Abstract: A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; and a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end.

Abstract: A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end, the splitter segment being configured to split an incoming fluid flow into a first, radially outer stream and a second, radially inner stream; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end, wherei

Abstract: A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; and a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end.

Abstract: A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.

Abstract: A hybrid grommet assembly for a vane comprising a body portion comprising a first lip opposite a second lip forming a slot receiver, said slot receiver configured to receive a shroud slot of a shroud; said body portion comprising a vane receiver extending from said body portion and configured to receive a vane; a fiber integral within said body portion; and a potting coupled to said grommet proximate said vane receiver, wherein said potting fills a gap between the grommet and the vane.

Abstract: A tool for seating a wear liner into a first groove of a fan case of a gas turbine engine includes a body, a handle, and a first guide foot. The body includes a first end and a second end. The handle is connected to and extends from the body. The first guide foot is connected to and extends from the first end of the body. The first guide foot includes a first end connected to the body and a second end opposite from the first end of the first guide foot. The second end of the first guide foot is rounded and includes a chamfered portion.

Abstract: A hybrid grommet assembly for a vane comprising a body portion comprising a first lip opposite a second lip forming a slot receiver, said slot receiver configured to receive a shroud slot of a shroud; said body portion comprising a vane receiver extending from said body portion and configured to receive a vane; a fiber integral within said body portion; and a potting coupled to said grommet proximate said vane receiver, wherein said potting fills a gap between the grommet and the vane.

Abstract: A gas turbine engine includes an annular structure disposed around an engine central longitudinal axis of the gas turbine engine. The annular structure defines an annular channel and comprises a first density, according to various embodiments. The gas turbine engine may further include a weight-saving filler disposed within the annular channel. The weight-saving filler may have a second density that is less than the first density. The gas turbine engine may further include an annular retention strap disposed around the engine central longitudinal axis of the gas turbine engine. The annular retention strap is at least partially embedded in the weight-saving filler, according to various embodiments.

Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.

Abstract: A stator assembly for a gas turbine engine includes an annular outer shroud, an annular inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly for a gas turbine engine includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly located at the case. The stator assembly includes an annular outer shroud secured to the case, an annular inner shroud secured to the case and a plurality of stator vanes extending from the outer to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

Abstract: A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.

Abstract: A stator assembly for a gas turbine engine includes an arcuate shroud including a shroud pocket, the shroud pocket having a shroud slot extending therethrough. A stator vane is insertable into the shroud pocket and includes a vane slot extending therethrough. A strap extends through the shroud slot and the vane slot to retain the vane to the shroud. A gas turbine engine includes a combustor and a stator and case assembly in in fluid communication with the combustor. The stator and case assembly includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly secured at the case.

Abstract: A stator includes a plurality of stator vanes and a shroud operably connected to the stator vanes. The shroud includes one or more positioning tabs configured to engage one or more corresponding alignment features of a mating component to radially position the shroud at the mating component, the one or more shroud positioning tabs position the outer shroud to define a radial tip clearance between an outer shroud and an adjacent rotor of the gas turbine engine. A gas turbine engine includes a stator and case assembly in fluid communication with a combustor. The stator and case assembly includes a stator located at a case. The stator has a plurality of stator vanes and a shroud including one or more positioning tabs configured to engage one or more corresponding case alignment features to radially position the shroud at the case.

Abstract: A stator assembly for a stator of a gas turbine engine is provided. The stator assembly having: a shroud defining a cavity; a plurality of inserts located within the cavity, each of the plurality of inserts defining a cavity; a plurality of vanes secured to the shroud, wherein each of the plurality of vanes has a tab portion located in the cavity of the shroud; and a rubber material disposed in the cavity of the shroud, the rubber material securing the tab portion of each of the plurality of vanes to the shroud.

Abstract: A tool for seating a wear liner into a first groove of a fan case of a gas turbine engine includes a body, a handle, and a first guide foot. The body includes a first end and a second end. The handle is connected to and extends from the body. The first guide foot is connected to and extends from the first end of the body. The first guide foot includes a first end connected to the body and a second end opposite from the first end of the first guide foot. The second end of the first guide foot is rounded and includes a chamfered portion.

Abstract: A stator vane arrangement may comprise a first shroud comprising a first side surface and a second side surface, a slot disposed in the first shroud, the slot at least partially defined by the first side surface and the second side surface, a stator vane extending at least partially through the slot, wherein the first side surface and the second side surface are disposed on opposite sides of the slot, and the first side surface is oriented at a first non-zero angle with respect to a radial direction.

Abstract: A gas turbine engine includes an annular structure disposed around an engine central longitudinal axis of the gas turbine engine. The annular structure defines an annular channel and comprises a first density, according to various embodiments. The gas turbine engine may further include a weight-saving filler disposed within the annular channel. The weight-saving filler may have a second density that is less than the first density. The gas turbine engine may further include an annular retention strap disposed around the engine central longitudinal axis of the gas turbine engine. The annular retention strap is at least partially embedded in the weight-saving filler, according to various embodiments.

Abstract: An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes a mount base and a bayoneted lug on the mount base. The mount base is configured to axially engage the flange where the bayoneted lug extends through the lug aperture. A fastener secures the components together. The fastener projects axially into a fastener aperture in the mount base for an axial length that is less than or equal to an axial length of the bayoneted lug.

Abstract: A liner assembly for placement between a mounting foot of a platform and a case of a gas turbine engine includes first and second annular liner segments configured to move independently of each other. The first annular liner segment is configured to be mounted on at least a portion of a radially outward surface of the mounting foot. The first annular liner segment includes a first flat portion and a first curved portion extending from a first end of the first annular liner segment. The second annular liner segment is configured to be mounted on at least a portion of a radially inward surface of the mounting foot. The second annular liner segment includes a second flat portion and a second curved portion extending from a first end of the second annular liner segment.

Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.