Other

Doosan Enerbility Co., Ltd.

David M Day

Darryl S Eng

Kwangil Kim

Jinuk Kim

Jeff Greenberg

Barry J Brown

Jason Kopko

Gene Chong

William T Pope

Bryan C Bernier

JaeBin Lee

Hongseung Seo

YeJee Kim

Younggi Mun

A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a hollow airfoil including a plurality of cavities positioned in the airfoil, an insert positioned in one or more of the plurality of cavities of the hollow airfoil, a plurality of cover plates, at least one of which is positioned at one of the inner diameter and at the outer diameter, and a plurality of impingement pans, at least one of which is positioned at one of the inner diameter and at the outer diameter.

Turbine nozzle assembly and gas turbine including the same

An internal core profile for a turbine nozzle airfoil of a gas turbine is provided. The turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

Internal core profile for a turbine nozzle airfoil

An internal core profile for a second stage turbine nozzle airfoil of a gas turbine is provided. The turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

An airfoil profile for a second stage turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

An airfoil profile for a turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Airfoil profile for a turbine nozzle

A support for a gas prop (hydraulic strut) for a vehicle access door includes an elongate sleeve that is positionable around the cylinder and rod of the gas prop. The support secures a weak or otherwise defective gas prop in its position in which the vehicle access door is held open. The elongate sleeve includes a first and second end. The first end of the elongate sleeve is adapted to be selectively positioned between: (1) abutting the distal end of the cylinder, and (2) coaxially receiving at least a portion of the length of the cylinder. One or more slots are defined at the second end of the elongate sleeve. Each of the slots is selectively engageable with the shaft or post of an attachment bracket for coupling the rod end to the vehicle. Additionally, each one of the slots is a different length, thereby accommodating various lengths of gas props.

Growing community of inventors

Cambridge City, IN, United States of America

David M Day