APPARATUS, SYSTEM AND/OR METHOD FOR COOLING TURBINE ROTOR BLADE PLATFORM

• Main Authors: SMITH AARON EZEKIEL, ELLIS SCOTT EDMOND
• Format: Patent
• Language: English
• Published: 18.07.2013
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

PROBLEM TO BE SOLVED: To provide an apparatus, a system and/or a method for cooling a turbine rotor blade platform.SOLUTION: There is disclosed a platform cooling arrangement in a turbine rotor blade having a platform at a joined part between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, wherein a suction side of the platform comprises a topside extending circumferentially from the airfoil to a suction side slash face, and wherein the suction side of the platform comprises an aft edge. The platform cooling arrangement includes: a manifold positioned within the aft side of the suction side of the platform; a high-pressure connector that connects the manifold to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the manifold to the low-pressure coolant region of the interior cooling passage; and a heat transfer structure positioned within the manifold.