General Electric Company

Yoon Seok Choi

Drew Michael Capps

Wei-Min Ren

Kevin E Turner

Letian Wang

Gregory Terrence Garay

Achalesh Kumar Pandey

Scott Mordin Hoyte

Mark Joseph Mielke

Ramakrishna Venkata Mallina

Wei Ning

Robert Bruce Dickman

Carl Lawrence MacMahon

Jagmeet Singh

Julie Ann Duselis

Keegan Nathaniel Mehrtens

A rotor blade system for a turbine engine having a longitudinal centerline axis. The rotor blade system includes a rotor configured to rotate about the longitudinal centerline axis and a plurality of rotor blades coupled circumferentially around the rotor, each rotor blade having a leading edge, a trailing edge, a suction side, and a pressure side. At least one rotor blade of the plurality of rotor blades has an axial sweep of both the leading edge and the trailing edge as compared to a base blade of the plurality of rotor blades.

Rotor blade system for turbine engines

A rotor blade system. The rotor blade system includes a rotor and a plurality of blades coupled to the rotor. The plurality of blades are arranged in an airfoil distribution pattern. The airfoil distribution pattern includes one or more baseline blades and one or more intentionally mistuned blades including an intentional mistuning feature.

Rotor blade system of turbine engines

An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

Active airfoil vibration control

A vibration-damping component, a gas turbine engine having the vibration-damping component and a method for forming such component are disclosed. The vibration-damping component comprises a body formed from an additive manufacturing material by an additive manufacturing process and defining a cavity within the body, and a vibration damper disposed within the cavity. The vibration damper comprises a damping element and a damping medium containing a viscoelastic material surrounding the damping element. The damping element has a relative motion when the component vibrates.

Vibration-damping components, gas turbine engine and method of forming such components

A system for creating a risk analysis for at least one turbomachine includes a database storing characteristics of one or more turbomachines and a processing module coupled to the database that receives the characteristics from the database and creates the risk analysis. The processing module includes a modeling module that creates a representation of the amount of rocking in a particular turbomachine based on the characteristics and a performance modeler coupled to the modeling module and that, based on the representation of the amount of rocking, creates the risk analysis.

Turbomachine airfoil life management system and method

Growing community of inventors

Cincinnati, OH, United States of America

Yoon Seok Choi