Hamilton Sundstrand Corporation

Christopher Simpson

Viktor Kilchyk

Mark R Gurvich

Blair A Smith

Murtuza Lokhandwalla

Brian R Shea

John D Monacchio

Michael E Folsom

A hybrid airfoil bearing for a shaft is provided and includes airfoil bearing components and passive magnetic bearing components. The airfoil bearing components include a top foil immediately surrounding the shaft and additional components. The passive magnetic bearing components are integrated into the shaft and the additional components of the airfoil bearing components to remove a static load of the shaft on the top foil.

Hybrid airfoil and auxiliary magnetic bearings

A shroud reinforcement is provided for a shroud that is coaxial with and partially surrounds a rotor and that includes tubular and flange sections and a transition section axially interposed between the tubular and flange sections. The shroud reinforcement includes first fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along an axial dimension of the rotor and being disposed to reinforce the transition section and second fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along a circumferential dimension of the rotor and being disposed to reinforce the transition section.

Rotor containment structure

A containment structure for a rotor includes a shroud and a shroud reinforcement. The shroud is coaxial with and partially surrounds the rotor and includes a tubular section, a transition section, and a flange section. The tubular section extends axially past a first side of the rotor. The transition section connects to the tubular section and is adjacent to a curved side of the rotor. The flange section connects to the transition section opposite the tubular section. The flange section extends radially past a radially outer side of the rotor. The shroud reinforcement is connected to a radially outer surface of the transition section. The shroud reinforcement encloses the transition section and includes a support scaffold and a reinforcing material. The support scaffold includes a series of geometric retaining features encircling a radially outer surface of the transition section. The reinforcing material couples to the support scaffold and restricts shroud radial expansion.

A heat exchanging arrangement is integrated within a gas turbine engine case that at least partially encloses a gas turbine engine. The gas turbine engine has an upstream end and a downstream end which are defined by a core fluid flow through the gas turbine engine. The heat exchanging arrangement includes at least one flow passage defined within the gas turbine engine case having an inlet port and an outlet port. The at least one flow passage is configured to direct at least a portion of a fluid flowing through the gas turbine engine from between a downstream position and an upstream position while traveling between the inlet port and the outlet port.

Integral engine case precooler

An environmental control system includes two environmental control system components with a duct extending between them. There is a drain in the duct including an orifice through the duct, a plenum in serial fluid communication with the orifice; and an orifice device removably connected to the duct, the orifice device including a second orifice in serial fluid communication with the plenum and the first orifice.

Drain hole orifice device

An acoustic liner for a duct of an air conditioning and temperature control system including a honeycomb structure having a thickness of about 0.375&#xb1;0.006 inches (0.953&#xb1;0.015 centimeters). The acoustic liner is configured to cover an outer surface of a cylinder having a length of about 30 inches (76 centimeters) and an outer diameter of about 8.30 inches (21.1 centimeters).

Growing community of inventors

West Hartford, CT, United States of America

Christopher Simpson