Abstract: A combustor dome assembly having a venturi and an auxiliary wall concentric with the venturi to provide an annular passage for channeling or directing a high velocity air jet from a swirler to a combustion chamber associated with a downstream end of the venturi, thereby facilitating the atomization of a film of water flowing along an inner surface of the venturi and out of the downstream end. In an alternative embodiment, a deflector is used (instead of the auxiliary wall) to direct the air flow towards the downstream end. The downstream end of the venturi may have a curved edge to permit the film of water flowing along an inner surface of the venturi to turn substantially perpendicular to the air flowing past the downstream end of the venturi which further enhances atomization of water. The venturi may also comprise a flange which is positioned in operative relationship with the downstream end for increasing the turbulence at the downstream end.

Abstract: A manifold system for a marine or industrial gas turbine engine, the system being independent of the engine. An annular steam manifold and an annular gaseous fuel manifold are provided transversely surrounding and substantially coaxial with the engine. The manifolds have a plurality of outlets, each connected by a flexible metal hose to its respective one of the engines' fuel nozzles. Each manifold is supported by a pair of stanchions mounted on the engine's foundation assembly and a pair of brackets attached to each stanchion. The brackets provide limited vertical, lateral, axial and tilt adjustments of the manifolds.

Abstract: A fuel nozzle having increased thermal resistance which eliminates or minimizes vaporization of fuel passing through the fuel nozzle. The fuel nozzle has a tubular heat shield which surrounds a nozzle stem to form an air gap between the nozzle stem and the heat shield. A radiation layer is located on an inner wall of the heat shield and an outer wall of the nozzle stem. The radiation layer is a layer or plating using a metal having a low emissivity, such as gold (Au).

Abstract: A fuel delivery system for a dual annular combustor having a pilot stage manifold, a first main stage manifold, and a second main stage manifold which are connected to a three-position staging valve. The staging valve is controlled by a fuel/air digital electronic control (FADEC) which directs the staging valve to a closed (staged) position, to a partially open (partially staged) position, or to an open (unstaged) position in accordance with a staging-valve-fuel-to-air-ratio control schedule.

Abstract: A gas turbine engine combustor liner having conventional dilution holes disposed therethrough and multi-hole film cooling holes to provide a cooling film on the hot side of the liner is provided with generally rectangular film starting apertures disposed downstream, with respect to the predetermined cooling film flow direction, of the dilution holes in predetermined otherwise cooling film dry areas on the hot side of the combustor liner. In one embodiment the multi-hole film cooling holes and the rectangular film starting apertures are angled sharply in the downstream direction and angled in a circumferential direction which generally coincides with a predetermined swirl angle of the flow along the surface of the liner within the combustion zone.

Abstract: A fuel delivery system for a dual annular combustor having a pilot stage manifold, a first main stage manifold, and a second main stage manifold which are connected to a three-position staging valve. The staging valve is controlled by a fuel/air digital electronic control (FADEC) which directs the staging valve to a closed (staged) position, to a partially open (partially staged) position, or to an open (unstaged) position in accordance with a staging-valve-fuel-to-air-ratio control schedule.

Abstract: An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct having contained therein a fuel manifold in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, hollow vanes in at least the outer swirler having passages therethrough in fluid communication with the fuel manifold to inject fuel into the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the swirler vanes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.

Abstract: An annular combustor includes a plurality of circumferentially spaced, radially extending dilution poles disposed in an intermediate zone thereof between a forward combustion zone and an aft combustion zone. Adjacent ones of the dilution poles define therebetween a throat for receiving the combustion gases from the forward zone. The dilution poles include circumferentially facing dilution holes for injecting dilution air into the throats for mixing with the combustion gases being channeled therethrough. The dilution poles are effective for blocking the combustion gases at a plurality of circumferentially spaced apart locations and accelerating the combustion gases through the throats for reducing residence time in the throat. The dilution air is injected through the dilution holes for improved penetration into the combustion gases in the throats for mixing therewith to form lean combustion gases which undergo final combustion in the aft zone for reducing NO.sub.x emissions.

Abstract: A steam deflector assembly for a steam injected gas turbine engine having an annular manifold as a part of the combustion chamber casing. The manifold has a port through the exterior of the casing and a plurality of evenly spaced steam passage holes leading to the interior of the casing. The deflector assembly comprises an exterior bracket surrounding the port to which a steam line is attached and a deflector plate and retainer member therefor located within the manifold. The assembly protects the casing from low cycle fatigue cracking and distributes the steam flow about the manifold.

Abstract: A backing support or bumper mounted downstream of the disk shaped flange of the venturi in adjacently lying fuel cup assemblies and extends to a mid portion of each flange to prevent rotation of the flange and possible disengagement of the fuel nozzle in the event of a bird strike or impact by a foreign object on the dome of the combustor or on the flange itself. The invention provides for a single or double supporting bumper faces or a pair of supporting surfaces on the bumper.

