Samer P Wasif

US Patent:

7413053, Aug 19, 2008

Filed:

Jan 25, 2006

Appl. No.:

11/339721

Inventors:

Samer P. Wasif - Oviedo FL, US
Clifford E. Johnson - Orlando FL, US

Assignee:

Siemens Power Generation, Inc. - Orlando FL

International Classification:

G10K 11/02

US Classification:

181293, 181210, 181211, 181213, 181292

Abstract:

Aspects of the invention are directed to an acoustic resonator with improved impingement cooling effectiveness. The resonator includes a plate with an inside face and an outside face. A plurality of passages extend through the plate. The resonator includes a side wall that extends from and about the plate. A plurality of cooling tubes are attached to the resonator plate such that an inner passage of each cooling tube is in fluid communication with a respective passage in the resonator plate. The resonator can be secured to a surface of a turbine engine combustor component to define a closed cavity. The ends of the cooling tubes are spaced from the surface. Thus, a coolant can enter the passages in the plate and can be directed to the surface so as to impingement cool the surface. The cooling tubes can minimize coolant loss by dispersion in the cavity.

US Patent:

7788926, Sep 7, 2010

Filed:

Aug 18, 2006

Appl. No.:

11/506993

Inventors:

Clifford E. Johnson - Orlando FL, US
Samer P. Wasif - Oviedo FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F02C 7/24
F02C 3/00
B64F 1/26

US Classification:

60725, 60 3937, 181210

Abstract:

One or more Helmholtz-type resonators () is/are provided at the junction () of a combustor () and a combustion chamber () of a gas turbine engine (). In one embodiment, adjacent Helmholtz-type resonators (), which may be separated by respective baffles (), have different volumes that help provide for damping different undesired combustion-generated acoustic pressure waves. In some embodiments, a structural member () may be provided between adjacent Helmholtz-type resonators () at the junction. At least one of the plurality of Helmholtz-type resonators comprises one or more inlet openings (), and one or more exit openings (). Embodiments (-) are described in which Helmholtz-type resonators provided at the junction are enlarged in size using various approaches. The positioning at the junction, upstream of the space () in which combustion occurs, and providing a plurality of differently sized resonators, provides for improved flexibility and resonator damping efficiencies.

US Patent:

7926279, Apr 19, 2011

Filed:

Sep 21, 2006

Appl. No.:

11/524740

Inventors:

Samer P. Wasif - Oviedo FL, US
Robert J. Bland - Oviedo FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60740, 60742

Abstract:

A gas sleeve () for a combustor () of gas turbine engine () attaches to a support housing () of the combustor () to convey a fuel gas and to fit within a fuel rocket (). The gas sleeve () comprises a plurality of apertures () formed to provide impingement cooling. The apertures () comprise a tilt angle directed toward a structure in need of impingement cooling, for instance a weld joint () that attaches the fuel rocket () to the support housing (). The apertures () additionally may comprise a rotational angle effective to create a rotationally swirling flow of the portion of fuel gas that passes through the apertures (). A method of operation using this structure also is provided.

US Patent:

8061141, Nov 22, 2011

Filed:

Sep 27, 2007

Appl. No.:

11/862426

Inventors:

Clifford E. Johnson - Orlando FL, US
Joachim Lepers - Düsseldorf, DE
Samer P. Wasif - Oviedo FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F02C 7/24

US Classification:

60725, 60752

Abstract:

A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least one opening, a resonator side wall coupled to the resonator outer plate, and a resonator inner plate defined by a portion of the liner. The resonator inner plate is coupled to the resonator side wall and has at least one slot formed therein having an aspect ratio of at least 4:1.

US Patent:

8146364, Apr 3, 2012

Filed:

Sep 14, 2007

Appl. No.:

11/855747

Inventors:

Clifford E. Johnson - Orlando FL, US
Robert J. Bland - Oviedo FL, US
Domenico Gambacorta - Oviedo FL, US
Samer P. Wasif - Oviedo FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F02C 7/24

US Classification:

60725, 431114

Abstract:

Embodiments of the present invention provide resonators () that have lateral walls () disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis () such that a film cooling of substantial portions of an intervening strip () is provided from apertures (A, B, ) in a resonator box () adjacent and upstream from the intervening strip (). This film cooling also cools weld seams () along the lateral walls () of the resonator boxes (). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.

US Patent:

20050016178, Jan 27, 2005

Filed:

Sep 19, 2003

Appl. No.:

10/667263

Inventors:

Samer Wasif - Oviedo FL, US
Udo Schmitz - Muelheim, DE
Robert Bland - Oviedo FL, US
Karsten Jordan - Essen, DE
John Glessner - Oviedo FL, US
J. Markovitz - Sanford FL, US
Bernd Prade - Muelheim, DE
David Kargetta - New Smyma Beach FL, US
Stephen Ramier - Oviedo FL, US
Stefan Dahlk - Kuerten-Bechen, DE

International Classification:

F23R003/42

US Classification:

060752000

Abstract:

A gas turbine engine () includes a cylindrical basket () having an axis () and a single main burner assembly () disposed within the basket. A burner insert () is disposed in an annular space between the burner assembly and the basket. The insert includes a face perpendicular to the axis of the basket. A plurality of passageways () are formed in the basket, positioned proximate to and downstream of the burner insert for allowing passage of a portion of an oxidizer flow () into a combustion chamber (). A fluid flow path (), defined between a combustion chamber liner portion () of the basket and a casing () spaced radially outward from the combustion liner portion, discharges a fluid into a flow reversal region () proximate an inlet () of the burner assembly. A fuel outlet () is disposed in the flow reversal region.

US Patent:

20100236245, Sep 23, 2010

Filed:

Mar 19, 2009

Appl. No.:

12/407133

Inventors:

Clifford E. Johnson - Orlando FL, US
Joachim Lepers - Rosenheim, DE
Samer P. Wasif - Oviedo FL, US

International Classification:

F02C 7/24

US Classification:

60725

Abstract:

A gas turbine combustion system has a combustion system wall delimiting a flow path for hot and pressurized combustion gas and at least one resonator with a resonator volume. The resonator volume is delimited by resonator walls, where one of the resonator walls is located adjacent to or is formed by the combustion system wall. The resonator has at least one cooling fluid supply opening which is open towards a cooling fluid source. It further has a neck opening which is open towards the flow path and which is implemented in the form of a neck slot.

US Patent:

20110300491, Dec 8, 2011

Filed:

Jun 8, 2010

Appl. No.:

12/795786

Inventors:

Samer P. Wasif - Oviedo FL, US

International Classification:

F23C 99/00

US Classification:

431 2

Abstract:

A method of influencing combustion dynamics, including measuring a combustion dynamics parameter, and controlling a diluent flow () delivered to a fuel flow () upstream of a pilot burner fuel outlet () in response to the measured combustion dynamics parameter.