Abstract: A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.

Abstract: A drive system for a multi-phase electric machine with a permanent magnet rotor, the drive system may comprise conduction paths for each phase. Detectors on each of the conduction paths may determine electrical condition of the conduction path. At least one selectable interconnection path may be present between all of the conduction paths and at least one selectable interconnection path may be operable to connect all of the conduction paths together responsively to at least one of the detectors determining that the electrical condition of its respective electrical path is representative of a predetermined electrical fault condition so that heating of the rotor during continued rotation of the rotor is prevented.

Abstract: A fuel tank inerting system uses two “half systems” for providing inerting gas for the fuel tanks. Each inerting system may be composed of a temperature control and air pressurization unit (TCPU) and an air separation unit (ASU). A cross-ship duct and valve allows using one TCPU (sized for about half capacity or more, but less than full system capacity) connected to two ASUs. The inerting system may provide for redundancy in the TCPU section.

Abstract: An integrated heat exchanger comprises a primary heat transfer zone and a secondary heat transfer zone integral to the primary heat transfer zone. The primary heat transfer zone comprises an ECS heat exchanger and the secondary heat transfer zone comprises a heat exchanger for a secondary system, such as an OBIGGS heat exchanger. The integrated heat exchanger reduces the negative impact that the OBIGGS heat exchanger has on the ECS heat exchanger by providing one ram face, thereby minimizing the flow disturbances associated with the OBIGGS heat exchanger. By integrating the OBIGGS and the ECS heat exchanger, the integrated heat exchanger reduces the negative impact of the pressure drop and heat load caused by the OBIGGS heat exchanger.

Abstract: A motor control architecture is provided that simultaneously controls multiple motors. The motor control system includes memory, a plurality of motor control processors, and a communication controller. The motor control processors are each responsive to control signals supplied from the communication controller to selectively retrieve system commands and motor positions from the memory, to generate motor commands, and to supply the generated motor commands to the memory. The communication controller selectively receives system commands and transmits the received system commands to the memory, selectively supplies the command signals to selected ones of the motor control processors, selectively receives motor positions from a plurality of motors, selectively transmits motor positions to the memory, selectively retrieves generated motor commands supplied to the memory, and selectively transmits the retrieved motor commands.

Abstract: A trigger mechanism for starting current acquisition for motor control applications is disclosed. The present invention may generate an edge (ADC trigger) that can be used to start current acquisition by the ADC. The present invention may reduce the overhead involved in synchronizing the current acquisition with PWM generation and also minimize the wait period for software conversions to complete by replacing software-based timing with a hardware-based trigger mechanism.

Abstract: A fluid coupler for connecting two hydraulic appliances together without requiring flexible hoses is described. The fluid coupler enables fluid-tight connecting between fixed position components and allows for separating the hydraulic appliances without decoupling the coupler while maintaining fluid-tightness of both appliances after separation.

Abstract: A centrifuge is employed to continuously remove particulates from a fluid. In one embodiment, the centrifuge removes small particles of soot from lubricating oil of diesel engines. The fluid is introduced into the centrifuge through a distribution rotor so that vortexes are not propagated in the fluid. Laminar flow of the fluid down the sides of the outer rotor may contribute to the soot-removal effectiveness of the centrifuge.

Abstract: A gas separation membrane comprises a blend of polyethersulfone (PES) and aromatic polyimide polymers that may comprise a plurality of first repeating units of formula (I), wherein X1, X 2 and X3 are herein defined.

Abstract: Methods and apparatus are provided controlling aircraft cabin pressure, and more specifically engine bleed air manifold pressure, during aircraft descent. An aircraft engine bleed air manifold control pressure setpoint is to either a descent pressure setpoint or a cruise pressure setpoint by determining a rotational speed of an aircraft engine component, determining a component speed setpoint value, and determining aircraft vertical speed. The engine bleed air manifold control pressure setpoint is set to the descent pressure setpoint if either the determined rotational speed of the aircraft engine component is below the component speed setpoint value or the aircraft vertical speed is less than a predetermined vertical speed value.

Abstract: A compressor ported shroud takes compressed air from the shroud of the compressor before it is completely compressed and delivers it to foil bearings. The compressed air has a lower pressure and temperature than compressed outlet air. The lower temperature of the air means that less air needs to be bled off from the compressor to cool the foil bearings. This increases the overall system efficiency due to the reduced mass flow requirements of the lower temperature air. By taking the air at a lower pressure, less work is lost compressing the bearing cooling air.

Abstract: A two fluid thermal storage device that may allow for independent heating and cooling includes a plurality of plate members with a set of dividers brazed between two of them. The set of dividers, which may define a series of passageways therein, may include a first sub-series of alternate passageways filled with a phase change material, and a second sub-series of remaining passageways that transports a fluid, the remaining passageways alternating between transporting a cooling fluid through a first fluid circuit and transporting a heating fluid through a second and independent fluid circuit. The remaining passageways that transport the cooling fluid through the first fluid circuit are defined by a first subset of dividers and the remaining passageways that transport the heating fluid through the second fluid circuit are defined by a second subset of dividers.

Abstract: A centrifuge is employed to continuously remove particulates from a fluid. In one embodiment, the centrifuge removes small particles of soot from lubricating oil of large diesel engines. The fluid in introduced into the centrifuge through an inducer so that vortexes are not propagated in the fluid. Flow constrainers and flow straighteners maintain laminar flow of the fluid as it passes axially through the centrifuge. An exducer decelerates the fluid prior to its exit from the centrifuge. The exducer thus contributes to maintaining laminar flow conditions. Laminar flow may contribute to the soot-removal effectiveness of the centrifuge.

Abstract: A hydrodynamic bearing set, for use with a thrust disk disposed between planar surfaces of a housing, includes first and second topfoils disposed adjacent first and second thrust disk axial bearing surfaces and removably secured to the housing. An underspring is secured between each planar housing surface and the corresponding topfoil. Dual-leaf spring pairs attached to at least one topfoil periphery function to urge the topfoils away from the thrust disk axial bearing surfaces by applying a force against a planar housing surface, another topfoil, or a spacer washer secured between adjacent topfoil dual-leaf pairs or frictionally retained within the housing. Alternatively, a wavy washer, a conical spring, a Belleville washer, or a coil spring can be substituted for the dual-leaf spring pairs.

Abstract: A cabin pressure control system and method improves cabin pressurization during aircraft take-off operations. The cabin pressure control system sets a cabin pressurization rate limit based on a cabin pressurization rate error. The cabin pressurization rate error is derived from a comparison of a sensed cabin pressure rate-of-change value and a predetermined cabin pressurization rate value.

Abstract: The present invention provides panels for a microchannel heat exchanger core wherein the panels may have greater than about 36 fins per inch of the panel. The microchannels of the panels may have an aspect ratio of at least about 10. Panels are also provided having microchannels and fins on one side of the panel or on opposite sides of the panel. Methods are also provided for machining the panels of the present invention.

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 multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

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.

Abstract: A lightweight high temperature bladed turbine disk intended for use in gas turbine engines. The bladed disk comprises a cast integral ring of single crystal airfoils with the primary and secondary crystallographic orientation being the same for each airfoil. Low-angle mismatch boundaries are present in the endwalls that couple adjacent airfoils. The cast ring of single crystal turbine blades is diffusion bonded to a high strength equiaxed disk. The resulting single crystal bladed disk is endowed superior performance, temperature capability, and lower weight and cost, relative to conventional turbines composed of individually cast single crystal blades, which are mechanically inserted into machined slots in the disk, or lower strength cast equiaxed blade rings that are diffusion bonded to a high strength turbine disk.