Patent application number | Description | Published |
20080259712 | FAST READ PORT FOR REGISTER FILE - Separate read and write ports in a memory system allow simultaneous access to a memory cell array by read and write operations. A single cycle operation of a central processing unit coupled to a memory array depends on a memory access capability providing simultaneous reading and writing to different locations. A pair of pull-down transistor stacks connected to memory cell latch loops allows a single selected pull-down stack of the pair to toggle a memory cell latch loop to a desired data content without any requirement for a precharge scheme. A single pull-down stack of transistors connected to a memory cell latch loop provides a read port with low input loading. A sense amplifier provides a mid-supply-level precharging capability provided by a feedback device within a front-end inversion stage. When not in a feedback mode, the front-end inversion stage cascaded with a second inversion stage provides a rapid read response. | 10-23-2008 |
20090319760 | SINGLE-CYCLE LOW POWER CPU ARCHITECTURE - An n architecture for implementing an instruction pipeline within a CPU comprises an arithmetic logic unit (ALU), an address arithmetic unit (AAU), a program counter (PC), a read-only memory (ROM) coupled to the program counter, to an instruction register, and to an instruction decoder coupled to the arithmetic logic unit. A random access memory (RAM) is coupled to the instruction decoder, to the arithmetic logic unit, and to a RAM address register. | 12-24-2009 |
20110219160 | FAST TWO WIRE INTERFACE AND PROTOCOL FOR TRANSFERRING DATA - An apparatus and method for exchanging data between devices. An interface between at least two devices features a serial clock line coupled to each device and a bidirectional serial data line coupled to each device. A delay relative to the clock signal is added to an edge of an output enable signal to prevent a collision between devices when control of the data line is switched. Multiple masters and slaves may be connected to the interface. | 09-08-2011 |
Patent application number | Description | Published |
20090217643 | Gas discharge device for a vehicle engine - The present invention provides gas discharge technique useful on vehicle engines. The technique comprises an s-shaped duct having an ejector formed therein to mix hot exhaust gas with a relatively cooler airflow entrained by the ejector. The s-shaped duct may be comprised of a number of segments that when integrated form the s-shape and ejector. A variety of cross sections including circular and rectangular are provided for the s-shaped duct. The segments may be composed of smaller subsections and may further have cooling slots. A nacelle is provided to at least partially enclose the s-shaped conduit and may have an inlet that is in fluid communication with the ejector of the s-shaped conduit. | 09-03-2009 |
20140260282 | GAS TURBINE ENGINE COMBUSTOR LINER - A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. | 09-18-2014 |
20140263712 | EXHAUST NOZZLE APPARATUS AND METHOD FOR MULTI STREAM AIRCRAFT ENGINE - A multi stream aircraft fixed geometry nozzle includes an inner nozzle, an outer nozzle, and a supersonic ejector. The outer nozzle is configured to channel a third stream from an aft end of a third stream duct surrounding a bypass duct of a multi stream aircraft engine to the supersonic ejector to merge the third stream with the primary stream. The fixed geometry nozzle is configured to operate between an SFC mode and a thrust mode such that, when the inner nozzle accelerates the primary stream supersonically to the supersonic ejector, at which the primary stream is merged with the third stream, in the SFC mode the total pressure of the primary stream is substantially the same as the total pressure of the third stream, and in the thrust mode the total pressure of the primary stream is substantially greater than the total pressure of the third stream. | 09-18-2014 |
20150013340 | GAS TURBINE ENGINE COMBUSTOR LINER - A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. | 01-15-2015 |