General Electric Company

Woodward Hrt, Inc.

Michael Alan Stieg

Brian Christopher Towle

Nicholas John Bloom

Darrell Glenn Senile

Donald Michael Corsmeier

Mark Willard Marusko

Michael Todd Radwanski

Jeffrey D Johnson

Gregory Scott Phelps

Chad Holden Sutton

Joseph Thomas Kopecek

Aaron Michael Dziech

John Stephen Mears

Valeria Proano Cadena

Brent Michael Ozanich

Kenneth Willett

Jesus Anaya

Daniel J Kirtley

Greg Scott Phelps

George Conway

Robert Andrew Stowers

Erich R Fitzpatrick

Kimberly Lynne Christman Kenoyer

Jeff Douglas Johnson

A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.

Combustor assembly for a turbine engine

A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.

A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.

A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

Piston ring assembly for a turbine engine

A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.

Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Combustor heat shield sealing

A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

Components and methods for forming components are provided. For example, a method for forming a component includes laying up a plurality of plies to form a component preform that defines an axis of symmetry and a circumferential direction. Laying up the plurality of plies includes overlapping ends of the plurality of plies to define overlap regions and offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plies passes through only one overlap region. In another embodiment, a component includes a body that is symmetric about an axis of symmetry and that defines a circumferential direction and a radial direction. The body is formed from a plurality of plies and has a substantially uniform thickness. Ends of the plurality of plies are overlapped to define a plurality of overlap regions, which are offset along the circumferential direction.

Axisymmetric components and methods for forming axisymmetric components

Combustor assemblies having heat shields heat shield attachment features are provided. For example, a combustor assembly includes a dome plate defining first and second apertures, and a heat shield defining first and second openings. The heat shield includes a first cup extending about the first opening and a second cup extending about the second opening. The combustor assembly further includes a collar having a first frame at least partially surrounding the first cup and a second frame at least partially surrounding the second cup. The collar includes a first fastening feature and the dome plate includes a second fastening feature. The first fastening feature mates with the second fastening feature to couple the heat shield to the dome plate. The combustor assembly also may include an attachment piece configured to couple the heat shield to the dome plate. Methods for forming ceramic matrix composite (CMC) heat shields also are provided.

Combustor heat shield and attachment features

A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

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. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.

A combustion liner for use in a combustor assembly is provided. The combustion liner includes a side wall that defines a combustion chamber having a main flow axis extending therethrough. The combustion chamber channels a flow of combustion gas therethrough along a mixer swirl flow axis oriented obliquely relative to the main flow axis. The combustion liner also includes film cooling holes defined within the side wall. The film cooling holes are configured to discharge a pressurized fluid jet into the combustion chamber, and arranged in at least a first row and a second row positioned a first distance from the first row. The film cooling holes are arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in the first row is directed along a discharge flow axis misaligned from film cooling holes in the second row.

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Cincinnati, OH, United States of America

Michael Alan Stieg