General Electric Company

Caterpillar Inc.

Andrew Greif

Steven Sebastian Burdgick

Saad Hasan

Lyle B Spiegel

Subhro Samarendra Nathak

Peter Xiao

Joseph Bobchik

An exhaust muffler for an internal combustion engine includes a housing. A plurality of partitions are disposed within the housing, defining a plurality of chambers. An inlet pipe and an outlet pipe are also disposed within the housing and both the inlet and outlet pipes include a perforated region. The perforated region permits fluid communication between the inlet pipe, outlet pipe and the plurality of chambers. To attenuate engine noise, the perforated regions of the inlet and outlet pipes are positioned at opposite ends of the housing, forcing the exhaust gas to pass through each of the plurality of partitions and chambers, thereby damping the sound waves with minimum effect on engine back pressure levels. Alternatively, the perforated regions of the inlet and outlet pipes may be aligned in a cross-flow chamber.

Exhaust sound attenuation device

A brush seal assembly and method for sealing a turbine machine rotary member relative to a stationary member circumscribing the rotary member. The seal assembly includes a first compliant seal component disposed at a radially inward region of the stationary member in rubbing contact with a surface of the rotary member. The seal assembly also includes at least one hard seal element formed integrally with a carrier of the first compliant seal component, located a specified axial distance from the first compliant seal component.

Seal member, assembly and method

A nozzle assembly for a turbine including an airfoil, inner and outer sidewalls, and inner and outer rings is provided. The sidewalls and rings are coupled together using a weld and mechanical interconnection, including axial and radial mechanical stops to allow for an accurate assembly, to ensure correct radial and axial positions of the parts during welding, to minimize weld shrinkage and to control an axial weld length. The configuration may further include one or more surfaces at an interface between a ring and a sidewall angled away from the interface to form a narrow groove. The configuration further may include a ring with a consumable root portion to facilitate the weld, and to provide a fixturing stop to further ensure that the parts remain in the correct position.

Turbine singlet nozzle assembly with radial stop and narrow groove

Embodiments of this invention include a nozzle assembly for a turbine, the nozzle assembly including an airfoil, inner and outer sidewalls, and inner and outer rings. Each of these sidewalls and rings are coupled together at an interface through a combination of a mechanical interconnection on one end and a welded connection on the other end. The mechanical interconnection includes either the sidewalls or the rings having a protruding hook and the other having a corresponding hook recess. The interconnection can also include axial and radial mechanical stops. The configuration may further include one or more surfaces at an interface between a ring and a sidewall angled away from the interface to form a narrow groove. The configuration further may include a ring with a consumable root portion.

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Geneva, IL, United States of America

Andrew Greif