Gas turbine blade and disk

In a gas turbine engine;

• a disk and blade arrangement comprising:
• a pair of axially spaced turbine disks;
• a plurality of radially extending blade retention fingers at the periphery of each disk;
• a plurality of blades;
• each blade having two axially spaced blade support chevrons having blade support surfaces, the plane of said support surfaces being substantially axial and at an angle between 25 degrees and 60 degrees from the radial direction;
• each of said fingers having a finger support chevron having a finger support surface contiguous with a blade support surface;
• said blade support surfaces and said finger support surfaces located on the center plane of a corresponding disk;
• each finger shaped such that the locus of the neutral axes of said finger is substantially radial and linear from the radius of the root of said finger to the radius of contact of said finger support surface with said blade support surface;
• and
• the plane of said blade support surfaces in the substantially axial direction being up to 10 degrees from the axial direction with the surfaces on each side of each chevron converging toward the radial centerline of the blade.

In a gas turbine engine;

• a disk and blade arrangement comprising:
• a pair of axially spaced turbine disks;
• a plurality of radially extending blade retention fingers at the periphery of each disk;
• a plurality of blades;
• each blade having two axially spaced blade support chevrons having blade support surfaces, the plane of said support surfaces being substantially axial and at an angle between 25 degrees and 60 degrees from the radial direction;
• each of said fingers having a finger support chevron having a finger support surface contiguous with a blade support surface;
• said blade support surfaces and said finger support surfaces located on the center plane of a corresponding disk;
• each finger shaped such that the locus of the neutral axes of said finger is substantially radial and linear from the radius of the root of said finger to the radius of contact of said finger support surface with said blade support surface;
• said blade having a hollow blade platform structure comprising;
• a blade platform;
• a radially spaced base plate;
• side plates, and one closed end;
• and
• said blade including an airfoil extending through said blade platform into the platform structure interior.

In a gas turbine engine;

• a disk and blade arrangement comprising:
• a pair of axially spaced turbine disks;
• a plurality of radially extending blade retention fingers at the periphery of each disk;
• a plurality of blades;
• each blade having two axially spaced blade support chevrons having blade support surfaces, the plane of said support surfaces being substantially axial and at an angle between 25 degrees and 60 degrees from the radial direction;
• each of said fingers having a finger support chevron having a finger support surface contiguous with a blade support surface;
• said blade support surfaces and said finger support surfaces located on the center plane of a corresponding disk;
• each finger shaped such that the locus of the neutral axes of said finger is substantially radial and linear from the radius of the root of said finger to the radius of contact of said finger support surface with said blade support surface;
• each finger having an integral T section supporting said chevron;
• the head of said T formed of a circumferentially extending web extending radially from the side of said disk remote from the other disk, and having a dimension in the circumferential direction increasing with radial distance at least to the location of said chevron;
• and
• the base of said T formed of an axial gusset extending radially from said disk, and having a dimension in the axial direction increasing with the radial distance to the location of said chevron.