Abstract: A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second surface exposable to a hotter, lower static pressure gas flow flowing across the second surface. The component further includes a generally straight film coolant passageway having an inlet on the first surface and an outlet on the second surface. The second surface has a seamless groove which is open substantially entirely along its longitudinal dimension extending from the outlet along the lower static pressure gas flow for improved film cooling of the second surface.

Abstract: The amount of fuel supplied by a low pressure pump and a high pressure pump to combustion means is controlled by a control unit. If most of the fuel delivered by the pumps is required by the engine a clutch engages to provide a direct mechanical drive between the pumps so that they are driven at the same speed. However if the combustion equipment requires a reduced flow of fuel the clutch disengages and the excess fuel is diverted by a valve to a turbine. The turbine drives the low pressure pump at a higher speed than the speed of the high pressure pump. The energy of the diverted fuel is converted to mechanical energy to drive the turbine so that the temperature rise of the diverted fuel is reduced.

Abstract: In a method for regulating a gas-turbine assembly, essentially consisting of a compressor unit (1), of an HP-combustion chamber (4), of an HP-turbine (6), of an LP-combustion chamber (9), of an LP-turbine (12) and of a generator (14), the rating of the fuel quantity (FH) for the HP-combustion chamber (4) is carried out responsive to a corrected temperature signal which is formed by the value of the temperature (T13) at the outlet of the LP-turbine (12), reduced by the particular temperature rise (.DELTA.T) detectable there. This temperature signal (T13-.DELTA.T) is recorded in that the temperature rise (.DELTA.T) generated by the fuel quantity (FL) introduced into the LP-combustion chamber (9) is subtracted from the measured temperature at the outlet of the LP-turbine (12). The uncorrected temperature signal at the outlet of the LP-turbine (12) is used for rating the fuel quantity (FL) for the LP-combustion chamber (9).

Abstract: Turbojet engine compressor . . . Its rotor (43) includes a movable end portion (45), such as a monoblock vaned disk able to be removed and replaced by a block. High and low pressure shaft lines (54) are formed into several portions to enable these operations to take place without having to dismantle the entire engine.

Abstract: A fixed geometry combustor for a gas turbine comprising at least one combustion chamber, a dilution chamber disposed downstream of said combustion chamber and in communication with said combustion chamber, at least one primary inspirator for introducing a fuel/air mixture into said combustion chamber in communication with said combustion chamber, and means for introducing dilution air into the dilution chamber.

Abstract: A speedy fixing device for tubes and bars of various shapes and sizes, having two elongate upright parallel teeth plates and an engaging base. The teeth plates are fixed firmly on an object which is to be affixed to the tube or bar, and have a plurality of longitudinal teeth in two vertical parallel slots of the engaging base. The engaging base has an inverted V-shaped bottom surface to contact an upper surface of a tube or a bar. The engaging base slides inward gradually to compress tightly the tube or the bar placed under the base and between the two plates. An elastic cushion is used to inhibit slipping.

Abstract: A combined cycle power generation system incorporates a carbonizer and a pressurized fluidized bed reactor for the generation of fuel gas and flue gases, respectively. A combustor is provided for the combustion of the fuel gas in the presence of the flue gases to produce hot gases. The hot gases are passed through a gas turbine where the gases expand and cool while performing work in the generation of electrical power. The exhaust gases from the gas turbine are passed though a heat recovery unit for the production of steam. The exhaust gases are then combined with air and passed to the pressurized fluidized bed reactor to provide excess secondary gas to aid in driving the gas turbine.

Abstract: A sectorized tubular structure able to resist implosion pressures, especially at the links between annular sectors. The tubular structure includes annular sectors interconnected by flat linking elements, each including at its ends at least one projection whose end enables the annular sectors to be supported. Thus, each linking element ensures the transmission of forces from one annular element to another. The unit is supported by fixing screws which are never in contact with the two annular sectors to be kept assembled.

Abstract: A method of establishing part-load operation is proposed for a turbine group. This gas turbine group consists essentially of a compressor unit (1), of an HP combustion chamber (4) downstream of the compressor unit (1), of an HP turbine (5) downstream of this HP combustion chamber (4), of an LP combustion chamber (8) operating by self-ignition and arranged downstream of the HP turbine (5), the hot gases (10) of which LP combustion chamber (8) being admitted to an LP turbine (11). The temperature at outlet from the HP turbine (5) remains essentially the same due to the reduction of the fuel quantity in the LP combustion chamber (8) to zero. Furthermore, the fuel quantity of the HP combustion chamber (4) remains approximately constant during the reduction of the fuel quantity in the LP combustion chamber (8) so that the temperature at inlet to the HP turbine (5) likewise remains constant.

Abstract: In a gas turbine combustion chamber, which consists of an inlet zone (1) with injection, an ignition delay zone (2), a reaction zone (3), a burn-out zone (4) and a transition zone (5) to the turbine, the reaction zone (3) has a cross-section which increases in such a way that the gas dynamics of the combustion process can take place at constant pressure or constant Mach number. By this means, the total pressure loss and the combustion chamber length necessary for the combustion are reduced and this is reflected in an improvement to the efficiency and the output.

