Raymond F Martell, 44530 Larchmont Dr, Cincinnati, OH 45215

2020028, Sep 10, 2020

Mar 5, 2019

16/292642

- Schenectady NY, US
Raymond Floyd Martell - Wyoming OH, US

F02K 3/072
F02C 3/067

A thrust balancing gear assembly for a turbo machine is provided. The gear assembly includes an input gear connected to an input drive shaft, an output gear connected to an output drive shaft, and a compound planet gear including a first planet gear and a second planet gear each connected to one another and positioned in axially adjacent arrangement. The first planet gear is connected to the input gear at a first interface and the second planet gear is connected to the output gear at a second interface.

2019037, Dec 12, 2019

Jun 8, 2018

16/003988

- Schenectady NY, US
Sathyanarayanan Raghavan - Ballston Lake NY, US
Ken Salas Nobrega - Schenectady NY, US
Arunkumar Natarajan - Niskayuna NY, US
Vadim Bromberg - Schenectady NY, US
Raymond Floyd Martell - Cincinnati OH, US
Meghan J. Borz - Buena NJ, US

B22F 3/00
B33Y 10/00
B33Y 80/00
B22F 3/24
B33Y 40/00
B28B 1/00
B28B 11/24

A binder jet printed article includes a part having a top portion, a bottom portion, and an overhang extending from the top portion and a support structure formed around the part that may block deformation of the part during post-printing thermal processing. The support structure includes a skid positioned adjacent to the bottom portion that may support the part, a first plurality of support features disposed along an outer perimeter of the skid, and a second plurality of support features disposed on the top portion of the printed part. The first and second plurality of support features form a lattice around the printed part such that the printed part is nested within the support structure.

2019024, Aug 15, 2019

Feb 9, 2018

15/892735

- Schenectady NY, US
Joshua Tyler Mook - Loveland OH, US
Raymond Floyd Martell - Wyoming OH, US
Changjie Sun - Clifton Park NY, US
Gautam Naik - Schenectady NY, US
Jordan Paule Tesorero - Lynn MA, US
Aigbedion Akwara - Cincinnati OH, US

F01D 25/24
F01D 9/04
F01D 25/28
B33Y 80/00

Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub. The turbine center frame further comprises an annular fairing extending between the outer case and the hub, a ligament extending from the fairing to the outer case to connect the fairing to the outer case, a plurality of struts extending from the hub to the outer case, and a boss structure defined on an outer surface of the outer case. The outer case, hub, fairing, ligament, plurality of struts, and boss structure are integrally formed as a single monolithic component. For instance, the turbine center frame is additively manufactured as an integral structure, and methods for manufacturing turbine center frames also are provided.

2019020, Jul 4, 2019

Jan 4, 2018

15/861802

- Schenectady NY, US
Brandon Wayne Miller - Liberty Township OH, US
Raymond Floyd Martell - Wyoming OH, US
Jeffrey Douglas Rambo - Mason OH, US
Ryan James Matthys - South Lebanon OH, US
Joel Francis Kirk - Monroe OH, US

F02C 7/143
F02C 7/18
F01D 5/08
F02C 3/06
F23R 3/28
F01D 9/06

A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.

2019017, Jun 6, 2019

Feb 7, 2019

16/269623

- Schenectady NY, US
Raymond Floyd Martell - Wyoming OH, US

F16H 57/04
F28D 7/00
F02C 7/32
F16H 57/02
B64D 33/08
F01D 25/12
F02C 7/14

A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.

2019001, Jan 17, 2019

Jul 12, 2017

15/647380

- Schenectady NY, US
Raymond Floyd Martell - Wyoming OH, US
Mark Leonard Hopper - West Chester OH, US
Scott Douglas Waun - Loveland OH, US

F02C 6/18
F02C 3/04
F02C 7/36

A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.

2018016, Jun 14, 2018

Dec 12, 2016

15/375348

- Schenectady NY, US
Raymond Floyd Martell - Wyoming OH, US

F16H 57/04
F16H 57/02
F02C 7/32
F02C 7/36
F01D 25/12

A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.

2017034, Nov 30, 2017

May 26, 2016

15/164946

- Schenectady NY, US
Raymond Floyd Martell - Sharonville OH, US
Alfred Albert Mancini - Cincinnati OH, US
Clayton S. Cooper - Loveland OH, US

F02C 9/26
F02C 7/22
F23R 3/34

A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.