General Electric Company

Mark Gregory Wotzak

Daniel Waslo

Duane Howard Anstead

Brian Lewis Devendorf

James John Luz

Thomas Charles McCarthy

Kenneth Arthur Gould

Bojan Lukovic

Keith Franklin Beatty

Martin Miles D'Angelo

Thomas Charles Mccarthy

Keith Beatty

An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.

Turbine engine with single wall cantilevered architecture

The present disclosure is directed to a gas turbine engine including an engine shaft rotatable with at least one of a fan section, a compressor section, or a turbine section, and an accessory gearbox assembly including a towershaft, a first gearbox, a torque transfer assembly, and a second gearbox. The towershaft is rotatable with the engine shaft and extended therefrom and mechanically coupled to the first gearbox. The first gearbox transmits mechanical energy from the engine shaft via a first shaft defining a first end and a second end. The first shaft extends at the first end from the first gearbox and through the torque transfer assembly and coupled thereto. The first shaft extends from the torque transfer assembly to the second gearbox at the second end and is coupled thereto. The first gearbox and the second gearbox each are coupled to one or more gearbox accessories.

Dual accessory gearbox

An annular air inlet duct circumscribing an axis of rotation of a rotatable member of a machine comprising a forward end and an aft end is described. The air inlet duct includes an unheated wall and a heated wall adjacent to a heat source. The heated wall includes a plurality of axially-spaced wall panels forming a cavity between each of a pair of adjacent wall panels of the plurality of axially-spaced wall panels.

Engine air inlet having a double-panel heated wall

An intershaft seal assembly including first and second or forward and aft carbon face seal rings supported on an annular housing and having first and second seal faces facing in opposite directions. Forward and aft springs operably disposed between housing and carbon face seal rings for biasing or urging carbon face seal rings in opposite directions. Annular forward and aft carriers mounted on and supported by annular housing and supporting carbon face seal rings. Forward and aft springs operably disposed between housing and the forward and aft carriers respectively. The springs may be wave springs. Inner and outer secondary seals may include inner and outer O rings disposed in annular inner and outer grooves in annular inner and outer surfaces in housing respectively and in sealing engagement with the forward and aft carriers. Carriers may be integral with carbon face seal rings in monolithic combined seal and carrier elements.

Intershaft seal with dual opposing carbon seal rings

An in-line propeller gearbox of a turboprop gas turbine engine includes an epicyclic gearing arrangement that has a sun gear, a ring gear and at least one planet gear disposed between and meshing with both the sun gear and the ring gear. The propeller gearbox includes a disk brake that can be operated to slow down or stop altogether the rotation of the propeller. The disk brake has an axially extending shaft having at one end a disk and at the opposite end a gear having teeth that engage with one of the gears in the epicyclic gearing arrangement. The disk brake includes a hydraulic caliper or an electric caliper that can be actuated to slow down rotation of the disk to an eventual full stop and to hold the disk at full stop to thereby stop rotation of the propeller.

Inline propeller gearbox brake

The present disclosure is directed to a sump housing for a gas turbine engine. The sump housing includes a base portion and a first wall extending outwardly from the base portion. The first wall and the base portion at least partially define an inner chamber. A second wall is positioned outwardly from the first wall and extends outwardly from the base portion. The base portion, the first wall, and the second wall at least partially define an outer chamber positioned outwardly from the inner chamber. A projection extending inwardly from the first wall engages a bearing assembly. The base portion, the first wall, the second wall, and the projection are integrally coupled together.

Sump assembly for a gas turbine engine

An in-line propeller gearbox of a turboprop gas turbine engine includes a lubricant reservoir disposed spaced radially offset from the engine's central axis of rotation and asymmetrically with respect to the central axis of rotation such that the central axis of rotation does not extend through the lubricant reservoir.

Integral offset oil tank for inline accessory gearbox

A gearbox vent apparatus includes: a gearbox; an accessory contained in a case mounted to the gearbox such than an interior space of the case communicates with an interior space of the gearbox, wherein the case includes a sidewall and an endwall, a hollow drive shaft mounted for rotation inside the case; an annular first seal element mounted to the drive shaft; an annular second seal element mounted to the case and contacting the first seal element so as to define a sealing interface; and a vent tube having a forward end coupled to the endwall in fluid communication with the drive shaft.

Gearbox with sealed accessory vent

An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut.

Intershaft integrated seal and lock-nut

A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane. The driveshaft vessel includes a forward face, an aft face, and opposing side faces and is configured to house at least a portion of a radial driveshaft. The outlet guide vane includes a leading edge and a trailing edge. The length of the trailing edge is substantially equal to a length of the forward face of the driveshaft vessel such that the trailing edge of the outlet guide vane is faired into the forward face of the driveshaft vessel.

Aircraft engine driveshaft vessel assembly and method of assembling the same

A method of assembling accessories with a turbine engine and an accessory apparatus for a gas turbine engine having a first shaft that rotates when the gas turbine engine is energized. The accessory apparatus includes a mount rail attached to the gas turbine engine and extending parallel to the first shaft of the gas turbine engine a first accessory having a first mounting block, to mount the first accessory to the mount rail, and an first accessory shaft to power the first accessory and a second accessory having a second mounting block, to mount the second accessory to the mount rail, and a second accessory shaft to power the second accessory.

Accessory apparatus and method of assembling accessories with a turbine engine

The present disclosure involves an oil scoop manifold receives and directs the oil in fore and aft directions to lubricate multiple bearing assemblies.

Growing community of inventors

Chestnut Hill, MA, United States of America

Mark Gregory Wotzak