Abstract: A balancing weight clip for balancing a rotor assembly of a gas turbine engine which includes a weight portion, and a first flange engaging portion and a second flange engaging portion extending from the weight portion. The weight portion and the first and second flange engaging portions define a flange receiving opening for receiving a flange of a disc of the rotor assembly. The first flange engaging portion is provided with a detent facing the second flange engaging portion and engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is elastically deformable so that the first and second flange engaging portions are elastically moveable away from one another to removably receive the flange in the flange receiving opening and engage the detent with the mating groove.

Abstract: The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.

Abstract: An integrated duct, baffle and knife edge seal arrangement employing the radially inner distal edge of the baffle for sealing the radially inner stator/rotor interface of an inter-stage cavity.

Abstract: A balancing weight clip for balancing a rotor assembly of a gas turbine engine which includes a weight portion, and a first flange engaging portion and a second flange engaging portion extending from the weight portion. The weight portion and the first and second flange engaging portions define a flange receiving opening for receiving a flange of a disc of the rotor assembly. The first flange engaging portion is provided with a detent facing the second flange engaging portion and engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is elastically deformable so that the first and second flange engaging portions are elastically moveable away from one another to removably receive the flange in the flange receiving opening and engage the detent with the mating groove.

Abstract: The interturbine duct (ITD) directs hot combustion gases from a high pressure turbine stage outlet to a low pressure turbine stage inlet in a gas turbine engine. The ITD comprises an outer wall and a heat resistant non-metallic resilient annular seal provided around an end of the outer wall that is adjacent to the high pressure turbine stage outlet.

Abstract: The air seal arrangement is for a disc wheel in a gas turbine engine. The disc wheel comprises a sleeve portion having an outer surface. The arrangement comprises a static knife edge seal in registry with the outer surface. The static knife edge seal has a free end adjacent to the outer surface.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.

Abstract: The air seal arrangement is for a disc wheel in a gas turbine engine. The disc wheel comprises a sleeve portion having an outer surface. The arrangement comprises a static knife edge seal in registry with the outer surface. The static knife edge seal has a free end adjacent to the outer surface.

Abstract: The interturbine duct (ITD) directs hot combustion gases from a high pressure turbine stage outlet to a low pressure turbine stage inlet in a gas turbine engine. The ITD comprises an outer wall and a heat resistant non-metallic resilient annular seal provided around an end of the outer wall that is adjacent to the high pressure turbine stage outlet.

Abstract: The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.

Abstract: An integrated duct, baffle and knife edge seal arrangement employing the radially inner distal edge of the baffle for sealing the radially inner stator/rotor interface of an inter-stage cavity.

Abstract: A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.

Abstract: A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.

Abstract: Disclosed is a heating element having improved performance, particularly at high power densities and high temperatures. The heating element comprises a substrate having a first layer comprising a silicon based electrically insulating material on its surface. On a surface of the first layer is a second layer comprising a silicon based electrically resistive material. Attached to the second layer are at least two separate areas of silicon based electrically conductive material. Each of these separate areas are suitable for connection to a power supply.