CLEARANCE CONTROL FOR THE TURBINE OF A GAS TURBINE ENGINE
Assignee
UNITED TECHNOLOGIES CORPORATION, HARTFORD, CT A CORP. OF DE
Filed
Aug 24, 1988
Granted
Sep 16, 1997
Location
PALM BEACH GARD FL US
Abstract
An aerodynamic buffer zone in the gap between the tip of an air cooled axial flow turbine blade of a gas turbine engine and its surrounding shroud or seal (outer air seal) is created by discretely discharging a high velocity stream of cooling air from the tip of the blade in a judicious direction. The stream is angularly oriented relative to the plane of rotation of the turbine so that it is discharged in the gap in the direction of the pressure side of the turbine and preferably at between a 15°-45° angle relative to the flat surface of the tip of the blade.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 29, 1989
Rescinded
Apr 9, 1997
Duration
8 years
Inventor
- 1FRANK W. HUBER
Record Details
- Patent number
- US 5667359
- Application
- 07236094
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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