Abstract: The invention relates to a micropump (10; 100) comprising at least a first plate (12), a second plate (20), an intermediate plate (18), a pump chamber (24), and inlet and outlet control members (28, 30). According to the invention, said inlet control member (28) is a non-return valve situated in the major portion of the thickness of said intermediate plate (18), being made of a moving member (40) and a membrane-forming portion (42) situated close to one of the plates (12, 20), connecting said moving member (40) to the remainder of said intermediate plate (18) and, by its resilience, enabling said valve (28) to move between a closed position and an open position, said moving member (40) having an orifice of limited volume passing therethrough.

Abstract: A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.

Abstract: A compressor protection and control subsystem for a rotary compressor provides temperature pressure, mis-wiring and vibrational protection for the scroll machine. The vibrational protection comprises a vibration sensor which is integrated on the circuit board of the protection and control subsystem. The vibration sensor, in conjunction with at least one timer, monitors the vibrations of the scroll machine and will shut down the machine when excess vibrations are sensed over a prespecified period of time. The temperature system monitors operating temperature conditions the pressure system monitors operating pressures and the mis-wiring system monitors the power supplied to the compressor. Once an undesirable characteristic is identified, the operation of the scroll machine is stopped. These protection systems are integrated into a single subsystem which identifies the reason of shutting off the scroll machine in order to simplify repairs needed.

Abstract: The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on a torque shaft that rotates to move a connecting link attached to the convergent flap of the nozzle. A pressure balancing hood is attached to the top surface on the forward end of the convergent flap to augment the lowering of the horsepower requirements. In another embodiment a tie rod/end cup arrangement and two piece torque shaft are utilized for ease of removal of the actuation system from the exhaust nozzle assembly.

Abstract: The invention is an airframe which includes a vehicle (12) having a solid propellant rocket engine (14) and a ramjet or scramjet engine (16); a thrust plug (18) extending from an end (20) of the vehicle which directs combustion gases (23 and 64) produced by the solid propellant rocket engine or ramjet/scramjet engine to produce forward thrust; a longitudinal passage (38) extending from the end of the vehicle to an opening (30) forward of the end which receives external air directed by forward movement of the vehicle and in which solid propellant (32) of the solid propellant rocket engine is located, and wherein during rocket operation solid propellant is combusted to produce the combustion gases in the longitudinal passage which are conveyed by the longitudinal passage into contact with the thrust plug and during ramjet/scramjet operation the longitudinal passage is open to flow of external air after operation of the solid propellant rocket engine is completed and which supports mixing and combustion of the a

Abstract: The invention refers to a hydrostatic pump or engine with infinitely variable debit or impulse of the rotative type, constituted by an external and fixed body (1) of cylindrical shape, and whose symmetry axis coincides with the axis (4) of the rotor (3); the named body is laterally fixed to two flat covers forming a case. A second body, or stator (2), with a cylindrical interior peripherical surface, and whose symmetry axis is in a coincident or parallel position with the rotor axis, is interposed at intervals between the rotor and the first body, being formed cameras (7) and (9), for the fluid circulation, and cameras (6) and (8), for the compensation and balance of forces acting in the interior and in the exterior of each stator side.

Abstract: The downhole pump has a barrel with a reciprocating plunger therein. The barrel has a first one-way valve, while the plunger has a second one-way valve. A barrel chamber is formed between the two one-way valves. The barrel chamber expands when the reciprocal movement between the plunger and the barrel is an upstroke movement and then contracts when the reciprocal movement is a downstroke movement. A bypass channel is provided between the barrel and the plunger so as to provide communication around the plunger and its one-way valve. The bypass channel is open when the reciprocal movement is near an end of the upstroke movement. When open, pressure across the plunger can equalize and gas inside the barrel chamber can vent around the plunger and/or pressure can equalize across the plunger one-way valve so as to prevent gas lock and minimize stress on the sucker rods.

Abstract: A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (76,78,80,92). The primary fuel and air mixing ducts (78,78) comprise first and second radial flow swirlers (60,62). The primary fuel injectors (64,66) inject fuel into the first and second swirlers (60,62). The primary fuel injectors (44,66) and the first and second swirlers (60,62) are arranged such the fuel to air ratio of the fuel and air flowing from the passages (61) of the first swirler (60) into the primary combustion zone (36) is different to the fuel to air ratio of the fuel and air flowing from the passages (65) of the second swirler (62) into the primary combustion zone (36).