TURBINE ROTOR BLADE

• Main Authors: JASON ADAM NEVILLE, SUMEET SONI, ROHIT CHOUHAN
• Format: Patent
• Language: English; Japanese
• Published: 01.09.2016
• 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 a turbine rotor blade with enhanced cooling and reduced tip leakage losses.SOLUTION: A turbine rotor blade (40) includes a tip portion (46) having a pressure tip wall (62), a suction tip wall (64), a tip leading edge (68), and a tip trailing edge (70), where the pressure tip wall and the suction tip wall define a trailing edge tip thickness. Also included is a squealer cavity (80) at least partially defined by the pressure tip wall and the suction tip wall, the squealer cavity including a trench (84) extending fully to the tip trailing edge to form an open flow path out of the tip trailing edge. Further included is a suction side wall (50) and a pressure side wall (48) extending from a root portion (44) of the turbine rotor blade to the tip portion, where the suction side wall and the pressure side wall define a trailing edge blade thickness, the trailing edge tip thickness being greater than the trailing edge blade thickness.SELECTED DRAWING: Figure 2 【課題】冷却の増強及び先端漏洩損失を低減したタービンロータブレードを提供する。【解決手段】タービンロータブレード（４０）は、正圧先端壁（６２）、負圧先端壁（６４）、先端前縁（６８）、及び先端後縁（７０）を有する先端部分（４６）を含み、正圧先端壁と負圧先端壁が後縁先端厚さを定める。また、正圧先端壁及び負圧先端壁によって少なくとも部分的に定められるスクイーラキャビティ（８０）を含み、該スクイーラキャビティが、先端後縁まで完全に延びて該先端後縁から外に出る開放流路を形成するトレンチ（８４）を有する。更に、タービンロータブレードの根元部分（４４）から先端部分まで延びる負圧側壁（５０）及び正圧側壁（４８）を備え、負圧側壁及び正圧側壁が後縁ブレード厚さを定め、該後縁先端厚さは、後縁ブレード厚さよりも大きい。【選択図】図２