Abstract: A fir tree structure is provided and includes a part extending radially inwardly from a rotating part and having an inward taper. The part has a spline profile forming fixing lobes and necks, which are interleaved with the fixing lobes. The spline profile has constantly changing radii of curvature characterized in that the radii of curvature are relatively reduced in high stress locations and relatively increased in low stress locations.

Abstract: An apparatus is provided for a turbine engine. This apparatus includes a rotor blade configured to rotate about an axis. The rotor blade includes a base and an airfoil. The base includes a platform, an attachment, a pocket and a contoured side surface. The pocket is located radially between the platform and the attachment. The pocket projects radially outward into the base and along the contoured side surface to the platform. The pocket extends axially within the base and along the contoured side surface between opposing axial ends of the pocket. The pocket projects laterally into the base to the contoured side surface. The contoured side surface includes a plurality of convex sections arranged axially along the axis between the opposing axial ends of the pocket. The airfoil projects radially outward from the platform to a tip of the airfoil.

Abstract: A rotor assembly includes a disk and a blade. The disk is rotatable about an axis that includes a plurality of slots distributed circumferentially along an outer periphery of the disk. The blade includes an airfoil and a root extending radially inward from the airfoil that is received in one of the slots. The disk and the root have an axial widths that define a variable rim width profile. The variable rim width profile includes a minimum rim width disposed radially outward from a bottom lobe of the root.

Abstract: A blade for mounting on a rotor disc of a turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

Abstract: A rotor blade includes an airfoil, a root, a cooling air passage and a cooling air deflector. The root extends axially along an axis between a first end of the root and a second end of the root. The root extends laterally between a first side of the root and a second side of the root. The root projects radially inward and away from the airfoil to an inner end of the root. The cooling air passage includes a passage inlet disposed at the inner end. The cooling air passage projects radially into the rotor blade from the passage inlet. The cooling air deflector projects radially inward from the inner end of the root to an inner end of the cooling air deflector. The cooling air deflector is disposed at the second side and is spaced laterally from the first side. The cooling air deflector includes a cooling air aperture.

Abstract: A fir tree structure is provided and includes a part extending radially inwardly from a rotating part and having an inward taper. The part has a spline profile forming fixing lobes and necks, which are interleaved with the fixing lobes. The spline profile has constantly changing radii of curvature characterized in that the radii of curvature are relatively reduced in high stress locations and relatively increased in low stress locations.

Abstract: A rotor assembly includes a disk and a blade. The disk is rotatable about an axis that includes a plurality of slots distributed circumferentially along an outer periphery of the disk. The blade includes an airfoil and a root extending radially inward from the airfoil that is received in one of the slots. The disk and the root have an axial widths that define a variable rim width profile. The variable rim width profile includes a minimum rim width disposed radially outward from a bottom lobe of the root.

Abstract: A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.

Abstract: A fir tree structure is provided and includes a part extending radially inwardly from a rotating part and having an inward taper. The part has a spline profile forming fixing lobes and necks, which are interleaved with the fixing lobes. The spline profile has constantly changing radii of curvature characterized in that the radii of curvature are relatively reduced in high stress locations and relatively increased in low stress locations.

Abstract: A blade for mounting on a rotor disc of a turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

Abstract: A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.

Abstract: A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.

Abstract: A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

Abstract: A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

Abstract: The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.

Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.