A component assembly for a gas turbine engine having a combustor defining a combustion chamber, the gas turbine engine defining a core air flowpath, a radial direction, and a circumferential direction is provided. The component assembly includes an outer shell at least partially defining the core air flowpath, the outer shell having an outer shell periphery that comprises a first array of integral outer shell airfoils that extend inward from the outer shell periphery; and an inner shell at least partially defining the core air flowpath, the inner shell having an inner shell periphery that comprises a second array of integral inner shell airfoils that extend outward from the inner shell periphery.

A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade disposed inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and including a plurality of cooling channels through which cooling air flows, a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other in a flow direction of fluid flowing through the casing to form an RS cavity into which cooling air is introduced, wherein when the segment body has a cross section along an imaginary plane including a radial straight line of the casing, the cooling channel is formed such that a width in a direction perpendicular to a radial direction of the casing is greater than a width in the radial direction of the casing.

A rotating assembly for a gas turbine engine has a balancing ring mounted to a first rotating component having a rotating unbalance about an axis of rotation. The ring is clocked at a circumferential position about the axis to counteract the rotating unbalance. A spacer is axially abutted against the first rotating component to set an axial position of the first rotating component relative to a second rotating component. The balancing ring is locked against rotation relative to the first rotating component in its circumferential position by the dual use spacer.

The exhaust mixer can have a conduit extending around a central axis, and along the axis to a trailing edge, the conduit extending between a radially-outer bypass path and a radially-inner core gas path, the conduit having a plurality of apertures spaced-apart from one another around the circumference of the conduit and fluidly connecting the bypass path to the core gas path upstream of the trailing edge.

An injector for a liquid rocket engine includes an array of injector elements. Each injector element includes a central passage and a plurality of peripheral transverse passages. The central passages are configured to provide axial injection flow and the peripheral transverse passages are configured to provide swirl injection flow about the axial injection flow. A portion of the injector elements are configured to provide the swirl injection flow in a clockwise direction and another portion of the injector elements are configured to provide the swirl injection flow in a counter-clockwise direction. The injector elements are arranged to form a plurality of circumferential rows. The injector elements of each individual circumferential row are either all of the clockwise direction or all of the counter-clockwise direction. At least one of the circumferential rows is of the clockwise direction and at least one of the circumferential rows is of the counter-clockwise direction.

A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.

An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade disposed inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and including a plurality of cooling channels through which cooling air flows, a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other in a flow direction of fluid flowing through the casing to form an RS cavity into which cooling air is introduced, wherein when the segment body has a cross section along an imaginary plane including a radial straight line of the casing, the cooling channel is formed such that a width in a direction perpendicular to a radial direction of the casing is greater than a width in the radial direction of the casing.

A single unducted rotor engine includes a power source; a casing surrounding the power source; an unducted rotor assembly driven by the power source having a single row of rotor blades; and an outlet guide vane assembly having a plurality of pairs of outlet guide vanes, each pair of the plurality of pairs of outlet guide vanes including a first outlet guide vane extending from the casing at a location downstream from the single row of rotor blades of the unducted rotor assembly and a second outlet guide vane also positioned downstream from the single row of rotor blades of the unducted rotor assembly. The first outlet guide vane of each pair of outlet guide vanes defines a first geometry. The second outlet guide vane of each pair of outlet guide vanes defines a second geometry. The first geometry is not equal to the second geometry.