FILM COOLING OF JET ENGINE COMPONENTS
Assignee
GENERAL ELECTRIC COMPANY, A CORPORATION OF NY
Filed
Jul 22, 1991
Granted
Aug 5, 1997
Location
CINCINNATI OH US
Abstract
A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second surface exposable to a hotter, lower static pressure gas flow flowing across the second surface. The component further includes a generally straight film coolant passageway having an inlet on the first surface and an outlet on the second surface. The second surface has a seamless groove which is open substantially entirely along its longitudinal dimension extending from the outlet along the lower static pressure gas flow for improved film cooling of the second surface.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 13, 1993
Rescinded
Mar 18, 1997
Duration
3 years, 11 months
Inventor
- 1CHING-PANG LEE
Record Details
- Patent number
- US 5653110
- Application
- 07733892
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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