Timothy A Swanson

US Patent:

7097421, Aug 29, 2006

Filed:

Oct 8, 2004

Appl. No.:

10/961178

Inventors:

Timothy A. Swanson - Coventry CT, US
James E. Jones - Palm City FL, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 25/24

US Classification:

415127, 415159, 60 3923

Abstract:

A vernier duct blocker comprising a plurality of vanes each having a width and comprising a forward portion and an aft portion defining a plurality of gas paths each of the plurality of vanes being separated by a plurality of widths, and a rotatably movable ring interposed between the forward portion and the aft portion comprising a plurality of openings each having a width, wherein the width of one of the plurality of vanes differs from the width of another one of the plurality of vanes.

US Patent:

7871242, Jan 18, 2011

Filed:

May 31, 2007

Appl. No.:

11/755925

Inventors:

Timothy A. Swanson - Coventry CT, US
Carl T. Elving - Southlake TX, US
Robert T. Brooks - Killingworth CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 9/00

US Classification:

415145, 415155, 415160, 415 1

Abstract:

A rotational flow balance system includes an actuator system which controls operation of both a fan duct blocker ring and a modulated exhaust cooling ring through a kinematic system. The kinematic system is controlled by the single actuator system such that the modulated exhaust cooling ring will remain in a fixed position while the fan duct blocker ring can be moved to satisfy operational requirements.

US Patent:

7874160, Jan 25, 2011

Filed:

Aug 21, 2007

Appl. No.:

11/894313

Inventors:

Timothy A. Swanson - Coventry CT, US
Sean P. Zamora - Coventry CT, US
Robert H. Bush - Glastonbury CT, US
Alex J. Simpson - Mansfield CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 1/00

US Classification:

60771, 23926519

Abstract:

A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle.

US Patent:

8356483, Jan 22, 2013

Filed:

Apr 10, 2008

Appl. No.:

12/100470

Inventors:

Dale William Petty - Wallingford CT, US
Shawn M. McMahon - Manchester CT, US
Michael Joseph Murphy - Vernon CT, US
Sean P. Zamora - Coventry CT, US
Timothy A. Swanson - Coventry CT, US

Assignee:

United Technologies Corp - Hartford CT

International Classification:

F02K 1/06

US Classification:

60770, 60771, 60231, 60232, 602261, 602263, 23926517, 23926519, 23926535

Abstract:

A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

US Patent:

20080072604, Mar 27, 2008

Filed:

Sep 26, 2006

Appl. No.:

11/527188

Inventors:

Timothy A. Swanson - Coventry CT, US
Debora F. Kehret - Manchester CT, US
Stefan M. Poth - South Windsor CT, US
Donald E. Grove - East Hartford CT, US

International Classification:

F02K 1/00

US Classification:

60770

Abstract:

A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked.

US Patent:

20080098742, May 1, 2008

Filed:

Oct 27, 2006

Appl. No.:

11/588884

Inventors:

Andreas Sadil - Newington CT, US
Timothy A. Swanson - Coventry CT, US
Roger O. Coffey - Glastonbury CT, US
Debora F. Kehret - Manchester CT, US

International Classification:

F02K 1/00

US Classification:

60770

Abstract:

A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.

US Patent:

20090241550, Oct 1, 2009

Filed:

Mar 25, 2008

Appl. No.:

12/054762

Inventors:

Dale William Petty - Wallingford CT, US
Timothy A. Swanson - Coventry CT, US
Shawn M. McMahon - Manchester CT, US

Assignee:

UNITED TECHNOLOGIES CORP. - Hartford CT

International Classification:

F02K 1/06

US Classification:

60771

Abstract:

Gas turbine engine systems involving flexible panels are provided. In this regard, a representative flexible panel assembly for a gas turbine engine includes: a flexible panel operative to define at least one of a throat area and an exit area of a nozzle of a gas turbine engine, the panel being further operative to selectively exhibit a range of positions to regulate exhaust of the engine.

US Patent:

20110088403, Apr 21, 2011

Filed:

Dec 16, 2010

Appl. No.:

12/970478

Inventors:

Timothy A. Swanson - Coventry CT, US
Sean P. Zamora - Coventry CT, US
Robert H. Bush - Glastonbury CT, US
Alex J. Simpson - Mansfield CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F02K 1/12

US Classification:

60771

Abstract:

A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle.