Ken R Lagueux

US Patent:

8038388, Oct 18, 2011

Filed:

Mar 5, 2007

Appl. No.:

11/682048

Inventors:

Melvin Freling - West Hartford CT, US
Ken Lagueux - Berlin CT, US
Christopher W. Strock - Kennebunk ME, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 11/00

US Classification:

4151744, 415200

Abstract:

A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. The seal member is coated with an abrasive material.

US Patent:

20120099992, Apr 26, 2012

Filed:

Oct 25, 2010

Appl. No.:

12/910989

Inventors:

Christopher W. Strock - Kennebunk ME, US
Ken Lagueux - Berlin CT, US
Paul W. Baumann - Amesbury MA, US
Matthew E. Bintz - West Hartford CT, US
Thomas W. Stowe - Hebron CT, US
Paul H. Zajchowski - Enfield CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 11/08
F16J 15/16

US Classification:

416174, 277300

Abstract:

A compressor rotor seal includes a bare radial inward end of a rotor vane in proximity to a rotor surface coated with an abrasive material.

US Patent:

20130017057, Jan 17, 2013

Filed:

Jul 15, 2011

Appl. No.:

13/183485

Inventors:

Ken Lagueux - Berlin CT, US

International Classification:

F01D 11/08

US Classification:

415 1, 4151733

Abstract:

An example blade outer air seal assembly includes a blade outer air seal that is biased toward a second part. The blade outer air seal and the second part move together radially during operation. Radial inward movement of the blade outer air seal is limited exclusively by the second part during operation.

US Patent:

20130028705, Jan 31, 2013

Filed:

Jul 26, 2011

Appl. No.:

13/190674

Inventors:

Ken Lagueux - Berlin CT, US

International Classification:

F01B 25/02

US Classification:

415 1, 415146

Abstract:

An active clearance control system utilizes a working fluid stream to control radial thermal growth and thereby a clearance between turbine blades and a corresponding shroud of a gas turbine engine. Conduits disposed about a turbine case and proximate to pads defined within the turbine case include a flow surface parallel to the pads. The pads are an area of increased thickness in the turbine case that receives impingement flow from the conduits. Grooves within the pads further increase impingement cooling flow effectiveness. The increased thickness of the pads provides the thermal mass desired to effect thermal expansion and contraction responsive to the cooling airflow.

US Patent:

61901245, Feb 20, 2001

Filed:

Nov 26, 1997

Appl. No.:

8/979065

Inventors:

Melvin Freling - West Hartford CT
Dinesh K. Gupta - South Windsor CT
Ken Lagueux - Berlin CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 514

US Classification:

4151734

Abstract:

A gas turbine engine seal system includes a rotating member having an abrasive tip disposed in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface.

US Patent:

6180262, Jan 30, 2001

Filed:

Dec 19, 1997

Appl. No.:

8/994926

Inventors:

Melvin Freling - West Hartford CT
Ken R. Lagueux - Berlin CT
Paul H. Zajchowski - Enfield CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 528

US Classification:

428633

Abstract:

An abrasive coating is prepared by plasma spraying a top coating over a bond coating medium. The resultant structure has an improved resistance to corrosion, and a lower thermal conductivity. The coating provides substantially enhanced engine efficiency and improved durability.

US Patent:

50888854, Feb 18, 1992

Filed:

Oct 12, 1989

Appl. No.:

7/420196

Inventors:

Fred M. Schwarz - Glastonbury CT
Ken R. Lagueux - Berlin CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 508

US Classification:

415115

Abstract:

A method for preventing rubbing between a gas turbine engine rotor and surrounding annular shroud during transient changes in engine power monitors high rotor speed for determining the existence of a thermal mismatch between the rotor and shroud supporting turbine case (9). The method directs the cooling flow modulating valve (44) to substantially shut off the flow of cooling air to the case (9) for a period of time sufficient to allow the thermal mismatch to pass.

US Patent:

50053523, Apr 9, 1991

Filed:

Jun 23, 1989

Appl. No.:

7/372398

Inventors:

Fred M. Schwarz - Glastonbury CT
Clifton J. Crawley - Glastonbury CT
Anthony Rausco - Middletown CT
Ken R. Lagueux - Berlin CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 718

US Classification:

60 3902

Abstract:

A method for scheduling the flow of cooling air to a gas turbine engine achieves a varying clearance between the turbine blade tips and surrounding annular shroud responsive to the current engine power level. Excess clearance is provided during operation at less than maximum normal engine power to accommodate the transient decrease in clearance following a step change in engine power level.