Arthur E Harris Deceased2325 Fitzpatrick Ter, Deltona, FL 32725

7665309, Feb 23, 2010

Sep 15, 2008

12/210356

David M. Parker - Oviedo FL, US
Weidong Cai - Oviedo FL, US
Daniel W. Garan - Orlando FL, US
Arthur J. Harris - Orlando FL, US

Siemens Energy, Inc. - Orlando FL

F02C 7/26

60776, 60740, 60746

A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas. The system delivers a secondary fuel/diluent mixture to a secondary combustion zone located along the length of the transition piece, while reducing the impact of elevated vibration levels found within the transition piece and avoiding the heat dissipation difficulties often associated with traditional vibration reduction methods.

2007000, Jan 4, 2007

Jun 29, 2005

11/169478

Rajeev Ohri - Winter Springs FL, US
Kristian Wetzl - Orlando FL, US
Herbert Reid - Orlando FL, US
Arthur Harris - Orlando FL, US
David Parker - Oviedo FL, US
Stephen Mumford - Longwood FL, US

F02C 3/14

060039370, 060748000

A fuel/air mixing apparatus, such as a main swirler assembly () comprising a sleeve (), provides for additional air entry around the perimeter of a bore () through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (). In some embodiments, a plurality of gaps () exists between spaced apart tabs () along a downstream end () of the sleeve (). During gas turbine operation, air flows through both a flashback annulus () and the gaps (). In other embodiments, a plurality of holes are placed upstream and in line with the tabs () to supplement the air flow through gaps (). In yet other embodiments, rows () of holes () are provided to supplement the airflow. Downstream ends () may interface with a downstream-oriented lip () or with an upstream-oriented lip (). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.

2007013, Jun 14, 2007

Dec 8, 2005

11/298323

Rajeev Ohri - Winter Springs FL, US
Arthur Harris - Orlando FL, US
Elliot Griffin - Winter Springs FL, US
Michael Koenig - Oviedo FL, US
Herbert Reid - Orlando FL, US
Paul Maples - Celebration FL, US

F23R 3/60

060796000, 060752000

Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.