Jong Shang Liu from 9372 Wood Dr, Scottsdale, AZ 85260, age 66

Resumes

Jong Liu

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Medicine Doctors

Jong Liu

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Specialties:

Diagnostic Radiology

Work:

Steward Medical GroupSteward Radiology Associates
736 Cambridge St FL 4, Brighton, MA 02135
(617)7892740 (phone), (617)7796343 (fax)

Languages:

English
Russian
Spanish

Description:

Dr. Liu works in Brighton, MA and specializes in Diagnostic Radiology. Dr. Liu is affiliated with St Elizabeths Medical Center.

Us Patents

Turbine Engine Components
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US Patent:

8371814, Feb 12, 2013
Filed:

Jun 24, 2009
Appl. No.:

12/490840
Inventors:

Dhinagaran Ramachandran - Karnataka, IN
Balamurugan Srinivasan - Karnatatka, IN
Gopal Muthiah - Tamil Nadu, IN
Jyothishkumar Venkataramanan - Tamil Nadu, IN
Jong Liu - Scottsdale AZ, US
Luis Tapia - Maricopa AZ, US
Malak Fouad Malak - Tempe AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F01D 5/18
US Classification:

416 90R, 415115
Abstract:

A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

Gas Turbine Engine Components With Improved Film Cooling
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US Patent:

8529193, Sep 10, 2013
Filed:

Nov 25, 2009
Appl. No.:

12/625854
Inventors:

Jyothishkumar Venkataramanan - Tamil Nadu, IN
Gopal Samy Muthiah - Tamil Nadu, IN
Dhinagaran Ramachandran - Karnataka, IN
Balamurugan Srinivasan - Karnataka, IN
Malak Fouad Malak - Tempe AZ, US
Jong Liu - Scottsdale AZ, US
Luis Tapia - Maricopa AZ, US
Daniel Crites - Mesa AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F03B 11/00
US Classification:

415115, 416 97 R
Abstract:

An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Gas Turbine Engine Components With Cooling Hole Trenches
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US Patent:

8628293, Jan 14, 2014
Filed:

Jun 17, 2010
Appl. No.:

12/818018
Inventors:

Dhinagaran Ramachandran - Karnataka, IN
Gopal Samy Muthiah - Tamil Nadu, IN
Jyothishkumar Venkataramanan - Tamil Nadu, IN
Balamurugan Srinivasan - Karnataka, IN
Jong Liu - Scottsdale AZ, US
Luis Tapia - Maricopa AZ, US
Daniel Cregg Crites - Mesa AZ, US
Malak Fouad Malak - Tempe AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F01D 5/08
US Classification:

415115, 416 97 R
Abstract:

An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.

Gas Turbine Engine Components With Film Cooling Holes Having Cylindrical To Multi-Lobe Configurations
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US Patent:

20130294889, Nov 7, 2013
Filed:

May 7, 2012
Appl. No.:

13/465647
Inventors:

Malak Fouad Malak - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Luis Tapia - Maricopa AZ, US
David Chou - Phoenix AZ, US
Jong Liu - Scottsdale AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F02C 7/18
US Classification:

415115
Abstract:

An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.

Gas Turbine Engine Components With Cooling Hole Trenches
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US Patent:

20130315710, Nov 28, 2013
Filed:

May 22, 2012
Appl. No.:

13/477883
Inventors:

Vighneswara Rao Kollati - Andhra Pradesh, IN
Balamurugan Srinivasan - Bangalore, IN
Jyothishkumar Venkataramanan - Tamil Nadu, IN
Sujatha Guntu - Andhra Pradesh, IN
Jong Liu - Scottsdale AZ, US
Daniel Cregg Crites - Mesa AZ, US
Luis Tapia - Maricopa AZ, US
Malak Fouad Malak - Tempe AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F04D 31/00
US Classification:

415116
Abstract:

An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.

Turbine Blades And Methods Of Forming Turbine Blades Having Lifted Rib Turbulator Structures
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US Patent:

20160069194, Mar 10, 2016
Filed:

Sep 9, 2014
Appl. No.:

14/480968
Inventors:

- Morristown NJ, US
Dhanvantri Joshi - Bangalore, IN
Sridhar Murari - Hyderabad, IN
Jong Liu - Scottsdale AZ, US
Malak Fouad Malak - Tempe AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F01D 5/18
B23P 15/02
Abstract:

The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs.

Turbine Blade Airfoils Including Film Cooling Systems, And Methods For Forming An Improved Film Cooled Airfoil Of A Turbine Blade
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US Patent:

20140356188, Dec 4, 2014
Filed:

Apr 26, 2013
Appl. No.:

13/871655
Inventors:

HONEYWELL INTERNATIONAL, INC. - , US
Balamurugan Srinivasan - Bangalore, IN
Jong Liu - Scottsdale AZ, US
Daniel C. Crites - Mesa AZ, US
Luis Tapia - Maricopa AZ, US
Malak Fouad Malak - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Assignee:

HONEYWELL INTERNATIONAL, INC. - Morristown NJ
International Classification:

F01D 5/18
B23P 15/02
US Classification:

416 97 A, 416235, 29889721
Abstract:

Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.

Turbine Blade Airfoils Including Showerhead Film Cooling Systems, And Methods For Forming An Improved Showerhead Film Cooled Airfoil Of A Turbine Blade
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US Patent:

20140154096, Jun 5, 2014
Filed:

Dec 3, 2012
Appl. No.:

13/692353
Inventors:

- Morristown NJ, US
Balamurugan Srinivasan - Bangalore, IN
Jong Liu - Scottsdale AZ, US
Daniel Cregg Crites - Mesa AZ, US
Luis Tapia - Maricopa AZ, US
Malak Fouad Malak - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F01D 5/18
US Classification:

416 97 R, 29889721
Abstract:

Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.