CHORDALLY BIFURCATED TURBINE BLADE
Assignee
GENERAL ELECTRIC COMPANY A NY CORP.
Filed
Aug 25, 1992
Granted
Oct 18, 1994
Location
IPSWICH MA US
Abstract
A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 12, 1993
Rescinded
Aug 31, 1993
Duration
5 months
Inventor
- 1DAVID M. KERCHER
Record Details
- Patent number
- US 5356265
- Application
- 07935061
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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