Anthony J Jones
Radiology at Ave Of Science, San Diego, CA

8438858, May 14, 2013

Aug 20, 2003

10/644705

Anthony Jones - San Diego CA, US
Mark Harris - San Diego CA, US
Eric Alexander - San Diego CA, US
Patrick Lydon - San Marcos CA, US

Hamilton Sundstrand Corporation - Rockford IL

F02C 3/00

60796, 60804

A rotational system for a miniature gas turbine engine includes a rotor shaft rotationally mounted to a forward bearing and an aft bearing. The rotor shaft is located axially with a single threaded rotor nut which provides an axial preload maintained by a fixed compressor wheel and spacers. A preload spring provides dynamic compensation for tolerance variation and undesirable axial movement during rotation of the shaft. A permanent magnet generator is mounted to the rotor shaft behind the forward bearing to generate electrical power for the engine and other accessories. The rotor shaft is inertia welded to a turbine wheel to form a cavity which provides a thermally conductive path away from the aft bearing. A seal ring mounted within a groove within the rotor shaft provides a pneumatic seal to further protect the aft bearing from thermal transfer between the turbine section and the compressor section.

8500064, Aug 6, 2013

Aug 10, 2011

13/207023

Louis J. Bruno - Ellington CT, US
Anthony C. Jones - San Diego CA, US
Todd A. Spierling - Byron IL, US
Gregory L. DeFrancesco - Simsbury CT, US

Hamilton Sundstrand Corporation - Windsor Locks CT

B64C 13/40, B64D 41/00

244 996, 244227, 244 58

A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.

2012011, May 17, 2012

Nov 16, 2010

12/947406

Paul E. Hilgeman - Santee CA, US
Anthony C. Jones - San Diego CA, US
Martin A. Peplow - San Diego CA, US

HAMILTON SUNDSTRAND CORPORATION - Windsor Locks CT

F02C 6/08, F02C 9/18

60772, 60785

A turbine controller controls the operation of a gas turbine generator used to drive an electric generator of an aircraft. The turbine controller controls the gas turbine generator according to air flow demand signals indicative of air flow required by an air management system that regulates cabin pressure and temperature of the aircraft.

5054283, Oct 8, 1991

Sep 19, 1989

7/409314

Anthony Jones - San Diego CA

Sundstrand Corporation - Rockford IL

F02C 7272

60 39142

In order to rapidly start turbine engines in a manner eliminating resort to complex mechanical components, an auxiliary impingement assembly is disclosed. The turbine engine will typically have a turbine rotor with impeller blades integral therewith. It will also include a combustor for producing hot gases of combustion and communicating with the turbine rotor through a turbine nozzle. The turbine engine will normally be driven by the hot gases of combustion produced by the combustor. With this arrangement, the auxiliary impingement assembly will include a self-contained independent source of hot gases which may be directed at the impeller blades to assist the combustor in starting the turbine engine.

7194866, Mar 27, 2007

Jun 20, 2003

10/600401

Anthony Jones - San Diego CA, US
Mark Harris - San Diego CA, US
Eric Alexander - San Diego CA, US
Patrick Lydon - San Marcos CA, US

Hamilton Sundstrand Corporation - Rockford IL

F02C 7/20, F02C 7/06, F02C 1/00

60796, 60798, 60 3908, 60758

A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The static structure defines airflow and lubrication passages which communicate lubricant and airflow to each shaft bearing such that an adequate measured quantity of lubricant is supplied to the bearings in response to engine speed. The airflow through the airflow passage carries the lubrication supplied to the forward bearing toward the aft bearing to further lubricate the aft hot section bearing.

8167540, May 1, 2012

Jan 30, 2008

12/011822

Robert Hans Schlinker - Canton CT, US
James C. Napier - San Diego CA, US
David R. Polak - Glastonbury CT, US
Ray-Sing Lin - Glastonbury CT, US
Scott A. Liljenberg - Wethersfield CT, US
Anthony C. Jones - San Diego CA, US

Hamilton Sundstrand Corporation - Rockford IL

F01D 25/06

415119, 416185, 416203, 416238, 416241 R, 416500

A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

4981018, Jan 1, 1991

May 18, 1989

7/354015

Anthony C. Jones - San Diego CA
Colin Rodgers - San Diego CA

Sundstrand Corporation - Rockford IL

F02C 308, F04D 2942

60726

A narrow efficient operating island for a centrifugal compressor may be increased in a construction including a compressor section 18 mounting blades 22 surrounded by an annular shroud 38 by placing bleed passages 88 in the shroud 38 and angling them in the direction of flow, both axially (FIG. 1) and radially (FIG. 3).

2011029, Dec 8, 2011

Jun 8, 2010

12/796028

James C. Napier - San Diego CA, US
Anthony C. Jones - San Diego CA, US

F02C 3/00

60751

An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel.

8356694, Jan 22, 2013

Aug 28, 2007

11/895961

Anthony C Jones - San Diego CA, US

Pratt & Whitney - East Hartford CT

F01D 25/18

184 611

A recirculating lubrication system for a gas turbine engine comprises: a storage reservoir for storing a quantity of lubrication oil for the engine; an operating reservoir for supplying lubrication oil for the engine; a transfer valve with an inlet coupled to an outlet of the storage reservoir and an outlet coupled to an inlet of the operating reservoir to transfer the quantity of lubrication oil from the storage reservoir to the operating reservoir before starting the engine; and a pump for circulating the transferred lubrication oil through at least one engine bearing and back to the operating reservoir.