A system is provided. The system includes a first environmental control sub-system, operating in a first mode, that receives a first medium at a first flow amount and a first pressure. The system also includes a second environmental control sub-system, operating in a second mode, that receives a second medium at a second flow amount and a second pressure. The first flow amount is greater than the second flow amount, and the second pressure is greater than the first pressure.
An airplane is provided. The airplane includes a pressurized compartment and an environmental control system. The environmental control system includes a compressing device. The compressing device includes a compressor and a turbine. The airplane also includes a first flow of first medium configured to enter the pressurized compartment and a second flow of the first medium configured to enter the turbine.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
F04B 35/04 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being electric
An airplane is provided. The airplane includes a vapor cycle air conditioning system that receives outside air, a bleed system with at least one port, and an electric fan. A source of outside air when the airplane is on ground is forced air from the electric fan. The source of the outside air when the airplane is at cruise is bleed air from the at least one port.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F04B 35/04 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being electric
A supercharge compound configuration of a forced induction intake and/or breather system for an internal combustion engine is provided. The system may be configured to improve the power output of an internal combustion engine when considered against similar internal combustion engines with conventional forced induction systems. The supercharge compound configuration may comprise a turbine that may be driven by the exhaust of the internal combustion engine. The turbine may also be operatively and/or directly coupled to a gearbox and/or a compressor.
F02B 39/06 - Mechanical drives; Variable-gear-ratio drives the engine torque being divided by a differential gear for driving a pump and the engine output shaft
The present disclosure relates to engine buffer systems. An engine buffer system (200) may include a low pressure supply line (230) and a high pressure supply line (240). A continuously variable valve (250) may be coupled to and/or in fluid communication with the low pressure supply line and the high pressure supply line. The continuously variable valve may be adjusted to supply any pressure between a pressure of the low pressure supply line and a pressure of the high pressure supply line to a buffer line (260).
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
6.
ENVIRONMENTAL CONTROL GENERATOR SYSTEM AND APPARATUS
An environmental control power generation system is provided. The system may include a turbine and a generator. The system may be configured to provide air form a high pressure bleed port and/or a low pressure bleed port to the turbine. The turbine may be configured to reduce the pressure of the supplied air and generate power through the generator. The power may be supplied to an aircraft power distribution system.
An environmental control system (200) is provided. The environmental control system may receive pressurized air from a single supply line (220). A pressure regulating turbomachine (230) may be located within the supply line. A motor-generator (232) may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator (232) may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator.
Combustion systems for a gas turbine engines are provided. The combustion system is configured to provide a fuel-air mist to achieve light-off during high altitude start (e.g., at altitudes greater than 45,000 ft.) without flame out. The combustion system may also be configured to provide additional air to the combustion chamber at high altitude to facilitate flame propagation and second stage burn.
F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
F23R 3/20 - Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
A method is provided for connecting a fitting to a reinforced thermoplastic duct including inserting a first end of the fitting having a plurality of barbs into an end of the duct. A clamp is installed around the duct. The duct is heated to a temperature greater than a glass transition temperature of a thermal plastic material used to form the duct. The duct is restructured to include a plurality of protrusions positioned between the plurality of barbs of the fitting.
A starter system for an auxiliary power unit (APU) includes a starter motor operably connectable to the APU. A clutch is arranged to operably connect the starter motor to the APU when engaged. A torque limiting control unit is disposed and configured to provide APU starter power to the starter motor according to a starting schedule. The starting schedule is configured to govern an acceleration rate of the starter motor after the clutch is engaged.
A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second heat exchanger receives the heated air flow from the first heat exchanger. The fuel pump provides a fuel flow. The valve is coupled to the fuel pump to intermittently include the second heat exchanger in the fuel flow based on a temperature of the fuel flow. A method of heating fuel in a gas turbine engine comprises providing fuel to a gas turbine engine with a fuel pump to sustain a combustion process, heating a flow of air with exhaust gas from the combustion process, and heating fuel from the fuel pump en route to the gas turbine engine with the flow of air based on a temperature of the fuel.
