United Technologies Corporation

Florida Turbine Technologies, Inc.

Pratt & Whitney Rocketdyne, Inc.

Yehia M El-Aini

Gary Alan Davis

Stuart K Montgomery

A Paul Matheny

Samy Baghdadi

Barry K Benedict

Robert J Morris

Joseph C Burge

Alan W Stoner

Myron Klein

Lawrence P Roberts

William Brian Diggs

Carl E Meece

George J Obranic, Jr

William S Mitchell

David Wiebe

Myron L Klein

A rotor comprises a disk having a rim. The rim has an axial face facing one of a forward or rearward direction. The rim defines a circumferential groove. A damper engages with the rim at both the axial face and the circumferential groove. The disk includes a rotor hub having a hub inner surface facing a longitudinal axis about which the rotor hub rotates. The rim is spaced radially outwardly relative to the hub inner surface. The axial face extends radially inwardly from the rim to the hub inner surface. The circumferential groove is formed within the hub inner surface. The damper comprises a split ring damper with a first leg mounted within the circumferential groove and a second leg that extends from the first leg, surrounds a radial lip of the hub inner surface, and extends radially outwardly to contact the axial face. An integrally bladed rotor is also disclosed.

Damper for an integrally bladed rotor

A Rotor includes a disk having a rim with an axial face, the rim defines a circumferential groove. A damper engaged with the rim at both the axial face and the circumferential groove.

A process for designing a labyrinth seal for flutter avoidance in which a computer generated Finite Element model of the lab seal is produced, the geometric parameters of the lab seal is determined, the lab seal flow parameters are determined, the solid model of the lab seal is analyzed using a finite element analysis program for a range of nodal diameters to determine frequencies and mode shapes, an aerodynamic damping and mechanical damping for the labyrinth seal is determined, and if the sum of the aerodynamic and mechanical damping is negative one or more of the labyrinth seal parameters are changed and the analysis is repeated.

Process for analyzing a labyrinth seal for flutter

A turbine disk includes a rotor and a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor and a tip having a shroud at a distal end. The shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces. The shrouds of adjacent turbine blades are separated by a tip shroud damper, and which includes a retention rail that cooperates with the outer diameter surface to maintain a positional relationship of the damper, a inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange. The tip shroud damper reduces the vibratory responses of modes involving axial and radial shroud motion to prevent high cycle fatigue (HCT).

Airfoil tip shroud damper

A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating.

Non-integral platform and damper for an airfoil

A labyrinth seal having two or more knife edges in which at least one of the knife edges has a varying radial height in the circumferential direction or a cavity formed between adjacent knife edges has a varying axial width so that the leakage flow across the gap will vary around the circumference in order that excess vibrations will not develop in the knife edges and break them. The radial height of the step that forms a gap with the lab teeth varies either sinusoidal or random. An axial spacing between the step and the associated tooth can also vary either sinusoidal or random. To minimize a cavity edge-tone effect, the corners of the steps are rounded.

Aerodynamically mistuned labyrinth seal

A blade includes an airfoil portion which defines at least one cavity with a damper located within the cavity, the damper includes a corrugated surface.

Internally damped blade

A stationary labyrinth seal system includes a seal housing having an annular cavity, a plurality of damping devices, and a retaining ring. The damping devices are positioned within the annular cavity and are maintained within the annular cavity by the retaining ring.

Damping device for a stationary labyrinth seal

An apparatus for controlling vibrations in a rotor stage rotating through core gas flow is provided. The apparatus includes a source of high-pressure gas and a plurality of ports for dispensing high-pressure gas. The rotor stage rotates through core gas flow having a plurality of circumferentially distributed first and second regions. Core gas flow within each first and second region travels at a first and a second velocity, respectively. The first velocity is substantially higher than the second velocity. The ports dispensing the high-pressure gas are selectively positioned upstream of the rotor blades, and aligned with the second regions such that high-pressure gas exiting the ports enters the second regions. The velocity of core gas flow in the second regions consequently increases, and substantially decreases the difference in core gas flow velocity between the first and second regions.

Active rotor stage vibration control

A rotor blade for a turbine engine rotor assembly is provided comprising a root, an airfoil, a platform, and apparatus for damping vibrations in the airfoil. The airfoil includes a pocket formed in a chordwise surface. The apparatus for damping vibrations in the blade includes a damper and a pocket lid. The damper is received within the pocket between an inner surface of the pocket and the pocket lid. The pocket lid is attached to the airfoil by conventional attachment apparatus and contoured to match the curvature of the airfoil.

Turbine engine rotor blade vibration damping device

A twisted compressor or fan hollow blade is damped by an internal loose slug. The slug contacts the skin of the blade at two transversely spaced locations. This slug is located with its center of gravity eccentric of a radial line through the contact location.

Internally damped blades

The internal blade damper is an elongated member with a damping surface of discrete width in contact with the interior blade surfaces. Contact is continuous throughout a substantial length. The damper extends between 2.degree. and 30.degree. from the radial direction, producing a direction of contact having some radial component. Centrifugal force loads the damping surface.

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Tequesta, FL, United States of America

Yehia M El-Aini