Sathyanarayanan Raghavan

20200194212, Jun 18, 2020

Dec 13, 2018

16/218718

- Schenectady NY, US
Scott Andrew Weaver - Ballston Lake NY, US
John Scott Price - Niskayuna NY, US
Stephen Lourenco Araujo - Niskayuna NY, US
Sathyanarayanan Raghavan - Ballston Lake NY, US

General Electric Company - Schenectady NY

H01J 35/12

An X-ray source target includes a structure configured to generate X-rays when impacted by an electron beam. The structure has an X-ray generating layer comprising X-ray generating material, and a thermally-conductive layer is adjacent to and in thermal communication with the X-ray generating layer. A stress relieving layer is adjacent to the thermally-conductive layer. The thermally-conductive layer is sandwiched between the X-ray generating layer and the stress relieving layer.

20190375006, Dec 12, 2019

Jun 6, 2018

16/001565

- Schenectady NY, US
Sathyanarayanan Raghavan - Ballston Lake NY, US
Ken Salas Nobrega - Schenectady NY, US
Vadim Bromberg - Schenectady NY, US
Arunkumar Natarajan - Niskayuna NY, US

B22F 3/00
B33Y 40/00
B33Y 80/00
B33Y 10/00
B29C 64/165
B29C 64/379
B28B 1/00
C04B 35/622
C04B 35/634
C04B 35/638
C04B 35/64

A setter assembly for use in additive manufacturing a binder-jet part includes a base, a first setter component having a first setter portion and a second setter portion that may be removably coupled to the first setter portion and a plurality of protrusions disposed on and extending away from a surface of the base. The plurality of protrusions may align the base with the first setter component and enable coupling of the first setter component to the base. The setter assembly also includes a second setter component positioned between the base and the first setter component. The second setter component is disposed on the surface and the first setter component, the second setter component, and the base can be assembled onto a printed part such that at least a portion of the printed part is nested between the first setter component and the second setter component.

20190375008, 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.

20190079491, Mar 14, 2019

Sep 12, 2017

15/702040

- Schenectady NY, US
Sathyanarayanan RAGHAVAN - Niskayuna NY, US
Arun Karthi SUBRAMANIYAN - Niskayuna NY, US
Changjie SUN - Schenectady NY, US
Arvind RANGARAJAN - San Ramon CA, US

G05B 19/4099
B33Y 50/02
B29C 64/40
B29C 64/393
B23K 26/342

According to some embodiments, an industrial asset item definition data store may contain at least one electronic record defining the industrial asset item. An automated support structure creation platform may include a support structure optimization computer processor. The automated support structure optimization computer processor may, for example, be adapted to automatically create support structure geometry data associated with an additive printing process for the industrial asset item. The creation may be performed, according to some embodiments, via an iterative loop between a build process simulation engine and a topology optimization engine.

20180135638, May 17, 2018

Nov 16, 2016

15/353182

- Schenectady NY, US
Luc Stephane Leblanc - Clifton Park NY, US
Sathyanarayanan Raghavan - Ballston Lake NY, US
Changjie Sun - Clifton Park NY, US
Ananda Barua - Schenectady NY, US

F04D 29/02
F04D 29/38

Coating systems for components of a gas turbine engine, such as a compressor casing, are provided. The coating system can include a ceramic material disposed along the compressor casing on a surface to be adjacent to a rotating compressor blade. The coating system is harder than the compressor blade and can reduce the rub ratio between the casing and blade. The coating system can thereby increase the lifetime of the compressor casing and blades. Methods are also provided for applying the coating system onto a compressor casing.

20180087515, Mar 29, 2018

Sep 28, 2016

15/278860

- Schenectady NY, US
Larry Steven Rosenzweig - Clifton Park NY, US
Sathyanarayanan Raghavan - Ballston Lake NY, US
Changjie Sun - Clifton Park NY, US
Ananda Barua - Schenectady NY, US
Jinjie Shi - Clifton Park NY, US

F04D 29/02
F04D 29/32
C23C 30/00

Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.

20170254210, Sep 7, 2017

Mar 7, 2016

15/063048

- Schenectady NY, US
Neelesh Nandkumar Sarawate - Niskayuna NY, US
Kenneth Martin Lewis - Liberty Township OH, US
Changjie Sun - Clifton Park NY, US
Yu Xie Mukherjee - West Chester OH, US
Sathyanarayanan Raghavan - Ballston Lake NY, US

F01D 5/20

An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.