Brendon J Leary, Age 3740 Rockwood Dr, Greenville, SC 29605

2021032, Oct 21, 2021

Jul 31, 2018

17/263360

- Schenectady NY, US
Tyler Henson - Greenville SC, US
Brendon Leary - Greenville SC, US
Zachary Snider - Greenville SC, US
Gregory Thomas Foster - Greenville SC, US
Victor Morgan - Greenville SC, US
James Tallman - Niskayuna NY, US

F01D 5/14
F01D 5/18

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

2021025, Aug 19, 2021

Aug 31, 2018

17/270261

- Schenectady NY, US
Joseph I BLOCK - Greenville SC, US
Brendon James LEARY - Greenville SC, US
Lyndsay Marie KIBLER - Greenville SC, US

F01D 5/18

An article of manufacture includes an article body portion (); at least one pedestal (A, A, ) integrally formed with the article body portion (), and disposed at an outer periphery of (), and structurally coupled to the article body portion (); and at least one internal feature () disposed at least partially within the article body portion () and at least partially within the pedestal (A, A, ). At least a portion of the internal feature () is hollow.

2021011, Apr 22, 2021

Oct 16, 2019

16/654496

- Schenectady NY, US
Brendon James Leary - Simpsonville SC, US
Jason Adam Neville - Greenville SC, US

F04D 29/44
F01D 5/32
F01D 25/24
F04D 29/26

The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

2021004, Feb 18, 2021

Aug 13, 2019

16/539803

- Schenectady NY, US
Lyndsay Marie Kibler - Cincinnati OH, US
Brendon James Leary - Simpsonville SC, US
David Vincent Bucci - Greenville SC, US

C23C 4/01
B33Y 80/00
B33Y 10/00
F01D 5/28
F01D 5/18

A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.

2020030, Sep 24, 2020

Feb 18, 2020

16/793138

- Schenectady NY, US
Nicholas William Rathay - Rock City Falls NY, US
Brendon James Leary - Simpsonville SC, US
Gregory Terrence Garay - West Chester OH, US
Gustavo Adolfo Ledezma - Delmar NY, US
David Wayne Weber - Simpsonville SC, US
Aaron Ezekiel Smith - Hermosa Beach CA, US

F01D 5/18
F01D 5/20
F01D 5/14

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

2019005, Feb 21, 2019

Aug 18, 2017

15/680734

- Schenectady NY, US
Thomas Etter - Muhen, CH
Brendon James Leary - Simpsonville SC, US
Julius Andreas Schurb - Zurich, CH

B23K 26/342
B33Y 10/00
B33Y 30/00
B33Y 50/02
B33Y 80/00
B23K 26/082
B23K 26/08
B23K 26/144

Additive manufactured components including portions having distinct porosities, and systems/methods of forming components including portions having distinct porosities are disclosed. The components may include a first portion having a first porosity. The first portion may include a first exposure pattern of a plurality of scan vectors extending over the first portion. The first exposure pattern may define the first porosity of the first portion. The component may also include a second portion positioned adjacent the first portion. The second portion may include a second porosity greater than the first porosity of the first portion. Additionally, the second portion may include a second exposure pattern of a plurality of scan vectors extending over the second portion. The second exposure pattern may be distinct from the first exposure pattern of the first portion, and may define the second porosity of the second portion.

2019001, Jan 17, 2019

Jul 13, 2017

15/648564

- Schenectady NY, US
Thomas Earl Dyson - Niskayuna NY, US
Brendon James Leary - Simpsonville SC, US
Gregory Terrence Garay - West Chester OH, US
Gustavo Adolfo Ledezma - Delmar NY, US
David Wayne Weber - Simpsonville SC, US
Aaron Ezekiel Smith - Montgomery OH, US

F01D 5/18

An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall () enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.

2019001, Jan 17, 2019

Jul 13, 2017

15/648541

- Schenectady NY, US
Nicholas William Rathay - Rock City Falls NY, US
Brendon James Leary - Simpsonville SC, US
Gregory Terrence Garay - West Chester OH, US
Gustavo Adolfo Ledezma - Delmar NY, US
David Wayne Weber - Simpsonville SC, US
Aaron Ezekiel Smith - Montgomery OH, US

F01D 5/18
F01D 5/14

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.