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Dipankar Pal, 57339 Dennison Rdg, Manchester, CT 06040

Known as:
Dirpankar Pal Pal Dipankar R Pal

Dipankar Pal Phones & Addresses

339 Dennison Rdg, Manchester, CT 06040   

1027 Gloucester Ferry Rd, Greenville, SC 29607    864-2361456   

4 Russell Dr, Salem, MA 01970    978-7450503   

192 Kennedy Dr, Malden, MA 02148    781-3241373   

University, MS   

Middletown, CT   

Oxford, MS   

5 Rivanna Ln, Greenville, SC 29607   

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Dipankar Pal resumes & CV records

Resumes

Dipankar Pal Photo 28

Systems Engineer

Location:
Greenville, SC
Industry:
Oil & Energy
Work:
Ge Power
Systems Engineer Ge Aviation Oct 2001 - Nov 2006
Lead Engineer
Education:
University of Mississippi 1996 - 1999
Doctorates, Doctor of Philosophy, Philosophy
Skills:
Gas Turbine, Power Generation, Thermal Management, Project Engineering, Engineering, Energy, Mechanical Engineering
Interests:
Social Services
Education
Environment
Science and Technology
Arts and Culture
Health
Languages:
English
Hindi
Bengali
Dipankar Pal Photo 29

Associate Director, Fluid-Thermal Engineering

Location:
Albany, NY
Industry:
Aviation & Aerospace
Work:
Pratt & Whitney
Associate Director, Fluid-Thermal Engineering Ge Power Jun 2015 - May 2017
Senior Systems Engineer Ge Power Dec 2006 - Jun 2015
Technical Leader Heat Transfer Ge Aviation Oct 2001 - Dec 2006
Lead Heat Transfer Engineer Mtu Aero Engines Oct 2000 - Nov 2001
Analytical Engineer University of Mississippi May 1997 - Sep 2000
Post Doctoral Researcher
Education:
University of Mississippi 1992 - 1997
Doctorates, Doctor of Philosophy, Philosophy
Skills:
Gas Turbine Thermal Management, Gas Turbine Cooling and Sealing Technology, Airfoil Component Cooling, Heat Transfer, Gas Turbine Secondary Flow Design, Gas Turbine Performance Integration, Product Development, Cfd, Fea, Six Sigma, Project Management, Leadership, Cross Functional Team Leadership, Microsoft Office, Strategic Planning, Power Generation Equipment, Energy Industry, Thermodynamics, Negotiation, Mentoring, Influencing, Technology Product Development, Ansys, Cfx, Gas Turbine Operability, Energy Efficiency, Fluid Dynamics, Mechanical Design, Systems Engineering, 1 D Flow Solver, Compressible Flow Solver, Secondary Flow System, Technical Leadership, Engineering, Mechanical Engineering, Film Cooling, Convection Cooling, Thermal Stress Optimization, Component Failure Mechanism, Failure Mode and Effects Analysis
Dipankar Pal Photo 30

Dipankar Pal

Dipankar Pal Photo 31

Dipankar Pal

Dipankar Pal Photo 32

Dipankar Pal

Dipankar Pal Photo 33

Dipankar Pal

Publications & IP owners

Us Patents

System And Method For Modifying Rotor Thrust

US Patent:
8434994, May 7, 2013
Filed:
Aug 3, 2009
Appl. No.:
12/534584
Inventors:
Dipankar Pal - Greenville SC, US
Andres Jose Garcia-Crespo - Greenville SC, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 3/00
US Classification:
415 1, 415104, 415111, 415115, 415116, 4151995
Abstract:
A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter.

Turbine Blade Cooling

US Patent:
2010022, Sep 2, 2010
Filed:
Feb 27, 2009
Appl. No.:
12/394486
Inventors:
Dipankar Pal - Greenville SC, US
James E. Thompson - Simpsonville SC, US
International Classification:
F01D 5/18
US Classification:
416 97 R
Abstract:
A turbine blade with a generally hollow airfoil having an outer wall that defines at least one radially extending chamber for receiving the flow of a coolant, the airfoil including a leading edge that resides in an upstream or forward direction, a trailing edge that resides in a downstream or aft direction, a convex suction side, and a concave pressure side, the turbine blade comprising: a plurality of inserts disposed within the chamber that are configured to initially receive at least a portion of the coolant entering the chamber and direct a substantial portion of the coolant through a plurality of insert apertures toward the inner surface of the outer wall; wherein the inserts are configured to form at least one inward bleed channel and a central collector passage into which the inward bleed channel flows.

