Abstract: In the combustion chamber of a gas turbine, an air distribution chamber (19) and a combustion space (7) are locationally separated from one another within the combustion chamber shell (1). A multiplicity of tubular elements (2) are located between the distibution chamber and the combustion space, in which elements a premixing and pre-evaporation of the fuel oil supplied via the premixing nozzles (15') and/or a premixing of the fuel gas supplied through the premixing nozzles (15") takes place with compressor air. Each tubular element (2) is provided with a flameholder (3) in the direction towards the combustion space (7). A diffusion nozzle (8) for fuel directed into the combustion space (7) is located within the flameholder. In operation on load, only a small part of the fuel supplied to each element (2) is burned by means of the diffusion nozzle (8), the major proportion, on the other hand, being burnt by means of the premixing nozzles (15' of 15").

Abstract: A power plant with a combustion chamber in which a fuel in burned in a fluidized bed of a particular material, comprises a storage container for the bed material which, upon a load reduction, is removed from the combustion chamber. The storage container is provided with a sieve or a grate which prevents slag lumps formed in the bed material from penetrating into a conduit for the return of the bed material to the combustion chamber. A tube projecting into the storage container forms the sieve.

Abstract: An apparatus and method are provided for preventing the plugging of cooling air distribution holes in a hollow gas turbine vane by particles entrained in the cooling air. The portion of the cooling air is bled from the vane and discharged into the hot gas downstream of the vane, the shunted bleed air carrying the entrained particles.

Abstract: Combustion supporting air in the resonator tube of a pulse jet engine is cyclically compressed by combustion and discharged through a decelerating passage of a diffuser in a tail section of the engine to internally pressurize an afterbody preceding atmospheric dishcarge of the combustion products through nozzle passages, followed by primary refill with air from the pressurized afterbody and secondary refill by reentry of external air. The nozzle passages are formed in angularly spaced, rearwardly diverging vane formations of the tail section projecting from a protective casing directing ram air intake into orifice openings formed in a rear end portion of the diffuser to regulate afterbody pressurization under control of ram pressure created by forward propulsion of the engine.

Abstract: The type which comprises a motor-compressor unit, suspended inside a housing with suction and discharge connectors and formed by a block, supporting a motor incorporating at least one discharge muffler, one cylinder with head lodging chambers and suction and discharge valves and a suction system admitting refrigerating gas coming from the suction connector of the housing and conveying it to the cylinder. In accordance with the invention, the system comprises a suction muffler (110) and one inside lining element (120) of the suction chamber built in one single hollow and airtight unit, while inside the suction muffler (110), at least two chambers (111, 112) are defined, interconnected one to the other by an internal peripheral communication duct (113), with inlet and outlet ends axially aligned and separated with relation to the outlet end of an internal peripheral inlet duct (115) and a gas outlet opening (116), respectively.

Abstract: A gas turbine system having an extraction channel supplying part of the discharged air of a compressor to another installation, and a method of controlling the gas turbine system wherein an inlet guide vane or any other regulator for regulating the flow rate of inlet air is disposed at the inlet of the compressor of a gas turbine engine, and the flow rate of the inlet air of the compressor is controlled in correspondence with the fluctuation of the flow rate of extraction air to provide a gas turbine system and a controlling method therefore which do not adversely affect the efficiency of the gas turbine engine regardless of the fluctuations of the flow rate of the extraction air.

Abstract: A motor driven pump for pumping a viscous solution of a solute in a solvent comprises an impeller for pumping the solution into an outlet chamber. A shaft is rigidly connected to the impeller and is rotatably mounted in hydrodynamic slide bearings for driving the impeller. A rotor is rigidly mounted on the shaft for rotation therewith in response to actuation of a stator that is operatively associated with the rotor for causing rotation of the shaft. A lubrication system is provided for delivering pressurized solvent to the bearings such that solvent leaking from the bearings flows into the outlet chamber.

Abstract: A bearing assembly for a small compact sized fan is provided which can utilize either a sintered bearing or a roller bearing, and which provides several embodiments for positioning the bearings in a radial and axial direction. The invention utilizes a bearing support tube for constraining the bearing in radial direction and an end cover cap attached to a flange of the fan duct to retain the bearings in an axial direction.

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: A coupling arrangement for supporting a power turbine in a gas turbine engine. The power turbine section comprises a stator structure, first and second rotors, and first and second bearings. The first and second rotors are coaxially disposed about a longitudinal axis of the stator. An annular gas flowpath is coaxially positioned between the first and second rotors. Annular arrays of turbine blades are coupled to the first and second rotors and extend into the flowpath so that a gas stream flowing through the flowpath reacts with the turbine blades causing the rotors to counterrotate. The first bearings are interposed between the first rotor and the stator structure to rotatably secure the first rotor to the stator structure. The second bearings are interposed between the second rotor and the first rotor to rotatably secure the second rotor to the first rotor.

Abstract: A gas turbine engine having a series intercooler positioned between a first and a second compressor. The intercooler has a first fuel heating system which has a heated fuel outlet and the heated fuel outlet is coupled to a combuston region of the engine. The intercooler also has a second feedwater intercooler stage which heats feedwater and the heated feedwater is input into a turbine exhaust heat exchanger. At least one turbine is positioned downstream of the combustor region and the turbine exhaust heat exchanger is downstream of the turbine. The intercooler may also include the first fuel heating system having the heated fuel outlet coupled to the combustor region and a second intercooler stage having a water input port.

