Douglas L Welch

Author:

Douglas Welch

ISBN #:

0671068148

Author:

Douglas Welch

ISBN #:

0738539074

Author:

Douglas B. Welch

ISBN #:

0925168270

US Patent:

7517184, Apr 14, 2009

Filed:

Jun 1, 2006

Appl. No.:

11/444562

Inventors:

Mark W. Costa - Storrs CT, US
Jan B. Kowza - Coventry CT, US
Curt R. Hetherington - Newington CT, US
Wendy P. Lopardi - Tolland CT, US
Douglas Welch - Portland CT, US

Assignee:

Unied Technologies Corporation - Hartford CT

International Classification:

F01D 25/24

US Classification:

415 1, 415 9, 415200

Abstract:

A turbine engine fan casing for containing a separated blade fragment comprising a support case having an axially extending impact zone, a substantially structurally continuous penetrable covering circumscribing the impact zone; and a containment covering circumscribing the penetrable covering. The containment covering comprises a textile fabric containing threads in a warp direction and a fill direction, wherein the threads in the warp direction are of a different denier than the threads in the fill direction.

US Patent:

58367446, Nov 17, 1998

Filed:

Apr 24, 1997

Appl. No.:

8/839997

Inventors:

Robert H. Zipps - East Hartford CT
Reginald H. Spaulding - Hebron CT
Edward S. Todd - East Hampton CT
Robert F. Kasprow - Wethersfield CT
Herman C. Klapproth - Enfield CT
Douglas A. Welch - Portland CT
Phyllis L. Kurz - Hebron CT
Joseph J. Cafasso - Glastonbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 2938

US Classification:

416193A

Abstract:

The present invention relates to a fan blade in an axial gas turbine engine. The blade platform is constructed to fracture adjacent the airfoil portion of the blade so as to locate the fractured edge of the platform in the root portion. As a result of this benign platform, damage to successive fan blades during a blade loss condition is reduced. In addition, various construction details are developed in the airfoil and root portion of the fan blade to reduce damage to fan blades during impact with adjacent blades.

US Patent:

61460990, Nov 14, 2000

Filed:

Jul 30, 1998

Appl. No.:

9/127710

Inventors:

Robert H. Zipps - East Hartford CT
Reginald H. Spaulding - Hebron CT
Edward S. Todd - East Hampton CT
Robert F. Kasprow - Wethersfield CT
Herman C. Klapproth - Enfield CT
Douglas A. Welch - Portland CT
Phyllis L. Kurz - Hebron CT
Joseph J. Cafasso - Glastonbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 2938

US Classification:

416193A

Abstract:

A fan in an axial flow gas turbine engine includes a plurality of fan blades. Each fan blade includes an airfoil portion and a root portion with a platform disposed radially therebetween. The platform of each blade extends circumferentially from the blade and is dimensioned to define, with an adjacent platform, an enlarged gap to insure that contact between adjacent platforms is avoided when a blade is released during a blade loss condition. A seal is provided to seal the enlarged gap between adjacent platforms during normal operation of the gas turbine engine.

US Patent:

54763630, Dec 19, 1995

Filed:

Oct 15, 1993

Appl. No.:

8/138521

Inventors:

Melvin Freling - West Hartford CT
Gary A. Gruver - South Windsor CT
Joseph J. Parkos - East Haddam CT
Douglas A. Welch - Portland CT

Assignee:

Pratt & Whitney - East Hartford CT

International Classification:

F01D 1108
F01D 514

US Classification:

4151731

Abstract:

A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

US Patent:

60481749, Apr 11, 2000

Filed:

Sep 10, 1997

Appl. No.:

8/927680

Inventors:

Marc Samit - West Hartford CT
Douglas A. Welch - Portland CT
Paul W. Duesler - Manchester CT
Patrick D. Markham - Glastonbury CT
Allan R. Penda - Amston CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 2938
F01D 518

US Classification:

416233

Abstract:

A hollow airfoil (34) for a gas turbine engine having a leading edge (50), a trailing edge (52), a pressure side (54), and a suction side (56) includes a solid region of enhanced chordal thickness (78), and buttresses (82, 84, 86, 88). The present invention airfoil is preferentially strengthened so as to reduce the risk of airfoil fracture due to impact of airfoil with successive airfoils during an airfoil loss condition.

Address:

2100 Ocean Shr Blvd APT 116, Ormond Beach, FL 32176

Phone:

386 441-7431

VIN:

3GNFK12397G154298

Make:

CHEVROLET

Model:

AVALANCHE

Year:

2007