BLADE DOVETAIL BOTTOM

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described. 1. A blade comprising:an airfoil extending radially outwardly of a dovetail, said dovetail having edges that will be at circumferential sides of the blade when the blade is mounted within a rotor; anda bottom surface of the dovetail that will be radially inward when the rotor blade is mounted in a rotor, and said bottom surface being formed such that a circumferentially central portion of said bottom surface is radially thicker than are circumferential edges.2. The blade as set forth in claim 1 , wherein said bottom surface increases generally constantly from the circumferential edges to the central portion.3. The blade as set forth in claim 1 , wherein said bottom surface is formed on a curve.4. The blade as set forth in claim 3 , wherein said bottom surface is convex.5. The blade as set forth in claim 4 , wherein said dovetail is formed of a material that is less strong than the rotor which will receive said blade.6. The blade as set forth in claim 1 , wherein said dovetail is formed of a material that is less strong than the rotor which will receive said blade.7. The blade as set forth in claim 1 , wherein said airfoil extends from a leading edge to a trailing edge claim 1 , and has suction and pressure sides claim 1 , and the circumferential edges of said blade are generally associated with said suction and pressure sides.8. The blade as set forth in claim 1 , wherein said central portion is at a circumferential center of the dovetail.9. The blade as set forth in claim 1 , wherein said blade is a fan ...

ROTARY MACHINES INCLUDING A HYBRID ROTOR WITH HOLLOW AND SOLID ROTOR BLADE SETS

A hybrid rotor may comprise a rotor disk having a peripheral rim, a plurality of solid rotor blades extending outwardly from the rotor disk, and a plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades. In various embodiments, the plurality of solid rotor blades may be integrally coupled to the rotor disk. In various embodiments, the plurality of hollow rotor blades may be mechanically retained in the rotor disk. 1. A hybrid rotor comprising:a rotor disk having a peripheral rim;a plurality of solid rotor blades extending outwardly from the rotor disk; anda plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades.2. The hybrid rotor of claim 1 , wherein the plurality of solid rotor blades are spaced around a circumference of the rotor disk in circumferentially spaced apart sets claim 1 , each set comprising one or more solid rotor blades and the plurality of hollow rotor blades are spaced around the circumference of the rotor disk in circumferentially spaced apart sets of one or more hollow rotor blades claim 1 , wherein each set of the one or more hollow rotor blades is disposed circumferentially adjacent and between a pair of adjacent circumferentially spaced apart sets of solid rotor blades.3. The hybrid rotor of claim 2 , wherein the peripheral rim includes a mechanical retention slot disposed between and adjacent the pair of adjacent circumferentially spaced apart sets of solid rotor blades claim 2 , the number of mechanical retention slots corresponding to the number of hollow rotor blades in the blade array and each mechanical retention slot configured to retain an individual rotor blade of the hybrid rotor.4. The hybrid rotor of claim 3 , wherein each set of the one or more solid rotor blades comprises the same or a different number of solid rotor blades and each set of the one or more hollow rotor blades ...

FAN BLADE DOVETAIL AND SPACER

A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

GAS TURBINE FAN FAIRING PLATFORM AND METHOD OF FAIRING A ROOT LEADING EDGE OF A FAN BLADE OF A GAS TURBINE ENGINE

A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade. 1. A gas turbine fan fairing platform comprising at least one body defining a surface and having an opening receptive to a blade , a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.2. The gas turbine fan fairing platform of claim 1 , wherein the at least one body is two bodies each having an opening such that the two bodies can attach to one another and the openings form a continuous border that surrounds the blade.3. The gas turbine fan fairing platform of claim 1 , wherein the two bodies are detachable from one another to allow them to be replaced.4. The gas turbine fan fairing platform of claim 1 , wherein the protrusion has a curved surface that blends into the surface of the at least one body.5. The gas turbine fan fairing platform of claim 1 , wherein the protrusion serves as a fairing for the blade.6. The gas turbine fan fairing platform of claim 1 , wherein the at least one body is made of at least one of a composite claim 1 , a polymeric material claim 1 , and a metal.7. The gas turbine fan fairing platform of claim 1 , wherein the material of the body is more resilient than that of the blade.8. The gas turbine fan fairing platform of claim 1 , wherein the at least one body seals to the blade.9. The gas turbine fan fairing platform of claim 1 , wherein the protrusion improves aerodynamic flow at the root leading edge of the blade in comparison to a platform that does not include the protrusion.10. The gas turbine fan fairing platform of claim 9 , wherein the improved aerodynamics allows the root leading edge of the blade to be thicker without sacrificing performance of a gas turbine engine ...