F02M 31/08 - Apparatus for thermally treating combustion-air, fuel, or fuel-air mixture for heating combustion-air or fuel-air mixture by hot gases, e.g. by mixing cold and hot air the gases being exhaust gases
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
A device for monitoring a physical system includes an interface in operable communication with the physical system and a control circuit in operable communication with the interface. The device also includes a memory in operable communication with the control circuitry and an electronic paper display in operable communication with the control circuitry. The electronic paper display continuously displays information related to the operation of the physical system.
A lube pump has a housing with a flange extending radially outwardly from a body of the housing. At least one rotor is received within the housing, and a shaft for powering the rotor extends away from the flange. A retention plate is positioned on an end of the flange closing the housing. A first set of bolts secure the flange to the retention plate. A second set of bolts secure the flange to the gearbox. The two sets of bolts extend in opposed directions. A gearbox including such a lube pump is also disclosed and claimed.
F04C 2/344 - Rotary-piston machines or pumps having the characteristics covered by two or more of groups , , , or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group or and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
F01C 21/00 - Component parts, details, or accessories, not provided for in groups
This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions. An actuator (18) is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller (32) in communication with the actuator (18) is configured to command the actuator between the stowed and deployed positions in response to an input. The controller (32) commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator (18) includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.
A local area network (LAN) includes a computer processing unit (CPU) (16) located within an aircraft cabin. A plurality of radios (18) is connected to the CPU (16) and to a radio frequency (RF) combiner and splitter (20). The RF combiner and splitter (20) allows for each of the radios (18) to transmit and receive common information over a plurality of different channels. As the number of users within the LAN increases additional radios can be connected to the CPU and the RF combiner and splitter (20) for increased signal coverage and capacity.
A dynamoelectric machine (100) comprises a first rotor shaft (102), a second rotor shaft (104) and a central element (106). The first rotor shaft (102) rotates about a central axis (C/L) of the machine (100) and has a first magnetic drive element (108) disposed about an outer circumference of the first rotor shaft (102). The second rotor shaft ( 104) rotates about the first rotor shaft (102) and has a second magnetic drive element ( 110) disposed about an inner circumference of the second rotor shaft (104). The central element ( 106) is disposed between the first rotor shaft (102) and the second rotor shaft (104) and is configurable to remain stationary while the first rotor shaft and the second rotor shaft rotate about the central axis (C/L). The central element ( 106) also includes a third magnetic drive element (112) for interacting with the first magnetic drive element (108), and a fourth magnetic drive element (114) for interacting with the second magnetic drive element (110).
A rotor (12) for a brushless permanent magnet generator/motor (10) comprises a retention slot (46) extending into a rotor flange (34) for receiving a root (48) of a permanent magnet (36). The retention slot (46) comprises a base (54) extending axially into the rotor flange (34), a pair of side walls (56, 58) extending radially from the base (54), and a pair of lugs (60, 62) projecting from the side wall (56, 58) to engage the root (48) to provide radial and tangential retention of the permanent magnet (36). In other embodiments, the permanent magnet (36) is further restrained in the axial direction by a spring pre-loaded axial retention ring (38).
H02K 21/26 - Synchronous motors having permanent magnets; Synchronous generators having permanent magnets with rotating armatures and stationary magnets
A top reading liquid sight level indicator mounts above a liquid contained in a liquid vessel comprises a measuring surface mounted to the liquid vessel that penetrates an upper surface of the contained liquid at a cant from normal to the liquid surface so that the points along the measuring surface that penetrate the liquid surface are visible from above the liquid vessel and represent the level of the liquid in the liquid vessel.
G01F 23/02 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by gauge glasses or other apparatus involving a window or transparent tube for directly observing the level to be measured or the level of a liquid column in free communication with the main body of the liquid
G01F 23/04 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by dip members, e.g. dip-sticks
20.
