Mark G Wotzak

US Patent:

20130283758, Oct 31, 2013

Filed:

Mar 11, 2013

Appl. No.:

13/793266

Inventors:

Mark Gregory Wotzak - Somerville MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/06

US Classification:

60 3908

Abstract:

The present disclosure involves an oil scoop manifold receives and directs the oil in fore and aft directions to lubricate multiple bearing assemblies.

US Patent:

7258746, Aug 21, 2007

Filed:

Mar 24, 2005

Appl. No.:

10/907217

Inventors:

Mark G. Wotzak - Watervliet NY, US

Assignee:

U.S. Government as represented by the Secretary of the Army - Washington DC

International Classification:

C23C 14/56
C23C 16/54

US Classification:

118 50, 118715, 118DIG 10, 427181, 427238, 427294

Abstract:

A coating apparatus includes a cylindrical holding chamber having open ends, an opening formed in an inner surface and an inner diameter; a specimen having a curved inner surface with a radius of curvature that is equal to one half the inner diameter of the cylindrical holding chamber, the specimen having a size such that, when inserted in the opening in the inner surface of the cylindrical holding chamber, the inner surface of the cylindrical holding chamber and the curved inner surface of the specimen form a continuous surface; a counter bore formed radially outward from the opening in the inner wall of the cylindrical holding chamber; at least one evacuation hole extending from an interior of the cylindrical holding chamber through a wall of the cylindrical holding chamber to the counter bore; a flat formed on an exterior surface of the cylindrical holding chamber around the counter bore; and fastener holes formed around the counter bore and extending from the flat into the wall of the cylindrical holding chamber.

US Patent:

20190061965, Feb 28, 2019

Filed:

Aug 22, 2017

Appl. No.:

15/682834

Inventors:

- Schenectady NY, US
Martin Miles D'Angelo - Boston MA, US
Daniel Waslo - Marblehead MA, US
Brian Lewis Devendorf - Georgetown MA, US
Mark Gregory Wotzak - Chestnut Hill MA, US

International Classification:

B64D 27/26
F02C 7/20
F01D 25/28

Abstract:

An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.

US Patent:

20180347471, Dec 6, 2018

Filed:

May 31, 2017

Appl. No.:

15/609338

Inventors:

- Schenectady NY, US
Mark Gregory Wotzak - Chestnut Hill MA, US

International Classification:

F02C 7/32
F02C 7/275
F16H 1/22

Abstract:

The present disclosure is directed to a gas turbine engine including an engine shaft rotatable with at least one of a fan section, a compressor section, or a turbine section, and an accessory gearbox assembly including a towershaft, a first gearbox, a torque transfer assembly, and a second gearbox. The towershaft is rotatable with the engine shaft and extended therefrom and mechanically coupled to the first gearbox. The first gearbox transmits mechanical energy from the engine shaft via a first shaft defining a first end and a second end. The first shaft extends at the first end from the first gearbox and through the torque transfer assembly and coupled thereto. The first shaft extends from the torque transfer assembly to the second gearbox at the second end and is coupled thereto. The first gearbox and the second gearbox each are coupled to one or more gearbox accessories.

US Patent:

20180216527, Aug 2, 2018

Filed:

Jan 27, 2017

Appl. No.:

15/417937

Inventors:

- Schenectady NY, US
Mark Gregory Wotzak - Chestnut Hill MA, US
Michael Macrorie - Winchester MA, US

International Classification:

F02C 7/042
F02C 3/04
F01D 25/30
F04D 29/32
F04D 29/54
F04D 29/56

Abstract:

A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.

US Patent:

20180016982, Jan 18, 2018

Filed:

Jul 15, 2016

Appl. No.:

15/211474

Inventors:

- Schenectady NY, US
Mark Gregory Wotzak - Chestnut Hill MA, US

International Classification:

F02C 7/047
B64D 27/12
F01D 25/10
F02C 3/04
F01D 25/14
B64D 33/02

Abstract:

An annular air inlet duct circumscribing an axis of rotation of a rotatable member of a machine comprising a forward end and an aft end is described. The air inlet duct includes an unheated wall and a heated wall adjacent to a heat source. The heated wall includes a plurality of axially-spaced wall panels forming a cavity between each of a pair of adjacent wall panels of the plurality of axially-spaced wall panels.

US Patent:

20170314468, Nov 2, 2017

Filed:

Apr 29, 2016

Appl. No.:

15/141917

Inventors:

- Schenectady NY, US
Mark Gregory Wotzak - Chestnut Hill MA, US

International Classification:

F02C 7/06
F01M 11/00
F02C 3/04

Abstract:

The present disclosure is directed to a sump housing for a gas turbine engine. The sump housing includes a base portion and a first wall extending outwardly from the base portion. The first wall and the base portion at least partially define an inner chamber. A second wall is positioned outwardly from the first wall and extends outwardly from the base portion. The base portion, the first wall, and the second wall at least partially define an outer chamber positioned outwardly from the inner chamber. A projection extending inwardly from the first wall engages a bearing assembly. The base portion, the first wall, the second wall, and the projection are integrally coupled together.

US Patent:

20170314474, Nov 2, 2017

Filed:

Apr 28, 2016

Appl. No.:

15/140532

Inventors:

- Schenectady NY, US
Mark Gregory Wotzak - Chestnut Hill MA, US

International Classification:

F02C 7/32
F02K 3/06
F16H 57/04

Abstract:

An in-line propeller gearbox of a turboprop gas turbine engine includes a lubricant reservoir disposed spaced radially offset from the engine's central axis of rotation and asymmetrically with respect to the central axis of rotation such that the central axis of rotation does not extend through the lubricant reservoir.