General Electric Company

Lawrence Paul Timko

Sean Robert Keith

Leslie Eugene Leeke, Jr

Brian Peter Arness

Gunnar Leif Siden

David Alan Frey

Jacob Charles Perry, Ii

Robert Alan Frederick

Ivan Elmer Woltmann

Daniel John Harris

Ronald Eugene Mc Rae, Jr

Andrew Jones, Jr

Eduardo Enrique Paz

Thurmond Douglas Senter

A gas turbine engine augmentor radial fuel spray bar has a counterswirling spray bar heat shield. Two embodiments of the heat shield include one with a cambered airfoil cross-section and another with a twisted airfoil cross-section and may have varying or constant degree of camber or twist, respectively, along a radial length of the spray bar heat shield. The spray bar may have one or more spray bar fuel tubes within the heat shield, openings in the heat shield, and fuel holes in the tubes operable for injecting fuel through the openings. A gas turbine engine augmentor having a plurality of circumferentially spaced apart radial flameholders may incorporate a plurality of the augmentor radial fuel spray bars with one or more of the augmentor radial fuel spray bars circumferentially disposed between one or more circumferentially adjacent pairs of the radial flameholders.

Augmentor radial fuel spray bar with counterswirling heat shield

The first stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z value is non-dimensional along the bucket centerline coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of &plusmn;0.160 inches.

First stage turbine bucket airfoil

A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.

Step-down turbine platform

A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.

Turbine airfoil for gas turbine engine

A gas turbine engine turbine blade shrouded tip has an airfoil tip with a cross-sectional airfoil shape, a blade tip shroud attached to the tip, and a shroud cooling circuit disposed within the blade tip shroud. The shroud cooling circuit is operable for cooling substantially all of the shroud and is in fluid communication with a hollow interior of the tip. One embodiment of the invention includes two circumferentially extending forward and aft seal teeth on a radially outer shroud surface of the shroud extending in a radial direction away from the hollow interior of the tip. The shroud cooling circuit includes circumferentially extending shroud cooling passages between clockwise and counter-clockwise shroud side edges of the shroud. Forward and aft pluralities of the shroud cooling passages within the tip shroud are in fluid communication with first and second cavities respectively in the hollow interior.

Internally cooled blade tip shroud

Growing community of inventors

Fairfield, OH, United States of America

Lawrence Paul Timko