Abstract: High temperature deterioration of an injector 34 for a gas turbine including a compressor and a turbine wheel 10, 14, 30 is avoided through the use of swirler blades 60 that form a forced vortex adjacent the ends 52, 58 of fuel and oxidant injection tubes 38, 40 to prevent separation of the mixed stream thereby eliminating backflows or eddies of burning fuel.

Abstract: A fuel injector 28 for gaseous and liquid fuel is disclosed. Various construction details are developed to enhance mixing and reduce nitrogen oxide emissions in a compact design. In one embodiment of the invention, the fuel nozzle 28 includes two radially spaced passages 68, 104 for air having swirlers 86, 112 and a liquid fuel passage 57 disposed between the air passages and a gaseous fuel passage 116 outwardly of the outermost air passage. In one detailed embodiment, a center body 76 is disposed in the inner air chamber to promote re-ciruclation of the hot gases.

Abstract: A spray nozzle including a body having a fluid inlet at one end thereof and an exit orifice at the other end thereof. The fluid inlet communicates with the exit orifice through a fluid flow path extending through the body. The exit orifice is adapted to atomize the fluid as the fluid leaves the body. The spray nozzle also includes a separate portion for atomizing the fluid independent of the exit orifice. The separate portion communicates with the fluid flow path upstream of the exit orifice. The separate portion produces a flat spray of the fluid as the fluid leaves the body. With these features, the spray nozzle is well suited as a fuel injector for a gas turbine.

Abstract: A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.

Abstract: Excellent fuel atomization in a turbine engine may be obtained with fuel injectors 46, 47 including elongated, laminar discharge orifices 72, 100 and impingement surfaces 76, 102 disposed in the path of fuel 78, 106 being discharged through the discharge orifices 72, 100. Preferably, the fuel 78, 106 is discharged as a flat spray generally tangentially to the annular combustion space 40 of an annular combustor 26.

Abstract: Improved performance in a hot gas generator is achieved by disposing a multiple port fuel injector 42 having three spaced fuel discharge ports 46, 48, 49 on the longitudinal axis 28 of a vessel 18 having a narrow inlet 22, an opposite narrow outlet 14 and an intermediate, enlarged chamber 24 which serves as a combustion chamber.

Abstract: The present invention comprises a gas turbine engine augmentor including a new and improved fuel spraybar therein. The spraybar includes a base having a manifold for receiving fuel, and a plurality of fuel tubes extending from the base and in flow communication with the manifold. The invention further includes means for cooling the fuel tubes for allowing independent thermal movement between the cooling means and the fuel tubes. In one embodiment of the invention, the cooling means comprises an elongate shield disposed upstream of the fuel tubes to block direct impingement of combustion gases against the fuel tubes while channeling a cooling fluid such as air over the fuel tubes.In accordance with another embodiment, the invention includes means for securing the shield to the fuel tubes for allowing unrestrained longitudinal thermal movement while restraining lateral movement therebetween beyond a predetermined amount.

Abstract: An improved air swirler and fuel injector for a gas turbine combustor system employs primary fuel injection into a primary recirculation combustion zone supplied by an inner annulus of swirling air at high fuel-air ratio under low power conditions. A selectively staged secondary fuel flow is supplied into an outer annulus downstream of secondary air swirlers supplying a secondary recirculation zone for combustion at higher fuel flows but lower fuel-air ratios under high power conditions. The secondary fuel flow may be separately injected into the outer annulus through conduit means extending through the primary air swirler vanes. Alternatively, the secondary fuel flow may be combined with the primary fuel in the fuel injector body and the momentum due to mass flow used to inject the fuel into the outer annulus.

Abstract: The present invention relates to a burner system, in particular for a gas turbine, with a main supply channel (2), debouching into a combustion chamber (1), for a fuel/air mixture having a swirler (5) and a burner lance (3) which passes through the swirler (5). To improve the transverse ignition properties between several such burner systems, optionally disposed on the burner chamber (1), and also to increase the flame stability, the burner lance (3) has, on the combustion chamber side with respect to the swirler (5) exit openings (12, 16) for fuel supplied to its interior or for a fuel-rich fuel/air mixture supplied to, or formed in, its interior.

Abstract: Fuel for a rocket engine consisting of hydrogen, oxygen and a hydrocarbon is admitted into the combustion zone through an injector whereby the hydrogen and hydrocarbon components are either pre-mixed in the injector or independently delivered and the oxygen is always independently delivered into the combustion zone.

