General Electric Company

Ge Infrastructure Technology, LLC

Daniel Robert Burnos

Ibrahim Sezer

Zachary John Snider

Gregory Thomas Foster

Jacob John Kittleson

Bradley James Miller

Johnathan Ray Wallen

Katherine Courtlyn Macmanus

Brian Gene Brzek

Lana Maria Osusky

Alexander Stein

Lee Larned Brozyna

Pradeep Jagannath Ghute

Allison Christine Gose

The present disclosure provides a turbine shroud with a cooling circuit and turbomachine with the subject turbine shroud. The turbine shroud includes a body with a rib thereon. The rib extends between a first and second sidewall of the body, the sidewalls extending between a forward end and an aft end of the body. The body is coupled to a turbomachine casing or an intermediate component for coupling the body to the turbomachine casing. A cooling circuit within the body is in fluid communication with a cooling chamber adjacent the body. The cooling circuit includes a plurality of inlet passages extending through the rib of the body, and a plurality of outlet passages fluidly coupled to the inlet passage and extending through an external surface of the body. The cooling circuit also includes a first plenum within the rib and in fluid communication with the plurality of inlet passages.

Turbine shroud and turbomachine with cooling circuit

The present disclosure provides a turbine shroud with a cooling circuit and turbomachine with the subject turbine shroud. The turbine shroud includes a body with a structural member thereon. The body is coupled to a turbomachine casing or an intermediate component for coupling the body to the turbomachine casing. A cooling circuit within the body is in fluid communication with a cooling chamber adjacent the body. The cooling circuit includes an inlet passage extending through the structural member of the body, and an outlet passage fluidly coupled to the inlet passage and extending through an external surface of the body.

A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed.

Turbine nozzle airfoil and/or trailing edge profile

A core for use in cooling a component used in a rotary machine is provided. The core includes a passage including a divider separating a first inlet portion and a second inlet portion to define a split pass inlet, which is fluidly coupled to at least one first pass, at least one second pass, and at least one turn. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged, such that the passage defines a serpentine passage.

Systems and methods for cooling an endwall in a rotary machine

A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.

System and method for near wall cooling for turbine component

A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.

The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Turbine nozzle airfoil profile

A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and are arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and are arranged along the second side portion. Each set of cooling air micro-channels has at least one transition manifold in fluid communication with an adjacent micro-channel and also in fluid communication with at least one of an intake end, an exhaust end, and mixtures thereof. The cooled structure described above is also embodied in a gas turbine.

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Greer, SC, United States of America

Daniel Robert Burnos