Abstract: Assist circuits for SRAM memory tests allow voltage scaling in low-power SRAMs. Word line level reduction (WLR) and negative bit line (NBL) boost assist techniques improve read stability and write margin of SRAM core-cells, respectively, when the memory operates at a lowered supply voltage. Assist circuits are activated at particular points in the memory cell circuit. The assist circuits are selectively activated for modifying the voltage along particular circuit elements to identify the potential defects that might be otherwise masked until substantially large. A March test invokes elements for activating the assist circuits to identify defects and indicate functional fault models (FFMs) associated with the defects.

Abstract: A device for controlling a power supply for a functional block in an integrated circuit, the device comprising: a signal generator configured to provide a clock signal to the functional block, an antenna comprising a transistor, and being located proximate to the functional block, the antenna being configured to receive the clock signal from the signal generator, and wherein the transistor of the antenna receives electrical power from the same power source that delivers power to the functional block, means to measure the clock signal output from the antenna, and output a control signal, and feedback means to control the voltage of the power supply to the functional block on the basis of the control signal.

Abstract: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

Abstract: Assist circuits for SRAM memory tests allow voltage scaling in low-power SRAMs. Word line level reduction (WLR) and negative bit line (NBL) boost assist techniques improve read stability and write margin of SRAM core-cells, respectively, when the memory operates at a lowered supply voltage. Assist circuits are activated at particular points in the memory cell circuit. The assist circuits are selectively activated for modifying the voltage along particular circuit elements to identify the potential defects that might be otherwise masked until substantially large. A March test invokes elements for activating the assist circuits to identify defects and indicate functional fault models (FFMs) associated with the defects.

Abstract: A circuit arrangement may include: a memory, composed of a memory cell array, including a plurality of memory cells, and a peripheral circuitry; a voltage source configured to provide at least one supply voltage; a test circuit integrated with the memory cell array and the voltage source, wherein the test circuit receives the supply voltage; the test circuit including: at least one test memory cell; at least one failure detection circuit configured to detect a data retention failure in the at least one test memory cell.

Abstract: A power supply noise measurement device for inclusion with an integrated circuit, the integrated circuit having a functional block, the noise measurement device comprising: a signal generator configured to provide a clock signal to the functional block, an antenna comprising a transistor, and being located proximate to the functional block, the antenna being configured to receive the clock signal from the signal generator, and a jitter estimator configured to provide a measure of the relative jitter between a signal output from the antenna and a reference clock signal, wherein the transistor of the antenna receives electrical power from the same power source that delivers power to the functional block.

Abstract: A device for controlling a power supply for a functional block in an integrated circuit, the device comprising: a signal generator configured to provide a clock signal to the functional block, an antenna comprising a transistor, and being located proximate to the functional block, the antenna being configured to receive the clock signal from the signal generator, and wherein the transistor of the antenna receives electrical power from the same power source that delivers power to the functional block, means to measure the clock signal output from the antenna, and output a control signal, and feedback means to control the voltage of the power supply to the functional block on the basis of the control signal.

Abstract: A circuit arrangement may include: a memory, composed of a memory cell array, including a plurality of memory cells, and a peripheral circuitry; a voltage source configured to provide at least one supply voltage; a test circuit integrated with the memory cell array and the voltage source, wherein the test circuit receives the supply voltage; the test circuit including: at least one test memory cell; at least one failure detection circuit configured to detect a data retention failure in the at least one test memory cell.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane PO situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: The present invention relates to a bladed stator for a turbo-engine, in particular a bladed stator sector comprising an inner platform (3) and an outer platform (4), at least one blade (2) fixed between said platforms (3, 4), at least one of said platforms (3, 4) comprising at least one flange (5, 6) having a first end (5a, 6a) fixed to the platform (3, 4) and a second, free end (5b, 6b), said flange (5, 6) comprising at least one non-opening free flexibility-increasing cutout (10).

Abstract: In a moving turbine wheel, blade inserts are used with at least two blades interconnected by common outer and inner platforms and sharing a common root. The blade inserts have hollow roots in which respective recesses are formed, and the insert roots belonging to the same wheel and/or two different wheels are voluntarily given different configurations in order to adjust the resonant frequencies of the inserts to values that are significantly different, thereby ensuring that the inserts in the same wheel and/or between two different wheels are out of tune.

Abstract: Distributor sectors (25) on which fixed vanes are placed adjacent to a casing (31) by means of sealing sectors (32) alternating with them in the axial direction and provided with force resistant faces (37; 39) through which forces exerted on the distributor sectors are transmitted to the casing. The inner surface of the casing (31) is smoother and is not fitted with any hooks; consequently, this casing (31) is less complicated to make and is less mechanically stressed to retain the distributor sectors, and the distributor sectors may be installed by a purely axial movement.

Abstract: For the or each moving wheel of the turbine, blade inserts are used each comprising at least two blades interconnected by common outer and inner platforms and sharing a common root. Inserts are used having hollow roots in which respective recesses are formed, and the roots of inserts belonging to the same wheel and/or the roots of inserts belonging to two different wheels are voluntarily given different configurations in the inserts of the roots so as to adjust the resonant frequencies of said inserts to values that are significantly different, thereby ensuring that the inserts in the same wheel and/or between two different wheels are out of tune. The invention is applicable to turbines both for aviation and for industrial applications.

Abstract: A fabric laminate (10) comprises first and second stretch fabrics (11 and 12) having an intermediate adhesive securement layer (13) between them. The adhesive securement layer (13) is in the form of a regularly repeated pattern which comprises an array of aligned adhesive elements (14) arranged in successive generally horizontally and vertically extending rows. The array of adhesive elements (14) is capable of offering resistance to elongation as the laminate (10) is subjected to distortion, with the pattern having a differential elongation characterized as offering different magnitudes of resistance to elongation when the fabric laminate (10) is subjected to distortion in selected different directions.