Abstract: A photon ignition system for igniting the air/fuel spray within a combustion chamber of a gas turbine engine is comprised of a photon source 20, a photon transmission means 22 and a focussing means 24. The source 20 has an output wavelength characteristic suitable for being absorbed by the hydrocarbon fuel droplets within the fuel spray. In accordance with one embodiment of the invention the source 20 comprises an ultraviolet flashlamp having spectral characteristics which are selected to be strongly absorbed by hydrocarbon fuel. In another embodiment of the invention the source 20 comprises a laser, such an excimer laser, having an output pulse with wavelengths within the strong absorption range of hydrocarbon fuel. The photon output of the source 20 is focussed within an optimum region of the fuel spray for igniting one or more droplets therein due to the absorption and subsequent heating of the droplets of the focussed photon output.

Abstract: A propfan turbo-engine has two shrouded propfan rotors arranged upstream of a gas turbine which are driven by a contra-rotating working turbine. In addition to a favorable flow onto the blades, a low weight of the engine can be achieved.

Abstract: A self starting turbine (10) is disclosed. An auxiliary pulse combustor (23) is provided having a separate output nozzle (36) from the discharge orifice (20) of a constant pressure combustor (18) for providing pressure pulses which impinge on the blades (22) of the rotor (14) of the turbine to provide starting torque. The utilization of a separate pulse combustion chamber (24) and discharge orifice 36 having a cross-sectional area different from the discharge orifice (20) of the constant pressure combustor (18) permits efficient pulse operation without adversely affecting the operation of the constant pressure combustor during normal sustained operation of the turbine.

Abstract: The diverging portion of discontinuous curvature is fitted with a controlled injection device for controlled injection of an additional jet of gas into the diverging portion in the same direction as the main flow of gas ejected by the nozzle, and said controlled injection device is disposed outside the diverging portion in the vicinity of the join zone between the first and second lengths in order to inject a determined flow of said additional gas into the diverging portion along a direction which is not tangential to the wall of the diverging portion.

Abstract: The control of nitrogen oxides (NOx) is an important feature in the design and operation of gas turbines. It has been found that the production of NOx is affected by the fuel-air ratio within the combustor liner. To this end, an improved combustor liner is proposed which allows the distribution of combustion air and dilution air into the combustion liner in accordance with temperature conditions immediately surrounding the combustor liner. In one embodiment, an apertured ring is rotated in and out of register with dilution air holes in the liner to selectively affect the amount of dilution air and therefore also combustion air into the liner. The ring is driven by a temperature sensitve metals trip wound about the combustor liner. In another embodiment of the invention, the residence time of the combustion reaction is affected by the selection of upstream and or downstream dilution air holes in accordance with the position of the ring holes.

Abstract: A lubrication pump with a stroking action of a delivery piston and with regulatable metering of the amount of lubricant delivered with each stroke of the pump, wherein the delivery piston is actuated by the pump and aspirates the lubricant into a suction space whose volume is adjustable, wherein furthermore the lubrication is fed from the suction space through an intermediate storage space to the lubricant outlet or to the lubrication circulation circuit and wherein a check valve is provided in the above-mentioned delivery path of the lubricant, so that, when viewed in the delivery direction of the lubricant, the check valve is located following the receiving space and upstream of the intermediate storage space.

Abstract: Undesirably high and damaging temperature gradients resulting from hot spots in combustors 26 for housing a hot gas generating oxidation reaction are avoided in a construction including a combustor housing haivng a wall 32, 34, 39 with an interior surface defining a combustion space 38, 40 and an exterior surface thereof and provided with an outlet 36. A plenum 44, 80, 82 surrounds the combustor 26 and a fuel injector 50, 52 is provided for introducing a fuel to be oxidized into the combustion space 38, 40. Oxidant inlets 54 to the combustion space 38, 40 are provided and various structures including the plenum 44, 80, 82 flow cooling gas in a path about the exterior surface of the walls, 32, 34, 39 to cool the combustor housing. Trip strips 114, 118 are located on the exterior surface of the walls 32, 34, 39 and extend into the cooling gas flow path and are located to minimize the temperature gradient between points along those walls 32, 34 and 39.

Abstract: The coated article includes a refractory metal substrate having an oxidation resistant intermetallic layer formed in situ thereon; e.g., a fused refractory metal silicide layer, and a ceramic layer applied on and adhering to the intermetallic layer to provide enhanced high temperature properties and improved resistance to premature catastrophic failure in high temperature oxidizing environments where dissimilar materials are present that may destructively react with the inermetallic layer.

Abstract: A flow inducing means 110 for use in an anti-icing system for a nose bullet 10 of a gas turbine engine of the type in which hot gas is caused to flow along the center of a rotating tube 7,62 towards the nose bullet 10 to heat it, and cooled air is centrifuged to the surface of the bore of the tube 7,62 and is displaced rearwardly along the tube. The tube 7,62 is open at its rear end, and the flow inducing means 110 is positioned adjacent the open end. The flow inducing means 110 comprises a plurality of radial vanes 111 which enters in a radially inwards direction and the vanes 111 are shaped and positioned to redirect the gas axially along the center of the tube 7. The flow inducer 110 may include a shroud 115 which has a circumferential inlet opening and an axial facing outlet 116. The shroud may serve as a flow separator which separates the incoming hot gas from the cooled gas exiting the tube.