Abstract: In a gas turbine engine having an annular combustor and an axial flow compressor discharging compressed air through a discharge annulus upstream of said combustor, the diffuser being supported on the engine independently of the combustor between the discharge annulus and a dome on the combustor and including inner and outer walls operative to direct first and second portions of compressor discharge to radially inner and outer air plenums at the combustor and a remaining third portion of compressor discharge flow to a combustor dome feed chamber ahead of the dome, an improvement in the form of radially oriented pins on the diffuser and guides on the combustor dome slidably received on the pins, the pins and guides cooperating in maintaining a predetermined positional relationship between the diffuser and the combustor during relative thermal growth of the latter whereby at normal operating temperature the diffuser outer wall seals against the combustor while a flow balancing slot is developed between the diffu

Abstract: A combustion chamber for gas turbines, especially for motor vehicles, which includes a first reaction chamber, an outlet opening of which terminates in a second coaxially disposed reaction chamber. Each reaction chamber is associated with a premixing chamber provided with an air inlet and a fuel injection nozzle. An insert surrounds the first reaction chamber and its premixing chamber and projects into a flame tube. The flame tube encompasses the second reaction chamber and an outer wall of the insert forms with an inner wall of the flame tube an annular premixing chamber for the second reaction chamber. Several fuel injection nozzles are arranged in a zone of the air inlet of the second reaction chamber.

Abstract: A fan drive system comprising a main drive shaft 13 which drives the fan through a frangible coupling 27 and an auxilliary drive shaft 30 which by-passes the coupling 27. The auxilliary shaft 30 is pre-twisted elastically in the opposite direction to the direction of rotation of the main shaft 13, and is held in the pre-twisted state by the coupling 27. When the coupling 27 disconnects the drive from the main shaft 13, for example when the fan becomes unbalanced and transverse loads exceed a predetermined magnitude, the auxilliary shaft 30 unwinds. Unwinding of the shaft 30 cushions the fan against suddenly applied loads when the coupling 27 breaks and also reduces the loads on the coupling 27 during normal balanced running.

Abstract: A compound propulsor for powering a vehicle, such as an aircraft. A compound propulsor includes a core gas turbine engine, a fan encased within a cowl, at least one propeller, and drive means for distributing a portion of the power produced by the core engine to the fan and another portion to the propeller. Preferably, the compound propulsor also includes variable geometry inlet guide vanes for varying the portions of power distributed to the fan and propeller.

Abstract: The airflow from the compressor of a gas turbine engine into the combustion chamber or chambers principally comprises combustion air which enters the upstream end of the combustion chamber and dilution air which enters the combustion chamber at some point downstream of the combustion chamber inlet, the combustion air being made up of primary and secondary air entering the combustion chamber primary and secondary zones.In order to cope with the control of emissions from the combustion chambers, it is desirable to control the combustion air fuel ratio over the engine operating range by controlling air mass flow to the combustion and dilution zones of the combustion chamber. The invention proposes that this control can be achieved by providing a variable rate diffuser upstream of the primary, secondary and dilution air inlets, the variable rate diffuser comprising vortex generator having an associated variable air bleed.

Abstract: A rotor stage assembly 20 of the type adapted for use in an axial flow gas turbine engine is disclosed. The assembly includes a rotor disk 36 having blade attachment slots 42 configured to receive a plurality of rotor blades 40. Each rotor blade is insertable into the disk in a generally axial direction. Each rotor blade is retained against fore and aft movement by a lock pin 52. The disk is adapted by a groove 44 and the blade is adapted by a groove 48 to receive the lock pin. During assembly the lock pin is slidable in the grooves 44,48 to bring the lock pin into engagement with the corresponding groove in a rotor blade in a corresponding groove in the disk.

Abstract: A nozzle/valve device for a ducted rocket motor is provided. The nozzle/valve device employs a design in which a nozzle throat blockage element can be moved by translational motion within the nozzle throat section of the device. The blockage element is designed so that in the closed position the nozzle throat has a minimum cross-sectional flow area and therefore the nozzle throat is never fully closed. The seals employed in the nozzle/valve device are isolated from contact with reaction products of the gas generator and effective use of minimum amounts of erosion resistant materials is achieved.

Abstract: A nozzle/valve device for a ducted rocket motor is provided. The nozzle/valve device employs a design in which a nozzle throat blockage element can be moved by rotational motion into and out of the nozzle throat section of the device. The blockage element is designed so that in the closed position the nozzle throat has a minimum cross-sectional flow area and therefore the nozzle throat is never fully closed. The seals employed in the nozzle/valve device are isolated from contact with reaction products of the gas generator and effective use of minimum amounts of erosion resistant materials is achieved.

Abstract: A mounting device for mounting the exhaust casing of a turbojet engine on a rigid support structure connected with an aircraft, there being at least two flows, i.e., a primary flow in the exhaust casing and a secondary flow in a shroud which surrounds the casing and which is fastened to the support structure by a rigid ring. The device consists of a plurality of arms each having means to control its orientation.

Abstract: A thermal shield structure with ceramic blocks for protecting high-temperature-exposed wall surface in which wedge-shaped supporting members and wedge-shaped members to be supported, respectively provided on the wall surface and ceramics blocks as a plurality of pairs of wedge-groove couplings, are engaged with each other to cover the wall surface with the ceramic blocks. In accordance with the invention, a gap small enough to prevent mutual disengagement of each pair of the wedge-shaped supporting member and the wedge-shaped supported member is provided therebetween to permit movement of the ceramic blocks towards the wall surface. A passage for an air supply into each wedge-shaped supporting member is provided so that each wedge-shaped supported member is urged by the pressure of supplied air to be retained in the wedge-shaped supporting member, whereby the ceramic blocks are held on the wall surface.

