General Electric Company

The United States of America As Represented by the Department of Energy

Uttara Vijay Kumar

Rahul Anil Bidkar

Deepak Trivedi

Steven Douglas Johnson

Ravindra Shankar Ganiger

Daniel Jason Erno

Arunkumar Natarajan

Ananda Barua

Jonathan Russell Ratzlaff

Prateek Jalan

Ken Ivcar Salas Nobrega

Randy Thomas Antelo

John Francis Morrison

Keith William Gary

A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A floating seal assembly is disposed at an interface of the rotor and the stator to seals at least portions of the rotor and the stator relative to each other. The floating seal assembly includes one or more inertial damping elements tuned to one or more frequencies.

Gas turbine engine with inertially damped seals

A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by a rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face and a primary seal body of the seal slider. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor apart from the primary seal body.

Seal assembly for a rotary machine having a flexible joint

A turbine engine comprising an engine core having a rotor and a stator, and a floating seal assembly sealing at least portions of the rotor and the stator relative to a higher-pressure area and a lower-pressure area. The floating seal assembly can comprise a carriage assembly at least partially defining a seal cavity and a seal body floating within the seal cavity. The floating seal assembly can further include at least one of a seal located between the seal body and the carriage assembly, and a seal face located between the seal body and the carriage assembly.

Turbine engine with a floating seal assembly

A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

Seals for managing thermal distortion in a turbomachine and methods for building the same

A face seal assembly including a thermal fluid circuit, a turbomachine including the face seal assembly and a method of operating the turbomachine are disclosed. The face seal assembly includes a seal ring including a seal bearing face, at least one internal cavity including a cavity inlet and a cavity outlet. The face seal assembly further including a fluid inlet channel in fluid communication with the cavity inlet of the at least one internal cavity and a pressurized fluid and a fluid outlet port in fluid communication with the cavity outlet of the at least one internal cavity. The at least one internal cavity, the fluid inlet channel and the fluid outlet port define a thermal fluid circuit providing thermal management of the seal ring. In the turbomachine, the face seal assembly is disposed between a stationary component and a rotating component including a rotating component bearing face.

Face seal assembly with thermal management circuit and an associated method thereof

A powder removal system includes a plurality of tubes including upstream and downstream ends, a manifold fluidly coupled to the tubes, and a pressurized air supply fluidly coupled to the manifold supplying pressurized air to the tubes via the manifold. The downstream ends of the tubes are inserted into a plurality of channels partially filled with powder.

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Glenville, NY, United States of America

Uttara Vijay Kumar