Patent ID: 8347635
Filing Date: 2013-01-08
Classification: F01D,F05B,F05D,Y10T

Abstract:
1. A gas turbine engine having a mid turbine frame, the mid turbine frame comprising: an outer case, an inner case, at least three spokes extending radially between the inner and outer cases, and a gas path defined through the mid turbine frame, the gas path disposed between the inner and outer cases, the inner case supporting at least one main shaft bearing, the inner case radially adjustably mounted to the outer case via the spokes; a radial positioning apparatus mounted to the outer case, the apparatus including at least three radial locators threadedly mounted to the outer case, each of the radial locators having a terminal portion extending radially outwardly of the outer case and having an inner end in contact with an end surface of a respective one of the spokes, the end surface being substantially normal to a radial axis of the respective one of the spokes the radial locators configured to adjust the radial position of the inner case relative to the outer case when the radial locators are threadingly adjusted relative to the outer case; and a locking apparatus associated with each radial locator, the locking apparatus mounted to an outer surface of the outer case by a fastening apparatus independent of the radial locator, the locking apparatus including at least one keying surface keyed to a corresponding surface on the terminal portion of the radial locator, said keying and corresponding surfaces cooperating to impede rotation and thus radial movement of the radial locator relative to the outer case when the locking apparatus is mounted to the outer case.