Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.

Abstract: A blade for a propulsion apparatus that includes a body formed of a first material. The body includes opposed pressure and suction sides and extends in span between a root and a tip. The body extends in court between a leading edge and a trailing edge. A tension element is positioned within the body and extends between the root and the tip. The tension element includes at least one string that is configured to be under tension such that at least a portion of the blade between the root and the tip is under compression.

Abstract: An apparatus and system for a marine propeller assembly are provided. In one aspect, the marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radial inner surface. The marine propeller assembly also includes a hub including a plurality of circumferentially-spaced dovetail receiving portions configured to receive a corresponding dovetail of the plurality of blades. At least one gap is formed between the radial inner surface and at least a portion of the dovetail receiving portion.

Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.

Abstract: A turbine engine that includes an engine casing including a shell and an angel wing member. The angel wing member includes a base defined at the shell, a tip positioned distal from the base, and a first side and a second side that define a thickness of the angel wing member. The thickness of the angel wing member is non-uniform between the base and the tip.

Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.

Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.

Abstract: A turbine engine that includes an engine casing including a shell and an angel wing member. The angel wing member includes a base defined at the shell and a tip positioned distal from the base. The turbine engine also includes a backsheet extending over the angel wing member such that an angled region is defined in the backsheet at an interface with the tip. The tip has a predetermined contour capable of mitigating stress concentrations in the angled region induced from said tip.

Abstract: A blade for a propulsion apparatus. The blade includes a body formed of a composite material and the body has opposed pressure and suction sides. The body extends in span between a root and a tip and extends in chord between a leading edge and a trailing edge. The body defines a body tip surface. A protective cover extends from near the tip of the blade toward the root of the blade along the leading edge and a trailing edge of the body. The protective cover defines a protective tip surface and an abrasive material is adhered to the protective tip surface.

Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.

Abstract: An airfoil including a plurality of spanwise fibers extending between the root and the tip and arranged between the leading edge and the trailing edge. The airfoil includes a matrix material surrounding and securing the plurality of spanwise fibers. The airfoil includes a residual airfoil portion extending between the leading edge and the trailing edge and extending between the root and a frangible line along the span. The residual airfoil portion includes a first portion of the plurality spanwise fibers including a first stiffness. The airfoil further includes a frangible airfoil portion extending between the leading edge and the trailing edge and extending between the tip and the frangible line. The frangible airfoil portion includes a second portion of the plurality of spanwise fibers including a second stiffness less than the first stiffness. The residual airfoil portion meets the frangible airfoil portion at the frangible line.

Abstract: A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

Abstract: A propeller assembly is provided. The propeller assembly includes a central hub including a forward end, an aft end, and a hub body extending therebetween along an axis of rotation of the central hub. The propeller assembly further includes a first retention member including a first radial interference member, the first retention member coupled to the forward end of the central hub and a second retention member including a second radial interference member, the second retention member coupled to the aft end of the central hub. The propeller assembly also includes a fairing platform extending between the first retention member and the second retention member, wherein the fairing platform is retained by the first radial interference member and by the second radial interference member.

Abstract: A platform for use between adjacent propulsion rotor airfoils joined to a rotor disk to provide an inner flowpath boundary includes: an axially extending I-beam supporting a radially outer skin having a flowpath surface; the I-beam including an inner I-flange disposed at an inner edge of an axially extending I-web, and an outer I-flange disposed at an outer edge of the I-web; the I-beam including a laterally-extending forward end flange at a forward end of the I-web, and a laterally-extending aft end flange at an aft end of the I-web; and the radially outer skin disposed on top of and joined to the radially outer I-flange such that the forward end flange and the aft end flange abut the outer skin.

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. Each of the first plurality of composite plies includes fibers oriented at least partially along a chordwise direction, a thickness direction, or both. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies includes at least one composite ply with fibers oriented along the span. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a leading edge sheath coupled to the leading edge of the airfoil. The leading edge sheath includes a flange extending from a frangible line toward the tip along the span and defining a first width along the chord at each point along the span S. The leading edge sheath further includes a base extending from the frangible line at least partially along the span to the root and defining a second width along the chord at a point along the span of the frangible line such that the second width is greater than the first width.

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a blade extending between the root and tip and extending between the leading edge and trailing edge. The blade includes a pressure side and a suction side defining a thickness therebetween at each point along the span. The blade defines a first chord reduction on at least one of the leading edge or trailing edge along a first portion of the span. Further, the blade defines a frangible line extending from the first chord reduction at least partially along the chord at a point along the span within the first portion of the span.

Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a retaining member extending at least partially between a leading edge and a trailing edge defining a frangible line extending at least partially along a chord at a point along the span of the retaining member. The airfoil further includes a frangible airfoil portion extending between the tip and the frangible line. The frangible airfoil portion includes a first plurality of composite plies, at least one composite ply of the first plurality of composite plies wraps around the retaining member. The airfoil includes a residual airfoil portion extending from the frangible line to the root including a second plurality of composite plies, at least one composite ply of the second plurality of composite plies wraps around the retaining member. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.