Donald W Peters

US Patent:

6871797, Mar 29, 2005

Filed:

Jul 7, 2003

Appl. No.:

10/614632

Inventors:

Donald W. Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K001/06

US Classification:

23926537

Abstract:

A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.

US Patent:

7007483, Mar 7, 2006

Filed:

Dec 14, 2004

Appl. No.:

11/013224

Inventors:

Donald W. Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/06

US Classification:

60771

Abstract:

A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.

US Patent:

7096661, Aug 29, 2006

Filed:

Mar 26, 2004

Appl. No.:

10/811374

Inventors:

Robert H. Bush - Glastonbury CT, US
Sean Zamora - Coventry CT, US
Harry Culver - Colchester CT, US
Donald William Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/00

US Classification:

60232, 60770, 23926519

Abstract:

An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.

US Patent:

7546738, Jun 16, 2009

Filed:

Dec 31, 2004

Appl. No.:

11/026955

Inventors:

Donald W. Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/12

US Classification:

60771, 23926541

Abstract:

A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the flaps for actuating the nozzle between a number of throat area conditions. First and second mode struts respectively restrict rotation of the downstream flap in first and second directions.

US Patent:

7581301, Sep 1, 2009

Filed:

Dec 22, 2006

Appl. No.:

11/644363

Inventors:

Jaime A. Arbona - Middletown CT, US
Donald W. Peters - Colchester CT, US
Robert J. Miller - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B23P 11/00

US Classification:

2952502

Abstract:

A fastener assembly for attaching components of dissimilar materials includes a fastener having a base portion and a protruding portion, and a mechanism for tightening the assembly. The base portion is shaped to be complementary for mating with an attachment feature formed within the non-metal component such that the base portion is retained within the non-metal component. The protruding portion including a base end and a distal end with the distal end including a threaded portion. The fastener assembly allows attachment of components fabricated from dissimilar materials without forming through holes in one of the components. Additionally, the fastener assembly compensates for differences in thermal expansion rates between the non-metal component and the metal component while providing a tight attachment therebetween.

US Patent:

7624567, Dec 1, 2009

Filed:

Sep 20, 2005

Appl. No.:

11/231067

Inventors:

Donald William Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/06
F02K 1/12

US Classification:

60204, 60771, 23926519, 23926539

Abstract:

A nozzle system includes a multitude of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of an exhaust gas path. Each divergent flap includes longitudinal sides having a set of extension which are located at different longitudinal stations such that the extensions on adjacent divergent flaps interfit when the nozzle is in a minimum dilated position yet provide support for the intermediate flap seal when the nozzle is in a maximum dilated position to thereby provide a relative increase in the nozzle area ratio range.

US Patent:

7624579, Dec 1, 2009

Filed:

Feb 15, 2006

Appl. No.:

11/355116

Inventors:

Donald W. Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/12

US Classification:

60771, 23926541

Abstract:

A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes an interface between a forward seal bridge bracket and an aft seal bridge bracket with a forward bridge support and an aft bridge support which provides axial and radial support for the divergent seals between adjacent divergent flaps. A divergent-convergent seal joint structure includes a horn and a fork. By having the forward bridge bracket retain the divergent seal in the axial direction, there is no need for axial sliding of the divergent seal relative to the divergent flap. The joint structure provides circumferential support as the axial and radial support are provided by the bridge-bracket interface. The joint interface permits the forward end section of the divergent seal and the forward end section of the divergent flap to include a radiused surface which provides a smooth interior interface between the convergent section and the divergent sections.

US Patent:

7721550, May 25, 2010

Filed:

Aug 10, 2005

Appl. No.:

11/200895

Inventors:

Donald W. Peters - Colchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/00

US Classification:

60771, 23926519

Abstract:

An aircraft engine nozzle assembly includes an adjustable flap portion that is movable about a pivot for changing the size of an exhaust exit area. A bracket having a curved slot establishes a range of possible movement of the flap portion. A link includes a guide member portion that is received in the curved slot for guiding the movement of the flap portion. The link is connected to a static engine structure and the bracket is movable with the flap portion. The curved slot establishes a range of possible movement of the flap portion along a direction of the curved slot.