A gas turbine engine assembly (10), includes a core gas turbine engine (12), a low-pressure turbine (14) coupled to the core turbine engine, a counter-rotating fan assembly (16) coupled to the low-pressure turbine, and a booster compressor (24) coupled directly to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate in the same direction.

Gas turbine engine assembly and methods of assembling same

Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.

Bleed air systems for use with aircrafts and related methods

A turbofan engine assembly (10) including a core gas turbine engine (13) including a high-pressure compressor (14), a combustor (16), and a high-pressure turbine (18), a low-pressure turbine (20) coupled to the core gas turbine engine, a counter-rotating booster compressor (22) including a first rotor section (50) configured to rotate in a first direction and a second rotor section (60) configured to rotate in an opposite second direction, and a gearbox (100) including an input (110) and an output (111, 112), the gearbox output coupled to at least one of the first and second rotor sections, the gearbox input coupled to the low-pressure turbine.

Turbofan engine assembly and method of assembling same

A blood filter includes a hub, a plurality of legs, and a plurality of arms. Each of the legs includes a hook at a distal end thereof, a first linear segment extending substantially parallel to a hub longitudinal axis, a second linear segment extending obliquely with respect to the longitudinal axis at a first angle, and an intermediate linear segment coupled to the first and second segments, the intermediate segment extending obliquely with respect to the longitudinal axis at a second angle less than the first angle. Each of the arms has a free end closer to the longitudinal axis than the hook of each of the legs. The free ends of the arms are spaced radially transverse to the longitudinal axis at substantially the same radial distance.

Removable embolus blood clot filter and filter delivery unit

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Gas turbine engine compressor arrangement

An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.

Engine mounting configuration for a turbofan gas turbine engine

A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means, for vibration stabilizing.

Turbine engine rotor stack

A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.

Shared flow thermal management system

A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially overlapping with the compressor section.

Gabriel L. Suciu

Papers

Gas turbine engine compressor arrangement

Engine mounting configuration for a turbofan gas turbine engine

Turbine engine rotor stack

Shared flow thermal management system

Gas turbine engine shaft bearing configuration