A valve for use in a gas turbine. The valve includes at least one valve body, at least first, second and third fluid delivery pipes positioned on the valve body, at least one outlet pipe positioned on the valve body and a rotatable spherical shutter inside the valve body (and including first and second distribution channels formed within the shutter so as to allow the outlet pipe to be selectively connected to one of the delivery pipes during rotation of the shutter.

A valve for use in a gas turbine. The valve includes at least one valve body, at least first, second and third fluid delivery pipes positioned on the valve body, at least one outlet pipe positioned on the valve body and a rotatable spherical shutter inside the valve body (and including first and second distribution channels formed within the shutter so as to allow the outlet pipe to be selectively connected to one of the delivery pipes during rotation of the shutter.

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle β with the axis A.

An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle β with the axis A.

A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

An engine has two pressure vessels arranged as a diametrically opposed pair. Each pressure vessel has an operating pressure sufficient to hold gas at a pre-defined pressure. At least one gas compressor is in communication with each pressure vessel, and the gas compressor is capable of compressing a gas in each pressure vessel to the pre-defined pressure. A pressure relief mechanism is in communication with each pressure vessel. The pressure relief mechanism is capable of returning the gas in each vessel to atmospheric pressure.

A two-part wastegate valve member assembly comprises a support member and a valve member. The support member defines an aperture. The valve member comprises a central portion extending through the aperture and two opposed end portions disposed on opposite sides of the aperture. Each of the two end portions has dimensions such that the valve member is held captive by the support member. The central portion and two opposed end portions of the valve member are integrally formed. A method for forming the two-part wastegate valve member assembly comprises casting a single manufacturing intermediate and subsequently processing the manufacturing intermediate so as to form the two-part assembly.

An actuator includes a housing that defines a first inlet to receive a fluid, a second inlet to receive the fluid and a chamber. The actuator includes an actuator rod movably coupled to the housing. The actuator rod includes a head. A first face of the head is responsive to the fluid from the first inlet, and a second face of the head is responsive to the fluid from the second inlet to move the actuator rod. The head defines at least one cross-bore. The actuator includes at least one plug coupled to the cross-bore to inhibit a flow of the fluid through the cross-bore in a first state such that the plug fluidly isolates the fluid from the first inlet from the fluid from the second inlet. The plug is to enable the flow of the fluid through the at least one plug in a second state.

A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.