turbine blade shroud

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Shroud. The continuous cooling cavity may form a labyrinth cooling circuit within the tip shroud.a tip shroud that is defined at one end of the turbine blade adjacent to the airfoil, the tip shroud having one or more hollow spaces defined therein;wherein all of the hollow spaces defined within the tip shroud are in fluid communication with each other and define a cooling cavity;wherein the airfoil includes a coolant passage defined therein, the coolant passage extending through the airfoil such that the coolant passage is in fluid communication with the cooling cavity;wherein the cooling cavity comprises a plurality of ribs formed therein, the ribs being sized and configured such that some of the ribs extend a partial way across the distance across the cooling cavity;wherein the cooling cavity comprises a pressure side cooling cavity, a suction side cooling cavity, and a coolant chamber, the coolant chamber comprising a chamber that resides substantially between the pressure side cooling cavity and the suction side cooling cavity;wherein the coolant chamber is in fluid communication with the coolant passage; andwherein the coolant chamber is in fluid communication with the pressure side cooling cavity and a suction side cooling cavity via a plurality of coolant chamber apertures.the ribs comprise elongated structures that connect the floor of the cooling cavity to the ceiling of the cooling cavity; andthe ribs are configured such that a labyrinth cooling circuit is formed within the cooling cavity.the ribs comprise a plurality of partition ribs; andthe partition ribs are sized and configured such that some of the partition ribs extend across at least a majority of the distance across the cooling cavity.the partition ribs comprise a plurality of outward extending partition ribs and a plurality of inward extending partition ribs;at least some of the outward extending partition ribs originate from a wall defining the coolant chamber and extend outwardly to a position short of an outer wall of the cooling cavity, thus defining a first gap between the outward extending partition rib and the outer wall of the cooling cavity; andat least some of the inward extending partition ribs originate from the outer wall of the cooling cavity and extend inwardly to a position short of the wall defining the coolant chamber, thus defining a second gap between the inward extending partition rib and the wall defining the coolant chamber.the outer wall of the cooling cavity is partially defined by one or more truncated ribs, the truncated ribs being substantially shorter than the partition ribs; andthe outward extending partition ribs originate from the wall defining the coolant chamber and extend to a position short of the truncated rib that defines the outer wall of the cooling cavity, thus defining a gap between the outward extending partition rib and the truncated rib.wherein the ribs comprise a plurality of partition ribs.the partition ribs comprise a plurality of outward extending partition ribs and a plurality of inward extending partition ribs;at least some of the outward extending partition ribs originate from the interior center wall and extend outwardly to a position short of an outer wall of the cooling cavity, thus defining a first gap between the outward extending partition ribs and the outer wall of the cooling cavity; andat least some of the inward extending partition ribs originate from the outer wall of the cooling cavity and extend inwardly to a position short of the interior center wall, thus defining a gap between the inward extending partition ribs and the interior center wall.the cooling cavity comprises a plurality of ribs, the ribs comprising elongated structures that connects the floor of the cooling cavity to the ceiling of the cooling cavity; andthe cooling cavity comprises a first interior wall that generally opposes a second interior wall across the cooling cavity;the ribs are configured such that some of the ribs originate at the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate at the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity; andthe ribs are sized and configured such that some of the ribs extend across at least a majority of the distance across the cooling cavity.a tip shroud positioned at one end of the turbine blade;a coolant passage that extends through the airfoil to the tip shroud; anda continuous cooling cavity being defined within the tip shroud and being in fluid communication with the coolant passage;wherein the continuous cooling cavity forms a labyrinth cooling circuit within the tip shroud;wherein the cooling cavity comprises a plurality of ribs formed therein;wherein the ribs are sized and configured such that some of the ribs extend a partial way across the cooling cavity and across at least a majority of the distance across the cooling cavity;wherein the cooling cavity comprises a pressure side cooling cavity, a suction side cooling cavity, and a coolant chamber, the coolant chamber comprising a chamber that resides substantially between the pressure side cooling cavity and the suction side cooling cavity;wherein the coolant chamber is in fluid communication with the coolant passage; andwherein the coolant chamber is in fluid communication with the pressure side cooling cavity and a suction side cooling cavity via at least one coolant chamber aperture.a plurality of hollow spaces are defined within the tip shroud;all of the hollow spaces defined in the tip shroud are in fluid communication with each other; andwherein the continuous cooling cavity comprises all of hollow spaces defined within the tip shroud.the cooling cavity comprises a plurality of ribs and a first interior wall that generally opposes a second interior wall across the cooling cavity;the ribs are configured such that some of the ribs originate at the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate at the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity; andthe ribs are arranged such that the placement of a rib that originates on the first interior wall of the cooling cavity generally alternates with the placement of a rib that originates on the second interior wall of the cooling cavity.ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS).MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTINGMACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINESNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. In some cases, the worn projections 21 may be overlayed with a different material from the seals 18 and notches 20 since less wear occurs to these surfaces.A wear resistant overlay may also be metallurgically bonded onto notches 20 of new blades to prevent wear in the first place.By way of example, as illustrated in Fig.

§119 to European Application No. A turbine blade as set forth in any claims 1 to 7 characterized in that said wear resistant surface is characterized in being highly resistant to spalling and chipping and in having a minimum of dilution with said alloy of said shroud.9. The shrouded tidal turbine is an emerging tidal stream technology that has a turbine enclosed in a venturi shaped shroud or duct (ventuduct), producing a sub atmosphere of low pressure behind the turbine.

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