Abstract: A removable secondary liquid dispensing module for use with an existing, automated liquid handling system that defines a work area having a plurality of discrete work stations. Each of the work stations of the automated liquid handling system includes a lab ware site and alignment structure enabling the removable securing standardized microtiter-plates at respective lab ware site. A plate positioning mechanism is configured to move and position the microtiter plates to and from the lab ware sites of the respective work stations thereof and into engagement with the respective carrier alignment structure thereof. Further, a primary liquid dispensing device is configured for selective contact-type dispensing of discrete quantities of fluid, in the range of about one (1) microliter to about ten (10) milliliters, into the test sites of the microtiter plates secured in the respective alignment structure of the respective work station.

Abstract: A universal calibration apparatus and method to estimate the dispense output from a low volume, non-contact, liquid dispensing systems that may be applied for every hardware configuration (e.g., tube length, orifice diameter, tip design, etc), reagent solution property and environmental condition. This same calibration technique is applied to calibrate or tune these non-contact liquid dispensing systems to dispense desired volumes (in the range of about 0.050 ?L to 50 ?L), irrespective of the hardware configuration or the solution properties. That is, the calibration technique is not dependent on any variables, but the result (the actual dispense volume) is dependant on the variable mentioned. By actuating selected pulse widths, and measuring the resulting volume, a Calibration Profile can be generated correlating the liquid volume dispensed from the orifice to the respective pulse width of the dispensing valve thereof through calibration points.

Abstract: A powder coating system includes a booth and one or more powder-recovery modules that are insertable into an equipment-receiving space of the booth. A color change method includes removing a first powder-recovery module from the equipment-receiving space and positioning a second powder-recovery module in the equipment-receiving space.

Abstract: A hybrid valve apparatus for use with an aspiration actuator and a dispensing actuator to transfer fluid from a reservoir to a test site on a substrate surface. The hybrid valve includes a valve assembly movable between an aspiration condition and a dispensing condition, and a manifold device coupled to the valve assembly. The manifold device includes a fluid aspiration conduit having a first aspiration port in fluid communication with the aspiration actuator. On an opposite end of the aspiration conduit is a second aspiration port in selective fluid communication with the valve assembly to selectively aspirate a liquid sample slug from the reservoir into a discrete sample path when the valve assembly is in the aspiration condition. The manifold device further includes a fluid dispensing conduit having a first dispensing port in fluid communication with the dispensing actuator, and a second dispensing port in selective fluid communication with the valve assembly.

Abstract: A fluid coupled speed retarder generating a restraining torque on a vehicule wheel system comprises a restraining shaft (50) coupled by a viscous fluid to a wheel (32) and axle (54) system through a coupling (30) which includes an impeller (48) with radial vanes (77) connected to the restraining shaft and a housing (44) with further radial vanes (46), the housing connected for rotation with the wheel (34). A braking force is developed upon demand by a selective locking of the restraining shaft (50) from motion, the relative motion between the impeller and housing in the viscous coupling generating the barking force.

Abstract: A system and method for burning-in an integrated circuit comprises a socket capable of receiving and supporting the IC, electrical leads in the socket for connecting to corresponding leads on the chip, and a heat sink in thermal contact with a cooling medium. A first thermal interface provides releasable thermal contact between the integrated circuit in the socket and a resiliently mounted heat absorbing member. A second thermal interface is provided between the heat absorbing member and the heat sink.

Abstract: An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.

Abstract: A powder coating system includes a booth and one or more powder-recovery modules that are insertable into an equipment-receiving space of the booth. A color change method includes removing a first powder-recovery module from the equipment-receiving space and positioning a second powder-recovery module in the equipment-receiving space.

Abstract: A booth of a powder coating system is designed for quick color changes. The booth includes a bottom wall supported above a floor. An inner space of the booth is defined above the bottom wall and an equipment-receiving space is defined beneath the bottom wall. The bottom wall has an opening providing communication between the inner space and the equipment-receiving space. The booth is adapted to receive a powder-recovery module beneath the bottom wall in the equipment-receiving space.

Abstract: An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

Abstract: An apparatus and method for delivering repetitive, precision, low volume liquid dispensing from a dispensing orifice of a non-contact liquid dispensing apparatus. An elongated communication passageway of the dispensing apparatus is defined by interior walls having one end in fluid communication with a system fluid reservoir and an opposite end terminating at the dispensing orifice. A system fluid is placed in the communication passageway extending substantially continuously from the system fluid reservoir to the dispensing orifice. A relatively small volume of gaseous fluid is aspirated through the dispensing orifice, and into the communication passageway in a manner such that the gaseous fluid extends substantially continuously across the transverse cross-sectional dimension of the communication passageway.

Abstract: A universal calibration apparatus and method to estimate the dispense output from a low volume, non-contact, liquid dispensing systems that may be applied for every hardware configuration (e.g., tube length, orifice diameter, tip design, etc), reagent solution property and environmental condition. This same calibration technique is applied to calibrate or tune these non-contact liquid dispensing systems to dispense desired volumes (in the range of about 0.050 &mgr;L to 50 &mgr;L), irrespective of the hardware configuration or the solution properties. That is, the calibration technique is not dependent on any variables, but the result (the actual dispense volume) is dependant on the variable mentioned. By actuating selected pulse widths, and measuring the resulting volume, a Calibration Profile can be generated correlating the liquid volume dispensed from the orifice to the respective pulse width of the dispensing valve thereof through calibration points..

Abstract: An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

Abstract: An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.

Abstract: A funeral procession warning apparatus includes a base unit having top and bottom sides and defining an interior cavity. A hollow pole extends upwardly from the top side and includes a light at its free end. A rechargeable battery is positioned within the cavity and is electrically connected to the light for delivering current thereto when a switch is properly positioned. A flag having indicia indicative of a funeral procession is coupled to the pole. A male connector is electrically connected to the battery and extends through the bottom side of the base unit. The apparatus includes a recharging unit having a socket for selectably mating with the male connector for recharging the battery when the recharging unit is connected to a power source. A receiver may be positioned in the cavity for allowing current delivery to the light source upon receiving a signal from a remote transmitter.

Abstract: A high pressure be seating assembly adapted for liquid sealing against a rigid surface having a connecting conduit. The tube sealing assembly includes a rigid, elongated, tube member having a spherical sector-shaped distal end portion with a radius substantially larger than the radius of the tube member. The tube member further includes a central conduit terminating at an apex of the spherical sector-shaped distal end portion to define an annular rim portion such that a fluid-tight seal can be formed between the central conduit of the tube member and the connecting conduit of the surface. This seal is formed at a contact interface between the rim portion and the surface when a relative axial force is applied therebetween.

Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.

Abstract: A removable secondary liquid dispensing module for use with an existing, automated liquid handling system that defines a work area having a plurality of discrete work stations. Each of the work stations of the automated liquid handling system includes a lab ware site and alignment structure enabling the removable securing standardized microtiter-plates at respective lab ware site. A plate positioning mechanism is configured to move and position the microtiter plates to and from the lab ware sites of the respective work stations thereof and into engagement with the respective carrier alignment structure thereof. Further, a primary liquid dispensing device is configured for selective contact-type dispensing of discrete quantities of fluid, in the range of about one (1) microliter to about ten (10) milliliters, into the test sites of the microtiter plates secured in the respective alignment structure of the respective work station.

Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.

Abstract: A funeral procession warning apparatus includes a base unit having top and bottom sides and defining an interior cavity. A hollow pole extends upwardly from the top side and includes a light at its free end. A rechargeable battery is positioned within the cavity and is electrically connected to the light for delivering current thereto when a switch is properly positioned. A flag having indicia indicative of a funeral procession is coupled to the pole. A male connector is electrically connected to the battery and extends through the bottom side of the base unit. The apparatus includes a recharging unit having a socket for selectably mating with the male connector for recharging the battery when the recharging unit is connected to a power source. A receiver may be positioned in the cavity for allowing current delivery to the light source upon receiving a signal from a remote transmitter.