Turbine Blade With Shielded Coolant Supply Passageway

US Patent:
2011020, Aug 25, 2011
Filed:
Feb 25, 2010
Appl. No.:
12/712509
Inventors:
Dipankar PAL - Greenville SC, US
International Classification:
F01D 5/18
B23P 15/02
US Classification:
416 97 R, 416 96 R, 29889721
Abstract:
A turbine blade for a turbine engine includes main coolant passageways which extend through the turbine blade to cool the blade. A tip coolant passageway conveys coolant from a location adjacent the base of the blade directly to the tip of the blade to provide cooling fluid directly to the tip of the blade. This ensures that the coolant arriving at the tip of the blade is at a relatively low temperature and can therefore provide effective cooling of the material located at the tip of the blade.

Hot Gas Path Component

US Patent:
2012031, Dec 20, 2012
Filed:
Jun 20, 2011
Appl. No.:
13/164113
Inventors:
Gary Michael Itzel - Simpsonville SC, US
Dipankar Pal - Greenville SC, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F23R 3/42
B22D 46/00
F28F 1/00
US Classification:
60752, 165177, 164 41
Abstract:
A hot gas path component is provided and includes a body having a surface and being formed to define a cavity, the cavity employing coolant flow through a pin-fin bank with coolant discharge through film-cooling holes defined on the surface, the pin-fin bank including first and second pluralities of pin-fins, the first plurality of pin-fins and the second plurality of pin-fins each being aligned with a determined flow streamline, and any two pin-fins of the first and second pluralities of pin-fins being separated from one another by a gap as a function of a film-cooling hole dimension.

Methods And Systems For Use In Regulating A Temperature Of Components

US Patent:
2013008, Apr 11, 2013
Filed:
Oct 7, 2011
Appl. No.:
13/268254
Inventors:
Stanley Frank Simpson - Simpsonville SC, US
Dipankar Pal - Greenville SC, US
Jeffrey Todd Knapp - Golden CO, US
International Classification:
F01D 5/18
B23P 15/02
F28F 27/00
US Classification:
416 97 R, 165 96, 29889721
Abstract:
A cooling system for use in regulating a temperature of a component is described herein. The cooling system includes a plurality of flow control assemblies that are defined across a sidewall of the component for channeling a cooling fluid across a surface of the sidewall. The plurality of flow control assemblies are configured to adjust a plurality of fluid flow characteristics of the cooling fluid. The plurality of flow control assemblies includes a first flow control assembly configured to adjust a first fluid flow characteristic, and at least a second flow control assembly configured to adjust a second fluid flow characteristic that is different than the first fluid flow characteristic.

Turbine Shroud For A Turbomachine

US Patent:
2014003, Feb 6, 2014
Filed:
Jul 31, 2012
Appl. No.:
13/562880
Inventors:
Dipankar Pal - Greenville SC, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F04D 29/40
US Classification:
4151821
Abstract:
A turbine shroud includes a body having an upstream edge, a downstream edge, and first and second side edges that collectively define a flowpath surface. A first interface member is arranged on the upstream edge at the first side edge. The first interface member includes a first edge portion having an end portion that extends out at a first non-perpendicular angle relative to the upstream edge and the first side edge from the flowpath surface to a second end portion. A second interface member is arranged on the upstream edge at the second side edge. The second interface member includes an edge section having an end section that extends into at a second non-perpendicular angle relative to the upstream edge and the second side edge the flowpath surface to a second end section.

Seal Pressurization In Box Shroud

US Patent:
2018023, Aug 16, 2018
Filed:
Nov 1, 2016
Appl. No.:
15/340733
Inventors:
- Schenectady NY, US
Russell DeFOREST - Greenville SC, US
Robert W. COIGN - Greenville SC, US
Dipankar PAL - Greenville SC, US
International Classification:
F01D 11/00
F01D 25/12
F01D 5/08
Abstract:
A shroud segment arranged radially outward of a gas flow path of a gas turbine. The shroud segment includes a body having walls defining an internal pocket for receiving a supply of air. A plurality of pressurization apertures is formed through one of the walls to fluidly connect an internal pocket of the body to an ambient area of the body. A seal slot section is formed in the wall at a position radially inward of the pressurization apertures to receive a seal to connect the shroud segment to an adjacent shroud segment. The pressurization apertures are arranged such that portions of the supply of air are configured to pass through the pressurization apertures and through the seal slot section as leakage into the gas flow path, thereby reducing ingestion of fluid from the gas flow path into the internal pocket of the shroud segment.

System And Method For Cooling Turbine Shroud Trailing Edge

US Patent:
2017017, Jun 22, 2017
Filed:
Dec 16, 2015
Appl. No.:
14/971478
Inventors:
- Schenectady NY, US
Benjamin Paul Lacy - Greer SC, US
Dipankar Pal - Greenville SC, US
San Jason Nguyen - Simpsonville SC, US
International Classification:
F01D 25/12
F02C 3/04
F01D 9/00
Abstract:
A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.

Possible Relatives

Dharam Pal  Dilip Pal  Dustin S Pal  Emery S Pal  Gary C Pal  Hemant Pal  Irene Pal  Dipankar Roy  Dipankar Das  Dipankar D Gupta 

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