Steven A Klusman from 16417 SW 14Th Avenue Rd, Ocala, FL 34473, age 79, Phone: 3178825361

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Self Contained Squeeze Film Damping System
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US Patent:

7329048, Feb 12, 2008
Filed:

Jul 19, 2005
Appl. No.:

11/184682
Inventors:

Steven Arlen Klusman - Indianapolis IN, US
Mark Stephen Henry - Indianapolis IN, US
Assignee:

Rolls-Royce Corporation - Indianapolis IN
International Classification:

F16C 19/06
US Classification:

384 99
Abstract:

A fluid damping system for damping a shaft within a gas turbine engine component. The fluid damping system including a damping liquid and a pressurized gas in a closed self contained system. In one aspect the damping liquid is cooled by being disposed in a heat transfer relationship with a fuel.

Compliant Spherical Bearing Mount
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US Patent:

8202003, Jun 19, 2012
Filed:

Apr 29, 2009
Appl. No.:

12/387163
Inventors:

Steven Arlen Klusman - Indianapolis IN, US
Preston Earl Light - Fishers IN, US
Assignee:

Rolls-Royce North American Technologies, Inc. - Indianapolis IN
International Classification:

F16C 32/06
US Classification:

384106, 384124, 384581, 384536, 384 99
Abstract:

A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, including a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft. A plurality of segmented damper springs are positioned around an exterior perimeter of a portion of the cylindrical bearing. Each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint. The width of each spring is less than the length of the bearing.

Turbine Engine Powered System With Hybrid Bearing
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US Patent:

8531071, Sep 10, 2013
Filed:

Oct 18, 2010
Appl. No.:

12/906326
Inventors:

Steven Arlen Klusman - Indianapolis IN, US
Assignee:

Rolls-Royce Corporation - Indianapolis IN
International Classification:

H02K 7/09
US Classification:

310 905, 310 90
Abstract:

One embodiment of the present invention is a unique turbine engine. Another embodiment is a unique turbine engine powered system. Another embodiment is a hybrid bearing system for use in a turbine engine and/or a turbine engine powered system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for hybrid bearings, turbine engine systems with one or more hybrid bearings and turbine engine powered systems with one or more hybrid bearings. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Power Augmentation System For An Engine Powered Air Vehicle
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US Patent:

20110154805, Jun 30, 2011
Filed:

Dec 21, 2010
Appl. No.:

12/974976
Inventors:

Craig Heathco - Martinsville IN, US
Robert T. Duge - Carmel IN, US
Steven Arlen Klusman - Indianapolis IN, US
International Classification:

F02C 6/14
F02K 3/00
US Classification:

602261, 60793
Abstract:

One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Rotating Machinery With Damping System
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US Patent:

20110171012, Jul 14, 2011
Filed:

Oct 14, 2010
Appl. No.:

12/904730
Inventors:

Daniel Kent Vetters - Indianapolis IN, US
Timothy Hoffmann - Greenwood IN, US
Steven Arlen Klusman - Indianapolis IN, US
International Classification:

F01D 25/00
US Classification:

4151742
Abstract:

One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Gas Turbine Engine And Foil Bearing System
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US Patent:

20110194933, Aug 11, 2011
Filed:

Dec 21, 2010
Appl. No.:

12/974961
Inventors:

Steven Arlen Klusman - Indianapolis IN, US
International Classification:

F01D 25/16
US Classification:

415229
Abstract:

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine foil bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine bearing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Mass Impact Damper For Rotors
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US Patent:

52191443, Jun 15, 1993
Filed:

Jul 20, 1990
Appl. No.:

7/555222
Inventors:

Allen E. Fox - Indianapolis IN
Steven A. Klusman - Indianapolis IN
Timothy A. Nale - Indianapolis IN
Assignee:

General Motors Corporation - Detroit MI
International Classification:

F16M 1300
US Classification:

248562
Abstract:

A vibration damper of a rotating shaft includes a floating housing attached to the shaft for radial vibratory displacement as a unit therewith, a plurality of cylindrical bores in the floating housing parallel to the axis of rotation of the shaft, and a plurality of smaller cylindrical impactors in the cylindrical bores. Each impactor is a metal sleeve having a smaller cylindrical tungsten rod therein with a damping medium around the rod. When the shaft experiences radial vibratory displacement, the sleeves impact the bores. When the sleeves impact the bores, the damping medium is squeezed from between the tungsten rods and the sleeves for vibration damping energy absorption in one mode. In addition, the tungsten rods impact the bores through the sleeves and initiate local plastic deformation of the bores the sleeves and the rods for energy absorption in another mode.

Turbomachine With Active Tip Clearance Control
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US Patent:

52638162, Nov 23, 1993
Filed:

Jun 22, 1992
Appl. No.:

7/901655
Inventors:

Matthew M. Weimer - Indianapolis IN
Steven A. Klusman - Indianapolis IN
Assignee:

General Motors Corporation - Detroit MI
International Classification:

F01D 502
F04D 1710
US Classification:

415131
Abstract:

A turbomachine including a case, a rotor, a plurality of rotor blades on the rotor each having a blade tip, a shroud around the rotor blade tips, and bearings mounting the rotor on the case for rotation about a centerline of the case and for bodily shiftable movement in the direction of the centerline. The rotor blade tips and an inside wall of the shroud flare radially outward in the direction of the centerline so that when the rotor moves in the direction of the centerline toward the shroud a clearance gap between the blade tips and the inner wall of the shroud decreases and vice versa. An electromagnetic actuator on the case magnetically attracts a thrust plate on the rotor against a net dynamic force on the rotor. A control system of the actuator controls the magnetic attraction of the actuator in response to signals from a position sensor measuring the actual magnitude of the clearance gap to maintain the actual clearance gap at a predetermined magnitude.