TANDEM DIFFERENTIAL MOBILITY ION MOBILITY SPECTROMETER FOR CHEMICAL VAPOR DETECTION
A DMS-IMS chemical sensing system employs two ion-separation technologies in tandem to extract signals of specific chemicals from the glut of signals present. The sensing system generally includes an atmospheric pressure ion generation system, a Differential Mobility (DMS) system, a time-of-flight IMS (TOF-IMS) system, and an ion detector system. The DMS extracts a narrow range of trace chemicals from an environmental sample for subsequent analysis, and a TOF-IMS then analyzes the resulting narrow range of isolated chemicals, allowing compound-specific detection thresholds at sub-ppb concentrations.
G01N 27/62 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating electric discharges, e.g. emission of cathode
21.
OIL SEPARATOR WITHI RAISED HOLES IN PERFORATED TUBE
A gas/oil separator is provided, wherein a pre-separator tube has an upper solid portion, and a lower perforated portion. Holes in the lower perforated portion allow a gas stream to move radially inwardly, and to a downstream filter pack. The holes have a raised portion extending radially outwardly, and prevent previously separated oil from being reintroduced into the gas stream.
F25B 43/02 - Arrangements for separating or purifying gases or liquids; Arrangements for vaporising the residuum of liquid refrigerant, e.g. by heat for separating lubricants from the refrigerant
A wind turbine assembly with a driving device for raising and lowering a wind turbine between a lower end and an upper end of a wind turbine tower comprises a guide member extending longitudinally along the outer surface of the tower, a sleeve member coupled to the wind turbine, and means for raising and lowering the sleeve member between the upper end and the lower end of the tower along the guide member. The sleeve member has an inner diameter that is larger than an outer diameter of the tower, and is slidably coupled to the tower. The sleeve member also includes a slot configured to engage with the guide member.
A mount system for an auxiliary component includes two side brackets (42, 44) and a top bracket (46) for rigidly attaching an auxiliary component (32) to an engine casing (22). Each side bracket (42, 44) defines mount segment (50, 52), a deformable member (SO) and two retainer members (62, 64) between the mount segments. The deformable member (60) plastically deforms during a fan-blade out event, thereby absorbing a majority of the high shock load experienced on the auxiliary component (32). The retainer members (62, 64) maintain the attachment between the auxiliary component (32) and the engine casing (22) subsequent to the fan-blade out event.
A diffuser is provided having a spaced apart shroud and backing plate. A diffuser vane is provided between the backing plate and shroud. The vane includes first and second sealing surfaces opposite from one another and adjacent to the backing plate and shroud. Leading and trailing surfaces are arranged opposite from one another and adjoin the first and second sealing surfaces. The first sealing surface includes a first protrusion extending therefrom approximate to the leading surface with a gap extending from the trailing surface to the first protrusion. The second surface includes a second protrusion extending therefrom proximate to the trailing surface with a second gap extending from the leading surface to the second protrusion. The surfaces provide four corners such that the protrusions are arranged on opposite corners from one another to create a pressure differential between the first and second sealing surfaces.
A diffuser includes multiple vanes rotatable about pivot pins between multiple positions. A mounting plate supports a backing plate. The vanes are arranged between the backing plate and the shroud. The pivot pins are in a slip fit relationship with the backing plate, vanes and shroud and are threadingly received by bosses in the mounting plate. The mounting plate and pivot pin arrangement better enables the backing plate and shroud to remain parallel with one another during deflection of the backing plate and/or shroud. Structure, such as integral protrusions and/or bolts, extend from between the backing plate and shroud through apertures in the vanes to better contain the vanes in the event of a catastrophic failure.
