Florida Turbine Technologies, Inc.

Other

Siemens Energy, Inc.

Doosan Enerbility Co., Ltd.

Barry J Brown

Jinuk Kim

Jeff Greenberg

Kwangil Kim

Darryl S Eng

Andres Jaramillo

David M Day

Clint Mayer

Ching-Pang Lee

Robert Anthony Ress, Jr

Joseph D Brostmeyer

Russell B Jones

Frank W Huber

Anthony J Malandra

Stephen E Murray

Eric Munoz

Tyler W Sloss

Martin W Bowers

Robert A Ress Jr

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 airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade 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 blade

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.

A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. The low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft. The speed reduction gear box is positioned between and mechanically couples the high speed shaft and the low speed shaft, which allows the fan and the integrated starter/generator on the low speed shaft to operate at a lower speed than the high speed shaft.

Multi-spool geared turbofan arrangement with integrated starter/generator

A turbine with a variable inlet guide vane assembly in which the vane airfoils extend between inner and outer buttons, and in which a center of rotation of the airfoil is located aft of an aerodynamic center of pressure of the airfoil. The trailing edge of the airfoil extends into both of the buttons such that no gap is formed between the airfoil trailing edge region and a static part of the turbine during movement of the airfoil from an opened position to a closed position.

Variable low turbine vane with aft rotation axis

A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, &#x3b1;, and exit angles, &#x3b2;. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, &#x3b1;, and exit angle values, &#x3b2;, set forth in one of Tables 1, 3, 5 and 7.

Gas turbine with optimized airfoil element angles

A diffuser for a turbo machine, such as an exhaust diffuser for an industrial gas turbine engine, the diffuser including a plurality of struts connecting the inner shroud of the diffuser to the outer shroud, where the struts have trailing edges with a step shape to reduce the losses and improve the performance of the diffuser. The stepped shaped trailing edge includes three or more steps with the middle step being the longest in the chordwise direction and the remaining steps being symmetric about the chord of the strut.

Exhaust diffuser strut with stepped trailing edge

A process for adjusting a throat area (the flow capacity) between airfoils in an airfoil configuration such as a stator ring used in a small gas turbine engine. The airfoils are designed with an over-extending trailing edge forming a throat area sized such that a worst case tolerances design flow area would be achieved. A fluid with a flow rate representing the actual fluid for normal operation in the airfoil configuration is passed through the airfoil throats and the flow rate is measured. A specified portion of the leading edge of each airfoil is removed until the design flow rate through the airfoil configuration is achieved. A plurality of iterations of measuring flow rates and removing trailing edge material is performed until the design flow rate is achieved.

Growing community of inventors

Jupiter, FL, United States of America

Barry J Brown