Abstract: A fuel system is disclosed for a gas turbine engine, which includes an augmentor pump having an inlet communicating with a fuel supply source and a discharge communicating with an augmentation stage of the engine, wherein the augmentor pump is connected to an accessory drive gearbox mounted to the engine, and a high speed clutch for selectively engaging and disengaging the augmentor pump and the accessory drive gearbox.

Abstract: A fuel system is disclosed for a gas turbine engine, which includes an augmentor pump having an inlet communicating with a fuel supply source and a discharge communicating with an augmentation stage of the engine, wherein the augmentor pump is connected to an accessory drive gearbox mounted to the engine, and a high speed clutch for selectively engaging and disengaging the augmentor pump and the accessory drive gearbox.

Abstract: A single drive, dual clutch accessory drive system for an aircraft including an input shaft connected to a low pressure spool of a turbine engine. The input shaft is rotatable at a first input speed and at a second input speed that is distinct from the first input speed. An output shaft is operatively connected to an aircraft accessory. A first drive path operatively connects the input shaft and the output shaft. The first drive path includes a first clutch and a gear system. The first drive path is operable to adjust the first input speed to a selected output shaft speed. A second drive path operatively connects the input shaft and the output shaft. The second drive path includes a second clutch. The second drive path is operable to rotate the output shaft at the second input speed.

Abstract: A dual drive, dual clutch accessory drive system for an aircraft including a first input shaft connected to a first pressure spool of a turbine engine. The first input shaft rotates at a first speed. A second input shaft is connected to a second spool of the turbine engine that is distinct from the first spool. The second input shaft rotates at a second speed. An output shaft operatively connected to an aircraft accessory. A first drive path selectively operatively connects the first input shaft with the output shaft. The first drive path includes a first clutch. The first drive path being operable to rotate the output shaft at the first speed. A second drive path operatively connects the second input shaft with the output shaft. The second drive path includes a second clutch. The second drive path is operable to rotate the output shaft at the second speed.

Abstract: An oil reservoir assembly includes a tank, a return passage, a pressurization valve, a first passage, and a vent valve. The tank includes a canister, a fill port, an first oil outlet, an second air outlet, and an inlet. The inlet is disposed in the canister and is connected to a restrictor. The return passage is connected to the inlet of the tank and to a scavenge pump. The pressurization valve is fluidly connected to the second air outlet of the tank. The first passage is connected to the pressurization valve and to an accessory gearbox of the engine. The vent valve is disposed in the return passage and includes a body, a channel extending through the body, an inlet orifice, and an outlet orifice. The inlet orifice is disposed in an end of the body. The outlet orifice is fluidly connected to the inlet orifice via the channel.

Abstract: An assembly for a coupling together rotatable components according to an example of the present disclosure includes, among other things, a rotor shaft extending along a centerline axis, the rotor shaft defining an inner bore extending from an axial end of the rotor shaft, a gear mounted on an outer diameter of the rotor shaft, a lock nut threadedly engaged with the outer diameter of the rotor shaft such that the lock nut abuts against an axial end face of the gear, and a retainer including a step portion extending from a head portion and including a projection portion extending from the step portion. The projection portion is insertable into the inner bore to bias the lock nut against the axial end face of the gear, and the step portion is dimensioned to establish an interference fit with the rotor shaft along the inner bore. A starter assembly and a method of assembly are also disclosed.

Abstract: An oil reservoir assembly includes a tank, a return passage, a pressurization valve, a first passage, and a vent valve. The tank includes a canister, a fill port, an first oil outlet, an second air outlet, and an inlet. The inlet is disposed in the canister and is connected to a restrictor. The return passage is connected to the inlet of the tank and to a scavenge pump. The pressurization valve is fluidly connected to the second air outlet of the tank. The first passage is connected to the pressurization valve and to an accessory gearbox of the engine. The vent valve is disposed in the return passage and includes a body, a channel extending through the body, an inlet orifice, and an outlet orifice. The inlet orifice is disposed in an end of the body. The outlet orifice is fluidly connected to the inlet orifice via the channel.

Abstract: A sealing arrangement for a shaft according to an example of the present disclosure includes a shaft and a sealing assembly. The sealing assembly includes a seal cartridge that has at least one sealing element. The first and second mating rings are configured to axially locate the seal cartridge with respect to the shaft. The second mating ring includes at least one tang that is configured to extend through at least one corresponding slot in the shaft, the at least one tang is configured to engage a retaining ring to axially retain the second mating ring on the shaft. A gearbox/accessory interface assembly and a method of sealing a gearbox with respect to an accessory are also disclosed.

Abstract: A link for mounting a first component to a second component according to an example of the present disclosure includes a first piece connectable to the first component, a second piece connectable to the second component, the second piece includes a main body portion receivable in an opening in the first piece. A primary fastener is configured to retain the main body portion of the second piece in the opening. A secondary fastener is configured to retain the main body portion of the second piece in the opening, the secondary fastener capable of withstanding higher loads than the primary fastener. A gas turbine engine assembly and a method of constraining a gearbox with respect to an engine are also disclosed.

Abstract: An assembly for a coupling together rotatable components according to an example of the present disclosure includes, among other things, a rotor shaft extending along a centerline axis, the rotor shaft defining an inner bore extending from an axial end of the rotor shaft, a gear mounted on an outer diameter of the rotor shaft, a lock nut threadedly engaged with the outer diameter of the rotor shaft such that the lock nut abuts against an axial end face of the gear, and a retainer including a step portion extending from a head portion and including a projection portion extending from the step portion. The projection portion is insertable into the inner bore to bias the lock nut against the axial end face of the gear, and the step portion is dimensioned to establish an interference fit with the rotor shaft along the inner bore. A starter assembly and a method of assembly are also disclosed.

