Abstract: Methods, apparatus, and systems for trapped rotatable weights to improve rotor balance are disclosed. An example apparatus includes a lock nut; a rotor assembly; a channel defined by the lock nut and the rotor assembly, the channel wrapped circumferentially around a geometric center of the rotor assembly; and a weight trapped within the channel.

Abstract: Methods, apparatus, and systems for trapped rotatable weights to improve rotor balance are disclosed. An example apparatus includes a lock nut; a rotor assembly; a channel defined by the lock nut and the rotor assembly, the channel wrapped circumferentially around a geometric center of the rotor assembly; and a weight trapped within the channel.

Abstract: A high pressure BLISK includes at least one circular row of airfoils circumferentially disposed about, integral with, and extending radially outwardly from an annular rim having an annular flat aft facing face with coplanar radially outer and inner face portions radially separated by an annular undercut extending into the rim from the aft facing face. Airfoil roots including root fillets extend around the airfoil between the rim and pressure and suction sides of the airfoils. An axially aftwardly extending annular cylindrical section extends aftwardly from the flat face. The BLISK being a first of axially adjacent first and second rotor sections connected by a rabbet joint. A forward arm of the second rotor section includes an outer forward facing annular face spaced apart from the aft facing face radially outwardly of the annular undercut and a radially inner forward facing annular face contacting the aft facing face.

Abstract: According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while also allowing for axial movement of the tie-bolt.

Abstract: According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while also allowing for axial movement of the tie-bolt.

Abstract: A high pressure BLISK includes at least one circular row of airfoils circumferentially disposed about, integral with, and extending radially outwardly from an annular rim having an annular flat aft facing face with coplanar radially outer and inner face portions radially separated by an annular undercut extending into the rim from the aft facing face. Airfoil roots including root fillets extend around the airfoil between the rim and pressure and suction sides of the airfoils. An axially aftwardly extending annular cylindrical section extends aftwardly from the flat face. The BLISK being a first of axially adjacent first and second rotor sections connected by a rabbet joint. A forward arm of the second rotor section includes an outer forward facing annular face spaced apart from the aft facing face radially outwardly of the annular undercut and a radially inner forward facing annular face contacting the aft facing face.

Abstract: A gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod therethrough. First and second bore annular flowpaths are radially located between first and second stage disk bores and tie rod. A means for increased cooling and/or heating in second stage disk bore is axially located within second stage disk bore. The means may include an airflow accelerator such as one or more annular ribs on the tie rod. A bore annular cross-sectional flow area between the second stage disk hub and the ribs may be substantially smaller than between the second stage disk hub and the tie rod. An axially unobstructed inlet into the second bore annular flowpath allows fully axially flowing and axially unobstructed flowing of second stage bore cooling air into inlet.

Abstract: A seal assembly for sealing a rotatable shaft in a gas turbine engine, wherein the shaft includes sections of greater shaft diameter located both forward and aft of the seal shaft coupling point is provided. The seal assembly includes a first semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The seal assembly also includes a second semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The first end of the second segment is coupled to the first end of the first segment, and the second end of the second segment is coupled to the second end of the first segment.

Abstract: Rotor disk stress is reduced in a bolted joint for connecting adjacent rotor disks in a gas turbine engine. The bolted joint includes a bolt hole formed in the first rotor disk and a tube disposed in the bolt hole such that a channel is defined between the tube and the bolt hole. A bolt is disposed in the tube such that a gap is defined between the bolt and the tube. The gap thermally insulates the bolt from hot fluid in the channel. A first passage provides fluid communication between the channel and a forward cavity, and a second passage provides fluid communication between the channel and an aft cavity. Hot fluid passing through the channel reduces thermal gradients in the first rotor disk. The tube thermally shields the bolt from the hot fluid to minimize differential thermal growth.

Abstract: Bolt hole stress in rotor disks having bolted joints is reduced by passing relatively hot secondary flow path air (such as compressor discharge air) through each bolt hole to heat the disk from inside the bolt hole. In doing so, the temperature distribution in the area of the bolt hole is made more uniform and the stress is dramatically reduced. The bolted joint includes a bolt hole formed in a first rotor disk and a bolt disposed in the bolt hole such that a channel is defined between the bolt and the bolt hole. A first nut or abutment is attached to a first end of the bolt, and a second nut or abutment is attached to a second end of the bolt. A first passage associated with the first abutment provides fluid communication with the channel, and a second passage associated with the second abutment provides fluid communication with the channel, thereby allowing the relatively hot fluid to pass through the channel during engine operation.

Abstract: Rotor disk stress is reduced in a bolted joint for connecting adjacent rotor disks in a gas turbine engine. The bolted joint includes a bolt hole formed in the first rotor disk and a tube disposed in the bolt hole such that a channel is defined between the tube and the bolt hole. A bolt is disposed in the tube such that a gap is defined between the bolt and the tube. The gap thermally insulates the bolt from hot fluid in the channel. A first passage provides fluid communication between the channel and a forward cavity, and a second passage provides fluid communication between the channel and an aft cavity. Hot fluid passing through the channel reduces thermal gradients in the first rotor disk. The tube thermally shields the bolt from the hot fluid to minimize differential thermal growth.

Abstract: Bolt hole stress in rotor disks having bolted joints is reduced by passing relatively hot secondary flow path air (such as compressor discharge air) through each bolt hole to heat the disk from inside the bolt hole. In doing so, the temperature distribution in the area of the bolt hole is made more uniform and the stress is dramatically reduced. The bolted joint includes a bolt hole formed in a first rotor disk and a bolt disposed in the bolt hole such that a channel is defined between the bolt and the bolt hole. A first nut or abutment is attached to a first end of the bolt, and a second nut or abutment is attached to a second end of the bolt. A first passage associated with the first abutment provides fluid communication with the channel, and a second passage associated with the second abutment provides fluid communication with the channel, thereby allowing the relatively hot fluid to pass through the channel during engine operation.