Abstract: A clutch system configured to transmit torque between an input shaft and an output shaft. The clutch system may include a clutch and a lubrication supply system. The clutch may include: an input portion disposed at an end of the input shaft; an output portion disposed at an end of the output shaft; and a sliding component that slides axially between the input and output portions to engage the clutch. The lubrication supply system may include: one or more lubricant feeds for delivering a lubricant to the clutch; and one or more lubricant drains for draining the lubricant from the clutch. The one or more lubricant feeds may include one or more respective valves. The one or more valves each may be configurable between settings that vary an amount of the lubricant delivered to the clutch via the respective one of the one or more lubricant feeds.

Abstract: A clutch system configured to transmit torque between an input shaft and an output shaft. The clutch system may include a clutch and a lubrication supply system. The clutch may include: an input portion disposed at an end of the input shaft; an output portion disposed at an end of the output shaft; and a sliding component that slides axially between the input and output portions to engage the clutch. The lubrication supply system may include: one or more lubricant feeds for delivering a lubricant to the clutch; and one or more lubricant drains for draining the lubricant from the clutch. The one or more lubricant feeds may include one or more respective valves. The one or more valves each may be configurable between settings that vary an amount of the lubricant delivered to the clutch via the respective one of the one or more lubricant feeds.

Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.

Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.

Abstract: A variable vane assembly for a compressor having a plurality of vanes is disclosed. The variable vane assembly may generally include a synchronizing ring and a plurality of attachment studs secured to the synchronizing ring. The variable vane assembly may also include a plurality of lever arms, with each lever arm having a first end and a second end. The first end of each lever arm may be attached to one of the vanes. Additionally, a plurality of rotational attachment devices may be configured to rotatably couple the second end of each lever arm to one of the attachment studs so as to define a rotational interface therebetween. Further, each of the attachments studs may be rigidly attached to one of the rotational attachment devices at the rotational interface such that there is substantially no relative radial and circumferential sliding motion between the synchronizing ring and the plurality of lever arms during rotation of the synchronizing ring.

Abstract: An attachment stud for a variable vane assembly is disclosed. The attachment stud may generally include a bottom segment, a middle segment, a top segment and a shoulder segment. The bottom segment may generally have a shape and configuration adapted to be secured to a synchronizing ring of the variable vane assembly. The middle segment may generally have a shape and configuration adapted to receive a rotational attachment device of the variable vane assembly. The shoulder segment may be disposed between the bottom segment and the middle segment. The top segment may generally have a shape and configuration adapted to receive a retaining device configured to rigidly attach the rotational attachment device to the attachment stud.

Abstract: Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring. The control mechanism also includes a linkage in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring.

Abstract: A variable vane assembly for a compressor having a plurality of vanes is disclosed. The variable vane assembly may generally include a synchronizing ring and a plurality of attachment studs secured to the synchronizing ring. The variable vane assembly may also include a plurality of lever arms, with each lever arm having a first end and a second end. The first end of each lever arm may be attached to one of the vanes. Additionally, a plurality of rotational attachment devices may be configured to rotatably couple the second end of each lever arm to one of the attachment studs so as to define a rotational interface therebetween. Further, each of the attachments studs may be rigidly attached to one of the rotational attachment devices at the rotational interface such that there is substantially no relative radial and circumferential sliding motion between the synchronizing ring and the plurality of lever arms during rotation of the synchronizing ring.

Abstract: An attachment stud for a variable vane assembly is disclosed. The attachment stud may generally include a bottom segment, a middle segment, a top segment and a shoulder segment. The bottom segment may generally have a shape and configuration adapted to be secured to a synchronizing ring of the variable vane assembly. The middle segment may generally have a shape and configuration adapted to receive a rotational attachment device of the variable vane assembly. The shoulder segment may be disposed between the bottom segment and the middle segment. The top segment may generally have a shape and configuration adapted to receive a retaining device configured to rigidly attach the rotational attachment device to the attachment stud.

Abstract: A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Abstract: A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.

Abstract: A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Abstract: A method of assembling a gas turbine engine that includes providing a rotor assembly including a rotor shaft, an air duct, and a rotor disk that includes a mounting arm, wherein the mounting arm extends radially inward from the rotor disk towards the rotor shaft and coupling a rotor impeller assembly to the mounting arm, wherein the rotor impeller assembly includes a carrier and a plurality of bleed tubes that each extend outwardly from the carrier and are configured to receive bleed air.