Parker-hannifin Corporation

Parker-hannifan Plc

Michael A Benjamin

Adel B Mansour

David Richard Barnhart

Marie Ann Mcmasters

Alfred Mancini

Rex Jay Harvey

Erlendur Steinthorsson

Peter V Buca

Andrew M Odar

Barry Walford Savel

Thomas A Burke

Erlendur Steinhorsson

An enclosure () comprising a wall structure () defining a container space () and electronic devices () contained within this space (). The wall structure () includes an entrance for providing an operative fluid (e.g., a heat-transfer fluid) into the container space () and an exit for draining the operative fluid therefrom. The wall structure () includes an inducement chamber that, when a motive fluid is introduced through an inlet (), produces a differential pressure that induces the operative fluid in the container space () to flow through the exit to an outlet (). The wall structure () can be at least partially constructed from a stack () of plates having openings and grooves forming the inlet, the outlet, the entrance, the exit, the fluid circuits, and the chambers.

Enclosure with fluid inducement chamber

A fuel injector for a gas turbine engine includes a bulkhead having adjacent angled wall segments, each of which includes an injector opening. Fuel injectors are supported by the bulkhead on adjacent wall segments. Each fuel injector includes an inlet fitting including ports for receiving fuel, a feed stem extending through the opening, and a manifold supported at the downstream end of the feed stem and including a plurality of manifold segments. Each manifold segment includes a plurality of nozzles arranged in a linear, planar array; with each nozzle including a fuel distribution assembly and an air swirler assembly. The manifold segments are supported at angles to one another, such that that the sprays from one array of nozzles in one segment are provided in a different direction than the sprays from another array of nozzles in an adjacent manifold segment.

Macrolaminate direct injection nozzle

A fuel nozzle for dispensing an atomized fluid spray into the combustion chamber of a gas turbine engine. The nozzle includes a body assembly with an inner fuel passage and an annular outer atomizing air passage. An array of turning vanes is disposed within the outer fuel passage. Each of the vanes is configured generally in the shape of an airfoil in having a pressure side and an opposing suction side, the suction side of each vane being spaced-apart from a juxtaposing pressure side of an adjacent vane to define a corresponding one of a plurality of aligned air flow channels therebetween. Fuel is directed through the fuel flow channels to be issued from the nozzle as a generally helical flow having a substantial uniform velocity profile.

Fuel nozzle for turbine combustion engines having aerodynamic turning vanes

An injector includes a plurality of flat, circular plates which provide fuel delivery and cooling of the injector. Fuel delivery passages in the plates have swirl chambers and spray orifices which are formed by chemical etching. A pair of fuel delivery plates define a fuel cavity therebetween, and include a plurality of radially-outwardly extending spokes, with the spokes from one fuel plate in adjacent, surface-to-surface relation with opposing spokes from the adjacent fuel plate. A fuel passage is defined between each of the opposing spokes, leading from the fuel cavity to a fuel outlet opening at the distal end of each spoke. A fuel tube delivers fuel to the fuel cavity between the plates, from where the fuel is then directed through the outlet openings. Downstream plates shape the fuel into appropriate sprays for ignition. An upstream cooling plate assembly directs air against the upstream fuel plate, and radially outwardly along the spokes of the upstream plate. The air is delivered through an air tube, concentric with the fuel delivery tube.

Injector with active cooling

A fuel injector for a gas turbine engine of an aircraft has an inlet fitting, a fuel nozzle, and a housing stem with an internal conduit fluidly interconnecting the nozzle and fitting. The fuel nozzle includes a fuel swirler, which includes a plenum for receiving fuel from the conduit. A plurality of fuel passages direct fuel from the plenum to discharge orifices. The downstream ends of the passages are angled such that a swirl component is imparted to fuel exiting the discharge orifices. The swirling fuel is then applied to a prefilmer, which outwardly surrounds the fuel swirler. The passages in the fuel swirler are arranged such that the discharge orifices surround the entire nozzle for the even distribution of fuel. The plenum and passages are dimensioned and configured to receive and distribute the fuel for uniform spray patternization and low pressure drop, which provides improved combustion and flame stability.

Pure airblast nozzle

A fuel nozzle for dispensing an atomized fluid spray into the combustion chamber of a gas turbine engine. The nozzle includes a body assembly with an inner fuel passage and an annular outer atomizing air passage. The inner fuel passage extends axially along a longitudinal axis to a first terminal end defining a first discharge orifice of the nozzle. The outer air passage extends coaxially with the inner fuel passage along the longitudinal axis to a second terminal end disposed concentrically with the first terminal end and defining a second discharge orifice oriented such that the discharge therefrom impinges on the fuel discharge from the first discharge orifice. An array of turning vanes is disposed within the outer air passage in a circular locus about the longitudinal axis. Each of the vanes is configured generally in the shape of an airfoil and has a pressure side and an opposing suction side. The vanes extend axially from a leading edge surface to a tapering trailing edge surface along a corresponding array of chordal axes, each of axes is disposed at a given turning angle to the longitudinal axis. The suction side of each vane is spaced-apart from a juxtaposing pressure side of an adjacent vane to define a corresponding one of a plurality of aligned air flow channels therebetween. Atomizing air is directed through the air flow channels to be issued from the second discharge orifice as a generally helical flow having a substantial uniform velocity profile.

A hybrid atomizing fuel nozzle includes a stem with primary and secondary fuel circuits. A nozzle assembly fixed at the downstream end of the stem includes primary and secondary nozzle portions. A shroud and swirler assembly surrounds the nozzle assembly, and includes an annular body with a prefilmer surface. A radial inflow swirler in the annular body directs a first swirling air flow radially inward toward the secondary nozzle portion. An outer air swirler disposed in surrounding relation to the annular body provides a converging second swirling air flow downstream of the prefilmer surface. Discrete fuel passages direct fuel streams outward and downstream toward and against the prefilmer surface. The fuel passes through the first air flow and is evenly distributed across the prefilmer surface in a thin continuous sheet. The first and second air flows then cause the sheet to form a conical spray of atomized fuel.

Hybrid atomizing fuel nozzle

Fuel atomization method for turbine combustion engines having aerodynamic turning vanes

A combustion system includes a combustion chamber and a fuel injection apparatus, where a radial inflow swirler stage in the injector housing includes a plurality of radial inflow swirlers spaced longitudinally from each other to direct air radially inward in a swirling motion to cause fuel streams to swirl and thoroughly mix with air before passing into the combustion chamber. A plurality of liquid fuel nozzles are supported in the housing in an annular arrangement to dispense liquid fuel in a plurality of sprays in the downstream direction. A plurality of gaseous fuel nozzles are also provided in the housing supported in an annular arrangement intermediate the liquid fuel nozzles. The plurality of gaseous fuel nozzles include a series of nozzles arranged in radial spokes between each of the liquid fuel nozzles, with the size of the openings in the gaseous fuel nozzles increasing in the radially outer direction from the longitudinal axis of the housing. An outer annular flow passage is provided around the nozzles to create a cylindrical sheet of air around all the fuel streams, while an annular flow passage is provided around each of the liquid fuel nozzles to provide an annular flow of air around each of the liquid fuel sprays. A central air passage provides air centrally of the arrangement of nozzles. The air vaporizes the liquid fuel as the fuel passes downstream through the housing.

Growing community of inventors

Shaker Heights, OH, United States of America

Michael A Benjamin