Abstract: A combustor dome assembly is provided with a single continuous annular dome plate having at least one circumferential row of spaced openings therethrough, a swirl cup assembly attached to each of the dome plate openings, and inner and outer cowls connected to the radially inner and outer ends of the dome plate. A ferrule located immediately upstream of the swirl cup assembly acts as an interface between a fuel nozzle and the swirl cup assembly. An integral cowl plate/ferrule retainer is located immediately upstream of and connected to the swirl cup assembly, where the ferrule retainer portion retains the ferrule while allowing it to float radially therewithin and the cowl plate portion includes flanges which extend beyond the outer diameter of the swirl cup to provide blockage in addition to that provided by the inner and outer cowls.

Abstract: A gas turbine engine combustor is provided, having a an annular single wall sheet metal liner which is generally annular in shape and having disposed therethrough a multi-hole film cooling means which includes at least one pattern of small closely spaced film cooling holes angled sharply in the downstream direction and angled in a circumferential direction wherein the circumferential angle generally coincides with the swirl angle of the flow along the surface of the liner. Another embodiment provides a corrugated aircraft engine sheet metal combustor liner which forms an axially extending wavy wall to help resist buckling, particularly useful for outer liners in the combustion section of the engine and in the exhaust section of gas turbine engines incorporating afterburners.

Abstract: An apparatus and method for effecting the disassembly of an annular combustor for the maintenance of very large power generation gas generators such as those used in military aircraft engines, commercial aircraft engines, and smaller power generation turbines. The apparatus utilizes rollers which are attachable to a lower half outer casing. An inversion ring located radially inward from the lower half outer casing is supported by the rollers. By disconnecting a removable upper half outer casing, the combustor segments of a first section of the combustor can be removed. Supports connected to the first section of the combustor are secured by pins to a tool ring which is in turn secured to the inversion ring so as to create a closed path. By removing pins which secure the inversion ring and lower half outer casing to supports connected to a second section of combustor segments, the combustor can be rotated so that the second section of formerly inaccessible segments can be easily removed.

Abstract: A fuel manifold is disclosed for providing fuel to a combustor disposed radially inside an annular casing. The manifold is disposed inside the casing and includes an arcuate manifold tube, a thermal insulation layer surrounding the tube, and a cover layer surrounding the insulation layer which is substantially rigid for protecting the insulation layer from physical damage.

Abstract: In accordance with one aspect of the invention, a venturi having a heat shield along its inner diameter and a thermal barrier coating along its outer diameter is provided, whereby the temperature gradient of the venturi is lowered and metal distress and erosion caused by water injected therethrough is reduced. In an alternate embodiment, a floating insert is placed within an area along the venturi's inner diameter, where it is held in position by a heat shield.

Abstract: A method of diluting combustion gases in a gas turbine engine combustor includes injecting primary dilution air into the combustion gases, and injecting trim dilution air into the combustion gases adjacent to the injected primary dilution air. A dilution air injector for practicing the method includes a plate, or centerbody in an exemplary embodiment, having a primary dilution hole for injecting a portion of compressed air into combustion gases as primary dilution air, and a trim dilution hole for injecting a portion of the compressed air into the combustion gases as trim dilution air. The primary and trim dilution holes are sized and configured so that the primary and trim dilution air cooperate with each other for penetrating into and diluting a predetermined portion of the combustion gases.

Abstract: A combustion assembly includes a combustor having inner and outer pilot liners, each being in the form of a lobed mixer having outer and inner cold and hot chutes. A plurality of carburetors are joined to a dome disposed at upstream ends of the liners for providing a pilot fuel/air mixture for generating pilot combustion gases in the hot chutes. A plurality of fuel spraybars are disposed downstream from the carburetors and are aligned radially with the cold chutes for selectively injecting main fuel into main airflow for generating a main fuel/air mixture ignitable by the pilot combustion gases. In a preferred and exemplary embodiment of the invention, lean combustion gases are obtained for reducing NO.sub.x emissions in a relatively short residence time.

Abstract: A method and apparatus for reducing thermal distress and creep of a disk post in a gas turbine engine, the disk post being defined between an adjacent pair of blade roots of a respective pair of turbine blades in a turbine disk. The blade roots extend radially outward of the turbine disk and each terminate in a blade platform to form a cavity above the disk post. A seal generally covers the cavity for preventing a flow of combustion gases over the disk post. The seal includes axial segments defining a channel over a radially outer surface of the disk post. A flow of insulative air is directed into the channel defined over the disk post and diffused to reduce its velocity. The insulative air effectively reduces heat transferred from the blade platforms and combustion gases to the disk post.

Abstract: A method of operating a double dome combustor includes channeling compressed airflow through an inner dome for generating inner combustion gases having an inner reference velocity greater than an outer reference velocity of outer combustion gases generated from compressed airflow channeled through an outer dome, and diffusing the outer and inner combustion gases in outer and inner combustion zones. One double dome combustor effective for practicing the method in accordance with the present invention includes outer and inner combustor liners and domes, with the domes having outer and inner carburetors disposed therein, respectively. The inner carburetors are sized for generating inner combustion gases in the inner combustion zone having an inner reference velocity greater than an outer reference velocity of the outer combustion gases generated in the outer combustion zone.

Abstract: A double dome combustor for a gas turbine engine includes first and second domes joined to outer and inner liners. The first and second domes are joined together by two load transmitting structural paths for providing increased rigidity of the first and second domes for accommodating pressure loading from compressed airflow. In one exemplary embodiment, a dome cowl having first and second cowls is used to additionally join together the first and second domes.