A motor is provided including a housing having separate motor and bearing cooling inlets. The motor is arranged within the housing and includes a stator and a rotor assembly supported on air bearings. The motor cooling inlet is in fluid communication with the stator, and the bearing cooling inlet is in fluid communication with the air bearings. The motor cooling inlet provides a first cooling fluid at a first pressure on the rotor assembly, and the bearing cooling inlet provides a second cooling fluid at a second pressure on the rotor assembly that is different than the first pressure. The pressures exerted on the rotor assembly produce bearing loads that generally cancel one another. This may be achieved by providing a vent in the housing that is common to both the motor cooling inlet and the bearing cooling inlet. As a result, journal bearings and seals of substantially the same size may be used, and several seals may be eliminated.
A thrust bearing (18) for a rotary machine (10) includes first, second and third layers (24, 26, 28). The second layer (26) includes a corrugated foil arranged between the first and third layers. The corrugated foil includes a wall having peaks (58) engaging the first layer and valleys (60) engaging the third layer. A depression (62) is arranged in the wall between first and second peaks. The depression is spaced from the first and third layers. The first layer (24) includes multiple arcuate top foils that are arranged adjacent to a thrust runner (16) of a rotatable shaft (12). A corresponding number of arcuate corrugated foils may be used to support the top foils. The third layer (28), which is provided by an annular main plate, includes multiple arcuate spacers (30) arranged circumferentially on the main plate. The spacers are generally aligned with a trailing edge (40) of the top foils. The depressions decrease the stiffness of the bump foils. The spacers direct the axial load through the thrust bearing in a desired manner.
An ECS system provides an ACM which locates the compressor (20) upon a common shaft (84) between a first turbine (22) and a second turbine (24). Each RAF is located remote from the ACM such that the turbines (22, 24) are located outboard on each end of the ACM to provide the highest efficiency possible with each turbine using a straight axial outlet diffuser. As the compressor (20) is located between the turbines (22, 24) the bypass circuits from the turbines are less circuitous and more efficient. Integral valve ports formed into the ACM housing portions results in a weight reduced design due to increase bypass efficiencies and simplified installations.
A system and method for providing a mechanical joint supporting a printed circuit board ⏧12] and a solder joint of power module ⏧20] terminals to a printed circuit board ⏧12], as well as a mechanical joint ⏧22] for facilitating a thermal interface between a power module ⏧20] and a heat sink or cold plate is disclosed. The system provides for both mechanical joints through a common mechanical support including a plurality of standoffs mounted to studs ⏧22] projecting from a heat sink or cold plate, wherein the assembly also provides for an insulating spacer ⏧30] to be clamped to the standoffs ⏧22] via a wing nut ⏧32] or similar fastener to support me printed circuit board ⏧12].
The present invention relates to a circuit for detecting a functional status of an electro-motor. Typical electro-motors need additional components to identify the functional status of the motor. This means additional weight for such motors determining the functional status. According to the present invention a circuit is provided using a part of a motor as a sensor for detecting the functional status of the electro-motor.
A body armor assembly (30) includes a plurality of rigid tiles that are supported in a manner to provide movement and flexibility while still providing the protection of rigid armor. In a disclosed example, a tile holder maintains a plurality of tiles in a selected alignment. The tile holder maintains a minimum overlap dimension between adjacent tiles. Some of the tiles are maintained by the tile holder in a manner that allows for the overlap dimension to increase beyond the minimum overlap dimension. In a disclosed example, at least two rigid layers have at least one ballistic material layer (170) between them to provide a rigid armor material composition.
An on-board inert gas generating system (10) includes a flow control valve (28) modulated according to changes in ambient conditions to minimize changes to oxygen content within a fuel tank (18). The quality of the nitrogen-enriched air stream (16) that is provided by the air separation module (12) varies in response to flow. Higher flow rates through the air separation module (12) removes less oxygen relative to lower flow rates. The amount of flow through the air separation module that produces the least amount of oxygen within the fuel tank (18) is determined for an ambient pressure (46) and provided by modulating the flow control valve (28).
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
B65D 90/44 - Means for reducing the vapour space or for reducing the formation of vapour within containers by use of inert gas for filling space above liquid or between contents
patents
