Abstract: A tube coupling for coupling a first tube and a second tube. The tube coupling includes an inner shroud including a ball portion and an outer shroud including a socket portion. The socket portion receives the ball portion. The tube coupling includes a compressive ring configured to elastically compress the outer shroud onto the inner shroud. The ball portion and the socket portion form a ball and socket joint. The ball and socket joint allows relative angular movement and relative axial movement between the inner shroud and the outer shroud.

Abstract: A tube assembly includes a first tube, a second tube, and a tube coupling. The tube coupling is for coupling the first tube to the second tube. The tube coupling may include protrusions, indentations, compressive rings, compressive bands, and/or connection members. The protrusions and/or indentions may be located on the first tube, the second tube, the compressive band, and/or the connection member. The compressive ring and/or compressive band is placed on an outer surface of the first tube and/or the second tube. The compressive ring provides an elastic compressive force to the first tube and/or the second tube such that the protrusion is secured within the indentation. The tube coupling provides a weld-free connection between the first tube and the second tube.

Abstract: A tube coupling for coupling a first tube and a second tube. The tube coupling includes an inner shroud including a ball portion and an outer shroud including a socket portion. The socket portion receives the ball portion. The tube coupling includes a compressive ring configured to elastically compress the outer shroud onto the inner shroud. The ball portion and the socket portion form a ball and socket joint. The ball and socket joint allows relative angular movement and relative axial movement between the inner shroud and the outer shroud.

Abstract: A gas turbine engine including a wall assembly, a seal assembly, and a member extended through the wall assembly is provided. The wall assembly defines an opening through which the member is extended, and the wall assembly defines a first side and a second side opposite of the first side along a direction of extension of the member through the wall assembly. The seal assembly includes a retaining portion extended at least partially co-directional to the member. The retaining portion is configured to couple around the member and extend through the opening. The seal assembly further includes a locking portion configured to sealingly attach to the wall assembly and the retaining portion at an interface between the locking portion and the retaining portion.

Abstract: In one exemplary embodiment of the present disclosure a fluid coupling assembly defining an axial direction, a radial direction, and a circumferential direction is provided.

Abstract: A seal assembly for a propulsion system couples a plurality of manifolds of a manifold assembly of the propulsion system generally in fluid communication. Each of the manifolds defines a first end and a second end. The seal assembly includes a coupling member attaching the first end and the second end of the manifold assembly together in fluid communication; one or more seals disposed between the coupling member and at least one of the first end and the second end of the manifold; and a retainer adjacent to the coupling member and the seal. The retainer defines a radial wall and an axial wall, in which the radial wall is extended generally from one or more of the first end and the second end of the manifold alongside the coupling member and the seal, and the axial wall is extended generally from the radial wall alongside the coupling member and the seal.

Abstract: A gas turbine engine including a wall assembly, a seal assembly, and a member extended through the wall assembly is provided. The wall assembly defines an opening through which the member is extended, and the wall assembly defines a first side and a second side opposite of the first side along a direction of extension of the member through the wall assembly. The seal assembly includes a retaining portion extended at least partially co-directional to the member. The retaining portion is configured to couple around the member and extend through the opening. The seal assembly further includes a locking portion configured to sealingly attach to the wall assembly and the retaining portion at an interface between the locking portion and the retaining portion.

Abstract: In one exemplary embodiment of the present disclosure a fluid coupling assembly defining an axial direction, a radial direction, and a circumferential direction is provided.

Abstract: The present disclosure is directed to a seal assembly for a propulsion system. The seal assembly couples a plurality of manifolds of a manifold assembly of the propulsion system generally in fluid communication. Each of the manifolds defines a first end and a second end. The seal assembly includes a coupling member attaching the first end and the second end of the manifold assembly together in fluid communication; one or more seals disposed between the coupling member and at least one of the first end and the second end of the manifold; and a retainer adjacent to the coupling member and the seal. The retainer defines a radial wall and an axial wall, in which the radial wall is extended generally from one or more of the first end and the second end of the manifold alongside the coupling member and the seal, and the axial wall is extended generally from the radial wall alongside the coupling member and the seal.

Abstract: Apparatus comprising a signal tube extending from an engine component on a hot side of a firewall in a gas turbine engine to an engine control mechanism disposed on a cool side of the firewall. The apparatus includes a fuse in the portion of the signal tube extending through the hot side. An exemplary fuse includes a temperature-sensitive inner member that is deformable upon exposure to temperatures greater than a predetermined temperature. The fuse is operative responsive to a breach in the signal tube to change from a first condition to a second condition to prevent an over-temperature situation on the cool side of the firewall. An outer member substantially enclosing the inner member provides information about the condition of the fuse. A system utilizing the fuse includes a gas turbine engine having a firewall separating a hot side from a cool side, an engine control mechanism disposed on the cool side, and a signal tube extending from a component on the hot side to the engine control mechanism.

Abstract: Method comprising providing a signal tube extending generally from an engine component disposed on a hot side of a firewall in a gas turbine engine to at least one engine control mechanism disposed on a cool side of the firewall. A fuse in the signal tube is operable responsive to a breach in the signal tube to change from a first condition to a second condition to prevent an over-temperature situation on the cool side of the firewall. The engine control mechanism operates the engine according to a first operating logic utilizing a pressure signal related to a static pressure of a fluid in the signal tube. Loss of the pressure signal causes the engine control mechanism to change to a second operating logic which does not utilize the pressure signal.

Abstract: Apparatus comprising a signal tube extending from an engine component on a hot side of a firewall in a gas turbine engine to an engine control mechanism disposed on a cool side of the firewall. The apparatus includes a fuse in the portion of the signal tube extending through the hot side. An exemplary fuse includes a temperature-sensitive inner member that is deformable upon exposure to temperatures greater than a predetermined temperature. The fuse is operative responsive to a breach in the signal tube to change from a first condition to a second condition to prevent an over-temperature situation on the cool side of the firewall. An outer member substantially enclosing the inner member provides information about the condition of the fuse. A system utilizing the fuse includes a gas turbine engine having a firewall separating a hot side from a cool side, an engine control mechanism disposed on the cool side, and a signal tube extending from a component on the hot side to the engine control mechanism.

Abstract: Method comprising providing a signal tube extending generally from an engine component disposed on a hot side of a firewall in a gas turbine engine to at least one engine control mechanism disposed on a cool side of the firewall. A fuse in the signal tube is operable responsive to a breach in the signal tube to change from a first condition to a second condition to prevent an over-temperature situation on the cool side of the firewall. The engine control mechanism operates the engine according to a first operating logic utilizing a pressure signal related to a static pressure of a fluid in the signal tube. Loss of the pressure signal causes the engine control mechanism to change to a second operating logic which does not utilize the pressure signal.