Abstract: In a dredge pump having a pump housing and an impeller in the housing, an impeller shaft projects through and beyond the housing in both directions. Two drive motors, one coupled rigidly to one end of the shaft and the other, to the other end, to drive the shaft, hence the impeller, are mounted on supports. The supports are mounted on pads made up of a pair of plates with an elastomeric block sandwiched between and bonded to them, by being connected to one of the plates of each pad. The other of the pad plates is mounted or secured to a fixed structure located with respect to the pads and impeller so that axial forces from the impeller shaft tending to put one set of pads in tension are countered by axial forces tending to put the other set of pads in compression. The pads permit substantial torsional movement, and provide compensation for slight misalignment of the drive motors, permitting the rigid coupling of the drive motors to the two ends of the impeller shaft.

Abstract: A tubular cylinder block is mounted for rotation about its axis within a cylindrical bore of a pump housing. The pump housing has circumferentially spaced inlet and outlet ports opening radially to the bore. Right angle intersecting diametric passages extend through the cylinder block and are alignable with the inlet and outlet ports during rotation of the drive block, the diametric passages being square in cross-section, and piston members of corresponding square transverse cross-section are slidably positioned within respective diametric passages with the piston members bearing square slots within side faces thereof intermediate of their ends facing axially. A square drive block is carried commonly within the piston member slot whose axis of rotation is adjusted eccentrically relative to the axis of rotation of the cylinder block. Cylinder block internal peripheral grooves separated by lands control fluid passage via the piston formed cavities between the inlet and outlet ports.

Abstract: A pyrotechnic delay system for controlling the time of events from initian of an initial ignition impulse to ignition of a secondary output.

Abstract: A modular catalytic combustor for a gas turbine has a plurality of individual, non-metallic cylindrical catalyst beds, and a support structure for each of the individual catalyst beds. Each catalyst bed together with its support structure forms an individual catalyst module. Each support structure includes an outer cooled support cylinder, with the individual support cylinders of the various modules interconnected in spaced relationship with cooling air passageways between. There are means for supplying compressed air, such as from a gas turbine compressor, into the space surrounding the support cylinders. The outer cooled support cylinders are provided with apertures for entry of cooling and purge air from the surrounding space. Each of the catalyst beds has an integral, cylindrical, outer ceramic shell, and is positioned within a corresponding outer support cylinder. A sheet metal heat shield is interposed between and concentric with each of the outer support cylinders and the catalyst bed within.

Abstract: A fuel combustor consists of an elongated casing 16 with an air inlet conduit portion 27 at one end, and having an opposite exit end 18. The casing is formed with an intermediate combustion space 19. An elongated heat pipe 29 is mounted longitudinally in the casing and is offset from and extends alongside the combustion space 19. The heat pipe 29 is in heat-transmitting relationship with the air intake conduit 27 for heating incoming air. Guide conduit structure 25 is provided for conveying the heated air from the intake conduit into the combustion space. A fuel discharge nozzle 26 is provided to inject fuel into the combustion space 19. A fuel conduit 32 from a fuel supply source 37 has a portion 33 engaged in heat transfer relationship of the heat pipe for preheating the fuel. The downstream end of the heat pipe 29 is in heat transfer relationship with the casing and is located adjacent to the downstream end of the combustion space.

Abstract: An improved energy conversion device for converting the energy carried by a laser beam to kinetic energy of a working fluid transparent to the laser radiation incorporates a seed gas having a relatively low dissociation temperature. The beam is focused to a beam spot the maximum diameter of which depends on the total power of the beam.

Abstract: A constant thrust hybrid rocket motor having a valve assembly therein which utilizes a fixed diameter orifice in combination with a valve having a variable sized opening therein in order to provide a regulated flow of oxidizer to the combustion chamber of the rocket motor. By selecting the size of the fixed diameter orifice such that it is slightly less than required to yield oxidizer flow at highest density oxidizer conditions (lowest temperature) and selecting the size of the combination of the fixed orifice and the open position of the variable opening such that it is slightly greater than required at lowest density oxidizer conditions (highest temperature), the operation of the rocket motor can be reliably maintained over a wide temperature range and without experiencing wide pressure variations by regulating the size of the variable opening.

Abstract: An augmentor system for a gas turbine engine is drained of residual fuel after augmentor shutdown by means of a drain conduit connected to the augmentor fuel spray apparatus through a valve which opens upon augmentor shutdown. The outlet to the drain conduit is disposed within the flameholder. A pressure differential causes the residual fuel to flow from the spray apparatus into the drain conduit and thereupon into the flameholder, whereupon it is burned.

Abstract: The basic gas turbine engine hydromechanical fuel control is adaptable to different engine configurations such as turbofan, turboprop and turboshaft engines by incorporating in the main housing those elements having a commonality to all engine configurations and providing a removable block for each configuration having the necessary control elements and flow passages required for that particular configuration. That is to say, a block with the elements peculiar to a turbofan engine could be replaced by a mating block that includes those elements peculiar to a turboshaft engine in adapting the control for a turboshaft configuration. Similarly another block with those elements peculiar to a turboprop engine could replace any of the other blocks in adapting the control to a turboprop configuration. Obviously the basic control has the necessary flow passages terminating at the interface with the block and these flow passages mate with corresponding passages in the block.

Abstract: An air modulation apparatus, such as for use in modulating cooling air to the turbine section of a gas turbine engine. The apparatus includes valve means disposed around an annular conduit, such as a nozzle, in the engine cooling air circuit. The valve means, when in a closed position, blocks a portion of the conduit, and thus reduces the amount and increases the velocity of cooling air flowing through the nozzle. The apparatus also includes actuation means, which can operate in response to predetermined engine conditions, for enabling opening and closing of the valve means.