Abstract: A flow restrictor assembly includes a threaded element and a sleeve. The threaded element defines a plurality of threads that extend from a first threaded element end towards a second threaded element end. The sleeve has an inner sleeve surface that engages edges of a portion of the plurality of threads and extends between a first sleeve end and a second sleeve end. A lubrication flow path is defined by the portion of the plurality of threads and the inner sleeve surface and is arranged to create a pressure drop in a lubricant that flows through the lubrication flow path.

Abstract: A sealing arrangement for a shaft according to an example of the present disclosure includes a shaft and a sealing assembly. The sealing assembly includes a seal cartridge that has at least one sealing element. The first and second mating rings are configured to axially locate the seal cartridge with respect to the shaft. The second mating ring includes at least one tang that is configured to extend through at least one corresponding slot in the shaft, the at least one tang is configured to engage a retaining ring to axially retain the second mating ring on the shaft. A gearbox/accessory interface assembly and a method of sealing a gearbox with respect to an accessory are also disclosed.

Abstract: A link for mounting a first component to a second component according to an example of the present disclosure includes a first piece connectable to the first component, a second piece connectable to the second component, the second piece includes a main body portion receivable in an opening in the first piece. A primary fastener is configured to retain the main body portion of the second piece in the opening. A secondary fastener is configured to retain the main body portion of the second piece in the opening, the secondary fastener capable of withstanding higher loads than the primary fastener. A gas turbine engine assembly and a method of constraining a gearbox with respect to an engine are also disclosed.

Abstract: A flow restrictor assembly includes a threaded element and a sleeve. The threaded element defines a plurality of threads that extend from a first threaded element end towards a second threaded element end. The sleeve has an inner sleeve surface that engages edges of a portion of the plurality of threads and extends between a first sleeve end and a second sleeve end. A lubrication flow path is defined by the portion of the plurality of threads and the inner sleeve surface and is arranged to create a pressure drop in a lubricant that flows through the lubrication flow path.

Abstract: A gearbox assembly includes an outer housing and a gear box shaft at least partially disposed in the outer housing. The gear box shaft includes an interior region and a reservoir dam that separates the interior region into a reservoir volume and a spline volume. The reservoir dam has a vent hole formed therein that passes through it such that a surface of the dam is in fluid communication with a region defined by the outer housing and outside of the gear box shaft.

Abstract: A mounting link between a gas turbine engine and a gearbox comprises a gearbox arm, a fusibly breakable bolt, and two engine attachment brackets. The gearbox arm attaches to the gearbox, and extends along an axis defining a first dimension between the gas turbine engine structure and the gearbox. The fusibly breakable bolt extends through the gearbox arm, and has a central shear section that mates with the gearbox arm. The engine attachment brackets have primary and secondary retention annuli, and attachment flanges that attach to the gas turbine engine structure. The primary retention annuli are each concentric to an outer section of the fusibly breakable bolt, and have a radius selected to tightly retain those outer sections in the first dimension. The secondary retention annuli are each concentric to a portion of the shear section, and have a larger radius to loosely retain the shear section.

Abstract: A link assembly between an engine and a gearbox includes a male link coupled to the engine or the gearbox, a female link coupled to the engine or the gearbox, wherein the female link receives the male link to allow translation of the male link relative to the female link and to form a radial interface, wherein the radial interface dampens translation of the male link relative to the female link, and a pin releasably coupled to the male link and the female link to selectively retain the male link and the female link.

Abstract: A mounting link between an engine and a gearbox comprises an engine attachment piece, a gearbox attachment piece, and primary and secondary retention fasteners. The engine attachment piece is rotatably secured to the engine, and the gearbox attachment piece is rotatably secured to the gearbox. The primary retention fastener rigidly constrains the gearbox attachment piece with respect to the engine attachment piece in a single degree of freedom, but is configured to shear at a breakpoint load. The secondary retention fastener constrains the gearbox attachment piece loosely with respect to the engine attachment piece, and can withstand the breakpoint load. The gearbox attachment piece and engine attachment piece abut in a friction fit that provides Coulomb damping.

Abstract: A gearbox mounting link between a gas turbine engine structure and a gearbox mounting location comprises an engine attachment piece rotatably secured to the gas turbine engine structure. The engine attachment piece comprises first and second plates extending in parallel planes and separated by a gap having a gap width. A gearbox attachment piece is situated between the parallel plates, and is secured to the gearbox. A breakable primary retention fastener extends snugly through the parallel plates and the gearbox attachment piece, thereby rigidly retaining the gearbox with respect to the gas turbine engine in two degrees of freedom so long as the breakable primary retention fastener remains intact. A durable secondary retention fastener extending snugly through the parallel plates, and extends with clearance through the gearbox attachment piece via an oversized fastener passage, thereby constraining the gearbox attachment piece in the event that the breakable primary retention fastener breaks.

Abstract: A gearbox mounting link between a gas turbine engine structure and a gearbox mounting location comprises two engine attachment brackets secured to an engine structure, and attachment plate rotatably attached between the engine attachment brackets, and a secondary retention sleeve and fastener. The attachment plate includes a fusibly separable section configured to attach to the gearbox, a static section, and a shear necks connecting the statis section to the fusibly separable section. The secondary retention sleeve is supported by and secured to the static section. The secondary retention fastener is supported by the secondary retention sleeve, and is disposed through an oversized fastener passage through the fusibly separable section, thereby loosely retaining the fusibly separable section in at least one of the two degrees of freedom in the event of a load sufficient to break the shear necks, separating the fusible separable section from the static section.