Abstract: A stem couples a fuel injector inlet to a fuel nozzle. The fuel nozzle includes a primary fuel flow portion and a secondary fuel flow portion. The stem includes an input end for receiving a primary fuel flow and a secondary fuel flow from the fuel injector inlet. The stem includes three concentric tubes with the first tube coupling the primary fuel flow from the injector to the primary portion of the nozzle. A second concentric tube couples the secondary fuel flow from the injector to the secondary portion of the nozzle. The primary fuel flow and the secondary fuel flow in the two concentric tubes are nonlinear with respect to the input and output ends of the stem. The third concentric tube provides structural support and an insulating space for the first two concentric tubes. Methods for constructing the stem are provided. Other embodiments are disclosed.

Abstract: A gaseous fuel injector for an industrial gas turbine plant is arranged to operate on fuel produced from a coal gasifier for normal running or natural gas for starting purposes. The injector is self purging to prevent the ingestion of natural gas or combustion products into the passage of the fuel injector for the lower calorific value fuel. The fuel injector has fuel ducts and gas flow passages in a duct assembly attached to the head of each flame tube of a gas generator. For starting, natural gas flows through the duct and the central passage, while air flows through the outer passage preventing ingestion of natural gas and combustion products into the outer fuel duct. When running on fuel from a coal gasifier both ducts run full of fuel, as do the passages. The air for the coal gasifier may be provided by the gas generator.

Abstract: A single-piece thermally isolated multi-point injector for a hydrazine fuel catalytic gas generator having a series of integral feed tubes each with a fuel passage and with the fuel inlet ends thereof spaced apart for ease of manufacture and inspection and associated with a distribution manifold. The feed tubes are arranged in spaced-apart circular arrays to facilitate formation thereof from an investment casting or by radial electrochemical machining cuts. The fuel injector retains the thermal isolation features of a welded or brazed capillary tube injector, but eliminates leakage points encountered in such a structure. The outlet end of each feed tube has a porous member associated therewith to obtain a uniform flow path of hydrazine fuel in all directions onto a catalyst bed.

Abstract: The fuel nozzles in a variable geometry combustor cooperate with an inwardly projecting liner wall section to define a sheltered pilot combustion zone within the liner. Simultaneously operable inlet valves are provided for admitting a selectively variable quantity of combustion air into the pilot zone.

Abstract: Multifuel burner having outlet locations for a plurality of fuels respectively connected with associated fuel feeding spaces arranged at a head of the burner, at least one of the fuel feeding spaces being for fuel gas and encompassing a plurality of outlet nozzles arranged annularly in a nozzle head, includes tube conduits connecting the outlet nozzles for fuel gas to the respective fuel feeding space associated therewith; the tube conduits having means for compensating for expansion of the tube conduits; the outlet nozzles having discharge openings directed outwardly at an angle of 20.degree. to 80.degree.

Abstract: A variable area air system means for air blast type fuel nozzles for use in gas turbine engines wherein fuel/air ratios are controlled for the purpose of controlling engine emission products to meet mandated emission standards over a wide range of engine operating conditions. The variable area air metering means is connected with a pressure responsive actuating means for controlling the air flow in single fuel system and dual fuel system air blast type fuel nozzle and support assemblies used in gas turbine engines.

Abstract: The fuel nozzles in a variable geometry combustor cooperate with an inwardly projecting liner wall section to define a sheltered pilot combustion zone within the liner. Simultaneously operable inlet valves are provided for admitting a selectively variable quantity of combustion air into the pilot zone.

Abstract: A pressure atomizing fuel nozzle assembly for a gas turbine engine includes a support housing in which a pressure-responsive fuel check valve and metering valve are disposed in line to provide a flow of primary fuel for engine start-up and low power operation and secondary fuel for higher power operation. The check valve is located upstream between the fuel inlet and a sleeve inside of which the metering valve is disposed. The check valve prevents the fuel manifold from draining after engine shut-down and controls fuel entry to both the secondary fuel chamber within the sleeve and to an annular primary fuel chamber between the sleeve and support housing connected in fuel flow relation to the secondary chamber by a fuel filter. The primary fuel flows through the primary chamber around the exterior of the secondary chamber and through an annular primary fuel conduit disposed around the secondary fuel conduit in the housing strut to the nozzle attached to the strut.

