Mihir N Desai, 36Los Angeles, CA

6729139, May 4, 2004

Sep 26, 2001

09/963180

Mihir C. Desai - Yorba Linda CA
Tomasz J. Stanecki - Bristol CT
Jeffrey S. Mattice - Enfield CT

Goodrich Pump Engine Control Systems, Inc. - Charlotte NC

F02C 310

60791, 60 39281

A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

6986641, Jan 17, 2006

Jul 7, 2003

10/614364

Mihir C. Desai - Yorba Linda CA, US
Tomasz J. Stanecki - Bristol CT, US
Jeffrey S. Mattice - Enfield CT, US

Goodrich Pump & Engine Control Systems, Inc. - Charlotte NC

F02C 3/10
F02C 9/28

416 44, 60791, 60 39281

A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

7058556, Jun 6, 2006

Sep 26, 2001

09/963221

Mihir C. Desai - Yorba Linda CA, US
Cristina Crainic - Longueuil, CA

Goodrich Pump & Engine Control Systems, Inc. - West Hartford CT
Pratt & Whitney Canada Corp. - Longueuil

G06F 7/48
G06F 17/10

703 8, 703 2, 700 31

An adaptive aero-thermodynamic engine model is disclosed which incorporates a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions. The engine model is adapted by measuring a plurality of engine operating parameters corresponding to the plurality of model engine operating parameters during steady state operation of the engine over a plurality of data points, matching each of the model engine operating parameters to respective measured engine operating parameters by iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions, estimating actual component efficiencies based upon the adapted nominal component efficiencies, and inputting the estimated actual component efficiencies into the engine model.

7770388, Aug 10, 2010

Nov 15, 2005

11/667741

Mihir C. Desai - Yorba Linda CA, US

Goodrich Pump & Engine Control Systems, Inc. - West Hartford CT

F04B 49/06

60420, 60428

A two-stage system for delivering fuel to a gas turbine including a first stage variable pump for serving as a primary source of fuel, a second stage fixed pump for selectively supplementing the variable pump, a bypass valve connected to the fixed pump for loading and unloading the fixed pump and a regulator valve assembly connected to the variable pump and the bypass valve for controlling operation of the variable pump and the bypass valve. Preferably, the two-stage system also includes a control valve connected to the regulator valve assembly for setting a pressure differential across the regulator valve assembly and, thereby, loading and unloading the fixed pump.

2005010, May 12, 2005

Nov 11, 2003

10/705362

Mihir Desai - Yorba Linda CA, US
William Dalton - Amston CT, US

F04B049/00

417220000

A flow control system for controlling a variable displacement pump including a metering valve in fluid communication with the pump for metering an output of the pump. A regulating valve receives a portion of the output of the pump as a bypass flow at a first pressure, wherein an output of the regulating valve is at an interim pressure. The interim pressure is substantially equal to an average of the first pressure and a low reference pressure. An actuator sets a displacement of the pump by acting on a piston connected to a cam ring of the pump. The actuator receives the interim pressure and, thereby, the output of the variable displacement pump is determined.

2007000, Jan 4, 2007

Jun 29, 2006

11/478038

Mihir Desai - Yorba Linda CA, US
Kurt Grochowski - Wallingford CT, US

F02C 3/30

060775000

The invention includes a fuel delivery system for a gas turbine engine in combination with an associated method and machine readable program. The system includes a fixed displacement pump having an inlet portion and a discharge portion, and a mixer operatively associated with the pump. The mixer includes a first inlet in fluid communication with the discharge portion of the pump for receiving a relatively high pressure bypass flow from the pump, a second inlet in fluid communication with a fuel source for receiving a relatively low pressure fuel flow from the fuel source, a mixing chamber within the mixer wherein the relatively high pressure bypass flow from the pump mixes with the relatively low pressure flow from the fuel source to generate an energized fuel mixture, and a discharge in fluid communication with the mixing chamber for directing the energized fuel mixture to the inlet of the pump.

2011023, Sep 29, 2011

Mar 22, 2011

13/069067

Date Ranjit - Pune, IN
Date Jaydeep - Pune, IN
Mihir Desai - La Canada CA, US

A61B 19/00

606130

A robotic surgical instrument system for performing a surgical procedure is envisaged wherein the system is a dual articulated arm configuration robot that enables entry into an operative space via an access port. Surgical arms are inserted into the operative space in a substantially straight line and then articulated inside the operative space. The articulation of the surgical arms by a surgical console is achieved using ‘triangulation’.

6241392, Jun 5, 2001

Jan 21, 2000

9/489747

Mihir C. Desai - Yorba Linda CA
Raymond D. Zagranski - Sommers CT

Coltec Industries Inc - Charlotte NC

F16C 3206

384100

A bearing for supporting a rotating shaft receiving a transverse load, wherein the bearing supports the shaft along a load line and wherein the bearing is closest to the rotating shaft at a running line. The bearing includes a circumferential inner surface, and a lubricant bay defined in the inner surface. The lubricant bay is axially and circumferentially offset from the load line such that a resulting pressure pad of lubricant within the bay provides a hydrostatic force that forces the running line to a location substantially perpendicular to the load line. Load capabilities of a bearing according to the present disclosure, therefore, are substantially insensitive to shaft bending and do not deteriorate in response to the shaft bending.