Rajiv N Rana from 9616 Kenneth Pl, Tempe, AZ 85284, age 70, Phone: 4807773450

Resumes

Rajiv Rana

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Location:

Tempe, AZ

Industry:

Electrical/Electronic Manufacturing

Work:

Honeywell
Retired

Skills:

Meditate on the Creator

Rajiv Rana

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Rajiv Rana

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Location:

United States

Us Patents

Air Cooled Turbine Blades And Methods Of Manufacturing
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US Patent:

8292581, Oct 23, 2012
Filed:

Jan 9, 2008
Appl. No.:

11/971459
Inventors:

Kin C. Poon - Tempe AZ, US
Malak F. Malak - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Ardeshir Riahi - Scottsdale AZ, US
David H. Chou - Phoenix AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F01D 5/08
US Classification:

416 97R
Abstract:

An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.

Turbine Blade Assemblies And Methods Of Manufacturing The Same
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US Patent:

8292587, Oct 23, 2012
Filed:

Dec 18, 2008
Appl. No.:

12/338746
Inventors:

Kin Poon - Tempe AZ, US
Rajiv Rana - Phoenix AZ, US
Bob Mitlin - Scottsdale AZ, US
Ardeshir Riahi - Scottsdale AZ, US
David Chou - Phoenix AZ, US
Steve Halfmann - Chandler AZ, US
Frank Mignano - Phoenix AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F01D 11/00
US Classification:

416193A, 415115, 415116, 416 90 R, 416 95, 416 96 R, 416 97 R, 416193 R
Abstract:

A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

Turbine Assemblies With Impingement Cooling
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US Patent:

8616832, Dec 31, 2013
Filed:

Nov 30, 2009
Appl. No.:

12/627609
Inventors:

Jason Smoke - Phoenix AZ, US
Bradley Reed Tucker - Chandler AZ, US
Bob Mitlin - Scottsdale AZ, US
Dan Crites - Mesa AZ, US
Rajiv Rana - Phoenix AZ, US
Alexander MirzaMoghadam - Phoenix AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F01D 5/14
US Classification:

415115, 416193 A, 416220 R
Abstract:

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

Axially-Split Radial Turbine
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US Patent:

20130280036, Oct 24, 2013
Filed:

Apr 19, 2012
Appl. No.:

13/451245
Inventors:

David K. Jan - Fountain Hills AZ, US
Christopher Zollars - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Tom Polakis - Tempe AZ, US
Ardeshir Riahi - Scottsdale AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F01D 13/00
US Classification:

415 66
Abstract:

An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.

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.

Turbine Sections Of Gas Turbine Engines With Dual Use Of Cooling Air
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US Patent:

20150275763, Oct 1, 2015
Filed:

Mar 27, 2014
Appl. No.:

14/227924
Inventors:

- Morristown NJ, US
John Gintert - Tempe AZ, US
Rajiv Rana - Tempe AZ, US
Lorenzo Crosatti - Phoenix AZ, US
Bradley Reed Tucker - Chandler AZ, US
Ed Zurmehly - Phoenix AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F02C 7/18
F02C 3/10
Abstract:

A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.

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.