Sync-ring assembly for a gas turbine engine exhaust nozzle

Patent · Tue Aug 31 04:00:00 EDT 1993

OSTI ID:5991323

Barcza, W K

A sync-ring assembly is described for selectively positioning divergent flap of a gas turbine engine exhaust nozzle relative to the exhaust nozzle's case, the nozzle having a centerline defined there through, the assembly comprising: a sync-ring pivotably connected to the divergent flaps by a plurality of positioning strut assemblies, the sync-ring having a first surface and a second surface radially outward of the first surface relative to the centerline, the second surface is semi-spherical, a plurality of shaft bores equally spaced about the circumference of the sync-ring, each shaft bore extending through the sync-ring between the first surface and the second surface, a liner having a cylindrical surface, the liner made of a wear resistant composite material and received within and supported by the nozzle case, the cylindrical surface slidably contacting the semi-spherical second surface, a plurality of shaft pins, each shaft pin extending through one of the shaft bores and protruding from the first surface, and each shaft pin pivotably connected to actuator means mounted to the nozzle case for selectively positioning the sync-ring relative to the nozzle case, and a plurality of supports mounted to the nozzle case, each support having a guide track therein; and, a plurality of roller bearings, each roller bearing rotatably mounted to one of the shaft pins, each bearing extending into one of the guide tracks; wherein the sync-ring is selectively rotatable between a first position in which all of the shaft pins are perpendicular to the cylindrical surface radially outward therefrom relative to the centerline, and a second position in which at least one of the shaft pins is at an angle of at least 5 to the cylindrical surface radially outward therefrom relative to the centerline, and the sync-ring is selectively positioned along a portion of the cylindrical surface.

• Assignee: United Technologies Corp., Hartford, CT (United States)
• Patent Number(s): US 5239815; A
• Application Number: PPN: US 7-763689
• OSTI ID: 5991323
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
BEARINGS
COMPOSITE MATERIALS
CYLINDERS
ENGINES
EXHAUST SYSTEMS
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MATERIALS
MECHANICAL PROPERTIES
NOZZLES
WEAR RESISTANCE