An internally cooled airfoil for a gas turbine engine includes a leading edge region, a mid-chord region, a transition region, and a trailing edge region. The mid-chord region has a double wall configuration with the two outer walls and two inner walls. The trailing edge region has a conventional single wall configuration. The transition region has a three wall configuration designed to provide a gradual transition from the four wall configuration to the two wall configuration and to minimize high stresses therein.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 12, 1995
Rescinded
Apr 9, 1997
Duration
1 year, 12 months
Inventor
- 1ROBERT P. MOORE
Record Details
- Patent number
- US 5702232
- Application
- 08354299
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
UNITED TECHNOLOGIES CORPORATIONMore from this assignee
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
TURBINE AIRFOIL SUCTION AIDED FILM COOLING MEANS
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