Constantin A Dinu

Address:

2211 Hudson Rd APT 1211, Greer, SC 29650

VIN:

4A3AK24FX7E024454

Make:

MITSUBISHI

Model:

ECLIPSE

Year:

2007

US Patent:

6996990, Feb 14, 2006

Filed:

Aug 27, 2003

Appl. No.:

10/648203

Inventors:

Constantin Alexandru Dinu - Greer SC, US

Assignee:

General Electric Company - Schnectady NY

International Classification:

F23R 3/40

US Classification:

60723, 60749, 431170

Abstract:

A flow controller is disposed between a preburner section in a diffuser and prior to the main fuel injector and catalytic sections in a turbine combustor. The flow from the burner section is typically not uniform in temperature and velocity and the flow splitter renders the flow substantially uniform at the fuel injector and catalyst inlet. The flow splitter comprises substantially equal mass annular flow areas defined by a first outer frustoconical element and the diffuser wall, a second element defining with the first element a second annular area and a central bluff disk defining with the second element the interior annular area. Vanes are provided on the flow splitter to enhance turbulent flow and substantially preclude swirling flow. As a result, flow uniformity at the catalyst inlet and main fuel injection is achieved.

US Patent:

7003958, Feb 28, 2006

Filed:

Jun 30, 2004

Appl. No.:

10/879102

Inventors:

Constantin Alexandru Dinu - Greer SC, US
Iris Ziqin Hu - Greer SC, US
James Michael Storey - Taylors SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60737, 60723, 60 39822

Abstract:

A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlets of the venturis upstream of the throats. Each diffuser transitions from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exit. Gaps between circumferentially and radially spaced diffusers at their exits are eliminated. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.

US Patent:

7007478, Mar 7, 2006

Filed:

Jun 30, 2004

Appl. No.:

10/879059

Inventors:

Constantin Alexandru Dinu - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60737, 60723, 60 39822

Abstract:

A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlet of the venturis upstream of the throat. The diffusers transition from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exits without substantial gaps therebetween. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.

US Patent:

7093438, Aug 22, 2006

Filed:

Jan 17, 2005

Appl. No.:

10/905686

Inventors:

Constantin Dinu - Greer SC, US
Thomas Raymond Farrell - Simpsonville SC, US
Kevin M. Gordon - Greer SC, US
James Michael Storey - Taylors SC, US
Krishna Kumar Venkataraman - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60737, 60723, 60 39822

Abstract:

A gas fuel injector includes a first header plate; a second header plate spaced downstream from the upstream header plate; and a plurality of venturi tubes arranged in rows and sealably secured to the first and second header plates. Each of the venturi tubes includes an inlet section, a throat section and an exit. The exit is shaped into a pattern that reduces space between each of the venturi tubes at the exit of each of the plurality of venturi tubes.

US Patent:

7509808, Mar 31, 2009

Filed:

Mar 25, 2005

Appl. No.:

10/907248

Inventors:

James M Storey - Taylors SC, US
Constantin Dinu - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60747

Abstract:

A gas fuel injector includes a first header plate, a second header plate, and a plurality of venturi tubes. The second header plate is spaced downstream from the first header plate. The plurality of venturi tubes is sealably secured to the first and second header plates. Each venturi tube of the plurality of venturi tubes is defined by a plurality of fixable components.

US Patent:

8006477, Aug 30, 2011

Filed:

Apr 1, 2008

Appl. No.:

12/060481

Inventors:

Constantin Dinu - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/06

US Classification:

60 3917, 60791

Abstract:

A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.

US Patent:

8127557, Mar 6, 2012

Filed:

Apr 7, 2008

Appl. No.:

12/098906

Inventors:

Constantin Dinu - Greer SC, US

Assignee:

General Electric Company - Schenetady NY

International Classification:

F02C 9/00

US Classification:

60773, 60 395

Abstract:

Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point.

US Patent:

8186165, May 29, 2012

Filed:

Mar 16, 2009

Appl. No.:

12/405195

Inventors:

Constantin Dinu - Katy TX, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00

US Classification:

60743, 60736, 60740, 431 11, 431208, 431214, 239 5

Abstract:

In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface.