Abstract: An instrumentation adaptor for a gas turbine engine includes a seat, a seal contacting a surface of the seat, a follower contacting the seal opposite the seat, a compressive component contacting the follower opposite the seal. The seal is constructed of a crushing seal material. The compressive component includes an exterior facing interface feature. The seal is in a compressed state.

Abstract: An annular seal plate for a shaft assembly in which the seal plate is disposed between and abuts a first adjacent element that rotates with the shaft and seal plate and a second adjacent element that does not rotate with the shaft. The annular seal plate includes an axial scoop defining an annular lubricant collection area disposed radially outwardly from an oil supply orifice that is in fluid communication with a source of pressurized lubricant supplied through the first adjacent element. Lubricant flows through the oil supply orifice and collects in the collection area. An oil passage places the collection area in fluid communication with a lateral surface facing and abutting the second adjacent element to provide lubricant to the interface between the annular seal plate and the second adjacent element.

Abstract: A bearing system is provided for a gas turbine engine. This bearing system includes a spring defined about an axis of rotation. The spring has a multiple of beams which extend between a flange and a damper attachment. A damper defined about the axis of rotation and mounted to the spring to at least partially axially overlap the multiple of beams.

Abstract: The present disclosure relates generally a system for preventing relative rotation between three components. The three components include tabs and slots such that at least one first tab and at least one second tab on one component is disposed within at least one slot formed in the other two components to prevent relative rotation between any two of the three components.

Abstract: A seal assembly is provided that extends along an axial centerline. The seal assembly includes a seal support, a seal housing, a plurality of torque pins and a plurality of stopper collars. The seal housing includes a plurality of slots arranged circumferentially around the centerline. The slots extend axially through the seal housing, and one or more of the slots has a lateral slot width. The torque pins are connected to the seal support. Each of the torque pins respectively extends axially through a uniquely associated one of the slots to a distal pin end. Each of the stopper collars is uniquely associated with and connected to a respective one of the torque pins at the pin end. One or more of the stopper collars has a lateral collar width that is less than the slot width.

Abstract: An anti-rotational system is provided comprising a pawl carrier mounted for rotation within a ratchet, the pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, wherein the pivot joint is between the contact portion and the counterweight portion, wherein the counterweight portion is configured to be radially inward of the contact portion in response to rotation of the pawl carrier in a first rotational direction at an angular velocity less than a predetermined angular velocity.

Abstract: A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

Abstract: A seal support and duct assembly of a gas turbine engine includes a seal support housing disposed about a central axis, a duct housing attached to the seal support housing, the duct housing and the seal support housing defining the seal support and duct assembly, an outer annular cavity, an inlet that supplies the outer annular cavity with cooling buffer air, an inner annular cavity disposed radially inward of the outer annular cavity, a first plurality of outlets that provide the cooling buffer air from the outer annular cavity to the inner annular cavity, and a second plurality of outlets that provide the cooling buffer air from the inner annular cavity to an area surrounding a bearing compartment.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A bearing system for a gas turbine engine includes a spring defined about an axis of rotation. The spring has a multiple of beams which extend between a flange structure and an attachment structure. A damper defined about the axis of rotation and mounted to the spring to at least partially axially overlap the multiple of beams.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A bearing system for a gas turbine engine includes a spring defined about an axis of rotation. The spring has a multiple of beams which extend between a flange structure and an attachment structure. A damper defined about the axis of rotation and mounted to the spring to at least partially axially overlap the multiple of beams.