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Kent G Hultgren

from Winter Park, FL
Age ~81
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Related to:
Lesley G Gibson, 64Alfred F Meyer, 84Gregory Meyer, 52Barbara Meyer, 82Ryan Searle, 33
Connected to:
Alexander M Hultgren, 34Barry Hultgren, 62Larry E Hultgren, 79Marisa R Hultgren, 35Patrick C Hultgren, 57Priscilla N Hultgren, 85Rachel V Hultgren, 35Russell Hultgren, 68Stacey R Hultgren, 40Robert L Hultgrien, 66

Kent Hultgren Phones & Addresses

  • 720 Williams Dr, Winter Park, FL 32789 (407) 628-4736

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Kent Hultgren Photo 1

Consultant

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Location:
Winter Park, FL
Industry:
Mechanical Or Industrial Engineering
Work:
Siemens
Consultant
Kent Hultgren Photo 2

Kent Hultgren

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Publications

Us Patents

System And Method For Measuring Coating Thickness

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US Patent:
8315834, Nov 20, 2012
Filed:
Dec 17, 2003
Appl. No.:
10/738882
Inventors:
Vladimir Gimelfarb - Oviedo FL, US
Kent Hultgren - Winter Park FL, US
Assignee:
Siemens Energy, Inc. - Orlando FL
International Classification:
G01B 5/02
US Classification:
702171
Abstract:
Embodiments of the invention relate to a system and a method for measuring the thickness of a coating applied to a substrate or component. Embodiments of the invention relate to measuring the distance between a surface of a component, both before and after the surface is covered with a coating material, and an optical measuring device such as a laser displacement sensor. In addition, aspects of the invention include the measurement of the temperature of the component surface before and after the application of the coating and after the component has cooled to substantially ambient temperature. In such case, a more accurate coating thickness calculation can be made by accounting for the thermal expansion of the component due to the deposition of a heated coating on the component surface. Accordingly, embodiments of the invention are particularly suited for thermal spray processes.

Gas Turbine Vane Cooling Air Insert

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US Patent:
51453150, Sep 8, 1992
Filed:
Sep 27, 1991
Appl. No.:
7/766934
Inventors:
William E. North - Winter Springs FL
Kent G. Hultgren - Winter Park FL
Christopher D. Dishman - Geneva FL
Gary S. Van Heusden - Oviedo FL
Assignee:
Westinghouse Electric Corp. - Pittsburgh PA
International Classification:
F01D 520
US Classification:
415115
Abstract:
A gas turbine stationary vane is provided having cooling air inserts and an inpingement plate attached to the outer shroud of the vane. The inserts extend only a short distance above their mounting surface on the outer shroud so that there is adequate access for properly welding the inserts to the outer shroud. Insert extensions are disposed in the end of each insert so as to form cooling air inlets which project above the impingement plate. The insert extensions are installed after the insert has been welded to the outer shroud so as to not interfere with access to the weld area. The insert extensions are attached to the inserts and the impingement plate by flexible seal collars, allowing the collars to form positive seals between the components.

Gas Turbine Blade Platform Cooling Concept

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US Patent:
61202495, Sep 19, 2000
Filed:
Apr 10, 1996
Appl. No.:
8/629952
Inventors:
Kent Goran Hultgren - Winter Park FL
Thomas Walter Zagar - Winter Springs FL
William E. North - Winter Springs FL
Stephen Humphrey Robbins - Thulston, GB
Graham Mark Upton - Derby, GB
Assignee:
Siemens Westinghouse Power Corporation - Orlando FL
International Classification:
F01D 518
US Classification:
416 97R
Abstract:
A turbine blade with a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Cooling air passages are formed in the blade root platform just below its radially outward facing surface on an overhanging portion of the platform opposite the convex surface of the blade airfoil. Each of these passage extends radially outward from an inlet that receives a flow of cooling air, and then extends through the platform. Cavities are formed in a radially inward facing surface of an over hanging portion of the platform opposite the concave surface of the blade airfoil. An impingement plate directs cooling air as jets into these cavities. A passage is connected to the cavities and directs this cooling air through the overhanging portion of the platform opposite the concave surface.

On-Line Monitor For Detecting Excessive Temperatures Of Critical Components Of A Turbine

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US Patent:
60628111, May 16, 2000
Filed:
Aug 6, 1998
Appl. No.:
9/129905
Inventors:
Paul J. Zombo - Cocoa FL
Brij B. Seth - Maitland FL
Kent G. Hultgren - Winter Park FL
Michael A. Burke - Pittsburgh PA
Assignee:
Siemens Westinghouse Power Corporation - Orlando FL
International Classification:
F01B 2526
US Classification:
415118
Abstract:
A monitor for detecting overheating of a critical component in a combustion turbine is provided. The monitor, when used in conjunction with a closed-loop cooling system, comprises a coating comprising an indicator material having an activation temperature. The coating is situated on the internal cooling passages of the critical component. The monitor further comprises a sensor connected to an outlet conduit of the cooling system for determining the amount of degradation of indicator material by monitoring the cooling fluid flowing through the outlet conduit. Embodiments further comprising "sniffer" tubes for use with open-loop air cooling systems also are provided.

