David Allen Ball

US Patent:

8136361, Mar 20, 2012

Filed:

May 4, 2006

Appl. No.:

11/381598

Inventors:

Carl Gerard Schott - Simpsonville SC, US
Kevin W. Kinzie - Moore SC, US
John Joseph Lynch - Greenville SC, US
David W. Ball - Easley SC, US
Gunnar Leif Siden - Greenville SC, US
Kenneth Neil Whaling - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 6/08
F02C 9/00
F02C 6/04

US Classification:

60782, 60785, 60795

Abstract:

A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

US Patent:

8142169, Mar 27, 2012

Filed:

Jan 6, 2009

Appl. No.:

12/348923

Inventors:

Kenneth Neil Whaling - Simpsonville SC, US
Dean Matthew Erickson - Simpsonville SC, US
Hua Zhang - Greer SC, US
David Wesley Ball - Easley SC, US
Christina Renee Pompey - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F04F 5/48

US Classification:

417189, 417 54, 417185, 417197

Abstract:

An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle.

US Patent:

8272222, Sep 25, 2012

Filed:

Jan 4, 2010

Appl. No.:

12/651585

Inventors:

Hua Zhang - Greenville SC, US
David Wesley Ball - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02G 3/00
F02C 6/04

US Classification:

60785, 60 39093

Abstract:

An inlet bleed heat system in a gas turbine includes a compressor discharge extraction manifold that extracts compressor discharge air, an inlet bleed heat manifold receiving the compressor discharge air, and a plurality of acoustic dispersion nozzles disposed at an output end of the inlet bleed heat manifold that reduce a velocity of the compressor discharge air in the inlet bleed heat manifold. Noise is generated from the shearing action between the surrounding atmosphere and air jets from orifices. When the air jet velocity is slowed using, for example, a multi-stage ejector/mixer, noise can be abated.

US Patent:

8474270, Jul 2, 2013

Filed:

Feb 15, 2012

Appl. No.:

13/396930

Inventors:

Carl Gerard Schott - Simpsonville SC, US
Kevin W. Kinzie - Moore SC, US
John Joseph Lynch - Greenville SC, US
David W. Ball - Easley SC, US
Gunnar Leif Siden - Greenville SC, US
Kenneth Neil Whaling - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 6/08
F02C 9/00
F02C 6/04

US Classification:

60782, 60785, 60795

Abstract:

A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

US Patent:

20080202092, Aug 28, 2008

Filed:

Feb 27, 2007

Appl. No.:

11/711306

Inventors:

Ravi Praveen S. Eluripati - Simpsonville SC, US
David Wesley Ball - Easley SC, US
Kenneth Neil Whaling - Simpsonville SC, US
Hua Zhang - Greer SC, US

International Classification:

F02C 7/12

US Classification:

60 3983

Abstract:

A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections. The inner section is generally cylindrical in cross section and has a plurality of holes therein. The angle between the direction of the bypass flow and the direction of the third flow, when the bypass flow meets the third flow in the mixer, is less than about 90 degrees.

US Patent:

20180223733, Aug 9, 2018

Filed:

Sep 3, 2014

Appl. No.:

15/507987

Inventors:

Hua ZHANG - Greenville SC, US
David Wesley BALL - Greenville SC, US
Qunjian HUANG - Shanghai, CN
Richard Lynn LOUD - New York NY, US
- Schenectady NY, US

International Classification:

F02C 7/045
F01D 25/30
F02M 35/12

Abstract:

An acoustic treatment assembly () for a turbine system includes a region of the turbine system having a flow path configured to allow a fluid flow therethrough. Also included is at least one sound attenuation structure () disposed in the flow path. The sound attenuation structure includes a substantially rigid frame () and a flexible membrane () retained by the frame.