General Electric Company

Adam Robert Kahn

Daniel J Kirtley

Nayan Vinodbhai Patel

Shai Birmaher

Duane Douglas Thomsen

Ryan Christopher Jones

Nicholas John Bloom

Gerardo Antonio Salazar Lois

John Herman Mueller

Scott Matthew Bush

Neeraj Kumar Mishra

Andrew Bradley Gebbia

Trevor James Hahm

Anil Raju

Dhanashegaran Shanmugam

Nathan Richard Hermanson

A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a CMC outer liner, a CMC inner liner, and a cowl structure, that are connected together via at least one outer connection and at least one inner connection. An outer seal member is arranged to seal an outer gap between an outer liner connecting flange and an outer dome connecting flange, and an inner seal member is arranged to seal an inner gap between an inner liner connecting flange and an inner dome connecting flange.

Gas turbine engine combustor having a ceramic matrix composite liner and dome

A dome-deflector structure for a combustor of a gas turbine includes a dome portion and a deflector portion, the dome portion and the deflector portion being connected together to form a dome-deflector cavity therebetween. The dome portion includes a plurality of dome-side cooling airflow passages therethrough arranged in a plurality of groups of dome-side cooling airflow passages, each group of dome-side cooling airflow passages being arranged to provide a flow of air therethrough in a respective group swirl direction, and adjacent groups of the dome-side cooling airflow passages providing the flow of air in a different group swirl direction with respect to one another.

Dome structure providing a dome-deflector cavity with counter-swirled airflow

The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.

Purge cooling structure for combustor assembly

A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor. The system further includes a first fluid flow supply including a compressor bleed connection, a feed manifold formed of bendable tubing, and a feed header extending between the compressor bleed connection and the feed manifold. The feed header includes a modulating valve configured to control an amount of fluid flow into the feed manifold. The system also includes a flow supply tube that extends between the feed manifold and the inducer and is couplable to at least one of the plurality of first fluid flow inlet openings through a sliding piston seal.

Method and system for modulated turbine cooling

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

Combustor assembly for a turbine engine

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Mason, OH, United States of America

Adam Robert Kahn