Abstract: A multi-ring spacer includes a first ring having a first clocking position, a second ring coaxial with the first ring, and having a second clocking position. A total kink angle of the multi ring spacer is dependent on an angular deviation of the second ring's clocking position relative to the first ring's clocking position.

Abstract: A rotor assembly is disclosed. In various embodiments, the rotor assembly includes a first rotor having a first plurality of tabs; a second rotor having a second plurality of tabs; and a rotor coupling ring having an anti-rotation tab configured for disposition between an adjacent pair of tabs from one of the first plurality of tabs or the second plurality of tabs.

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance pin configured for insertion into an opening in the rotating component, a balance clip configured for installation to the rotating component over the balance pin to retain the balance pin in the opening via exertion of a retention force on the balance pin. A method of correcting an imbalance of a rotating assembly includes inserting a balance pin into a balancing opening in a rotating component of the rotating assembly, and installing a balance clip at the balancing opening over the balance pin to retain the balance pin in the balancing opening via exertion of a retention force by the balance clip on the balance pin.

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.

Abstract: A rotor assembly is disclosed. In various embodiments, the rotor assembly includes a first rotor having a first plurality of tabs; a second rotor having a second plurality of tabs; and a rotor coupling ring having an anti-rotation tab configured for disposition between an adjacent pair of tabs from one of the first plurality of tabs or the second plurality of tabs.

Abstract: An anti-rotation assembly may include a first shaft, a second shaft, and a locking sprocket. The first shaft may have a first crenelated end rim, the second shaft may have a second crenelated end rim, and the locking sprocket may be configured to engage the first crenelated end rim and the second crenelated end rim to anti-rotatably couple the first shaft to the second shaft. That is, the locking sprocket may be configured to prevent relative rotation between the two shafts. The anti-rotation assembly may further include an axial retaining ring configured to axially retain the locking sprocket.

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.

Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance pin configured for insertion into an opening in the rotating component, a balance clip configured for installation to the rotating component over the balance pin to retain the balance pin in the opening via exertion of a retention force on the balance pin. A method of correcting an imbalance of a rotating assembly includes inserting a balance pin into a balancing opening in a rotating component of the rotating assembly, and installing a balance clip at the balancing opening over the balance pin to retain the balance pin in the balancing opening via exertion of a retention force by the balance clip on the balance pin.

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice.

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: An anti-rotation assembly may include a first shaft, a second shaft, and a locking sprocket. The first shaft may have a first crenelated end rim, the second shaft may have a second crenelated end rim, and the locking sprocket may be configured to engage the first crenelated end rim and the second crenelated end rim to anti-rotatably couple the first shaft to the second shaft. That is, the locking sprocket may be configured to prevent relative rotation between the two shafts. The anti-rotation assembly may further include an axial retaining ring configured to axially retain the locking sprocket.

Abstract: A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice.

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.