Mark Earl Henry

US Patent:

6367241, Apr 9, 2002

Filed:

Aug 27, 1999

Appl. No.:

09/384497

Inventors:

Mark Stephen Henry - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis IN
Rolls-Royce Corporation - Indianapolis IN

International Classification:

F02C 618

US Classification:

60 3907, 415104, 415105, 415106, 417365, 310 905

Abstract:

A thrust compensation apparatus for high-speed rotating machinery includes an electromagnetic thrust bearing having a thrust rotor and a thrust stator, a first chamber filled with a pressurized medium on one side of the bearing, and a second chamber on the other side of the bearing. The pressure differential across the bearing augments the electromagnetic force between the rotor and stator in order to counteract the axial thrust load of the high-speed rotating machinery.

US Patent:

6640933, Nov 4, 2003

Filed:

Jul 10, 2001

Appl. No.:

09/902410

Inventors:

Mark Stephen Henry - Indianapolis IN
Steven Robert Wellborn - Indianapolis IN

Assignee:

Rolls Royce Corporation - Indianapolis IN

International Classification:

F16C 124

US Classification:

184 51, 184 623, 384462

Abstract:

A lubrication system is provided for use with a bearing including an outer race, an inner race, and bearing elements disposed therebetween. Rotation of the bearing and a shaft journaled thereby induces air movement having a first air velocity and a path adjacent the bearing. The lubrication system includes a structure providing a passageway through which a lubricant entrained in gas is delivered at a second velocity to the bearing. The lubrication system further includes a flow modifier disposed relative to the bearing and the structure to modify the first air velocity to promote movement of the lubricant into the bearing.

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.

US Patent:

8215895, Jul 10, 2012

Filed:

Mar 3, 2008

Appl. No.:

12/041034

Inventors:

Mark S. Henry - Indianapolis IN, US
Daniel Kent Vetters - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

F04D 27/02

US Classification:

415 1, 415111, 415116, 415175, 415180

Abstract:

Embodiments of the present invention include a method and system for carrying out vapor-phase lubrication of a component, such as a bearing for example. The method and apparatus can be applied to a turbine engine. The method includes the step of directing a first stream of fluid containing atomized lubricant to the component at a first velocity. The system provides a first fluid injection system configured to perform the first step. The method also includes the step of directing a second stream of fluid at a second velocity less than the first velocity to the component. The second stream is for controlling a temperature of the component. The system provides a second fluid injection system configured to perform the second step. Both of the directing steps are carried out concurrently.

US Patent:

62326880, May 15, 2001

Filed:

Apr 28, 1999

Appl. No.:

9/301302

Inventors:

Robert Anthony Ress - Carmel IN
Mark Stephen Henry - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis IN
Rolls-Royce Corporation - Indianapolis IN

International Classification:

H02K 709

US Classification:

310 905

Abstract:

The present invention contemplates an internally reinforced high-speed magnetic thrust disk. In one embodiment the internally reinforced composite thrust disk comprises a plurality of high strength fibers coupled together by a soft magnetic alloy. Further, in one aspect the disk having internally reinforced zones for controlling bore growth and counteracting forces associated with the reaction between the stator and the rotor of the electromagnetic thrust bearing system.

US Patent:

59776773, Nov 2, 1999

Filed:

Mar 10, 1998

Appl. No.:

9/040253

Inventors:

Mark S. Henry - Indianapolis IN
Victor Iannello - Roanoke VA
Eugene E. Pfaffenberger - Indianapolis IN
Donald W. Burns - Danville IN

Assignee:

Allison Engine Company - Indianapolis IN

International Classification:

H02K 709

US Classification:

310 905

Abstract:

The present invention contemplates a combination bearing for supporting a rotating rotor within a gas turbine engine. The combination bearing including a magnetic bearing system and dry solid lubricated rolling element auxiliary bearings units for sharing the shaft load. The rotating central shaft being normally supported by the active electromagnetic bearing system. The auxiliary bearing unit being soft mounted to the shaft and engine housing and rotatable with the shaft. Soft mounting of the bearings between the housing and the shaft allows a substantially stable transition from the all magnetic bearing support to a physically contacting mechanically assisted support of the shaft.

US Patent:

57497001, May 12, 1998

Filed:

Jul 17, 1996

Appl. No.:

8/682107

Inventors:

Mark S. Henry - Indianapolis IN
Brian P. King - Greenwood IN

Assignee:

Allison Engine Company, Inc. - Indianapolis IN
Allison Advanced Development Company - Indianapolis IN

International Classification:

F01D 300

US Classification:

415104

Abstract:

The present invention contemplates a hybrid magnetic bearing thrust disk. In one embodiment the hydrid magnetic bearing thrust disk comprises a high magnetic permeable portion that is supported by a high specific strength circumferential ring. The high specific strength circumferential ring resisting the dynamic loads applied to the hydrid thrust disk.

US Patent:

20160258440, Sep 8, 2016

Filed:

Feb 29, 2016

Appl. No.:

15/056317

Inventors:

- Indianapolis IN, US
Mark S. Henry - Indianapolis IN, US

International Classification:

F04D 27/00
F04D 29/66
F04D 29/38
F04D 29/56
F04D 29/52
F04D 29/32

Abstract:

A gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The gas turbine system includes a flutter control system that is adapted to use blade tip timing to determine blade flutter and to direct high pressure air from the compressor to the fan blade row to alter the surface unsteady pressure so that it is out of phase with the blade motion to reduce or eliminate fan blade flutter.