Turbomachine Rotor With Improved Cooling

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US Patent:
57555567, May 26, 1998
Filed:
May 17, 1996
Appl. No.:
8/649507
Inventors:
Kent Goran Hultgren - Winter Park FL
Leroy Dixon McLaurin - Winter Springs FL
Oran Leroy Bertsch - Titusville FL
Perry Eugene Lowe - Oviedo FL
Assignee:
Westinghouse Electric Corporation - Pittsburgh PA
International Classification:
F04D 2958
US Classification:
416 96R
Abstract:
A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn.

Apparatus For Cooling A Gas Turbine Airfoil

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US Patent:
58138277, Sep 29, 1998
Filed:
Apr 15, 1997
Appl. No.:
8/843414
Inventors:
Raymond Scott Nordlund - Orlando FL
Kent Goran Hultgren - Winter Park FL
Robert Kenmer Scott - Geneva FL
Zachary Sinnott - Winter Park FL
William Edward North - Winter Springs FL
Steven Douglas Ward - Cincinnati OH
Assignee:
Westinghouse Electric Corporation - Pittsburgh PA
International Classification:
F01D 518
US Classification:
415115
Abstract:
An apparatus for cooling the trailing edge portion of a gas turbine vane. Two radially extending passages connected to the outer shroud direct cooling fluid to a plenum formed about mid-span adjacent the trailing edge. Two arrays of cooling fluid passages extend from the plenum. One array extends radially outward toward the outer shroud while the other array extends radially inward toward the inner shroud. The plenum distributes the cooling fluid to the two arrays of passages so that it flows radially inward and outward to manifolds formed in the inner and outer shrouds. The manifolds direct the spent cooling fluid to a discharge passage.

Apparatus For Restraining Motion Of A Turbo-Machine Stationary Vane

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US Patent:
56181612, Apr 8, 1997
Filed:
Oct 17, 1995
Appl. No.:
8/544350
Inventors:
Theodore Papageorgiou - Winter Park FL
Kent G. Hultgren - Winter Park FL
Rocco J. Covelli - Winter Springs FL
Assignee:
Westinghouse Electric Corporation - Pittsburgh PA
International Classification:
F01D 904
US Classification:
415190
Abstract:
A stationary vane assembly for a turbo-machine in which the vane is restrained against motion in the circumferential direction by first and second locking pins. The second locking pin extends radially through a turbine cylinder and engages a notch in a downstream support rail formed on the vane outer shroud. The first locking pin is affixed to the front radial flange of the cylinder and has a projection that extends into a notch in an upstream support rail formed on the outer shroud. An over-sized slot in the first locking pin allows the circumferential location at which the first locking pin is fixed to the cylinder to be adjusted, thereby ensuring that the first locking pin can be pre-loaded against the outer shroud notch at assembly in a manner that will allow it to restrain the motion of the vane.

Cooling Scheme For Turbine Hot Parts

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US Patent:
61053635, Aug 22, 2000
Filed:
Apr 27, 1998
Appl. No.:
9/067593
Inventors:
Kent Goran Hultgren - Winter Park FL
Brian Charles Owen - Orlando FL
Steven Wayne Dowman - Orlando FL
Raymond Scott Nordlund - Orlando FL
Ricky Lee Smith - Oviedo FL
Assignee:
Siemens Westinghouse Power Corporation - Orlando FL
International Classification:
F02C 300
US Classification:
60 3975
Abstract:
A closed-loop cooling scheme for cooling stationary combustion turbine components, such as vanes, ring segments and transitions, is provided. The cooling scheme comprises: (1) an annular coolant inlet chamber, situated between the cylinder and blade ring of a turbine, for housing coolant before being distributed to the turbine components; (2) an annular coolant exhaust chamber, situated between the cylinder and the blade ring and proximate the annular coolant inlet chamber, for collecting coolant exhaust from the turbine components; (3) a coolant inlet conduit for supplying the coolant to said coolant inlet chamber; (4) a coolant exhaust conduit for directing coolant from said coolant exhaust chamber; and (5) a piping arrangement for distributing the coolant to and directing coolant exhaust from the turbine components. In preferred embodiments of the invention, the cooling scheme further comprises static seals for sealing the blade ring to the cylinder and flexible joints for attaching the blade ring to the turbine components.
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Kent G Hultgren from Winter Park, FL, age ~81 Get Report