Michael K Sahm

US Patent:

6634596, Oct 21, 2003

Filed:

Feb 14, 2002

Appl. No.:

10/077277

Inventors:

Jose Albero - Quebec J6W 5P5, CA
Louis J. Bruno - Ellington CT 06029
Richard Dussault - Quebec J4P 2V8, CA
Charles E. Lents - Rockford IL 61103
Wayne A. Thresher - Springfield MA 01108-1742
Michael K. Sahm - Avon CT 06001
Robert G. Thompson - San Diego CA 92131

International Classification:

F02K 312

US Classification:

244 53A, 244 53 R, 60224

Abstract:

An integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

US Patent:

6663044, Dec 16, 2003

Filed:

Sep 20, 2002

Appl. No.:

10/251719

Inventors:

Jules Ricardo Munoz - Vernon CT
Luca Bertuccioli - Enfield CT
Michael K. Sahm - Avon CT
Jay Fletcher - Marlborough CT
Charles E. Lents - Amston CT
Richard Welch - Rockford IL
Steve Squier - Rockford IL
Arthur Chris Becker - Andover CT

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

B64D 1100

US Classification:

2441185, 62172, 62 93, 62 87, 62402, 60 3907, 60366

Abstract:

The present invention relates to a vapor compression cycle environmental control system for use on aircraft. The system includes an environmental control subsystem which supplies pressurized ram air at a desired temperature to the aircrafts flight deck and/or cabin. The environmental control subsystem uses a vapor compression cycle subsystem to provide the ram air at the desired temperature. The system further includes an air turbine driven by engine bleed air to provide power to an aircraft mounted accessory drive and to provide heated air to an anti-ice system. The aircraft mounted accessory drive provides power to an air compressor which forms part of the environmental control subsystem and to a working fluid compressor which forms part of the vapor compression cycle subsystem.

US Patent:

6672856, Jan 6, 2004

Filed:

Jun 28, 2002

Appl. No.:

10/187165

Inventors:

H. Ezzat Khalifa - Manlius NY
Michael K. Sahm - Avon CT

Assignee:

Carrier Corporation - Syracuse NY

International Classification:

F04C 1816

US Classification:

4182011, 415207, 4152112

Abstract:

A screw compressor includes a housing containing at least one rotor for generating a discharge flow in a discharge flow direction; a diffuser communicated with the housing and having a collecting portion for receiving the discharge flow, a diffuser throat and a diffuser portion, said diffuser extending from the housing in a diffuser direction; and at least one turning vane positioned in the collecting portion and adapted to guide flow from the discharge flow direction to the diffuser direction.

US Patent:

6704625, Mar 9, 2004

Filed:

Feb 14, 2002

Appl. No.:

10/076898

Inventors:

Jose Albero - Lachenaie, CA
Charles E. Lents - Rockford IL
Michael K. Sahm - Avon CT
Richard C. Welch - Rockford IL

Assignee:

Hamilton Sunstrand Corporation - Windsor Locks CT

International Classification:

B64B 124

US Classification:

701 3, 244 53 R, 244 58, 244202

Abstract:

The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.

US Patent:

6796527, Sep 28, 2004

Filed:

Sep 20, 2002

Appl. No.:

10/251720

Inventors:

Jules Ricardo Munoz - Vernon CT
Luca Bertuccioli - Enfield CT
Michael K. Sahm - Avon CT
Jay Fletcher - Marlborough CT
Charles E. Lents - Amston CT
Steve Squier - Rockford IL
Richard Welch - Rockford IL
Arthur Curtis Becker - Andover CT

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

B64D 1100

US Classification:

2441185, 244 58, 454 74, 454 76, 60 39142

Abstract:

The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

US Patent:

6817575, Nov 16, 2004

Filed:

Sep 20, 2002

Appl. No.:

10/251721

Inventors:

Jules Ricardo Munoz - South Windsor CT
Luca Bertuccioli - East Longmeadow MA
Michael K. Sahm - Avon CT
Jay Fletcher - Marlborough CT
Charles E. Lents - Amston CT
Steven E. Squier - Rockford IL
Richard Welch - Rockford IL
Arthur Curtis Becker - Andover CT

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

B64D 1308

US Classification:

2441185, 60 3907, 454 76

Abstract:

The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

US Patent:

6845630, Jan 25, 2005

Filed:

Feb 14, 2002

Appl. No.:

10/077281

Inventors:

Louis J. Bruno - Ellington CT, US
Charles E. Lents - Rockford IL, US
Michael K. Sahm - Avon CT, US
Wayne A. Thresher - Springfield MA, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

F25D 900
B64D 1302

US Classification:

623233, 62402, 454 71

Abstract:

The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

US Patent:

6868664, Mar 22, 2005

Filed:

Dec 13, 2001

Appl. No.:

10/015439

Inventors:

Jose Albero - Lachenaie, CA
Richard Dussault - St-Lambert, CA
Robert G. Thompson - San Diego CA, US
Patrick Germain - Outremont, CA
Michael K. Sahm - Avon CT, US
Eric Tremaine - Longueuil, CA

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K011/00

US Classification:

60224, 602261, 60 3935

Abstract:

A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.