Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.

Abstract: A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

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: Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.

Abstract: A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

Abstract: An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the circumferential offset defined from the base to the tip of each of the inner lobes is the same for all of the inner lobes and opposite to that of a swirl component of a main gas path flow entering the exhaust mixer.

Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.

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: An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the circumferential offset defined from the base to the tip of each of the inner lobes is the same for all of the inner lobes and opposite to that of a swirl component of a main gas path flow entering the exhaust mixer.

Abstract: Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.