HOLLOW FAN BLADE FOR A GAS TURBINE ENGINE

A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to the airfoil around the opening. The cover encloses the cavity and provides a continuous first major surface. The cavity is divided into at least first and second subcavities. A different filler material is disposed within the first and second subcavities. 1. A blade comprising:a root; and first and second major surfaces;', 'an internal cavity comprising at least one rib dividing the internal cavity into at least first and second subcavities;', 'a first filler material disposed within the first subcavity; and', 'a second filler material disposed within the second subcavity, wherein the first filler material is different than the second filler material., 'an airfoil connected to the root and formed from a first metallic material, the airfoil comprising2. The blade of claim 1 , further comprising:an opening in the first major surface; anda cover covering the opening.3. The blade of claim 2 , further comprising a socket around the opening claim 2 , wherein the cover is received in the socket.4. The blade of claim 3 , further comprising an adhesive bond between the cover and the socket5. The blade of claim 1 , wherein the first filler material and the second filler material each comprise a material selected from the group consisting of: a plastic claim 1 , a composite claim 1 , a non-metallic foam claim 1 , a solid metal claim 1 , a metallic foam claim 1 , and a gas.6. The blade of claim 1 , wherein the second filler material comprises a material selected from the group consisting of: a plastic claim 1 , a composite claim 1 , a non-metallic foam claim 1 , a solid metal claim 1 , a metallic foam claim 1 , and a gas.7. The blade of claim 5 , wherein the metallic foam is selected from the group consisting of:6XXX-series aluminum alloy, and 7XXX-series aluminum alloy.8. The blade of claim 2 , further comprising an adhesive bond ...

FAN BLADE ASSEMBLY

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil. 1. A fan blade assembly , comprising:a conductive airfoil including a forward airfoil edge;a conductive sheath including an airfoil contact surface, the airfoil contact surface coated with a nonconductive material; andan adhesive disposed on at least a portion of the nonconductive material to bond the conductive sheath to the conductive airfoil at the airfoil contact surface.2. The fan blade assembly of claim 1 , wherein the adhesive comprises a nonconductive adhesive.3. The fan blade assembly of claim 1 , wherein the adhesive comprises a conductive adhesive.4. The fan blade assembly of claim 1 , wherein the conductive airfoil is formed from an aluminum alloy.5. The fan blade assembly of claim 1 , wherein the conductive sheath is formed from a material selected from the group consisting of: titanium and titanium alloy.6. The fan blade assembly of claim 1 , wherein:the conductive airfoil further includes an airfoil forward edge, a pressure side and a suction side;the conductive sheath further includes a sheath head section and first and second flanks extending from the sheath head section; andwherein the conductive sheath covers at least a portion of the airfoil forward edge, the first flank covers at least a portion of the suction side, and the second flank covers at least a portion of the pressure side.7. The fan blade assembly of claim 1 , wherein the nonconductive material comprises a ceramic.8. The fan blade assembly of claim 1 , wherein the conductive sheath covers substantially the entire forward airfoil edge.9. The fan blade assembly of claim 1 , whereinthe conductive airfoil comprises ...

FAN BLADE TALL DOVETAIL FOR INDIVIDUALLY BLADED ROTORS

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described. 1. A blade comprising:an airfoil extending radially outwardly of a dovetail, said dovetail having edges that will be at circumferential sides of the blade when the blade is mounted within a rotor; anda bottom surface of the dovetail that will be radially inward when the rotor blade is mounted in a rotor, and said bottom surface being formed such that a circumferentially central portion of said bottom surface is radially thicker than are circumferential edges.2. The blade as set forth in claim 1 , wherein said bottom surface increases generally constantly from the circumferential edges to the central portion.3. The blade as set forth in claim 1 , wherein said bottom surface is formed on a curve.4. The blade as set forth in claim 3 , wherein said bottom surface is convex.5. The blade as set forth in claim 4 , wherein said dovetail is formed of a material that is less strong than the rotor which will receive said blade.6. The blade as set forth in claim 1 , wherein said dovetail is formed of a material that is less strong than the rotor which will receive said blade.7. The blade as set forth in claim 1 , wherein said airfoil extends from a leading edge to a trailing edge claim 1 , and has suction and pressure sides claim 1 , and the circumferential edges of said blade are generally associated with said suction and pressure sides.8. The blade as set forth in claim 1 , wherein said central portion is at a circumferential center of the dovetail.9. The blade as set forth in claim 1 , wherein said blade is a fan ...

