Shroud configurations for turbine rotor blades

A rotor blade for a turbine of a gas turbine, the rotor blade comprising:

• an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges and radially between an outboard tip and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc;
• a tip shroud attached to the outboard tip of the airfoil, the tip shroud comprising:
• an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface;
• and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud;
• a seal rail protruding from the outboard surface of the tip shroud along a first axis corresponding to a radial direction to define a height, the seal rail extending along a second axis corresponding to a circumferential direction to define a length, the seal rail extending along a third axis, relative to the length, to define a narrow thickness in an axial direction;
• wherein the seal rail comprises:
• opposing and substantially planar rail faces, including a forward rail face and an aftward rail face, the narrow thickness in the axial direction being defined along a periphery of the seal rail by rail edges that span between the forward rail face and the aftward rail face;
• a cutter tooth coinciding with a cutter tooth section disposed on the seal rail, the cutter tooth section of the seal rail being axially thickened relative to the narrow thickness;
• wherein the rail edges include:
• opposing inboard and outboard rail edges, the inboard rail edge being defined at a connection between the seal rail and the outboard surface of the tip shroud, the outboard rail edge being offset from the inboard rail edge by the height of the seal rail;
• opposing rotationally leading and rotationally trailing rail edges, each of which are positioned near the shroud edge, such that the rotationally leading rail edge leads the rotationally trailing edge during operation, given the rotation direction of the rotor blade when installed in the turbine;
• a rotationally leading section that extends from the cutter tooth section to the rotationally leading rail edge;
• and
• a rotationally trailing section that extends from the cutter tooth section to the rotationally trailing rail edge;
• and
• a leakage gap, the leakage gap being configured for increasing a leakage level during operation of the turbine within which the rotor blade is installed;
• wherein the leakage gap comprises both:
• the height of the seal rail within the rotationally leading section being appreciably reduced compared to the height of the seal rail within the cutter tooth section;
• and
• the height of the seal rail within the rotationally trailing section being appreciably reduced compared to the height of the seal rail within the cutter tooth section.

A rotor blade for a turbine of a gas turbine, the rotor blade comprising:

• an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges and radially between an outboard tip and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc;
• a tip shroud attached to the outboard tip of the airfoil, the tip shroud comprising:
• an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface;
• and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud;
• seal rails protruding from the outboard surface of the tip shroud along a first axis corresponding to a radial direction to define a respective height, the seal rails including a forward seal rail that is positioned forward of and oriented substantially parallel to an aftward seal rail;
• wherein each of the seal rails extends along a second axis corresponding a circumferential direction to define a respective length;
• wherein each of the seal rails extends along a third axis, relative to the length, to define a narrow thickness in an axial direction;
• wherein each of the seal rails comprises:
• opposing and substantially planar rail faces, including a forward rail face and an aftward rail face, the narrow thickness being defined along a periphery of each seal rail by rail edges that span between each forward rail face and each corresponding aftward rail face;
• a cutter tooth having a circumferential length coinciding with a cutter tooth section disposed on each seal rail, the cutter tooth section of each seal rail comprising a circumferential section of each seal rail that is axially thickened relative to the narrow thickness of each seal rail;
• opposing rotationally leading and rotationally trailing rail edges, the rotationally leading rail edge leading the rotationally trailing edge during operation, given the rotation direction of the rotor blade when installed in the turbine;
• a rotationally leading section that extends from the cutter tooth section to a rotationally leading rail edge;
• and
• a rotationally trailing section that extends from the cutter tooth section to a rotationally trailing rail edge;
• wherein the forward seal rail comprises a substantially constant height across the cutter tooth section, the rotationally leading section, and the rotationally trailing section;
• and
• wherein the aftward seal rail comprises a leakage gap configured for increasing a leakage level during operation of the turbine in which the rotor blade is installed;
• the leakage gap comprising at least one of:
• the height of the aftward seal rail within the rotationally leading section being appreciably reduced compared to a constant height that the aftward seal rail comprises across both the rotationally trailing section and the cutter tooth section;
• and
• the height of the aftward seal rail within the rotationally trailing section being appreciably reduced compared to a substantially constant height that the aftward seal rail comprises across both the rotationally leading section and the cutter tooth section.

