A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

The invention relates to a mixing arrangement for mixing a fuel with a stream of oxygen containing gas flowing along an axis in an axial channel, especially in the second combustor of a gas turbine with sequential combustion. The mixing is improved and the mixing length reduced by said mixing arrangement comprising an injector with at least one injector ring, which is passed by said stream of gas inside and outside.

The invention relates to a mixing arrangement for mixing a fuel with a stream of oxygen containing gas flowing along an axis in an axial channel, especially in the second combustor of a gas turbine with sequential combustion. The mixing is improved and the mixing length reduced by said mixing arrangement comprising an injector with at least one injector ring, which is passed by said stream of gas inside and outside.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure as a first loop.

A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.

A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.