Victor Silva Deceased139 Melrose Ave, Needham, MA 02492

8092163, Jan 10, 2012

Mar 31, 2008

12/058972

Jason David Shapiro - Methuen MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

General Electric Company - Schenectady NY

F01D 25/28

415189, 4152092, 4152093, 4152131

A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

8172522, May 8, 2012

Mar 31, 2008

12/058980

Jason David Shapiro - Methuen MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

General Electric Company - Schenectady NY

F01D 25/28

415189, 4152092, 4152093, 4152131

A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

8235652, Aug 7, 2012

Dec 29, 2007

11/967177

Mark Broomer - Boston MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

General Electric Company - Schenectady NY

F01D 9/06

415115

A turbine nozzle segment includes a band having a flowpath side and a non-flowpath side and an enclosure disposed on the non-flowpath side of the band. A plenum may be defined between the band and the enclosure and a discourager may extend from the enclosure.

8296945, Oct 30, 2012

Dec 29, 2007

11/967178

Mark Broomer - Boston MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

General Electric Company - Schenectady NY

B23P 6/00

298891, 2988922, 2940208, 415115

A method for repairing a turbine nozzle segment includes providing a turbine nozzle segment having an enclosure with an integral discourager, removing the enclosure and/or the discourager from the turbine nozzle segment and attaching a new enclosure ad/or discourager to the turbine nozzle segment.

2012010, May 3, 2012

Oct 29, 2010

12/915223

George Joe-Kueng Chan - Salem MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

F04D 29/42

4151821

A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.

2013010, May 2, 2013

Oct 31, 2011

13/285783

Robert Francis Manning - Newburyport MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

F01D 5/18
B23P 15/02

416 97 R, 29889721

An airfoil includes a leading edge, a trailing edge, and a pair of sides extending from the leading edge to the trailing edge. The airfoil also includes an internal cooling flow passage defined between the sides, wherein the passage has a passage axis along which cooling air is to flow. The airfoil further includes a plurality of flow paths extending through at least one of the sides such that the flow paths are configured to discharge cooling air from the passage, wherein each of the flow paths has a broken flow path axis oriented to intersect the passage axis at an acute angle.

2021027, Sep 9, 2021

May 20, 2021

17/325650

- Schenectady NY, US
Gregory Michael LASKOWSKI - Rowley MA, US
Robert PROCTOR - West Chester OH, US
Curtis STOVER - Mason OH, US
Robert Francis Manning - Newburyport MA, US
Victor Hugo Silva CORREIA - Milton Mills NH, US
Jared Peter BUHLER - Tewksbury MA, US
Robert Carl MURRAY - Rotterdam NY, US
Corey BOURASSA - Mechanicville NY, US
Jonathan Russell RATZLAFF - Loveland OH, US

B01D 45/16
F02C 7/18
B04C 3/06
F02C 6/08
F01D 5/18
F01D 9/06
F02C 7/052

A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

2019006, Feb 28, 2019

Aug 22, 2017

15/683332

- Schenectady NY, US
Donald Brett DeSander - Arlington MA, US
Victor Hugo Silva Correia - Milton Mills NH, US

F01D 5/22
F01D 5/28

A turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.