848results about "Power plant exhaust arrangements" patented technology

A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid capture duct 62. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes 36 defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction 18 that would otherwise impede thorough mixing of two fluid streams.

A gas turbine engine exhaust nozzle includes a row of laterally sinuous chevrons extending from an aft end of an exhaust duct. The chevrons have radially outer and inner surfaces bound by a laterally sinuous trailing edge extending between a base of the chevrons adjoining the duct and an axially opposite apex of the chevrons. Each chevron has a compound arcuate contour both axially and laterally, and the sinuous trailing edge of the chevrons further compounds the arcuate configuration of each chevron.

A gas turbine engine exhaust nozzle includes a nacelle having an inlet and main outlet at opposite ends, and a main duct extending therebetween. A secondary bypass duct extends radially through the nacelle upstream of the main outlet and includes an unobstructed secondary inlet joined to the main duct, and a secondary outlet surrounding the main outlet for collectively discharging exhaust flow in confluent streams.

Compact exhaust mixer assemblies comprising a compact mixer and a trimmable open centerbody are provided. The trimmable center body allows for adjustments of the open centerbody after manufacturing and during production testing. The trimmable open centerbody may be used to compensate for production tolerances making it possible to obtain the desired core effective area for proper engine operation. The compact mixer may be either lobed or serrated. The compact exhaust mixer assemblies have a length of about half that of conventional exhaust mixer assemblies.

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area.

The invention is a propulsion system for a V / STOL aircraft. In detail, the invention includes a turbo-fan engine having a fan section with a variable pitch fan, a compressor section, a combustion section, a turbine section, said turbine section having a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. The engine further having a selectable operating point wherein a portion of the power generatable by the low-pressure turbine at a selected operating power setting is extracted to drive the fan section. A turbine outlet duct is included for directing the turbine section exhaust gases. A first angular shaped nozzle section is co-incident with the turbine outlet duct for directing exhaust from the fan section. A second nozzle section mounted to the first angular shaped nozzle section between the fan section and the compressor section. A system is included to shift said selectable operating point of said engine to a second operating point at the selected power setting increasing the power extracted by the low-pressure turbine portion of the turbine section; such that power extracted by the low-pressure turbine portion and applied to the fan section can be increased without changing the selected power setting and the pitch of the blades of the variable pitch fan section can be increased to absorb the increased power.

A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such that air discharged from the noise suppression system generates a streamwise vortex downstream from each respective chevron.

An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for controlling exhaust flow discharged therethrough. An arcuate unison bar surrounds the duct adjacent to the frame and includes circumferentially spaced apart cam followers engaging corresponding cams affixed to the flaps. An actuator is joined to the bar for selective rotation thereof between opposite first and second directions to pivot open and closed the flaps atop the apertures.

A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the inner barrel presenting a surface having a first series of undulations made up of negative undulations alternating with positive undulations, the centerbody presenting a second series of undulations made up of negative undulations alternating with positive undulations, the negative and positive undulations of the series of undulations being of radial height that varies angularly and being disposed in such a manner that the negative undulations of the first series are disposed facing negative undulations of the second series, and vice versa, so as to generate turbulence and radial shear between the primary and secondary flows while conserving a constant flow section around the entire circumference of the nozzle.

A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X′) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner and outer lobes (22 and 21) distributed circumferentially around the longitudinal axis (X-X′) of the mixer. The lobe structure (20) is made of a ceramic matrix composite material and further comprises a stiffener ring (30) that forms a connection between at least some of the lobes of said structure. Thus, the major portion of the mixer, i.e. the lobe structure, is made of a ceramic matrix composite material, thereby significantly reducing the weight of the mixer, and consequently reducing the weight of the nozzle.

This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds the inner duct over the apertures to form a bypass channel terminating at the auxiliary outlet. A row of flaps are hinged at upstream ends to selectively cover and uncover the apertures for selectively bypassing a portion of exhaust flow from the inner duct through the outer duct in confluent streams from both main and auxiliary outlets. When the flaps cover the apertures, the intakes ventilate the bypass channel and discharge flow through the auxiliary outlet.

Embodiments of the invention relate to a supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine. By shaping the nacelle, embodiments of the invention may function to reduce sonic boom strength, cowl drag, and / or airframe interference drag. Embodiments of the invention may also function to improve total pressure recovery and / or total thrust of the primary flow path through the engine.

An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtained from a pressurized storage container or air obtained from a synthetic jet actuator into the area proximate to one or more engine nozzle portions, thereby disrupting the noise-generating gas streams generated by the engine exhaust and the travel of the airplane through the air. The apparatus is particularly useful for reducing engine noise during the takeoff period of aircraft flight.