Abstract: An extendible stud, consisting of two substantially identical C-studs each of which has opposed flanges of substantially different widths and inwardly turned lips at the flange outer edges, and each C-stud having an elongate central area in its web located at substantially the middle of said C-stud cross-section, which two C-studs are interconnected by the narrow flange of each being held within the channel formed by the wider flange and the associated lip and web of the other C-stud, and the elongate central areas of the webs of the two C-studs abutting one another.

Abstract: A gas turbine engine assembly including an improved apparatus for cooling the combustor to preclude thermal failure of the combustor and to preclude NO.sub.x formation. The system includes a liquid pump driven by the turbine shaft and supplying a cooling fluid to an annular chamber defined around the central combustion chamber of the combustor. The cooling fluid is thereby placed in heat exchange relation to the combustor to absorb heat from the combustion products within the combustion chamber and convert the fluid to a relatively higher energy condition, whereafter the fluid in its high energy condition is injected into the combustion chamber for mixture with the combustion products and delivery with the combustion products to the turbine inlet.

Abstract: A system and method of operating a system comprising an air separation plant and a gas turbine engine, the method comprising: providing a nitrogen-rich stream from the air separation plant; expanding and thereby cooling the nitrogen-rich stream; and delivering the expanded stream to the inlet of the compressor of the gas turbine engine to combine with the air stream entering the inlet of the compressor to form a total feed stream with reduced temperature and oxygen content so as to increase power output, increase efficiency and reduce NOx emissions of the gas turbine.

Abstract: A solar rocket for propelling and powering the electronics of a spacecraft includes a black body cavity of thermal storage material. Propulsion tubes and a connected nozzle axially extend through the black body cavity for burning propellant in order to provide thrust for the rocket. An insulation sleeve is removably located at the outer periphery of the cavity of thermal storage material. Energy conversion diodes surround the insulation sleeve. The thermal storage material, the insulation sleeve and the energy conversion diodes form a receiver. The receiver has a pair of spaced apart holes therethrough which lead into an interior space of the black body cavity in order to receive sunlight. A mirror assembly is located near each hole of the receiver for harnessing sunlight and providing radiant energy through the holes into the internal space of the black body cavity.

Abstract: An ophthalmologic apparatus has an illuminating system for illuminating the fundus of an eye to be examined with infrared light from substantially the front of the eye to be examined through a pupil area, the illuminating system having a light source, and an image pickup camera for receiving infrared reflected light from the fundus of the eye to be examined illuminated by the illuminating system on an image pickup surface conjugate with the front eye part of the eye to be examined. The turbid state of the light transmitting body portion of the eye to be examined can be ascertained by the image output from the image pickup camera.

Abstract: An exhaust housing having an eductor is provided. The eductor includes an outer annular casing circumscribing an inner annular casing to define a flow path therebetween for receiving the exhaust gas from the turbine section of an engine. A plurality of struts are integral with both casings. The struts have passages that extend from the exterior of the outer casing to the interior of the inner casing. A non-oil lubricated bearing is mounted within the interior of the inner casing for journaling a rotating shaft. During operation, the kinetic energy of the high velocity exhaust gas flowing between the casings and into a tailpipe induces cooling airflow from the exterior of the exhaust section, through the passages, across the bearing, and then out to the tailpipe.

Abstract: A method and apparatus is disclosed for synthesizing a fuel flow and a metering valve position used in a fuel control system of a turbomachine. Various construction details have been developed which provide a method to manipulate conventional turbine engine parameters to generate a synthesized fuel flow signal and metering valve position signal. In one embodiment, a synthesis means includes means to sense temperature, pressure and high pressure shaft speed, and means to manipulate the sensed signals to generate a synthesized fuel flow. A function generator responds to the synthesized fuel flow signal to generate a synthesized metering valve position signal.

Abstract: A guard rail for use with linearly-arranged reinforcement bars is provided, the guard rail including a housing for guarding reinforcement bars with the housing including structure for capturing the reinforcement bars therein, and structure on the capturing structure for guiding movement of the capturing structure between a non-secured position and a position wherein the housing is securely maintained in a guarding position over the reinforcement bars extending into the housing.

Abstract: Disclosed is a space launch system having a main engine which uses turbopumps to provide fuel and oxidizer to the main engine combustion chamber, and one or more booster engines that use high pressure fuel and/or oxidizer to pressurize the fuel and oxidizer tanks of the booster engine to obtain the pressure differential necessary to drive fuel and oxidizer from the fuel and oxidizer tanks of the booster engine to the combustion chamber of the booster engine.

Abstract: A system for re-igniting an aircraft gas turbine jet engine which has flamed out, using a plurality of electromagnetic wave powered plasma plume igniters in an intermittent mode to avoid compressor stall, and bootstrap the engine back up to normal operating conditions. The system uses electromagnetic wave powered plasma plume igniters to provide a source of thermal energy to ignite fuel, and the Fully Automatic Digital Engine Control (FADEC) which is a standard component on aircraft using aircraft gas turbine jet engines, to control the igniter operation preventing compressor stall during the re-ignition process.