Abstract: A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies. A front tab extends downwardly from the front end of the top portion relative to the longitudinal plane. The rear end of the top portion is flat and generally contained in the longitudinal plane. A pair of lateral tabs extends downwardly from each of said lateral sides of the top portion relative to the longitudinal plane.

Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.

Abstract: A diffuser pipe for a gas turbine engine comprises a hollow pipe body including a first end, a second end fluidly connected to the first end, and at least one flattened area proximate to the second end. A ring is connected to the second end. The ring is an outlet of the diffuser pipe. At least one stiffener is disposed on the at least one flattened area. The ring and the at least one stiffener reduce vibratory stresses at the second end of the pipe body. A method of manufacturing a diffuser pipe of a gas turbine engine is also presented.

Abstract: A turbine blade adapted for mounting to a turbine rotor includes a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib disposed at the blade tip. The stiffening rib projects from the pressure side of the airfoil portion of the turbine blade.

Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.

Abstract: A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.

Abstract: A turbine blade comprising a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib at the blade tip. The stiffening rib extends in a substantially tangential direction on the pressure side of the airfoil portion of the turbine blade.