Michael P Cass

US Patent:

8172512, May 8, 2012

Filed:

Apr 23, 2008

Appl. No.:

12/107811

Inventors:

Keith E. Short - Rockford IL, US
Jeffrey M. Makulec - Rockford IL, US
Brian Kent Rockwell - Rockford IL, US
Michael F. Cass - Rockford IL, US
Gregory W. Vermillion - Rockford IL, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

F01D 15/00

US Classification:

4151213, 4151241

Abstract:

An accessory gearbox system for a gas turbine engine includes an accessory compressor mounted to a gearbox housing. The gearbox housing defines a seal air core, and the gearbox housing communicates a seal airflow through the seal air core.

US Patent:

8424416, Apr 23, 2013

Filed:

Jun 18, 2010

Appl. No.:

12/818535

Inventors:

Keith E. Short - Rockford IL, US
Michael F. Cass - Rockford IL, US
Craig R. Legros - Rockford IL, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

F16H 37/06
B64D 35/00

US Classification:

74665GB, 74423

Abstract:

An apparatus is provided and includes a rotatable shaft on which a first bevel gearbox is disposed, a layshaft on which a second bevel gearbox is disposed, the first and second bevel gearboxes being coupled to transmit shaft rotation to the layshaft, an accessory gearbox to which the layshaft and one or more accessories are coupled and a generator operably disposed on the layshaft between the second bevel gearbox and the accessory gearbox.

US Patent:

20100242496, Sep 30, 2010

Filed:

Mar 30, 2009

Appl. No.:

12/413634

Inventors:

Michael F. Cass - Rockford IL, US
James S. Elder - South Windsor CT, US
Brian D. Merry - Andover CT, US
Gabriel L. Suciu - Glastonbury CT, US
Chritopher M. Dye - South Windsor CT, US

International Classification:

F02C 6/00
F02C 7/32

US Classification:

60802, 74 158

Abstract:

An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis.

US Patent:

20110146434, Jun 23, 2011

Filed:

Jun 3, 2010

Appl. No.:

12/792849

Inventors:

Keith E. Short - Rockford IL, US
Michael F. Cass - Rockford IL, US
Michael R. Blewett - Stillman Valley IL, US

International Classification:

F16H 57/02
F16D 1/06

US Classification:

74405, 74606 R

Abstract:

A gearbox for an aircraft has a first side wall, a second side wall, a gear train, and an aircraft accessory. The aircraft accessory has a housing, an input attaching to the gear train for receiving rotative input from the gear train, and a first shaft for selectively coupling and uncoupling the gear train from the input. The housing attaches to the first side wall and the second side wall.

US Patent:

20110293460, Dec 1, 2011

Filed:

May 26, 2010

Appl. No.:

12/787554

Inventors:

Sara Dexter - Rockford IL, US
Michael F. Cass - Rockford IL, US

International Classification:

F04C 2/00

US Classification:

418209

Abstract:

A vane pump has an inlet window and a discharge window formed within a cam surface. The vane pump includes a rotor carrying a plurality of radially extending vanes which are biased into contact with the cam surface. The rotor has a direction of rotation such that one end of the inlet window can be described as an upstream end, and an opposed end as a downstream end. The inlet window extends for a relatively long width along a rotational axis of the rotor at the upstream end. Angularly inwardly extending sides reduce an axial width of the inlet window in a direction moving in a downstream direction from the upstream end.

US Patent:

61893137, Feb 20, 2001

Filed:

Apr 16, 1999

Appl. No.:

9/292681

Inventors:

Michael Andrew Cass - Rockford IL
Keith Everett Short - Rockford IL

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

F02C 7224

US Classification:

60 3931

Abstract:

An aircraft engine assembly includes an engine, an engine control actuator responsive to flow of high pressure fuel therethrough for actuating engine controls, a fuel heat exchanger for heating fuel, a fuel controller for controlling flow of fuel in the aircraft engine assembly, a fuel pump having a low pressure section for pressurizing the fuel to a low pressure, and a high pressure section for pressurizing the fuel to a high pressure, an engine gearbox, a seal plate, and a manifold mounted on the engine gearbox and having the fuel pump and the fuel controller mounted thereon, with the seal plate between the fuel pump and fuel controller and the manifold. The manifold provides fuel flow paths between the fuel pump and fuel controller and the several other components of the aircraft engine assembly, replacing the several pipe connections of the prior art. Therefore, it is not necessary to disconnect and reconnect the several pipe connections when removing and reinstalling the fuel pump or fuel controller during repair or replacement. The seal plate assures that leaks are avoided.

US Patent:

20170037863, Feb 9, 2017

Filed:

Aug 7, 2015

Appl. No.:

14/821389

Inventors:

- Charlotte NC, US
Joseph Wetch - Roscoe IL, US
Adrian L. Stoicescu - Roscoe IL, US
Michael F. Cass - Rockford IL, US

International Classification:

F04D 29/22
F02M 59/44
F04D 29/28

Abstract:

An impeller spinner for a fuel pump can include a head and a shank. The head can have a base at one end and a tip at an opposite end. The shank can have a body portion nearest the head with a first diameter and a fastener portion adjacent to the body portion at an end opposite the head with a second diameter.