FAN BLADE ASSEMBLY

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive ceramic coating is applied to a sheath receiving surface of the airfoil before it is bonded to the sheath. 1. A fan blade assembly , comprising:a conductive airfoil including a sheath receiving surface, the sheath receiving surface coated with a nonconductive material;a conductive sheath; andan adhesive disposed on at least a portion of the nonconductive material to bond the conductive sheath to the conductive airfoil at the sheath receiving surface.2. The fan blade assembly of claim 1 , wherein the adhesive comprises a nonconductive adhesive.3. The fan blade assembly of claim 1 , wherein the adhesive comprises a conductive adhesive.4. The fan blade assembly of claim 1 , wherein the conductive airfoil is formed from an aluminum alloy.5. The fan blade assembly of claim 1 , wherein the conductive sheath is formed from a material selected from the group consisting of: titanium and titanium alloy.6. The fan blade assembly of claim 1 , wherein:the conductive airfoil further includes an airfoil forward edge, a pressure side and a suction side;the conductive sheath further includes a sheath head section and first and second flanks extending from the sheath head section; andwherein the conductive sheath covers at least a portion of the airfoil forward edge, the first flank covers at least a portion of the suction side, and the second flank covers at least a portion of the pressure side.7. The fan blade assembly of claim 1 , wherein the nonconductive material comprises a ceramic.8. The fan blade assembly of claim 1 , wherein the conductive sheath covers substantially the entire forward airfoil edge.9. The fan blade assembly of claim 1 , whereinthe conductive airfoil comprises a first metal;the conductive sheath ...

Fan blade spacer

The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material.

Electrically grounding fan platforms

A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.

Spinner for Electrically Grounding Fan Blades

A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.

ROTARY MACHINES INCLUDING A HYBRID ROTOR WITH AN INTEGRALLY BLADED ROTOR PORTION

Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades. 1. An integrally bladed rotor portion for a hybrid rotor , the integrally bladed rotor portion comprising:a rotor disk portion having a peripheral rim configured to mechanically retain an individual rotor blade; anda blade portion comprising an integral rotor blade extending outwardly and integrally from the rotor disk portion, the individual rotor blade configured to extend radially outwardly from the rotor disk portion in a blade array with the integral rotor blade.2. The integrally bladed rotor portion of claim 1 , wherein the integral rotor blade comprises a plurality of integral rotor blades spaced around a circumference of the rotor disk portion in circumferentially spaced apart sets claim 1 , each set comprising one or more integral rotor blades.3. The integrally bladed rotor portion of claim 2 , wherein the individual rotor blade comprises a plurality of individual rotor blades spaced around the circumference of the rotor disk portion in circumferentially spaced apart sets claim 2 , each set comprising at least one individual rotor blade.4. The integrally bladed rotor portion of claim 3 , wherein each set of the one or more individual rotor blades is disposed circumferentially ...

Blade dovetail bottom

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

Fan blade dovetail and spacer

Fan blade dovetail and spacer

System comprising a rotor and a blade with a curved blade dovetail bottom

Fan blade assembly

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil.

Integrally bladed rotor portion, corresponding hybrid rotor and rotary machine

Rotary machines including a hybrid rotor (200) with an integrally bladed rotor portion (202) are provided. The integrally bladed rotor portion (202) for the hybrid rotor (200) comprises a rotor disk portion (210) and a blade portion (211). The rotor disk portion (210) has a peripheral rim configured to mechanically retain an individual rotor blade (300). The blade portion (211) comprises an integral rotor blade (220) extending outwardly and integrally from the rotor disk portion (210). The individual rotor blade (300) is configured to extend outwardly from the rotor disk portion (210) in a blade array with the integral rotor blade (220). The hybrid rotor (200) is also provided and comprises the integrally bladed rotor portion (202) and a plurality of individual rotor blades (300) extending outwardly from the rotor disk portion (210) in a blade array with a plurality of integral rotor blades (220).

Fan blade assembly

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil.

Fan blade tall dovetail for individually bladed rotors

A fan blade for a gas turbine engine includes an airfoil that defines a pressure and suction side. A neck supports the airfoil and interconnects to a dovetail by opposing radii. The dovetail includes a bearing surface tangent to one of the radii at a tangent point. The dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck. A first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90.

Spinner for electrically grounding fan blades

A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.

Fan blade spacer

The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material.

Fan blade tall dovetail for individually bladed rotors

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

Rotary machines including a hybrid rotor with an integrally bladed rotor portion

Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades.