Abstract: A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end.

Abstract: An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

Abstract: A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: A compressor scroll is provided for redirecting an airflow from a compressor. The compressor scroll includes a spiral-shaped body; a radial inlet formed in the body for receiving the airflow from the compressor as inlet airflow; and an outlet formed in the body such that inlet airflow flows through the body and exits the outlet as outlet airflow, with at least a portion of the outlet airflow crossing at least a portion of the inlet airflow.

Abstract: A gearbox for an auxiliary power unit (APU) includes a front side defining a generator interface configured to be coupled to a generator, the front side further defining an oil pump and fuel control component interface configured to be coupled to an oil pump and fuel control component, and a starter interface configured to be coupled to a starter. The gearbox further includes a back side on an opposite side to the front side and configured to house a gear train; a bottom side defining an oil tank interface configured to be coupled to an oil tank; and a debris conduit extending from the generator interface to the oil tank interface.

Abstract: An eductor assembly is provided that includes a primary nozzle, a cooler plenum, and a surge plenum. In one embodiment, and by way of example only, the primary nozzle is configured to accelerate and discharge turbine exhaust gas therefrom and the cooler plenum surrounds the primary nozzle and includes at least a fluid inlet and a fluid outlet. The surge plenum partially surrounds the primary nozzle and the cooler plenum and includes at least a fluid inlet and a fluid outlet. The surge plenum fluid outlet axially aligns and is coterminous with the cooler plenum fluid outlet.

Abstract: A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.

Abstract: A compressor scroll is provided for redirecting an airflow from a compressor. The compressor scroll includes a spiral-shaped body; a radial inlet formed in the body for receiving the airflow from the compressor as inlet airflow; and an outlet formed in the body such that inlet airflow flows through the body and exits the outlet as outlet airflow, with at least a portion of the outlet airflow crossing at least a portion of the inlet airflow.

Abstract: A flexible fitting for connecting a plurality of rigid tubings to form a tubing assembly including a housing, having a plurality of bores defined therein and a plurality of tube fittings, each fixedly attached to an end portion of one of the plurality of rigid tubings and disposed therein one of the plurality of bores. Each of the plurality of tube fittings includes an o-ring channel having an o-ring disposed therein and in sealing contact with a sidewall of the housing when the flexible fitting is assembled. The combination of the tube fittings and the o-rings permit movement of tubing assembly, and more particularly the rigid tubing, about an axis of the tube fitting, translation along the axis of the tube fitting, and provide angulation of the rigid tubing relative to the housing.

Abstract: A gearbox for an auxiliary power unit (APU) includes a front side defining a generator interface configured to be coupled to a generator, the front side further defining an oil pump and fuel control component interface configured to be coupled to an oil pump and fuel control component, and a starter interface configured to be coupled to a starter. The gearbox further includes a back side on an opposite side to the front side and configured to house a gear train; a bottom side defining an oil tank interface configured to be coupled to an oil tank; and a debris conduit extending from the generator interface to the oil tank interface.

Abstract: A combination filter includes a filter housing having first and second inlet ports and first and second outlet ports. A first filter bowl is coupled to the housing. The first filter bowl inner surface defines a first cavity that is in fluid communication with the first inlet port and the first outlet port. A second filter bowl is coupled to the housing and is at least partially disposed within the first cavity of the first filter bowl. The second filter bowl defines a second cavity that is in fluid communication with the second inlet port and the second outlet port. A first filter is disposed within the first filter bowl for filtering fluid that flows between the first inlet port and the first outlet port, and a second filter is disposed within the second filter bowl for filtering fluid that flows between the second inlet and outlet ports.

Abstract: A compact removal feature comprises a plurality of recesses, such as radius slots, on an inner diameter (ID) of a bearing inner ring. The removal tool can engage the removal feature and remove the entire bearing assembly without damage to the parts. The placement of the removal feature on the bearing inner ring ID allows for a reduction in inner ring length (and weight) while maintaining bearing assembly integrity.

Abstract: A low profile tension style flexible joint for pneumatic ducting may be useful as, for example, a joint for aircraft engine pneumatic ducting. The joint of the present invention may be used at both ends of a duct that passes high temperature (up to about 1200° F.) and high pressure (up to about 110 psia) compressor air to the combustor of a turbomachine. Some turbomachines, such as the turbo engine of a jet-powered aircraft, require a very short curved duct to fit into an unusually small aircraft installation envelope. Moreover, these installations also require those features found in conventional flex joints, including being able to support the axial load inherent in pressurized ducting systems. Unlike conventional flexible joints, such as ball joints, gimble joints and pressure compensated joints, the low profile tension style flexible joint of the present invention provides a low profile, low weight design with the ability to support the axial load inherent in pressurized ducting systems.

Abstract: An eductor assembly is provided that includes a primary nozzle, a cooler plenum, and a surge plenum. In one embodiment, and by way of example only, the primary nozzle is configured to accelerate and discharge turbine exhaust gas therefrom and the cooler plenum surrounds the primary nozzle and includes at least a fluid inlet and a fluid outlet. The surge plenum partially surrounds the primary nozzle and the cooler plenum and includes at least a fluid inlet and a fluid outlet. The surge plenum fluid outlet axially aligns and is coterminous with the cooler plenum fluid outlet.

Abstract: A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.

Abstract: A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.

Abstract: A gas turbine engine integrates the functions of an auxiliary power unit (APU) with one or more functions of an ECS, and that is capable of operating in both an unfired mode and a fired mode. The gas turbine engine includes a combustor system that is configured to allow the gas turbine to quickly transition from the unfired mode to the fired mode, by bypassing a portion of the air flowing to the combustor system around the combustor.