Charalambos B Polyzopoulos, 543322 Dallas Blvd, Orlando, FL 32833

2018022, Aug 16, 2018

Dec 22, 2016

15/388105

- Muenchen, DE
Miguel Bascones - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US
Abhijeet Tiwary - Orlando FL, US

B22D 25/02
B22D 29/00
F23R 3/28

Casting method and cast manifold are provided. The method allows configuring conduits, such as conduits () in a fuel feed boss () and/or a base rocket (), which are part of the manifold for removing a ceramic core () from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.

2018023, Aug 16, 2018

Dec 22, 2016

15/388133

- Muenchen, DE
Miguel Bascones - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US
Abhijeet Tiwary - Orlando FL, US

F02C 7/22
F23R 3/28

A fuel manifold () configured to form a base support structure () to support a plurality of fuel nozzles () in a combustor of a gas turbine engine is provided. The fuel manifold includes stage fuel galleries (), and fuel feed bosses () may be configured to connect to respective tubes arranged to deliver gas fuel to the stage fuel galleries (). Fuel feed bosses () are integrally formed with base support structure () and this allows the body of fuel manifold () to be free of weld joints for affixing the fuel feed boss to the base support structure.

2018017, Jun 28, 2018

Dec 22, 2016

15/388155

- Muenchen, DE
Miguel Bascones - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US
Abhijeet Tiwary - Orlando FL, US

F02C 7/22
F23R 3/34

A fuel manifold () configured to form a base support structure () to support a plurality of fuel nozzles () including a pilot fuel nozzle is provided. A restraining element () is arranged in the base support structure () to support the pilot fuel nozzle. Restraining element () is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness () in a portion () of a wall () interposed between the inner diameter () of restraining element () and respective proximate edges () of a number of pilot bolt holes () disposed around the restraining element.

2018003, Feb 1, 2018

Jul 29, 2016

15/223529

- Orlando FL, US
James M. Hurney - Port Orange FL, US
Charalambos Polyzopoulos - Orlando FL, US

F01D 9/02
F01D 11/00

A static wear seal for an interface between two components is provided. The static wear seal includes a body portion including a receptacle configured to receive an insert portion. The insert portion is disposed within the receptacle. The receptacle is formed within the body portion at a surface of the body portion known to wear due to contact with a turbine component and includes a locking means such that the insert portion is retained within the receptacle. The insert portion is configured to receive wear due to contact with the turbine component. A transition seal assembly for a gas turbine engine including at least two seals wherein one of the two seals is a static wear seal is provided as well as a method to protect a wear surface of a static wear seal sealing an interface between the turbine components.

2017022, Aug 10, 2017

Sep 5, 2014

15/502638

- München, DE
Richard L. Thackway - Oviedo FL, US
David P. Holzapfel - Charlotte NC, US
Stephen A. Ramier - Fredericton, New Brunswick, CA
Charalambos Polyzopoulos - Orlando FL, US
Kevin J. Spence - Winter Springs FL, US
Joseph Scott Markovitz - Sanford FL, US

SIEMENS AKTIENGESELLSCHAFT - Muenchen

F23R 3/48
F23R 3/46

A cross-flame duct () for connecting adjacent combustors () together in a gas turbine to guard against flameout conditions within the combustors (), whereby the cross-flame duct () may include first and second ducts () forming a slip joint to prevent stress from developing within the cross-flame duct () is disclosed. The cross-flame duct () remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct () and enhancing the useful life of the cross-flame duct () and associated components. The first and second ducts () may also include cooling chambers () positioned between outer sleeves () and inner housings () and maintained with one or more standoffs () to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers () may be supplied with cooling fluids via one or more fluid ports () extending through the outer sleeves () enabling air to flow through the cooling chambers () and into the combustors ().

2017021, Jul 27, 2017

Aug 14, 2014

15/329639

- München, DE
Vinayak V. Barve - Oviedo FL, US
Richard L. Thackway - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US
Khalil Farid Abou-Jaoude - Winter Springs FL, US

Siemens Aktiengesellschaft - Munchen

F23C 1/08
F23L 7/00
F23R 3/28
F23D 11/24

A nozzle cap () is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis () of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer () to form a first atomized ejection cone. An array of atomizers () is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.

2017021, Jul 27, 2017

Aug 14, 2014

15/328525

- München, DE
Vinayak V. Barve - Oviedo FL, US
Richard L. Thackway - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US

F23R 3/28
F23D 14/78
F23D 11/38
F23R 3/36
F23D 14/76

A multi-functional fuel nozzle () for a combustion turbine engine is provided. A nozzle cap () may be disposed at a downstream end of the nozzle. A heat shield () is mounted onto the nozzle cap. A plurality of cooling channels () is arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. The plurality of cooling channels may be arranged to discharge cooling air over a forward face of an atomizer assembly in the multi-functional fuel nozzle.

2017020, Jul 20, 2017

Aug 14, 2014

15/328228

- München, DE
Vinayak V. Barve - Oviedo FL, US
Richard L. Thackway - Oviedo FL, US
Charalambos Polyzopoulos - Orlando FL, US
Khalil Farid Abou-Jaoude - Winter Springs FL, US

SIEMENS AKTIENGESELLSCHAFT - Munchen

F02C 3/30
F02C 7/22
F23R 3/36

A multi-functional fuel nozzle () for a combustion turbine engine is provided. An annular fuel-injecting lance () may include a first fluid circuit () and a second fluid circuit (). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer () is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice () responsive to the first fluid circuit to form a first atomized ejection cone (), and a second ejection orifice () responsive to the second fluid circuit to form a second atomized ejection cone (). The first and second ejection cones () formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.