Christian M Hansen

US Patent:

7435055, Oct 14, 2008

Filed:

Mar 29, 2005

Appl. No.:

11/093162

Inventors:

Christian M. Hansen - Simpsonville SC, US
Alfred P. Matheny - Jupiter FL, US
Brian Potter - Greenville SC, US

Assignee:

Siemens Power Generation, Inc. - Orlando FL

International Classification:

F01D 5/32

US Classification:

416215, 416220 R

Abstract:

A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

US Patent:

8128354, Mar 6, 2012

Filed:

Jan 17, 2007

Appl. No.:

11/654353

Inventors:

Christian M. Hansen - Simpsonville SC, US
Friedrich T. Rogers - West Palm Beach FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F01D 1/04

US Classification:

415191, 4152093

Abstract:

A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

US Patent:

8191410, Jun 5, 2012

Filed:

Aug 28, 2009

Appl. No.:

12/549670

Inventors:

Christian Michael Hansen - Simpsonville SC, US
Douglas Giles Moody - Piedmont SC, US
Karl Dean Minto - Ballston Lake NY, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

G01M 15/14

US Classification:

7311205

Abstract:

A mechanical drive train for testing a full scale compressor rig is disclosed. The drive train can include an electric motor, a gear box, and a gas turbine. The compressor rig is coupled to the drive train between the gear box and gas turbine. The drive train can further include a torque converter for transferring torque from the electric motor to the compressor rig. The drive train is configured to test a full scale compressor rig over the entire speed and load operating range, allowing for full compressor mapping from choke to stall at full load, part load (power turn down) and partial speed conditions. The drive train can also be used to test a compressor rig or gas turbine over the full range of operability for the compressor rig or gas turbine without having to connect the gas turbine to the power grid at the power generation site.

US Patent:

20100068050, Mar 18, 2010

Filed:

Sep 12, 2008

Appl. No.:

12/209314

Inventors:

Christian Michael Hansen - Simpsonville SC, US
Roger Claude Beharrysingh - Simpsonville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 9/04

US Classification:

4152093

Abstract:

Base hooks of a vane includes an approximate two times thicker radial geometry, with dimensioning and tolerancing that results in a line-line to loose fit on the forward OD hook surface and the aft ID hook surface. Tolerances thus stack up on the opposite, non-critical surfaces of the hooks (the forward ID hook surface and the aft OD hook surface). The base of the vane is curved to match that of the casing. An interface between the vane base and the casing groove includes a metal alloy liner. Also, a wear coating is provided on the vane attachment hooks. The liner protects the casing groove from wear damage, while the hook coating and the liner provide a wear coupling between the vane base and the casing that provides a barrier between the vane bases and the casing to decrease the wear rate.

US Patent:

20180017074, Jan 18, 2018

Filed:

Jul 13, 2016

Appl. No.:

15/208913

Inventors:

- Schenectady NY, US
Nandakumar AR - Bangalore, IN
Christian Michael Hansen - Simpsonville SC, US
Jeremy Peter Latimer - Greenville SC, US

International Classification:

F04D 29/54
F04D 29/64

Abstract:

This disclosure provides systems and methods for reducing stress in vane shroud assemblies by defining a gap between adjacent portions of the airfoil and the shroud whereby stress from the securing force is relieved in a portion of the shroud. The airfoil has a distal end with a contact surface and a tenon. The shroud has a contact surface with the airfoil and accommodates the tenon. An attachment device provides the securing force between the airfoil and shroud contact surfaces through the shroud and the gap serves to reduce stress on the shroud.

US Patent:

20180010617, Jan 11, 2018

Filed:

Jul 11, 2016

Appl. No.:

15/206464

Inventors:

- Schenectady NY, US
Kenneth Damon Black - Travelers Rest SC, US
Christian Michael Hansen - Simpsonville SC, US
Donald Earl Floyd - Greenville SC, US
James Adaickalasamy - Bangalore, IN
Brett Darrick Klingler - Greenville SC, US
Khoa Dang Cao - Simpsonville SC, US
Kyle Eric Benson - Greenville SC, US
Devin Patrick Perkins - Taylors SC, US
Damian Anthony McClelland - Greenville SC, US

International Classification:

F04D 29/64
F02C 3/04
F04D 29/52
F04D 29/54
F04D 29/02
F04D 29/32

Abstract:

A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.

US Patent:

20170184021, Jun 29, 2017

Filed:

Mar 13, 2017

Appl. No.:

15/456957

Inventors:

- Schenectady NY, US
- Spring TX, US
Loren K. Starcher - Sugar Land TX, US
Sulabh K. Dhanuka - Houston TX, US
Dennis M. O'Dea - Somerset NJ, US
Samuel D. Draper - Simpsonville SC, US
Christian M. Hansen - Greenville SC, US
Todd Denman - Greenville SC, US
James A. West - Liberty Township OH, US

International Classification:

F02C 3/34
F02C 6/18
B01D 53/26
F02C 9/50
F01D 15/10
F01D 15/12
F01K 7/16
F01K 23/10
F02C 3/04
B01D 53/94

Abstract:

A system includes a gas turbine system having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compress and supply an exhaust gas to the turbine combustor. The gas turbine system also has an exhaust gas recirculation (EGR) system. The EGR system is configured to recirculate the exhaust gas along an exhaust recirculation path from the turbine to the exhaust gas compressor. The system further includes a main oxidant compression system having one or more oxidant compressors. The one or more oxidant compressors are separate from the exhaust gas compressor, and the one or more oxidant compressors are configured to supply all compressed oxidant utilized by the turbine combustor in generating the combustion products.

US Patent:

20150101347, Apr 16, 2015

Filed:

Oct 16, 2013

Appl. No.:

14/055091

Inventors:

- Schenectady NY, US
Michael James Healy - Greenville SC, US
Christian Michael Hansen - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/32

US Classification:

60805, 416220 R

Abstract:

A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.