James A Bertoncello

US Patent:

20130074946, Mar 28, 2013

Filed:

Sep 19, 2012

Appl. No.:

13/622510

Inventors:

Siemens Energy, Inc. - Orlando FL, US
ABHIJEET TIWARY - ORLANDO FL, US
TIMOTHY A. FOX - HAMILTON, CA
JAMES BERTONCELLO - CHARLOTTE NC, US
STEVEN WILLIAMS - CHARLOTTE NC, US
DANIEL W. GARAN - CHULUOTA FL, US

Assignee:

SIEMENS ENERGY, INC. - ORLANDO FL

International Classification:

B67D 7/72

US Classification:

137154

Abstract:

A casting () for a support housing (), including: a fuel manifold () comprising an a-stage gas gallery () and a b-stage gas gallery (); a-stage and a b-stage rocket bases () integrally cast with the fuel manifold (), the a-stage gas gallery () in fluid communication with the a-stage stage rocket bases and the b-stage gas gallery () in fluid communication with the b-stage rocket bases; and one oil tube passageway () for each fuel rocket base (), each oil tube passageway () spanning from an upstream end () of the fuel manifold () to an interior () of a respective fuel rocket base (). Each oil tube passageway () is disposed radially inward of an inner perimeter () of the b-stage gas gallery ().

US Patent:

20130074501, Mar 28, 2013

Filed:

Sep 19, 2012

Appl. No.:

13/622452

Inventors:

SIEMENS ENERGY, INC. - Orlando FL, US
Stephen A. Ramier - Fredericton, CA
Timothy A. Fox - Hamilton, CA
James Bertoncello - Charlotte NC, US
Steven Williams - Charlotte NC, US

Assignee:

SIEMENS ENERGY, INC. - Orlando FL

International Classification:

F02C 7/24
B21D 53/84
F23R 3/42

US Classification:

60725, 60752, 2988922

Abstract:

A combustor () for a gas turbine engine () has a circumferentially extending liner () defining at least a portion of an interior combustion chamber () and a hot gas path (). The liner includes a resonator section () including at least one resonator (A, B) having a resonator chamber (A, B) formed on an exterior of the liner. A thermal barrier coating () is disposed along an inner surface of the liner including an inner surface () of the resonator section. The resonator further includes a plurality of apertures () and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.

US Patent:

20220389827, Dec 8, 2022

Filed:

Aug 6, 2020

Appl. No.:

17/634969

Inventors:

- München, DE
Kunyuan Zhou - Berlin, DE
Wojciech Dyszkiewicz - Charlotte NC, US
Adam J. Weaver - Oviedo FL, US
Robert H. Bartley - Oviedo FL, US
James Bertoncello - Charlotte NC, US
Mahmut Faruk Aksit - Kadiköy, Istanbul, TR
Ertugrul Tolga Duran - Pendik, Istanbul, TR
Erdem Gorgun - Pendik, Istanbul, TR
Sadik Hazer - Pendik, Istanbul, TR
Ali Ihsan Yurddas - Pendik, Istanbul, TR

Assignee:

SIEMENS ENERGY GLOBAL GMBH & CO. KG - München

International Classification:

F01D 11/00
F16J 15/08
F01D 9/02

Abstract:

A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

US Patent:

20210354646, Nov 18, 2021

Filed:

May 10, 2021

Appl. No.:

17/316583

Inventors:

- Universal City CA, US
James Anthony BERTONCELLO - Orlando FL, US
Shawn Michael KISH - Apopka FL, US

International Classification:

B60R 21/02

Abstract:

Aspects of the disclosure relate to a method, apparatus, and system for restraining a passenger in a ride vehicle. The system includes a ride seat and a restraint system configured to restrain the passenger against the ride seat. The restraint system includes a crossbar for placing against the passenger, a support bar having a first support bar end coupled to the crossbar and a second support bar end rotatably coupled to a pivot mounted to an upper-rear portion of the ride seat, and a flap coupled to the support bar. The flap is configured to insert into, or extract from, a slot formed within a seat side structure when the support bar is rotated about the pivot and indicate whether the crossbar has attained a minimum closed position for restraining the passenger based on a position of a marking on the flap relative to the slot.

US Patent:

20200307650, Oct 1, 2020

Filed:

Nov 22, 2019

Appl. No.:

16/692920

Inventors:

- Universal City CA, US
Rachel Sarah Wilcox - Orlando FL, US
James Anthony Bertoncello - Orlando FL, US

International Classification:

B61B 1/02
B61B 3/00
A63G 31/00

Abstract:

A gap blocking system includes a loading platform having a gap separating a first portion of the loading platform from a second portion of the loading platform. A ride vehicle is coupled to a transport extending through the gap. A guardrail assembly having a plurality of guardrail units is coupled to the first portion, where the guardrail units are configured to transition between a first position and a second position. The guardrail units are configured to block access to the gap when in the first position. The ride vehicle includes an engagement feature configured to interface with an individual guardrail unit of the guardrail units to selectively transition the individual guardrail unit from the first position to the second position. The individual guardrail unit is configured to permit the ride vehicle to occupy a guest-accessible position adjacent to or on the loading platform in the second position.

US Patent:

20170314405, Nov 2, 2017

Filed:

Nov 18, 2014

Appl. No.:

15/525349

Inventors:

- München, DE
James BERTONCELLO - Charlotte NC, US
Anthony L. SCHIAVO - Oviedo FL, US
Timothy A. FOX - Hamilton, CA
Reinhard SCHILP - Winter Park FL, US

International Classification:

F01D 9/02
F01D 25/28

Abstract:

A transition exit frame () for supporting a transition () extending downstream from a combustor () to a turbine assembly () in a turbine engine () and including one or more transition exit frame inserts () configured to reduce thermal distortion created during operation of the turbine engine () is disclosed. The transition exit frame () may be formed from one or more transition exit frame bodies (). The transition exit frame body () may be formed from a first material () having a first coefficient of thermal expansion. The transition exit frame insert () may form at least a portion of the transition exit frame body (). The transition exit frame insert () may be formed from a second material () having a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion of the first material () to reduce distortion within the transition exit frame body () during operation of the turbine engine ().