Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Abstract: A shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. When the movable locking apparatus is engaged with the fixed locking apparatus, the turbine shaft is only able to turn in one direction. When the movable locking apparatus is disengaged from the fixed locking apparatus, the turbine shaft is able to turn in both directions. In this way, a turbine shaft can be prevented from reverse rotation.

Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Abstract: A seal runner may have an inner annular member, an outer annular member, and a radial wall member joined to the inner annular member according to an angle and extending from the inner annular member to the outer annular member. The seal runner may be positioned axially along a shaft and a bearing may be positioned axially along the shaft such that it is radially between the inner annular member and the outer annular member. In this regard, the seal runner may resemble a “C-shape.” A seal may interface with a seal land radially outboard of the outer annular member. Thus, the seal may be positioned axially near to the bearing so that the axial length of a shaft and accompanying bearing compartment hardware may be minimized.

Abstract: An improved film damper oil delivery pathway from an oil reservoir to a thin film fluidic damper is provided. An oil supply tube may be configured to mate to a bearing outer race. The bearing outer race may comprise internal oil flow circuit(s) configured to supply oil from the oil tube to the thin film damper for improved bearing compartment designs.

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 shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. When the movable locking apparatus is engaged with the fixed locking apparatus, the turbine shaft is only able to turn in one direction. When the movable locking apparatus is disengaged from the fixed locking apparatus, the turbine shaft is able to turn in both directions. In this way, a turbine shaft can be prevented from reverse rotation.

Abstract: A shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. When the movable locking apparatus is engaged with the fixed locking apparatus, the turbine shaft is only able to turn in one direction. When the movable locking apparatus is disengaged from the fixed locking apparatus, the turbine shaft is able to turn in both directions. In this way, a turbine shaft can be prevented from reverse rotation.

Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Abstract: An improved film damper oil delivery pathway from an oil reservoir to a thin film fluidic damper is provided. An oil supply tube may be configured to mate to a bearing outer race. The bearing outer race may comprise internal oil flow circuit(s) configured to supply oil from the oil tube to the thin film damper for improved bearing compartment designs.

Abstract: A seal runner may have an inner annular member, an outer annular member, and a radial wall member joined to the inner annular member according to an angle and extending from the inner annular member to the outer annular member. The seal runner may be positioned axially along a shaft and a bearing may be positioned axially along the shaft such that it is radially between the inner annular member and the outer annular member. In this regard, the seal runner may resemble a “C-shape.” A seal may interface with a seal land radially outboard of the outer annular member. Thus, the seal may be positioned axially near to the bearing so that the axial length of a shaft and accompanying bearing compartment hardware may be minimized.

Abstract: A shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. When the movable locking apparatus is engaged with the fixed locking apparatus, the turbine shaft is only able to turn in one direction. When the movable locking apparatus is disengaged from the fixed locking apparatus, the turbine shaft is able to turn in both directions. In this way, a turbine shaft can be prevented from reverse rotation.

Abstract: An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine.

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 seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.

Abstract: A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors.

Abstract: A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.

Abstract: A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors.