Blisk of cooled fuel feed pylons

FIELD: engines and pumps.

SUBSTANCE: each pylon has three channels plugged from side, open ends of two of these channels are closed by plugs, channels are connected by holes, and in central channel there is a damper with several holes.

EFFECT: elimination of pylons burnout at high thermal loads, enhanced reliability of blisk of fuel supply, expanded performance range of fuel consumption at practically constant pressure drop on nozzles for improvement of combustion efficiency of fuel-air mixture.

2 cl, 4 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: method for high-speed athodyd of aircraft comprising combustion chamber consists in fuel feed at supersonic speed via set of pylons flown by oxygen, for example, of air. Then, fuel-air mix is ignited to initiate chain mechanism of combustion and power release in the chamber flow circuit. At air-fuel interface at outlet of one of pylons a jet of cold oxygen plasma is generated of definite crosswise size to act to oxygen by electric discharge of definite specific power input and reduced intensity of electric field.

EFFECT: higher thrust, lower power input to combustion initiation.

4 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used in space and defence branch. The high-speed ramjet engine (HSRJE) contains series located air-intake, a combustion chamber (CC) and an output nozzle. CC has fuel supply nozzles with a possibility of formation of fuel-air mix. The area of inlet section of the combustion chamber is designed greater than the area of its output section, meanwhile the area of output section of the combustion chamber is determined in view of the temperature of ignition of fuel-air mix. CC geometrical parameters are determined in view of description of the ratios. Excess of the area of CC inlet section over the area of its outlet section can be provided by formation of local coning in the zone of the latter or gradual coning of CC by flow.

EFFECT: improvement of reliability and efficiency of ignition, increase of completeness and stability of combustion of fuel, and also increase of draft and profitability of the engine, reliability of its starting and depreciation of fabrication of the engine due to radical design simplification and manufacturing technology.

6 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed process consists in that high-rate airflow is forced into combustion chamber and decelerated therein to make fuel mix to be ignited. Besides, fuel mix flow is decelerated to subsonic Mach number via contraction of combustion chamber. Fuel mix is ignited owing to keeping fuel in combustion chamber for time interval higher than that of induction in fuel oxidation reaction. Said time of keeping fuel in combustion chamber is set in compliance with claimed ratios. Combustion chamber contraction is ensured by gradual or local decrease in chamber cross-section.

EFFECT: simplified engine, higher reliability and completeness of fuel combustion.

3 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: air intake, combustion chamber and nozzle make the engine gas circuit. Laser radiation source can generate radiation in preset frequency resonant with that of the line of molecular oxygen absorption from the main electron state to excited metastable state. Fuel feed device is composed of a vertical set of pylons and arranged across said engine circuit. Optical system is arranged in said circuit downstream of fuel feed device and comprises at least one pair of opposed radiation reflectors to make radiation scanning zone there between. Laser source feed waveguide is arranged at one of said reflectors. Fuel feed device is arranged in air intake path. Every pylon accommodate fuel channel, buffer fuel tank and injector nozzle, all being hydraulically communicated. Fuel feed pressure control valve is connected by lines with fuel channels of every pylon. Pairs of optical system radiation reflectors are arranged downstream of injector nozzles of one or several pylons to make separate scanning zones. Bottom boundary of every scanning zone is located above top rear edge of injector nozzle of appropriate pylon and directed therefrom toward combustion chamber with scanning zone defined in claimed item of this invention.

EFFECT: decreased delay and firing temperature, higher completeness of air-fuel mix.

6 cl, 13 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed ramjet comprises housing, air intake with central body accommodating fuel atomizer composed by gas-jet resonator with sharp edge connected by pylons with air intake, combustion chamber, igniter, nozzle, control system and solid-fuel cartridge for start acceleration. Concept of combustion consists in combustion of cartridge solid-fuel charge, air compression in air intake, generation of internal shock waves in engine flow section, feed of nano-dispersed fuel via atomizer into combustion chamber fuel including nanotubes with encapsulated hydrogen, initiation of pulsating fuel-air mix combustion in the chamber at 100-4000 Hz, expansion of combustion products and control over combustion conditions.

EFFECT: higher acceleration, better fuel combustion completeness, improved weight and size characteristics.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: device for interaction with air or gas to work as a compressor or expander comprises housing, torque transfer shaft and rotor. Said shaft extends through the housing to run about axis and is engaged with rotor. Rotor keeps its revolution at the rim circumferential speed of about 2000-5400 feet/sec. Circular area inside said rotor and said housing makes the flow passage. Said housing includes also the discharge opening for outflow of high-energy gas or air outward from said circular area or its inflow thereto. Shaft contains material of high specific compression or expansion strength and gas flow passage to feed gas or air to rotor or to discharge then therefrom. Some parts of said shaft are wound of fibre bundle of high expansion strength material stretched to half the breaking strength. Rotor surrounds shaft part inside said housing and has gas or air passages to allow air flowing radially and to retain the flow from rotor. Rotor contains material with high expansion strength material and compressive material compressed by fibre bundles stretched to half the breaking strength. Material with high compression strength is engaged with the shaft by compression or by at least one winding of fibre bundle. Machine as a compressor comprises circular area inside the rotor and the housing to make air of gas passage to force the flow in spiral radially from rotor outside via circular area and with decrease in rate. Note here that circular area discharges airflow or gas flow radially outside the rotor. Jet or mechanical engine comprises above described machine as a compressor.

EFFECT: decreased fuel consumption, higher efficiency, lower emission of CO2, lower cost.

16 cl, 11 dwg, 8 tbl

FIELD: engines and pumps.

SUBSTANCE: hypersonic ramjet engine includes a fuel injector arranged in the nose part of the engine before the air intake and a combustion chamber and a nozzle, which are located after it, as well as the excitation device of oxygen molecules with resonance laser emission in the combustion chamber. The oxygen molecule excitation device includes a laser emission source with the frequency resonantly coinciding with the frequency of the absorption line of molecular oxygen from the main electronic state to excited state, and an optic system. The optic system is arranged in the air intake at the combustion chamber inlet and has the possibility of continuous scanning of air-fuel flow with a laser beam from the laser emission source perpendicular to the flow axis in the area meeting the condition h/D=0.025-0.05 where D is diameter of a flow part at the combustion chamber inlet, and h is transverse size of the scanning area.

EFFECT: reduction of weight and dimensional characteristics of the engine owing to shortening the length of energy release zones.

4 cl, 1 dwg

Vortex propeller // 2465481

FIELD: engines and pumps.

SUBSTANCE: vortex ejector propeller is made in the form of streamlined hollow nacelle the internal surface of which forms an air path consisting of in-series located inlet device made in the form of confuser, diffuser, vortex chamber and outlet device. Nacelle is provided with device for compressed air supply inside air path in the form of nozzles interconnected with compressed air source, located in front part of nacelle and directed at an angle equal to 10-60° to axis of air path so that vortex is created.

EFFECT: reduction of weight and improvement of reliability.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises feeding fuel into supersonic airflow and inducing chemical reaction of combustion of produced supersonic flow of fuel-air mix by producing flat inclined shock wave and initiating stationary inclined detonation wave. Prior to producing flat inclined shock wave, supersonic flow of fuel-air mix is irradiated additionally by laser multiple-reflected radiation with frequency in resonance with frequency of line of molecular oxygen absorption from primary electron state into excited metastable state. Hypersonic ramjet engine comprises elongated housing with air inlet on one end and laser radiation source. Housing intermediate part is made up of combustion chamber and provided with fuel feed device and wedge-like body with taper vertex facing supersonic flow. Laser radiation source is arranged ahead of wedge in the inclined shock wave formation zone with radiation reflectors arranged at wedge vertex.

EFFECT: intensified combustion due to increased rate of chemical reactions.

4 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: pancake hypersonic straight-flow air breathing engine (HSFABE) for bringing the transport vehicle into movement includes many equally-spaced posts separated with paths, and pilot portion of the post, which is enclosed inside each of the above posts. Geometry of pilot portion of the post is effective to receive the pilot portion of air of supersonic air flow from HSFABE air intake and to reduce the pilot portion of air to subsonic speed. The rest portion of the main air of supersonic air flow bypasses the pilot portion of the post via paths and remains at supersonic speed. Each post includes inward directed pilot fuel atomisers and outward directed main fuel atomisers. Pilot portion of the post is enclosed in the limits of each post.

EFFECT: reducing heat load of combustion chamber, shortening the length of combustion chamber at using the fuel injection directly to the flow.

33 cl

FIELD: power industry.

SUBSTANCE: combustion chamber assembly includes the main housing formed with a supply header with a fuel feed system and fuel atomisers continued from the supply header and provided with fuel by means of the fuel feed system of the supply header. The supply header has a sandwich structure and is made of separate elements. The number of separate elements of the header exceeds the number of fuel types in the fuel feed system. The fuel feed system includes at least one gas line channel and at least one liquid fuel channel. The supply header is made of at least three separate elements.

EFFECT: invention allows designing an effective combustion chamber assembly at considerable reduction of costs for manufacture of the main housing.

12 cl, 6 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed fuel system comprises fuel tank (1) with booster pump (2), fuel line (3) arranged partly inside rotor shaft and blades. Fuel line of every blade is provided with rotor rpm controller. Electrically driven starting and low-rpm pump (5) is arranged at fuel line section downstream of booster pump with outlets in number corresponding to that of engines (8) and engine working condition control pump (7) driven by rotor shaft (11) via gearing (12) of gearbox (10). Fuel manifold (15) is arranged at inlet of blade (14) fuel lines (9) to transfer fuel from fixed fuel line sections to their moving sections (9′) in every blade (14). Fuel manifold (15) consists of two compartments (16, 17). Fixed compartment (16) is secured at fixed pipe (13) inside rotor shaft (11). Moving compartment (17) is fitted on rotor shaft (11) and has circular chambers (18, 19) for fuel transfer.

EFFECT: possibility to rule out inertia of fuel feed and to effect the fuel pressure control.

3 cl, 2 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. This is the method of gas-turbine plant operation in transient mode in which controller determines values of control command for mass-flow rate of incoming air, for fuel mass-flow rate, for mass-flow rate of water or steam, when water and steam are used; at least one command value is dynamically compensated in order to compensate various dynamics of supply systems for synchronisation of resulting changes in mass-flow rate of fuel, water, steam and combustion air delivered to combustion chamber, so that fuel-air mixture composition was within ignition zone. Also presented is a control system meant for implementation of proposed method, and gas-turbine plant including such control system.

EFFECT: providing fast operation in transient mode with consistent flame of premixed mixture.

13 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used in het engine fuel feed systems. Proposed is the heat engine fuel feed system. Note here that the latter consists of at least one fuel line (1) extending to combustion process (3) along which at least one vale unit is arranged. At first step 1 when exhaust valve (7) is closed shutoff valve (4) and control valve (5) are closed. At step 2 exhaust valve (7) opens to make fuel (V1) evacuate from fuel line section (1') and drain line (6'). At step 3 exhaust valve (7) closes. At step 4 control valve (5) opens. At step 5, fuel chamber (V1) is filled with fuel forced from fuel line extending to combustion process (3). Then, at step 6 control valve (5) is closed and exhaust valve (7) is opened to drain said fuel (V1) fed after step (5).

EFFECT: controlled pumping of fuel residues from line extending to combustion process.

7 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used in power engineering, particularly in gas transfer plants, self-contained electric power stations and other power plants including gas turbine drive running on natural gas. In compliance with this method fuel is fed to separate burners at critical flow parameters in channels with identical flow sections. Lengthwise profiles of all channels comply with that of any randomised channel, being preferably the first one made at precision defined by fabrication error. Note here that walls of said channels feature equal surface roughness. Note here also that equality of flow rates of fuel fed into inlet of every channel is ensured by adjusting element arranged at channel inlet and composed by, preferably, a chamfer of geometrical sizes that can be varied at tuning of said channel to preset flow rate.

