Steven A Strang

US Patent:

6547518, Apr 15, 2003

Filed:

Apr 6, 2001

Appl. No.:

09/827850

Inventors:

Robert Paul Czachor - Cincinnati OH
Steven Andrew Strang - Loveland OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 904

US Classification:

415137, 4152094

Abstract:

A gas turbine frame has inner and outer annular bands, respectively, joined together by generally radially extending struts therebetween. A radially outer conical support arm extends radially outwardly from the outer band and a radially inner conical support arm extends radially inwardly from the inner band. Circumferentially spaced apart inner and outer openings are disposed in the inner and outer conical support arms, respectively. Each of the struts has at least one radially extending hollow passage which extends through the inner and outer bands. The frame is a single piece integral casting. The inner and outer conical support arms have an equal number of the inner and outer circumferentially spaced apart openings. The inner circumferentially spaced apart openings are equi-angularly spaced apart and the outer circumferentially spaced apart openings are equi-angularly spaced apart. Each pair of the inner and outer circumferentially spaced apart openings are linearly aligned with the hollow passage of a corresponding one of the struts.

US Patent:

61388963, Oct 31, 2000

Filed:

Oct 5, 1998

Appl. No.:

9/166239

Inventors:

Adrian M. Ablett - Cincinnati OH
Charles W. Carrier - West Chester OH
Brian J. Humke - Cincinnati OH
Steven A. Strang - Loveland OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B23K 2012
B23K 3102

US Classification:

228113

Abstract:

First and second superalloy workpieces are inertia welded together by rotating the first workpiece to an initial contact speed greater than about 750 surface feet per minute, and frictionally engaging under a weld load the first and second workpieces to effect an inertia weld therebetween.

US Patent:

52248259, Jul 6, 1993

Filed:

Dec 26, 1991

Appl. No.:

7/813546

Inventors:

Steven A. Strang - Loveland OH
Bruce A. Borelli - Mason OH
George G. Cunningham - Fairfield OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 102

US Classification:

4152093

Abstract:

A locator pin retention device comprises a pin with threaded and smooth portions cooperating with a bushing having spaced apart threaded and smooth portions to allow alignment of inner and outer gas turbine engine members exposed to different thermal environments, allowing thermal growth of the inner member in a radially outward direction toward the outer member and reacting axial and circumferential loads to prevent transverse movement to the outer structural member. The device reduces machining of the structural members because machined retention means are inexpensive and replaceable parts.

US Patent:

20180073388, Mar 15, 2018

Filed:

Sep 9, 2016

Appl. No.:

15/260641

Inventors:

- Schenectady NY, US
Steven Andrew Strang - Loveland OH, US
Charles Stanley Orkiszewski - Cincinnati OH, US
Subramanya Shankar - Bangalore, IN
Nitesh Jain - Bangalore, IN
Michael Riehle - West Chester OH, US

International Classification:

F01D 21/04
F01D 5/30
F01D 21/02
F02K 3/06

Abstract:

The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.

US Patent:

20140212284, Jul 31, 2014

Filed:

Dec 21, 2012

Appl. No.:

13/725150

Inventors:

General Electric Company - , US
Steven Strang - Cincinnati OH, US
Aaron Todd Williams - Cincinnati OH, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady OH

International Classification:

F01D 9/02

US Classification:

4152082, 29889

Abstract:

A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands.

Address:

6333 Pne Ln, Loveland, OH 45140

Phone:

(513)8312760

VIN:

3VWEF71K27M171477

Make:

VOLKSWAGEN

Model:

JETTA

Year:

2007

Address:

6333 Pne Ln, Loveland, OH 45140

Phone:

(513)8312760

VIN:

5TELU42N77Z335381

Make:

TOYOTA

Model:

TACOMA

Year:

2007