Patrick J Mohr

US Patent:

7476085, Jan 13, 2009

Filed:

Jun 28, 2006

Appl. No.:

11/476097

Inventors:

Patrick J. Mohr - Greer SC, US
Emilio Fernandez - Taylors SC, US
Anil B. Rajanna - Karnataka State, IN
Seerangan Murugesan - Karnataka State, IN
Kamlesh Dewangan - Kranataka State, IN

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/30

US Classification:

416219R, 416248

Abstract:

Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

US Patent:

7556477, Jul 7, 2009

Filed:

Oct 4, 2005

Appl. No.:

11/163067

Inventors:

Graham D. Sherlock - Greenville SC, US
Daniel A. Nowak - Greenville SC, US
Stephen J. Balsone - Simpsonville SC, US
Patrick J. Mohr - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/28

US Classification:

416224, 416228

Abstract:

A tip cap for use in a turbine bucket. The tip cap may include a shield of an oxidant resistant material and a cap positioned within the shield of a high strength material.

US Patent:

7771171, Aug 10, 2010

Filed:

Dec 14, 2006

Appl. No.:

11/638818

Inventors:

Patrick Mohr - Greer SC, US
Daniel Nowak - Greenville SC, US
Emilio Fernandez - Taylors SC, US
Michael Arnett - Simpsonville SC, US
David Williams - Seneca SC, US
Carlos Collado - Moore SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/22

US Classification:

416191, 416196 R, 416212 A, 416224

Abstract:

A system in a turbine engine for preventing wear on a tip shroud of a turbine blade that includes a pocket formed in a contact surface of the tip shroud and a plug that fits within the pocket and has a durable outer surface. The durable outer surface may include a cobalt-based hardfacing powder. The pocket may be machined out of the contact surface, and the plug may include a plug of predetermined size that fits snugly into the pocket. In some embodiments, the durable outer surface may substantially align with the contact surface after the plug is fitted into the pocket. In other embodiments, the durable outer surface may remain slightly raised from the contact surface after the plug has been fitted into the pocket.

US Patent:

20020090584, Jul 11, 2002

Filed:

Jan 5, 2001

Appl. No.:

09/755582

Inventors:

Patrick Mohr - Rockford IL, US

International Classification:

F23M003/04

US Classification:

431/010000

Abstract:

A liquid fuel burner comprising a burner tip outputs a thin ring of oil that may be more easily atomized by the flow of atomizing oxidant at lower pressures. The liquid fuel burner comprises a fuel conduit and an atomizing oxidant conduit coaxial about the fuel conduit. The fuel conduit and atomizing oxidant conduit output fuel and oxidant into a furnace through the burner tip. The burner tip includes a central dispersion head in the output end of the fuel conduit which operates to fan the liquid fuel oil outward into a thin fan shaped ring that then is atomized by the surrounding flow of high velocity oxidant.

US Patent:

20080101939, May 1, 2008

Filed:

Oct 26, 2006

Appl. No.:

11/586793

Inventors:

William Zemitis - Simpsonville SC, US
Steve Byam - Fountain Inn SC, US
Patrick Mohr - Greer SC, US

International Classification:

F01D 5/30

US Classification:

416219 R

Abstract:

A turbine blade that may include an airfoil and a blade dovetail, the blade dovetail being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail may include a dovetail backcut sized and positioned according to blade geometry to maximize a balance between stress reduction on the disk, stress reduction on the blade, a useful life of the turbine blade, and maintaining or improving the aeromechanical behavior of the turbine blade. A start point of the dovetail backcut, which defines a length of the dovetail backcut along a dovetail axis, may be determined relative to a datum line positioned a fixed distance from a forward face of the blade dovetail along a centerline of the dovetail axis. The start point of the dovetail backcut may be at least approximately 1.215 inches in an aft direction from the datum line.

US Patent:

58237690, Oct 20, 1998

Filed:

Mar 26, 1996

Appl. No.:

8/622014

Inventors:

Mahendra L. Joshi - Altamonte Springs FL
Patrick J. Mohr - Mims FL

Assignee:

Combustion Tec, Inc. - Apopka FL

International Classification:

F27D 1700

US Classification:

432181

Abstract:

A process and apparatus for combustion of a fuel and oxidant in which a first portion of a fuel is mixed with an oxidant to form a fuel-lean fuel/oxidant mixture in a fuel-lean combustion zone. The remaining portion of fuel is mixed with the fuel-lean fuel/oxidant mixture downstream of the fuel-lean combustion zone, forming a substantially stoichiometric fuel/oxidant mixture. The stoichiometric fuel/oxidant mixture is ignited, forming a primary flame having high luminosity and low NO. sub. x emissions.

US Patent:

61767026, Jan 23, 2001

Filed:

Apr 7, 1999

Appl. No.:

9/287455

Inventors:

Patrick J. Mohr - Mims FL
David S. Neff - Longwood FL
Joseph G. Gaddone - Oviedo FL
Jack L. Nitzman - Altamonte Springs FL

Assignee:

Combustion Tec - Apopka FL

International Classification:

F23C 506

US Classification:

431186

Abstract:

A remotely controllable gaseous fuel burner having a burner body with a fuel inlet, a fuel outlet, and a constricted throat region immediately upstream of the fuel outlet. A concentrically disposed and longitudinally movable fuel conduit is disposed within the burner body forming an annular region between the burner body and the fuel conduit. The fuel conduit having a conduit fuel outlet forms a conduit fuel inlet in a wall of the fuel conduit. The outer surface of the conduit fuel outlet immediately upstream of the conduit fuel outlet is tapered and has an outside diameter larger than the inside diameter of the constricted throat.

US Patent:

55671411, Oct 22, 1996

Filed:

Aug 9, 1995

Appl. No.:

8/512956

Inventors:

Mahendra L. Joshi - Altamonte Spring FL
Lee Broadway - Eustis FL
Patrick J. Mohr - Mims FL
Jack L. Nitzman - Altamonte Spring FL

Assignee:

Combustion Tec, Inc. - Apopka FL

International Classification:

F23C 500

US Classification:

431 8

Abstract:

A method and apparatus for combustion of a liquid fuel and oxygen which produces a fishtail or fan-shaped flame configuration.