EFFECT: uniform temperature field ahead of gas turbine plant turbine.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed plant comprises gas turbine engine with compressor, gas turbine air preparation device, fuel system with combustion chamber, fuel feed and adjustment device, engine and actuator oil lubing system with oil cooling heat exchanger, pressure pump, fuel heating heat exchanger, all being arranged in separate adjustable circulation circuit. Additionally, said plant incorporated a heat pump. The latter comprises at least one heat exchanger, one pressure booster, one condenser heat exchanger and one pressure reducer. Evaporator heat exchanger inlet is connected to gas turbine air preparation device outlet. Evaporator heat exchanger outlet is connected to compressor inlet. Condenser heat exchange inlet is connected with fuel feed device while its outlet is connected with fuel heating heat exchanger.

EFFECT: higher efficiency, reduced influence of atmospheric air parameters, higher safety.

1 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to gas turbine fuel feed systems. Fuel feed at starting after log outage at low temperature consists in fuel warming up before fuel feed to fuel filter. Note here that prior to feeding, ice is separated from fuel and heated to breakup. Thereafter, water resulted from breakup is added to warmed up fuel. Said water is additionally heated to warmed-up fuel temperature, preferably, to that approximating to boiling point. Note that ice and water are heated by air bled from gas turbine compressor.

EFFECT: reliable takeoff after long stay at low temperatures.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: injector unit of gas-turbine engine combustion chamber includes a plate of annular shape with injector modules installed on it in several rows, and a primary fuel collector connected to the plate, collector cavity being connected to fuel channels with injector modules. Injector modules are installed with register ledges inserted into the blind holes made in the plate and provided with mixing chambers of frustum-of-a-cone shape. All the injector modules have central fuel channel. Tangential air swirlers are made between the housing and the central body in the form of inclined blades. The central fuel channel is made blind with inserted tangential holes. Injector modules in rows are installed on the plate in staggered order.

EFFECT: improving fuel combustion completion at all the modes, reducing harmful emissions and providing uniform temperature field at combustion chamber outlet.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to energetic, chemical and transport machine building and may be used in gas turbine plants combustion chambers. Proposed fuel combustion method involves preliminary separation of air flow into coaxial annular jets, twisting of neighbouring adjacent jets in opposite directions, at that parts of neighbouring twisted in opposite directions jets closest to each other are supplied in radial direction towards each other forming turbulent shifting layer. Fuel is supplied to this layer for further ignition of generated fuel-air mixture. Preliminary right after air flow separation into coaxial annular jets, one part of fuel is supplied to generated rotating coaxial annular jets tangentially, contrary to direction of coaxial annular air jet rotation preferably to direction opposite to its axial movement. The rest part is supplied to generated turbulent shifting layer in direction of combustion zone, preferably in the form of hollow annular jet formed from several continuous single fuel jets. 40-50% of total fuel flow is supplied tangentially, and the rest part of fuel flow is supplied to generated turbulent shifting layer.

EFFECT: enhancement of the method efficiency.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: injector unit of gas-turbine engine combustion chamber includes a plate of annular shape with injector modules installed on it in several rows containing fuel and air channels, and a fuel collector connected to the plate, collector cavity being connected to fuel channels with injector modules. Over three concentric rows of injector modules are installed, the modules are installed with register ledge inserted into blind hole made in the plate. The plate is designed convex towards air flow.

EFFECT: invention is meant for improvement of fuel combustion completion, reduction of harmful emissions at all the modes and provision of uniform temperature field at combustion chamber outlet in a circumferential direction at all the modes.

4 cl, 6 dwg

Drain system // 2244142

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: system is designed for utilization of fuel leaks in drain systems of gas-turbine engines. Proposed system contains drain tank divided into upper and lower spaces by spring-loaded flexible partition. Upper space is connected through check valve and drain valve with nozzle manifolds, through other check valve, with atmosphere, and through third check valve, with fuel pump input. Lower space is connected with high-pressure source through pressure selector. Fuel-air medium sensor is installed under check valve communicating with atmosphere. Selector is made in form of electromagnetic valve with spool device. Check valve connected with fuel pump is located lower than minimum permissible fuel level in tank, level being set by program. Such design of drain system precludes getting of air to fuel pump input and meets ecological requirements as to effective combustion of fuel owing to return of fuel from drain tank into fuel tank at steady state operating conditions of engine.

EFFECT: provision of pollution-free engine.

1 dwg

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