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Steven C Vise

from Loveland, OH
Age ~56
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Also known as:
Steven Clayton Vise, Steven L Vise, Steven S Vise, Steven Vise Shannon Holman, Steve C Vise
Phone and address:
677 Winding Woods Dr, Loveland, OH 45140
(513) 677-9508
Related to:
Ashley Marie Delk, 39
Connected to:
Amanda S Vise, 34Jay M Vise, 42Judy K Vise, 76Sharon L Vise, 71Tamas L Visegrady, 53Mehran Viseh, 62Jane E Visek, 49Lisa J Visek, 60Matthew J Visek, 49Teri L Visek, 68

Steven Vise Phones & Addresses

  • 677 Winding Woods Dr, Loveland, OH 45140 (513) 677-9508 (513) 761-6604
  • 8425 Mayfair St, Cincinnati, OH 45216 (513) 761-6604
  • Fairfield, OH
  • Louisville, KY
  • 677 Winding Woods Dr, Loveland, OH 45140 (513) 417-6381

Work

Company: Ge Position: Engineer

Languages

English

Emails

v***[email protected]

Industries

Aviation & Aerospace

Resumes

Resumes

Steven Vise Photo 1

Engineer

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Location:
677 Winding Woods Dr, Loveland, OH 45140
Industry:
Aviation & Aerospace
Work:
Ge
Engineer
Languages:
English

Publications

Us Patents

Methods And Apparatus For Cooling Gas Turbine Engine Combustors

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US Patent:
6546732, Apr 15, 2003
Filed:
Apr 27, 2001
Appl. No.:
09/844205
Inventors:
Craig Douglas Young - Maineville OH
Paul Edward Sabla - Cincinnati OH
Steven Clayton Vise - Cincinnati OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F23R 306
US Classification:
60772, 60740, 60748
Abstract:
A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

Gas Turbine Combustor Liner With Asymmetric Dilution Holes Machined From A Single Piece Form

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US Patent:
6553767, Apr 29, 2003
Filed:
Jun 11, 2001
Appl. No.:
09/878836
Inventors:
Gilbert Farmer - Cincinnati OH
Daniel D. Brown - Fairfield OH
Myron E. Rutherford - Cincinnati OH
Steven C. Vise - Cincinnati OH
Jeffrey M. Martini - Liberty Township OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 314
US Classification:
60752, 2989001
Abstract:
An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction. The shell is machined from a single piece integrally formed near net shape form such as a forging, a casting, or more particularly a spin or centrifugal casting. The invention includes a method for making the annular gas turbine engine combustor liner by forming a single piece integrally formed near net shape form and machining it to produce the shell and the above features in the shell.

Method And Apparatus For Cooling Gas Turbine Engine Igniter Tubes

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US Patent:
6557350, May 6, 2003
Filed:
May 17, 2001
Appl. No.:
09/859611
Inventors:
Gilbert Farmer - Cincinnati OH
Ella Christine Kutter - Miamisburg OH
Steven Clayton Vise - Cincinnati OH
John Robert Staker - Cincinnati OH
Tariq Kay Harris - Cincinnati OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 722
US Classification:
60776, 60 39821
Abstract:
A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.

Methods And Apparatus For Washing Gas Turbine Engine Combustors

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US Patent:
6932093, Aug 23, 2005
Filed:
Feb 24, 2003
Appl. No.:
10/372889
Inventors:
Paul James Ogden - Mason OH, US
Craig Douglas Young - Maineville OH, US
Steven Clayton Vise - Loveland OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
B08B009/00
B08B003/02
US Classification:
134 221, 134 2218, 134 23, 134169 A, 134198
Abstract:
A method facilitates washing a gas turbine engine combustor. The method comprises coupling a nozzle assembly against the combustor, wherein the nozzle assembly includes an inlet end, a discharge end, a hollow nozzle body extending therebetween, and a centerbody positioned within the nozzle body, coupling the nozzle assembly to a fluid source, and discharging an annulus of fluid from the nozzle assembly into the combustor to facilitate removing particulate matter from the combustor.

Fabricated Cowl For Double Annular Combustor Of A Gas Turbine Engine

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US Patent:
7222488, May 29, 2007
Filed:
Sep 10, 2002
Appl. No.:
10/238542
Inventors:
Gilbert Farmer - Cincinnati OH, US
Steven Clayton Vise - Loveland OH, US
Craig Douglas Young - Maineville OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 3/06
F02C 1/00
US Classification:
60747, 60804, 60746
Abstract:
A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein. The cowl further includes a plurality of circumferentially spaced stiffening ribs, where each stiffening rib includes: a middle portion including a rear edge configured to substantially conform to a forward surface of the middle annular portion so that an area extending between the forward and rear edges is upstream of the middle annular portion; an outer portion including a forward edge configured to conform to a rear surface of the outer annular portion; and, an inner portion including a forward edge configured to conform to a rear surface of inner annular portion. The middle rib portion further includes a forward edge configured to extend through the radial slots when positioned in the middle annular portion, whereas the inner and outer rib portions further include a rear edge configured to extend through the radial slots when positioned in the inner and outer annular portions.

Igniter Tube And Method Of Assembling Same

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US Patent:
7546739, Jun 16, 2009
Filed:
Jul 5, 2005
Appl. No.:
11/174746
Inventors:
Thomas George Holland - Dayton OH, US
Steven Clayton Vise - Loveland OH, US
Marie Ann McMasters - Mason OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 7/26
F02C 7/264
US Classification:
60772, 60 39821, 60 39827, 60 3983
Abstract:
An igniter tube assembly includes an axis of symmetry extending therethrough, an igniter tube that includes a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that the igniter tube circumscribes the igniter and such that a gap is defined between the igniter tube and the igniter, a ferrule coupled to the igniter tube, and a plurality of cooling air openings extending through at least one of the igniter tube and the ferrule to facilitate channeling cooling air into the gap.

Method And Apparatus For Cooling Gas Turbine Engine Combustors

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US Patent:
7654091, Feb 2, 2010
Filed:
Aug 30, 2006
Appl. No.:
11/468486
Inventors:
Steven Vise - Loveland OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 7/22
US Classification:
60776, 60748, 60756
Abstract:
A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.

Combustor Liner And Method Of Fabricating Same

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US Patent:
7669422, Mar 2, 2010
Filed:
Jul 26, 2006
Appl. No.:
11/460114
Inventors:
Baha Suleiman - Middletown OH, US
Steven Clayton Vise - Loveland OH, US
Daniel Dale Brown - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F23R 3/06
US Classification:
60772, 60754
Abstract:
A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis.
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Steven C Vise from Loveland, OH, age ~56 Get Report