Abstract: The present invention relates to the use of 1-deamino-8-D-arginine vasopressin (desmopressin), or a pharmaceutically acceptable salt thereof or a pharmaceutical composition containing any of them, in the preparation of a medication which minimizes metastatic dissemination during cancer surgery. Additionally, the invention also relates to pharmaceutical compositions comprising the same and to a method of treating a mammal in order to inhibit metastatic spread during surgical extirpation of a cancer mass.

Abstract: A driving shoe that is also comfortable for walking includes extensive cushioning in the shoe's heel regions and sides and a line of substantially constant curvature in the heel region extending to the rear of the shoe that allows for rapid pivoting between the accelerator and brake without having to lift the foot during driving and for a more natural gait during walking.

Abstract: A multilingual character conversion system for alphanumeric communications comprises an input unit, provisioning database, translation unit and output unit. The provisioning database contains informtion about the recipient messaging device and associations for a plurality of output character sets. The translation unit converts the incoming message to the form in which the message can be displayed on the recipient device.

Abstract: A gas turbine engine has a device for admitting a rotating fluid flow from an annular space of the casing to the inlet portion of a combustor to form a rotating fluid flow in the inlet portion of the combustor. The rotating fluid flow is formed in the annular space of the casing by supplying a fluid from a compressor to the blades of the turbine rotor disk.

Abstract: A method of operation of a gas turbine engine having a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a compressed fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.

Abstract: A gas turbine engine has a compressor, a combustor mounted downstream of the compressor, power turbine mounted downstream of the combustor, a counter-rotating compressor turbine having a temperature sensor at its outlet, a temperature control system for controlling the temperature at the outlet of the compressor turbine, and a fuel supply control system for supplying fuel to the combustor. The engine has a drive motor for causing the compressor to rotate and a motor control system having a motor power-up module with an input connected to the fuel supply control system, and a motor power output control module having a first input connected to the motor power-up module, a second input connected to the temperature sensor, and an output which is connected to the drive motor.

Abstract: A membrane for most commonly known nozzles has an elastically flexible, compressible resilient material placed between said inside surface of said plate and the opposite surface of the insert face; an annular outer portion that is initially flat; a projection at its center portion in bell-shaped dome form at its active surface which abuts against the inside surface of the central plate, said membrane forming a supplementary recess in its opposite surface and said insert front surface; an annular hermetic seal enclosing a small air chamber, said air chamber being deformable under pressure by the deformation of said membrane; said projecting dome at the center portion of the membrane being seated against the inside walls of the outlet orifice in the plate, describing an annular seal against said walls of said outlet channel.

Abstract: A gas turbine engine comprising a turbine mounted downstream of a compressor and a heat exchanger interconnected between the turbine and compressor and to a heated fluid source, which is connected to a fuel source, has a compressor flow duct having a plurality of flow duct areas, each providing a different compression ratio, and a plurality of outlet taps, each communicating with a respective area of the plurality of flow duct areas, that supplies combustion air to the gas turbine engine flow duct and also controls an outlet tap switch having a plurality of positions for selectively opening to the atmosphere one outlet tap and disconnecting the rest of the outlet taps from the atmosphere in each switch position.

Abstract: A method of operating a gas turbine engine having a compressor, a combustor between a waste fluid compressor and a power turbine, a counter-rotating compressor turbine installed downstream of the power turbine, and a heat exchanger having two circuits, in which a heated fluid is prepared by burning fuel with combustion air in a mixture with a waste fluid obtained downstream of a compressor turbine that which is cooled, compressed and heated before mixing with combustion air while keeping the temperature of the waste fluid downstream of the compressor turbine constant and removing a partial flow of the waste fluid into the atmosphere before heating the waste fluid prior to supplying the waste fluid for mixing with the combustion air.

Abstract: An apparatus and method for treating cancer and other illnesses in humans and animals are described. The treatment involves the low-power, pulsed application of radio frequency tuned with precision of at least one half part per million. Alternative embodiments are described for apparatus that generates the required RF signals and applies such signals therapeutically. Laboratory data is reported, showing the successful use of the disclosed apparatus and methods to suppress and eliminate cancerous tumors in mice.

Abstract: A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.

Abstract: A pipe system introduces an element launcher, which may be a pig, a foam-pig, an inflatable sphere, or a foam sphere, by mechanically displacing the element into the piping system.

Abstract: In a gas turbine engine bladed disk (36) positioned between rotor disk (14) and combustor (16). Bladed disk (36) is mounted for rotation together with rotor disk (14) and has blades (38) projecting toward inlet portion (20) of combustor (16). The bladed disk has openings (40) between blades (38) for establishing communication between source of compressed fluid (12) and turbine blades (15). Seals (46, 48) are provided between bladed disk (36) and casing (10).

Abstract: A gas turbine engine that has a turbine (1) mounted downstream of a combustor (5), a compressor turbine (2) mounted downstream of turbine (1) for producing power for driving a compressor (3), a heat exchanger (6) having a first circuit (61) connected to compressor turbine (2) and a second circuit (62) connected between compressor (2) and turbine (1) and a fluid discharge device (7) between compressor (3) and combustor (5). The gas turbine engine has a reactor (8) that has a heating device (9), inlets (F, W) connected to sources of fuel and water and an outlet connected to combustor (5). Heating device (9) is connected the outlet of compressor turbine (2). The engine also has a system for keeping the temperature at the outlet of compressor turbine (2) constant.

Abstract: In a gas turbine engine in which bearings (18, 30) of turbine (12) and compressor turbine (22) and exhaust duct (32) of compressor turbine (22) are attached to external annular wall (46) of heat exchanger (44). External annular wall (46) of heat exchanger (44) has heat insulation layer (48) on the inside surface. The engine has cooling device (94) for cooling external annular wall (46) of heat exchanger (44) on the side opposite to heat insulating layer (48).