Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

Abstract: A gas turbine engine turbine section has tie rod assemblies interconnecting an inner diameter structure and an outer casing. Each tie rod has: an inner diameter end; an outer diameter end; and an eyelet of an outer diameter spherical bearing formed at the outer diameter end. A first clevis carries a spherical ball of the bearing, a shank of said clevis extending to an outer diameter (OD) end. A tensioning bolt is mated to a threaded opening in said clevis OD end whereby tightening said bolt applies a tension to said rod. A radial span between a center of the outer diameter spherical bearing and an inner diameter surface of the outer casing is at least 50% greater than that between an outer diameter (OD) surface of the outer ring and the center.

Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.

Abstract: A pressure zoned spraybar for an augmentor section of a gas turbine engine may comprise a fuel conduit and a pressure valve in fluid communication with the fuel conduit. A fuel nozzle may be downstream of the pressure valve. The pressure valve may be configured to regulate a flow of fluid to the fuel nozzle.

Abstract: A gas turbine engine turbine section has tie rod assemblies interconnecting an inner diameter structure and an outer casing. Each tie rod has: an inner diameter end; an outer diameter end; and an eyelet of an outer diameter spherical bearing formed at the outer diameter end. A first clevis carries a spherical ball of the bearing, a shank of said clevis extending to an outer diameter (OD) end. A tensioning bolt is mated to a threaded opening in said clevis OD end whereby tightening said bolt applies a tension to said rod. A radial span between a center of the outer diameter spherical bearing and an inner diameter surface of the outer casing is at least 50% greater than that between an outer diameter (OD) surface of the outer ring and the center.

Abstract: A vane strut assembly is disclosed, The vane strut assembly may include a first panel, a second panel, and a coupling mechanism that couples the first panel and the second panel to one another. The coupling mechanism may include a first fitting that is attached to the first panel, a second fitting that is attached to the second panel, and a cable disposed between the first fitting and the second fitting.

Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A vane strut assembly is disclosed, The vane strut assembly may include a first panel, a second panel, and a coupling mechanism that couples the first panel and the second panel to one another. The coupling mechanism may include a first fitting that is attached to the first panel, a second fitting that is attached to the second panel, and a cable disposed between the first fitting and the second fitting.

Abstract: A pressure zoned spraybar for an augmentor section of a gas turbine engine may comprise a fuel conduit and a pressure valve in fluid communication with the fuel conduit. A fuel nozzle may be downstream of the pressure valve. The pressure valve may be configured to regulate a flow of fluid to the fuel nozzle.

Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

Abstract: An air modulating system for a gas turbine engine includes a fixed plate with a fluid passage inlet, a floating plate with a first side adjacent to the fluid passage inlet, an actuated mount configured to move the floating plate relative to the fixed plate, and a linkage element for connecting the floating plate to the actuated mount. The linkage element includes a mounting flange configured to slidably engage the floating plate.

Abstract: 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.

Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

Abstract: An air modulating system for a gas turbine engine includes a fixed plate with a fluid passage inlet, a floating plate with a first side adjacent to the fluid passage inlet, an actuated mount configured to move the floating plate relative to the fixed plate, and a linkage element for connecting the floating plate to the actuated mount. The linkage element includes a mounting flange configured to slidably engage the floating plate.