STATOR VANE MOUNTING PLATFORM
Assignee
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEUR D'AVIATION S.N.E.C.M.A.
Filed
Nov 29, 1985
Granted
Aug 13, 1996
Location
SAINT SAUVEUR FR
Abstract
A stator vane mounting platform is disclosed which provides internal cooling chambers which facilitates the flow of cooling air through the chambers and thus, the cooling of the stator assembly. Baffles define an upstream chamber and a downstream cooling chamber between adjacent stator vanes so as to maximize the airflow and, consequently, the cooling effects of this airflow. The internal cooling chambers are defined by a thick wall and a relatively thin wall, the thin wall being in direct contact with the hot gases passing through the stator assembly. Mounting lugs and flanges are directly attached to the thicker wall so as to mount the stator assembly to the turbine engine structure and to accommodate all of the mechanical stresses encountered during the turbine engine operation.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 16, 1987
Rescinded
Oct 11, 1995
Duration
8 years, 7 months
Inventor
- 1ANN-ELISABETH F. BOURGUIGNON
Record Details
- Patent number
- US 5545002
- Application
- 06820269
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Related by domain
GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED DUAL VORTEX CAVITY
General Electric
SOLID ROCKET PROPELLANT
GAS TURBINE ENGINE FAN (U)
General Electric
TURNING VANE ARRANGEMENT FOR IR SUPPRESSORS
SIKORSKY AIRCRAFT CORPORATION
MODULAR ROCKET BOOSTED PENETRATING WARHEAD
LOCKHEED MARTIN CORP.
INTEGRAL SOLID BOOSTER AND HYBRID THRUST SUSTAINING SYSTEM AND PROJECTILE INCORPORATING THE SAME
ENVIRONMENTAL AEROSCIENCE CORPORATION