Russell J Bergman

US Patent:

20110206501, Aug 25, 2011

Filed:

Feb 24, 2010

Appl. No.:

12/711327

Inventors:

Russell J. Bergman - Windsor CT, US
Scott A. Kovach - Higganum CT, US

International Classification:

F02C 7/12
B22D 25/00
B22D 31/00

US Classification:

415177, 164 691

Abstract:

A segmented engine component has multiple segments which are connected to each other via a featherseal arrangement. Each of the components has a combined featherseal slot and lightening pocket.

US Patent:

20110229305, Sep 22, 2011

Filed:

Mar 17, 2010

Appl. No.:

12/726021

Inventors:

Russell J. Bergman - Windsor CT, US
Joseph W. Bridges - Durham CT, US
Kevin R. Richter - North Haven CT, US

Assignee:

Pratt & Whitney - East Hartford CT

International Classification:

F01D 25/12
F01D 9/00
B32B 3/10

US Classification:

415115, 4152081, 4281951, 428131

Abstract:

Embodiments of a cover plate and material blank for forming the cover plate may include features and characteristics to accommodate tolerance issues in a turbine vane assembly. In one embodiment, the cover plate is formed from a material blank configured to provide the cover plate with a flexible flange area that can be secured to the turbine vane assembly. The flange area may have a range of motion that may be responsive to an installation force, which effectively modifies the configuration of the cover plate to such degree as to seal the cover plate to the turbine vane assembly.

US Patent:

20110233876, Sep 29, 2011

Filed:

Mar 25, 2010

Appl. No.:

12/731285

Inventors:

Russell J. Bergman - Windsor CT, US
James P. Chrisikos - Vernon CT, US
Leonard A. Bach - West Hartford CT, US

International Classification:

F02C 7/28
F16J 15/02
F16J 15/44

US Classification:

277628

Abstract:

A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.

US Patent:

20110236199, Sep 29, 2011

Filed:

Mar 23, 2010

Appl. No.:

12/730180

Inventors:

Russell J. Bergman - Windsor CT, US
Stephen J. Yee - Wethersfield CT, US
Leonard A. Bach - West Hartford CT, US
Lawrence J. Willey - East Hampton CT, US
Brandon W. Spangler - Vernon CT, US

International Classification:

F01D 9/02

US Classification:

4152081

Abstract:

A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.

US Patent:

20130183145, Jul 18, 2013

Filed:

Jan 17, 2012

Appl. No.:

13/351290

Inventors:

Joseph T. Caprario - Cromwell CT, US
Russell J. Bergman - Windsor CT, US
Pamela A. Humphrey - Windsor CT, US
Jonathan Perry Sandoval - East Hartford CT, US

International Classification:

F01D 11/00

US Classification:

4151737

Abstract:

A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

US Patent:

20130266416, Oct 10, 2013

Filed:

Apr 4, 2012

Appl. No.:

13/439277

Inventors:

Russell J. Bergman - Windsor CT, US
Shawn J. Gregg - Wethersfield CT, US
Michael Papple - Verdun, CA
Paul M. Lutjen - Kennebunkport ME, US
Joseph T. Caprario - Cromwell CT, US
Mohammed Ennacer - St-Hubert, CA
Thurman Carlo Dabbs - Dover NH, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 25/12
F01D 9/02

US Classification:

415 1, 415115

Abstract:

A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

US Patent:

20140000283, Jan 2, 2014

Filed:

Jul 2, 2012

Appl. No.:

13/539806

Inventors:

Brandon W. Spangler - Vernon CT, US
Russell J. Bergman - Windsor CT, US

International Classification:

F01D 25/12
F02C 7/18

US Classification:

60806, 415116, 415 1

Abstract:

A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.

US Patent:

20140000285, Jan 2, 2014

Filed:

Jul 2, 2012

Appl. No.:

13/539842

Inventors:

Russell J. Bergman - Windsor CT, US
Leonard A. Bach - West Hartford CT, US
Brandon W. Spangler - Vernon CT, US

International Classification:

F01D 9/02
F02C 7/12

US Classification:

60806, 415178

Abstract:

A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.