Patent ID: 7770379
Filing Date: 2010-08-10
Classification: F02K,F16C

Abstract:
1. A vectorable nozzle assembly for a gas turbine engine, comprising: bearing means including first and second relatively rotatable bearing elements for mounting respective first and second rotatable components for relative rotation about a common axis; pneumatic or hydraulic actuator means having a pair of co-acting annular members, including a first annular member fixed with respect to the said first rotatable component and the first bearing element, and a second annular member fixed with respect to the said second rotatable component and the second bearing element; and means for energising and/or de-energising said actuator means to effect movement of the said co-acting annular member and thereby relative rotation of the said first and second bearing elements about the said bearing axis wherein the said actuator means comprises at least one chamber defined between the pair of relatively rotatable annular members each having at least one dividing element extending into the chamber to divide the interior of the chamber into separate circumferential regions, and means for generating a pressure differential in said chamber across one or more of the said dividing elements to effect said relative rotation of the said first and second bearing elements.