General Electric Company

Adrian Lional Scott

John Wesley Harris, Jr

Scott Edmond Ellis

William Scott Zemitis

Michelle Jessica Iduate

Xiaoyong Fu

James Sutherland Stanley

Turbine blade tip shroud surface profiles are disclosed. Embodiments of the tip shroud include a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end of the airfoil. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading and/or trailing Z-notch of the tip shroud, and/or downstream and/or upstream side radially outer surfaces of wings of the tip shroud. The surface profiles are stated as shapes having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table.

Turbine blade tip shroud surface profiles

A platform cooling arrangement in a turbine rotor blade having a platform, wherein the rotor blade includes an interior cooling passage, and wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a first plate that resides inboard and in spaced relation to the platform underside and forming a first plenum; a second plate that resides inboard and in spaced relation to the first plate, the second plate forming a second plenum. The second plenum includes an inlet channel that connects to the high-pressure coolant region of the interior cooling passage, and the first plenum includes an outlet channel that connects to the low-pressure coolant region of the interior cooling passage.

Apparatus and methods for cooling platform regions of turbine rotor blades

A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that in operation, includes at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a plate that comprises a plate topside; a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.

A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.

Growing community of inventors

Greer, SC, United States of America

Adrian Lional Scott