Alan H Epstein

US Patent:

6392313, May 21, 2002

Filed:

Jul 15, 1999

Appl. No.:

09/354544

Inventors:

Alan H. Epstein - Lexington MA
Stephen D. Senturia - Brookline MA
Ian A. Waitz - Newton MA
Jeffrey H. Lang - Sudbury MA
Stuart A. Jacobson - Somerville MA
Fredric F. Ehrich - Marblehead MA
Martin A. Schmidt - Reading MA
G. K. Ananthasuresh - Philadelphia PA
Mark S. Spearing - Newton MA
Kenneth S. Breuer - Newton MA
Steven F. Nagle - Cambridge MA

Assignee:

Massachusetts Institute of Technology - Cambridge MA

International Classification:

H01L 2984

US Classification:

290 52, 310 40 MM, 60 3936, 257414

Abstract:

The invention overcomes limitations of conventional power and thermodynamic sources by with micromachinery components that enable production of significant power and efficient operation of thermodynamic systems in the millimeter and micron regime to meet the efficiency, mobility, modularity, weight, and cost requirements of many modern applications. A micromachine of the invention has a rotor disk journalled for rotation in a stationary structure by a journal bearing. A plurality of radial flow rotor blades, substantially untapered in height, are disposed on a first rotor disk face, and an electrically conducting region is disposed on a rotor disk face. A plurality of stator electrodes that are electrically interconnected to define multiple electrical stator phases are disposed on a wall of the stationary structure located opposite the electrically conducting region of the rotor disk. A first orifice in the stationary structure provides fluidic communication with the first rotor disk face at a location radially central of the rotor blades, and a second orifice in the stationary structure provides fluidic communication with the first rotor disk face at a location radially peripheral of the rotor blades. An electrical connection to the stator electrode configuration is provided for stator electrode excitation and for power transfer with the stator electrode configuration as the rotor disk rotates.

US Patent:

6871487, Mar 29, 2005

Filed:

Feb 14, 2003

Appl. No.:

10/367227

Inventors:

Anthony D. Kurtz - Ridgewood NJ, US
John Chivers - Derby, GB
Alan Epstein - Lexington MA, US

Assignee:

Kulite Semiconductor Products, Inc. - Leonia NJ

International Classification:

F02C009/54

US Classification:

60 39281, 60 3927, 60795

Abstract:

The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.

US Patent:

7074016, Jul 11, 2006

Filed:

May 23, 2003

Appl. No.:

10/445249

Inventors:

Alan H. Epstein - Lexington MA, US
Antoine Deux - Falls Church VA, US
Yoav P. Peles - Rensselaer NY, US
Laurent Jamonet - Aix-en-Provence, FR

Assignee:

Massachusetts Institute of Technology - Cambridge MA

International Classification:

F01D 1/06
F04B 17/00

US Classification:

417348, 417406, 415 84

Abstract:

A turbopump including a rotor having a first face and a second face and being characterized by a rotor axial height between the first and second rotor faces and by a rotor diameter. A rotor housing includes bearing surfaces for supporting rotation of the rotor, includes turbine inlet and turbine outlet ports and pump inlet and pump outlet ports, and includes pump and turbine fluid sealing surfaces. A plurality of turbine blades of a turbine blade axial height, and a plurality of pump blades of a pump blade axial height, are disposed on a face of the rotor. The turbine blades and pump blades can be together disposed on the rotor first face. Further or alternatively, a turbopump axial height including rotor bearings, turbine blade and pump blade axial height, and rotor axial height, can be less than rotor diameter.

US Patent:

7159401, Jan 9, 2007

Filed:

Dec 23, 2004

Appl. No.:

11/023035

Inventors:

Anthony D. Kurtz - Ridgewood NJ, US
John Chivers - Derby, GB
Alan Epstein - Lexington MA, US

Assignee:

Kulite Semiconductor Products, Inc. - Leonia NJ

International Classification:

F02C 9/54

US Classification:

60772

Abstract:

The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.

US Patent:

8176725, May 15, 2012

Filed:

Sep 9, 2009

Appl. No.:

12/556359

Inventors:

Jams W. Norris - Lebanon CT, US
Alan Epstein - Lexington MA, US
Gary D. Roberge - Tolland CT, US
Mark W. Costa - Storrs CT, US
Andrew P. Berryann - Coventry CT, US
Daniel B. Kupratis - Wallingford CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 3/02

US Classification:

602261, 60761

Abstract:

A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.

US Patent:

20100122519, May 20, 2010

Filed:

Nov 9, 2009

Appl. No.:

12/614640

Inventors:

Alan Epstein - Lexington MA, US
Richard C. Miake-Lye - Lexington MA, US

International Classification:

F02C 3/20
C10L 1/04
C07C 9/00

US Classification:

60 39461, 208 16, 585 16

Abstract:

A method of managing contrail formation of a gas turbine engine includes delivering an ultra-low sulfur fuel to a combustor of a gas turbine engine to limit an amount of sulfur byproduct produced in an exhaust of the gas turbine engine.

US Patent:

20130220004, Aug 29, 2013

Filed:

Feb 29, 2012

Appl. No.:

13/409036

Inventors:

Alan H. Epstein - Lexington MA, US
Elizabeth A. Mitchell - Marlborough CT, US

International Classification:

G01M 15/14

US Classification:

7311201

Abstract:

An exemplary debris detection method according to one example embodiment of the present disclosure includes, among other things, monitoring turbomachine performance, and initiating a debris warning when an actual rate of change in turbomachine performance varies from a predicted rate of change in the performance.

US Patent:

20130223991, Aug 29, 2013

Filed:

Feb 29, 2012

Appl. No.:

13/407836

Inventors:

Gabriel L. Suciu - Glastonbury CT, US
Alan H. Epstein - Lexington MA, US
Wesley K. Lord - South Glastonbury CT, US
Michael E. McCune - Colchester CT, US
Brian D. Merry - Andover CT, US

International Classification:

F01D 15/12

US Classification:

4151221

Abstract:

A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.