A rotor blade for a turbine of a gas turbine, the rotor blade comprising:

• an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges and radially between an outboard tip and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc;
• a tip shroud attached to the outboard tip of the airfoil, the tip shroud comprising:
• an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface;
• and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud;
• seal rails protruding from the outboard surface of the tip shroud along a first axis corresponding to a radial direction to define a respective height, the seal rails including a forward seal rail that is positioned forward of and oriented substantially parallel to an aftward seal rail;
• wherein each of the seal rails extends along a second axis corresponding a circumferential direction to define a respective length;
• wherein each of the seal rails extends along a third axis, relative to the length, to define a narrow thickness in an axial direction;
• wherein each of the seal rails comprises:
• opposing and substantially planar rail faces, including a forward rail face and an aftward rail face, the narrow thickness being defined along a periphery of each seal rail by rail edges that span between each forward rail face and each corresponding aftward rail face;
• a cutter tooth having a circumferential length coinciding with a cutter tooth section disposed on each seal rail, the cutter tooth section of each seal rail comprising a circumferential section of each seal rail that is axially thickened relative to the narrow thickness of each seal rail;
• opposing rotationally leading and rotationally trailing rail edges, the rotationally leading rail edge leading the rotationally trailing edge during operation, given the rotation direction of the rotor blade when installed in the turbine;
• a rotationally leading section that extends from the cutter tooth section to a rotationally leading rail edge;
• and
• a rotationally trailing section that extends from the cutter tooth section to a rotationally trailing rail edge;
• wherein the aftward seal rail comprises a substantially constant height across the cutter tooth section, the rotationally leading section, and the rotationally trailing section;
• and
• wherein the forward seal rail comprises a leakage gap, the leakage gap comprising at least one of:
• the height of the forward seal rail within the rotationally leading section being appreciably reduced compared to a constant height that the forward seal rail comprises across one of or both the rotationally trailing section and the cutter tooth section;
• and
• the height of the forward seal rail within the rotationally trailing section being appreciably reduced compared to a substantially constant height that the forward seal rail comprises across one of or both the rotationally leading section and the cutter tooth section.

A rotor blade for a turbine of a gas turbine, the rotor blade comprising:

• an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges and radially between an outboard tip and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc;
• a tip shroud attached to the outboard tip of the airfoil, the tip shroud comprising:
• an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface;
• and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud;
• seal rails protruding from the outboard surface of the tip shroud along a first axis corresponding to a radial direction to define a respective height, the seal rails including a forward seal rail that is positioned forward of and oriented substantially parallel to an aftward seal rail;
• wherein each of the seal rails extends along a second axis corresponding a circumferential direction to define a respective length;
• wherein each of the seal rails extends along a third axis, relative to the length, to define a narrow thickness in an axial direction;
• wherein each of the seal rails comprises:
• opposing and substantially planar rail faces, including a forward rail face and an aftward rail face, the narrow thickness being defined along a periphery of each seal rail by rail edges that span between each forward rail face and each corresponding aftward rail face;
• a cutter tooth having a circumferential length coinciding with a cutter tooth section disposed on each seal rail, the cutter tooth section of each seal rail comprising a circumferential section of each seal rail that is axially thickened relative to the narrow thickness of each seal rail;
• opposing rotationally leading and rotationally trailing rail edges, the rotationally leading rail edge leading the rotationally trailing edge during operation, given the rotation direction of the rotor blade when installed in the turbine;
• a rotationally leading section that extends from the cutter tooth section to the rotationally leading rail edge;
• and
• a rotationally trailing section that extends from the cutter tooth section to the rotationally trailing rail edge;
• wherein each of the forward seal rail and the aftward seal rail comprises the a leakage gap;
• wherein the leakage gap of the forward seal rail comprises at least one of:
• the height of the forward seal rail within the rotationally leading section being appreciably reduced compared to a constant height that the forward seal rail comprises across one of or both the rotationally trailing section and the cutter tooth section;
• and
• the height of the forward seal rail within the rotationally trailing section being appreciably reduced compared to a substantially constant height that the forward seal rail comprises across one of or both the rotationally leading section and the cutter tooth section;
• and
• wherein the leakage gap of the aftward seal rail comprises at least one of:
• the height of the aftward seal rail within the rotationally leading section being appreciably reduced compared to a constant height that the aftward seal rail comprises across one of or both the rotationally trailing section and the cutter tooth section;
• and
• the height of the aftward seal rail within the rotationally trailing section being appreciably reduced compared to a substantially constant height that the aftward seal rail comprises across one of or both the rotationally leading section and the cutter tooth section.