Siemens Aktiengesellschaft

Siemens Canada Limited

Erick J Deane

Charalambos Polyzopoulos

Miguel Bascones

Abhijeet Tiwary

David James Wiebe

Stephen A Ramier

Reinhard Schilp

David M Ritland

Robert H Bartley

Daniel W Garan

Joseph Scott Markovitz

Mark L Adamson

Yadollah Naghian

Jaishree Sharma

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.

Fuel manifold with integrally formed retainer for a pilot nozzle in a combustor of a gas turbine engine

A 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.

Casting method and manifold cast with conduits effective for removing a core from the cast without forming extraneous holes in the body of the manifold

An acoustically dampened gas turbine engine () having a gas turbine engine combustor () with an acoustic damping resonator system () is disclosed. The acoustic damping resonator system () may be formed from one or more resonators () formed from a resonator housing () positioned within the gas turbine engine combustor () at an outer housing () forming a combustor basket () and extending circumferentially within the combustor (). In at least one embodiment, the resonator housing () may include resonator chambers () that may be welded in place within resonator chamber () receivers () but easily replaceable without exposing the resonator housing () to damage. In another embodiment, an inner surface () of the resonator chamber () may be offset radially outward from an inner surface () of the resonator housing (), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (). The acoustic damping resonator system () may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.

Acoustic damping system for a combustor of a gas turbine engine

A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.

Combustor apparatus in a gas turbine engine

Growing community of inventors

Fort Mill, SC, United States of America

Erick J Deane