Abstract: A gas turbine engine is provided with an improved fuel system that features a fuel manifold with a primary and secondary fuel flowpath circumventing a combustor section of the engine. The manifold is formed with a double-walled construction for the purpose of withstanding high temperatures or fires around the combustor section and, additionally, to provide a secondary flowpath for draining any fuel leakage from the manifold. The two walls of the manifold include an inner wall that encloses the primary fuel flowpath through the fuel system. A concentric outer wall encloses the inner wall and protects the primary fuel flowpath. The double-walled system is made possible with a unique manifold assembly utilizing double-walled manifold segments that interconnect fuel flowpaths through fuel injector base sections. When assembled, these parts connect together to form an integral double-walled fuel manifold assembly.

Abstract: A dual fuel injector for a gas turbine engine is arranged to maintain pre-determined air fuel ratios in adjacent upstream and downstream opposite handed vortices and to reduce the deposition of carbon on the injector. The injector comprises a central duct, a deflecting member, a first radially directed outlet, and a shroud which defines an annular duct, and a second radially directed outlet. The ducts receive a supply of compressed air and the central duct receives gaseous fuel from an annular nozzle and the annular duct receives liquid fuel from a set of nozzles.When the injector is operating on liquid fuel, the fuel and air mixture issues from the second outlet and compressed air flows from the first outlet and prevents migration of fuel between the two vortices, thereby maintaining a rich air fuel ratio in the upstream vortex which reduces the emissions of NOx. Also, the flow of air from the first outlet reduces the deposition of carbon from the liquid fuels on the deflecting member.

Abstract: The invention relates to fuel burners and the combination of fuel burners and annular combustion equipment particularly for use in gas turbine engines.The present invention seeks to provide a fuel burner that requires a relatively small access hole in the engine casing in order to reduce stress concentrations in the casing.The fuel burner comprises a fuel feed arm and a fuel injector. The fuel feed arm and the fuel injector are cylindrical, and are arranged coaxially in end-to-end abutting relationship. The fuel feed arm has internal passages for the supply of fuel to the fuel injector, and the fuel injector has an air duct passing normally through the fuel injector for the flow of air into a cooperating combustion chamber. The fuel injector supplies fuel into the air duct to mix with the air flowing therethrough.The invention also provides combustion chamber equipment for use in conjunction with the fuel burners.

Abstract: A dual fuel burner for a gas turbine engine comprises a gas fuel manifold and ducts opening into a central air passage, a liquid fuel manifold and tangentially arranged apertures opening into an annular liquid fuel passage terminating in an annular nozzle. The central air passage has an upstream swirler, and is arranged to receive a flow of compressed air at its upstream end and to discharge a flow of compressed air and either gaseous or liquid fuel from its downstream end. The burner also has a water manifold so that water can be injected into the fuel and air flow via ducts and an annular air passage, to control NOx emission.In an alternative arrangement, the liquid fuel can be injected into the annular air passage.The burner is intended to operate on a range of high calorific fuels, both liquid and gaseous, and is designed to minimize the surface area on which carbon may accumulate during operation.

Abstract: A fuel nozzle designed to reduce pollutant emissions and minimize the buildup of coke in the secondary fuel passage of a dual orifice fuel nozzle for the combustor of a gas turbine engine sizes the orifices and passages of the air and fuel so as to increase the pressure in the secondary passage during its inoperative mode and when the primary fuel passage is in the operative mode and having the air and fuel issuing from both the primary and secondary orifices swirl in the same direction.

Abstract: Improvement to the starting characteristics of an annular combustor for a gas turbine engine that employs dual fuel nozzles (primary and secondary fuel flow systems) by redistributing the total fuel admitted to the nozzles in an asymmetrical pattern to deliver the requisite amount of fuel to the igniter by the primary flow system feeding fuel to that igniter.

Abstract: A device for priming an empty or partially full burner manifold of a gas turbine engine with fuel before it is required to supply from the burner manifold to the associated burners comprises a fuel accumulator and a control valve.A fuel pressure signal supplied to the control valve terminates the supply of relatively high pressure fuel to the fuel accumulator via the control valve. A metered quantity of fuel is supplied via the control valve to the burner manifold from the fuel accumulator by the motive force of a spring acting on a piston in the accumulator. The metered quantity of fuel is supplied via the control valve to the burner manifold, to fill the burner manifold and to prevent undesireable drops in the quantity of fuel being supplied to other manifolds when the regulated fuel is supplied to the burner manifold.

