MATTHEW DURHAM COLLIER
Pilots at Wild Horse Crk Dr, Simpsonville, SC

2013014, Jun 6, 2013

Dec 1, 2011

13/308927

Matthew Durham Collier - Simpsonville SC, US
Anthony Louis Giglio - Simpsonville SC, US
Gayathri Puram - Bangalore, IN

GENERAL ELECTRIC COMPANY - Schenectady NY

F01D 5/18

416 1, 416 97 R

A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.

2012012, May 17, 2012

Nov 17, 2010

12/948364

Stephen Paul WASSYNGER - Simpsonville SC, US
Daniel Howard TRAGESSER - Simpsonville SC, US
Matthew Durham COLLIER - Simpsonville SC, US

General Electric Company - Schenectady NY

F01D 5/26

416190

A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.

2013007, Mar 21, 2013

Sep 19, 2011

13/235765

Matthew Durham Collier - Simpsonville SC, US
Gayathri Puram - Bangalore, IN
Paul Kendall Smith - Simpsonville SC, US

F01D 5/14

416223 A

A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

2012012, May 17, 2012

Nov 11, 2010

12/944209

Mark Steven Honkomp - Taylors SC, US
Matthew Durham Collier - Simpsonville SC, US
Jason Douglas Herzlinger - Greenville SC, US

GENERAL ELECTRIC COMPANY - Schenectady NY

F01D 5/26

416190

A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.

2012023, Sep 20, 2012

Mar 17, 2011

13/050440

Bradley BOYER - Greenville SC, US
Matthew D. COLLIER - Simpsonville SC, US

GENERAL ELECTRIC COMPANY - Schenectady NY

F01D 5/30

416221

A bucket for a turbomachine rotor wheel includes an airfoil portion, a shank portion and a dovetail mounting portion, the shank portion including opposite sides, one of the sides formed with a substantially axially-oriented groove extending between forward and aft ends of the shank portion. The other one of the opposite sides is formed with at least one substantially radially-oriented groove. The substantially axially-oriented groove is adapted to receive an elongated damper pin, and the at least one substantially radially-oriented groove is adapted to receive an elongated radial seal pin.

2012019, Aug 2, 2012

Jan 28, 2011

13/015747

Sanjeev Kumar Jain - Bangalore, IN
Rajnikumar Nandalal Suthar - Vadodara, IN
Matthew Durham Collier - Simpsonville SC, US

F01D 11/08, B22C 9/10, B22D 25/02

4151731, 164 6

A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance.

7731482, Jun 8, 2010

Jun 13, 2006

11/423789

Benjamin Arnette Lagrange - Greer SC, US
Randall Richard Good - Simpsonville SC, US
Gary Charles Liotta - Simpsonville SC, US
Jon Robert DeLong - Simpsonville SC, US
Matthew Durham Collier - Simpsonville SC, US
James William Vehr - Travelers Rest SC, US
Anthony Aaron Chiurato - Simpsonville SC, US

General Electric Company - Schenectady NY

F01D 5/26

416190, 416193 A, 416500

A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.