Charles R Lejambre

US Patent:

7726937, Jun 1, 2010

Filed:

Sep 12, 2006

Appl. No.:

11/519629

Inventors:

P. William Baumann - Amesbury MA, US
Om Parkash Sharma - South Windsor CT, US
Charles R. LeJambre - New Britain CT, US
Sanjay S. Hingorani - Glastonbury CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/54

US Classification:

415191, 4151995, 4152084, 4152085, 4152112

Abstract:

A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.

US Patent:

20090067993, Mar 12, 2009

Filed:

Mar 22, 2007

Appl. No.:

11/689651

Inventors:

Gary D. Roberge - Tolland CT, US
Charles R. Lejambre - New Britain CT, US
Charles R. Watson - Windsor CT, US

International Classification:

F01D 17/16
F02K 1/06

US Classification:

415145, 60771, 415 1

Abstract:

A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions.

US Patent:

6375419, Apr 23, 2002

Filed:

Jun 2, 1995

Appl. No.:

08/459986

Inventors:

Charles R. LeJambre - Marlborough CT
Bruce P. Biederman - Meriden CT
Aaron J. Gleixner - Philadelphia PA
Chad J. Yetka - West Palm Beach FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 514

US Classification:

415191, 415192, 4152082, 416223 A, 416238

Abstract:

A flow directing element, such as a vane for a turbine engine compressor, has a variable chord to improve compressor surge margin without compromising compressor efficiency. The vane has an airfoil section ( ) with a leading edge ( ), a trailing edge ( ), a root ( ) and a tip ( ). The chord of the airfoil generally increases from a first value at the root to a second larger value at a part span location ( ) intermediate the root and the tip so that when the airfoil is installed in a compressor, the location of the trailing edge becomes closer to the compressor discharge as the spanwise distance from the root increases. The chord is generally constant from the part span location to the tip.

US Patent:

20160319837, Nov 3, 2016

Filed:

Dec 3, 2014

Appl. No.:

15/103817

Inventors:

Robert J. MORRIS - Hartford CT, US
Carroll V. SIDWELL - Hartford CT, US
Coy B. WOOD - Hartford CT, US
Charles R. LEJAMBRE - Hartford CT, US
- Farmington CT, US

International Classification:

F04D 29/36
F04D 29/66
F04D 29/38
F04D 27/00
F04D 29/32

Abstract:

A gas turbine engine includes a plurality of blades, a sensor configured to detect vibration on one or more of the plurality of blades, and a controller coupled to the sensor and configured to adjust a blade incidence upon an onset of vibration being detected by the sensor wherein the adjustment of the blade incidence reduces the vibration.