259 results about "Nozzle throat" patented technology

Sustor2 provides deep cooling of a gas flow, practically total condensation of a vapor, and fast and effective removal of the condensed liquid with a significantly reduced pressure losses compared with the prior art. Sustor2 performs the said operations by developing a strong swirling flow starting from its entrance, followed by spiral flow convergence in the inlet disc-like part, and then in a converging-diverging nozzle, by centrifugal removal of droplets, and removal of the liquid film through slits, then by spiral flow divergence and leaving the vortex chamber through tangential outlet.A gas enters from a pipeline (see the arrow in the A-A cross-section shown in FIG. 7) connected to Sustor2 by a flange and the inlet transition pipe ITP in FIG. 7, spirally converged in the disc-like part, marked by A-A in FIG. 6, enters the converging-diverging nozzle (FIG. 6). The flow is high-speed and swirling even at the near-entrance region of the vortex chamber. This swirl results in the centrifugal force that presses the through-flow to the sidewall. The flow accelerates near the nozzle throat up to a supersonic velocity with subsonic axial and supersonic swirl velocity components. This acceleration results in the gas temperature drop down to 200K and even less values. The reduced temperature causes rapid condensation of vapor into droplets. The centrifugal force pushes the droplets to the sidewall where they are removed through slits. Next the dried gas spirally diverges and leaves the vortex chamber through the tangential outlet. This results in the pressure recovery and transformation of the swirl kinetic energy into the longitudinal kinetic energy of the gas. Both the effects decrease pressure losses which is the Sustor2 advantage compared with the prior art.

A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio.

A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.

In a coffee / espresso machine with a milk froth generating device (1) for preparing cappuccino, an outflow distributor (13) which includes two outflow tubes (16, 17) being liquid-conductively connected to an espresso inflow (14). The outflow tubes (16, 17) are bent downwardly from the ends of a distributor tube (15) of the outflow distributor (13). The milk froth generating device (1) which comprises a Venturi tube (2), a mixing and frothing chamber (4) and following in flow direction, a nozzle arrangement (22) according to the Laval principle having a nozzle throat is also liquid-conductively connected to the outflow distributor (13). The nozzle arrangement (22) opens directly into a central connecting section (15') of the distributor tube (15).

The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine so as to define a cold stream flow channel, the nacelle having an upstream end surrounding the fan of the engine and a stationary downstream end forming a gas exhaust nozzle, the nozzle having a throat section that corresponds to its smallest cross-section. The turbomachine further comprises means for taking in air from the cold stream flow channel upstream from the nozzle throat section, and means for injecting the taken-in air downstream from the nozzle throat section so as to open the throat section artificially.

A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.