Abstract: Coke hereinbefore known to form in the secondary passage of a dual orifice fuel nozzle for the combustor of a turbine type power plant is prevented from forming by imposing increased air pressure in the secondary passage during its inoperative mode and when the primary fuel passage is in the operative mode, without relying on purging or requiring an external air source.

Abstract: A gas turbine engine fuel injector has distinct and separate flow paths for liquid and gaseous fuel which each terminate in outlets of decreasing cross-sectional area in order to prevent combustion products from the flame tube or tubes of the engine from flowing back into the injector, the separate fuel flow paths preventing fuel from migrating from one path to the other. Compressor delivery air is also arranged to flow through the fuel outlets and some mixing of fuel and air takes in the outlets before the fuel enters the flame tube.The fuel injector is formed in two separate and co-operating parts, a fuel feed arm attached to the engine casing and readily removable through a relatively small access aperture in the casing and a fuel and air inlet means which is attached to the head of the flame tube and defines the fuel and air inlets into the flame tube.

Abstract: A fuel distribution system for regulating split of fuel flow between a pilot nozzle system and a main nozzle system for a combustor includes a flow network for directing fuel from a main fuel metering valve into an unrestricted line to a small pilot nozzle orifice producing a fine fuel spray pattern at low fuel flow rates and further including a fuel splitter valve interposed between the outlet from the fuel metering valve and a fuel conduit connected to a main fuel nozzle of increased orifice size to atomize higher rates of fuel flow thereto and wherein the fuel splitter valve includes an electrically energizable component that receives a control signal of desired pilot fuel/air ratio generated by a controller in part utilizing a signal of total actual fuel flow and total actual air flow to produce the control signal to control operation of the splitter valve so as to regulate the amount of fuel flow to the main nozzle system in accordance with the control signal thereby to produce a residual flow of fuel to

Abstract: A gas turbine engine fuel injector which burns liquid and gaseous fuel and also has a water injection system to reduce the formation of nitrogen oxides (NO.sub.x). The water can be discharged into a combustion chamber through an annular nozzle which is located between an inner annular fuel and air discharge nozzle and an outer gas discharge nozzle which comprises a circumferential row of discrete discharge nozzles. This allows the water to be injected at the most suitable point whichever fuel is being burnt. The water can also be injected into the inner annular fuel and air discharge nozzle.

Abstract: A dual fuel injector for a gas turbine engine having means for water injection to reduce NOx emissions, comprises an outer annular gas fuel duct with a venturi section with air purge holes to prevent liquid fuel entering the gas duct, an inner annular liquid fuel duct having inlets for water and liquid fuel and through which compressor air flows, the inner annular duct terminating in a nozzle, and a central flow passage through which compressor air also flows, terminating in a main diffuser having an inner secondary diffuser. The surfaces of both diffusers are arranged so that their surfaces are washed by the compressor air to reduce or prevent the acretion of carbon to the injector, the diffusers in effect forming a hollow pintle.

Abstract: A burner construction in which staging of combustion is obtained by a primary pressure-atomizing nozzle having a low spray angle to maintain combustion within a central core of the combustor, and a secondary fuel aerating nozzle delivering fuel in a hollow cone configuration surrounding the primary fuel spray for combustion in an annulus between the central core and the wall of the combustor. Although most of the air for primary combustion is supplied with the fuel nozzle, additional air may be introduced at the upstream end of the combustor by high penetration jets that enter the central core and additional air for secondary combustion is introduced by one or more rows of holes in the combustor wall near the upstream end.

Abstract: In a two stage burner construction in which primary fuel burns in an annulus in a primary combustion zone and secondary fuel is discharged through the primary zone to a secondary zone downstream of the primary zone, vortex generators are used in the passage through which the fuel and air entering the primary zone to enhance the mixing and to improve the toroidal flow in the combustion zone. Other vortex generators are used to improve the mixing of the secondary fuel and air to improve secondary combustion. The vortex generators may be used in conjunction with a trip on the secondary nozzle tube to further enhance primary combustion.

Abstract: A fuel nozzle for a gas turbine engine permits alternate use of different fluid fuels such as gaseous or liquid fuels without intermixing until delivery of the fuel to the combustion chamber. The nozzle provides concentric fuel delivery passages and allows for differing rates of expansion between the two passages.

Abstract: Fuel is injected through very fine holes normally into a swirled airstream. A finally atomized fuel results and a solid cone of fuel and air passes into the combustion chamber. The injector gives high combustion efficiency at idle conditions reduces smoke at high power conditions.