Resumes
Resumes
Zhifeng Dong Phones & Addresses
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Mason, OH
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9442 Ambleside Dr, Cincinnati, OH 45241 (513) 779-4619
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13230 104Th St, Miami, FL 33176 (305) 234-0592
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West Chester, OH
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2230 Stonebriar Rd, Fort Wayne, IN 46814 (260) 625-6820
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9442 Ambleside Dr, West Chester, OH 45241 (513) 227-3704
Work
Position:
Financial Professional
Education
Degree:
Associate degree or higher
Publications
Us Patents
Methods And Apparatus For Maintaining Rotor Assembly Tip Clearances
View pageUS Patent:
7165937, Jan 23, 2007
Filed:
Dec 6, 2004
Appl. No.:
11/005870
Inventors:
Zhifeng Dong - Cincinnati OH, US
Michael J. Epstein - Mason OH, US
Glen William Royal - Cincinnati OH, US
Robert J. Albers - Park Hills KY, US
Michael J. Epstein - Mason OH, US
Glen William Royal - Cincinnati OH, US
Robert J. Albers - Park Hills KY, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 11/08
F03B 11/02
F03B 11/02
US Classification:
4151732, 415175, 415177, 2988922
Abstract:
A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.
Aerodynamic Fastener Shield For Turbomachine
View pageUS Patent:
7249463, Jul 31, 2007
Filed:
Sep 15, 2004
Appl. No.:
10/941213
Inventors:
William C. Anderson - Springdale OH, US
Jesse Senyo - Williamstown KY, US
Michael J. Epstein - Mason OH, US
Zhifeng Dong - Cincinnati OH, US
Jesse Senyo - Williamstown KY, US
Michael J. Epstein - Mason OH, US
Zhifeng Dong - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 7/20
F01D 25/12
F01D 25/12
US Classification:
60798, 415112, 415116, 60 3983
Abstract:
A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts.
Transpiration Clearance Control Turbine
View pageUS Patent:
7740443, Jun 22, 2010
Filed:
Nov 15, 2006
Appl. No.:
11/599791
Inventors:
Kenneth Edward Seitzer - Cincinnati OH, US
Wojciech Sak - West Chester OH, US
Zhifeng Dong - Cincinnati OH, US
Robert Paul Ziegler - Fort Thomas KY, US
William Lee Herron - Cincinnati OH, US
Wojciech Sak - West Chester OH, US
Zhifeng Dong - Cincinnati OH, US
Robert Paul Ziegler - Fort Thomas KY, US
William Lee Herron - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 11/08
US Classification:
415116, 415126, 415175
Abstract:
A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.
Compound Clearance Control Engine
View pageUS Patent:
7823389, Nov 2, 2010
Filed:
Nov 15, 2006
Appl. No.:
11/599834
Inventors:
Kenneth Edward Seitzer - Cincinnati OH, US
Wojciech Sak - West Chester OH, US
Zhifeng Dong - Cincinnati OH, US
Robert Paul Ziegler - Fort Thomas KY, US
Chris Charles Glynn - Hamilton OH, US
Wojciech Sak - West Chester OH, US
Zhifeng Dong - Cincinnati OH, US
Robert Paul Ziegler - Fort Thomas KY, US
Chris Charles Glynn - Hamilton OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 6/08
US Classification:
60782, 60785
Abstract:
A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.
Flange With Axially Extending Holes For Gas Turbine Engine Clearance Control
View pageUS Patent:
8197186, Jun 12, 2012
Filed:
Jun 29, 2007
Appl. No.:
11/771333
Inventors:
Zhifeng Dong - Cincinnati OH, US
John Joseph Rahaim - Cincinnati OH, US
John Joseph Rahaim - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 25/14
F01D 25/24
F01D 25/24
US Classification:
415116, 4152131
Abstract:
A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.
Flange With Axially Curved Impingement Surface For Gas Turbine Engine Clearance Control
View pageUS Patent:
8393855, Mar 12, 2013
Filed:
Jun 29, 2007
Appl. No.:
11/771290
Inventors:
Zhifeng Dong - Cincinnati OH, US
John Joseph Rahaim - Cincinnati OH, US
John Joseph Rahaim - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 25/14
F01D 25/24
F01D 25/24
US Classification:
415116, 4152131
Abstract:
A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.
Swirl-Enhanced Aerodynamic Fastener Shield For Turbomachine
View pageUS Patent:
20060056957, Mar 16, 2006
Filed:
Sep 15, 2004
Appl. No.:
10/941214
Inventors:
Zhifeng Dong - Cincinnati OH, US
Michael Epstein - Mason OH, US
William Anderson - Springdale OH, US
Jesse Senyo - Williamstown KY, US
Michael Epstein - Mason OH, US
William Anderson - Springdale OH, US
Jesse Senyo - Williamstown KY, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F03B 11/00
US Classification:
415110000
Abstract:
A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.
Method And Apparatus For Reducing Axial Compressor Blade Tip Flow
View pageUS Patent:
20070122280, May 31, 2007
Filed:
Nov 30, 2005
Appl. No.:
11/164636
Inventors:
Zhifeng Dong - Cincinnati OH, US
John Rahaim - Cincinnati OH, US
John Rahaim - Cincinnati OH, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F01D 5/18
US Classification:
41609700R
Abstract:
A turbine machine of the type having a high pressure compressor positioned in a casing is provided with a plurality of rotating compressor blades with at least one air channel formed in the blades for air flow communication from the base to the tip for extracting and pressurizing air from an inner area proximate the disk and conveying the extracted and pressurized air into an area between the blade tip and casing for blocking air flow across the tips of the blades.