Michael Eric Mehrer

US Patent:

7095601, Aug 22, 2006

Filed:

Aug 20, 2004

Appl. No.:

10/922699

Inventors:

Michael E. Mehrer - San Diego CA, US
Joseph James - San Diego CA, US

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

G08B 21/00

US Classification:

361253, 361247, 361256

Abstract:

An exciter circuit for a gas turbine engine delivers a first single high-energy spark followed by subsequent sparks of relatively lower energy to ensures start reliability by specifically clearing ice build-up at the ignition plugs.

US Patent:

7509812, Mar 31, 2009

Filed:

Aug 20, 2004

Appl. No.:

10/922471

Inventors:

Michael E. Mehrer - San Diego CA, US

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

F02C 7/22

US Classification:

60778, 60776, 60786, 60 39821, 60 39827

Abstract:

A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.

US Patent:

7559696, Jul 14, 2009

Filed:

Aug 30, 2004

Appl. No.:

10/929803

Inventors:

Carlos Oncina - Ellensburg WA, US
Michael E. Mehrer - San Diego CA, US
Bing Tong - San Diego CA, US
Pete Suttie - San Diego CA, US
William Dornfield - San Diego CA, US

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

F16C 32/06

US Classification:

384100, 384114

Abstract:

An active thrust management system varies pressure responsive to changes in rotor assembly thrust to maintain a desired position. The system includes a bearing supporting rotation of a rotor assembly within a pressurizing chamber. The rotor assembly is supported on a cushion of air generated between the bearing and the rotor assembly. Pressure within a cavity adjacent the rotor assembly opposes a thrust force to maintain a desired position of the rotor assembly. Modulating airflow into the pressurizing chamber adjacent the rotor assembly compensates for changes in the thrust generated by the rotor assembly to maintain the desired rotor assembly position.

US Patent:

7622821, Nov 24, 2009

Filed:

May 25, 2005

Appl. No.:

11/136746

Inventors:

Michael E. Mehrer - San Diego CA, US
John P. Spencer - Payson AZ, US
Massoud Vaziri - Redmond WA, US

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

H02J 3/14
B64D 41/00
B64C 19/00

US Classification:

307 32, 244 58, 244 751

Abstract:

An Auxiliary Power System includes an APU controller and an aircraft load controller which include an APU load capacity algorithm which provides an uncomplicated and robust method of APU load control. The APU load capacity algorithm defines three load zones: a continuous APU load capacity zone (zone A); a time controlled zone (zone B); and a fault zone (zone C). Each zone is related to altitude to the service ceiling of the APU to provides consistent APU load capacity that addresses APU performance variation and deterioration effects to an end of the APU useful life.

US Patent:

7840333, Nov 23, 2010

Filed:

Mar 30, 2007

Appl. No.:

11/731216

Inventors:

Michael E. Mehrer - San Diego CA, US
Peter J. Suttie - San Diego CA, US
Alex Seguritan - San Diego CA, US
Gilles E. Marion - Genas, FR

Assignee:

Hamilton Sundstrand Corporation - Rockford IL

International Classification:

F02C 7/22

US Classification:

701100, 60788

Abstract:

An event-driven starter controller regulates the speed of a gas turbine engine based on detected events. The event-driven starter controller is used to supply motive force to the gas turbine engine prior such that the gas turbine engine is able to ignite (i. e. , achieve light-off). In particular, in response to engine speed reaching a defined threshold, the event-driven starter controller causes the speed of the starter motor to ramp or increase through a defined range of speeds suitable for engine light-off (i. e, light-off window). Upon reaching an upper threshold of the light-off window, the event-driven starter controller causes the speed of the starter motor to decrease through the range of speeds suitable for engine light-off. If at any time during the light-off window the event-driven starter controller detects a successful light-off condition, the event-driven starter controller causes the speed of the gas turbine engine to increase toward a second threshold.

US Patent:

7904229, Mar 8, 2011

Filed:

Sep 18, 2007

Appl. No.:

11/856758

Inventors:

Rhonda D. Walthall - Escondido CA, US
Walter E. Ainslie - Ramona CA, US
Michael E. Mehrer - San Diego CA, US
William K. Dornfeld - San Diego CA, US
David R. Adair - Valley Center CA, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

G06F 19/00

US Classification:

701100, 701 8, 701 10, 701 99, 701 1

Abstract:

A method of determining lubrication oil consumption in a gas turbine engine that has an engine operating cycle interval comprising a starting phase, a running phase and a shutdown phase, comprises the steps of: measuring lubrication oil level upon initialization of the starting phase of each engine operating cycle interval; comparing the starting phase measured lubrication oil level during the starting phase with a starting phase baseline lubrication measurement; recording the starting phase lubrication oil level measurement; determining average engine lubrication oil consumption rate during the complete engine operating cycle interval by dividing the difference between the starting phase lubrication oil measurement and the baseline lubrication oil measurement; and repeating these steps for each subsequent engine operating cycle interval; wherein the starting phase baseline lubrication oil level measurement is initially a predetermined lubrication oil level and then the previous starting phase lubrication oil measurement for subsequent engine operating cycle intervals.

US Patent:

8446284, May 21, 2013

Filed:

Jun 23, 2011

Appl. No.:

13/166907

Inventors:

Michael E. Mehrer - San Diego CA, US
André M. Ajami - Spring Valley CA, US

Assignee:

Pratt & Whitney - East Hartford CT

International Classification:

G08B 21/00
F16K 21/18
G01F 23/00

US Classification:

340618, 137392, 73290 R

Abstract:

A method of indicating low oil level of lubrication oil for a gas turbine engine automatically eliminates false low oil readings due to temperature-induced lubrication oil shrinkage and operation-induced changes in lubrication oil level.

US Patent:

20140007675, Jan 9, 2014

Filed:

Jul 9, 2012

Appl. No.:

13/544443

Inventors:

Michael E. Mehrer - San Diego CA, US
Richard Gunderson - Santee CA, US
Wagdy Wahba - San Diego CA, US

Assignee:

HAMILTON SUNDSTRAND CORPORATION - Windsor Locks CT

International Classification:

G01F 23/00

US Classification:

73295

Abstract:

A liquid replenishment system includes a reservoir, a first temperature sensor positioned in the reservoir at a full level, a second temperature sensor positioned in the reservoir at an add level, and a controller. The controller is connected to both the first and second sensors. The controller receives temperature signals from the first and second temperature sensors at first and second times. The controller sends an add liquid signal if temperature sensed by the first temperature sensor is substantially different at the first and second times and if temperature sensed by the second temperature sensor is substantially different at the first and second times. The controller sends a full signal if temperature sensed by the first temperature sensor is substantially the same at the first and second times and if temperature sensed by the second temperature sensor is substantially the same at the first and second times.