Abstract: The present specification generally relates to a composition for the manufacture of bio-degradable, bio-compostable, ocean degradable, biocompatible articles that contain a bio-based thermoplastic component. In particular, it has been found, in accordance with the practice of this invention, that marked improvement in tensile strength, toughness and elongation of polyhydroxy alkanoate (PHA) can be achieved by dispersing in the PHA an elastomer, using a compatibilizer, and then optionally cross-linking the dispersed elastomer, The polyhydroxy alkanoate elastomer blends of the present invention comprise from 20-99 percent by weight of the PHA, from 3-40 percent by weight of the elastomer and 2-25 percent by weight of compatibilizer and can be used to produce a wide array of articles that as they degrade release active natural polymers that are beneficial to growth performance, intestinal digestive and immune function of an animal that may have ingested the article.

Abstract: A repaired oxidation and corrosion resistant coating may comprise a repair material applied to a damaged portion of the oxidation and corrosion resistant coating. The repair material may be free of hexavalent chromium and may be compatible with a plurality of oxidation and corrosion resistant materials that comprise hexavalent chromium. The repair material may be burnished. The oxidation and corrosion resistant coating may comprise hexavalent chromium.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A cover plate for a rotor assembly is disclosed. In various embodiments, the cover plate includes an annular member having a radially inner portion and a radially outer portion with respect to a longitudinal axis, the radially inner portion including an aft face and an angled forward face, the angled forward face defining a forward face angle with respect to a cylindrical plane that is coaxial with the longitudinal axis, the face angle having a value that is greater than or equal to fifty degrees; a first tab and a second tab disposed proximate the radially inner portion of the annular member; and a slot disposed between the first tab and the second tab.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore disposed about the central axis, a rim and a web disposed radially between the bore and the rim. The bore has a fore surface and an aft surface. The aft surface of the bore may include an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and an aft base transition portion radially inward of the aft ramp portion. The fore surface of the bore may include a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and a fore base transition portion radially inward of the fore ramp portion. The aft ramp portion includes a substantially linear portion and the fore ramp portion includes a substantially linear portion.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.

Abstract: A cover plate for a rotor assembly is disclosed. In various embodiments, the cover plate includes an annular member having a radially inner portion and a radially outer portion with respect to a longitudinal axis, the radially inner portion including an aft face and an angled forward face, the angled forward face defining a forward face angle with respect to a cylindrical plane that is coaxial with the longitudinal axis, the face angle having a value that is greater than or equal to fifty degrees; a first tab and a second tab disposed proximate the radially inner portion of the annular member; and a slot disposed between the first tab and the second tab.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore disposed about the central axis, a rim and a web disposed radially between the bore and the rim. The bore has a fore surface and an aft surface. The aft surface of the bore may include an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and an aft base transition portion radially inward of the aft ramp portion. The fore surface of the bore may include a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and a fore base transition portion radially inward of the fore ramp portion. The aft ramp portion includes a substantially linear portion and the fore ramp portion includes a substantially linear portion.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A repaired oxidation and corrosion resistant coating may comprise a repair material applied to a damaged portion of the oxidation and corrosion resistant coating. The repair material may be free of hexavalent chromium and may be compatible with a plurality of oxidation and corrosion resistant materials that comprise hexavalent chromium. The repair material may be burnished. The oxidation and corrosion resistant coating may comprise hexavalent chromium.

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.