Fuel drainage system gas turbine engine
(57) Abstract:Fuel drainage system is designed for a gas turbine engine. Fuel drainage system gas turbine engine includes a drain tank connected to it via the suction hole line pumping fuel pump and line bypass fuel. Drainage tank with float valve, artery bypass fuel are connected by one end with the outlet of the fuel pump and the other with float valve, made with the placement of the levels of its opening and closing above the level of the intake holes. This embodiment of the system will allow to exclude the ingress of air at the inlet to the fuel pump. 1 Il. The invention relates to the field of aircraft engine industry.Known drainage system gas turbine engine containing drain tank connected to the tank and to the fuel system of the engine, the mainline pumping fuel with established therein shutoff valve and ejector, and placed in the tank and connected with shut-off valve, the fuel level sensor .A disadvantage of the known system is its structural complexity and low reliability of electric machines.Naibolee (CCD), containing drain tank connected to it via the suction hole line pumping fuel pump, highway bypass fuel . After pumping fuel from the drain tank efficiency gear pump is maintained by the circulation of the mixture of fuel with air. However, if the pump is rigidly connected with the rotor of the motor, the duration of pump operation on a mixture of fuel with air can be more than 99% of the resource of the engine, because the pumping of clean fuel does not exceed a few minutes immediately after starting. Long-term work on a mixture of fuel with air leads to premature wear of pump parts and its failure.The technical problem solved by the invention is to improve the reliability of the fuel drainage system by eliminating the ingress of air at the inlet to the fuel pump.This problem is solved due to the fact that the fuel drainage system gas turbine engine that includes a drain tank connected to it via the suction hole line pumping fuel pump, highway bypass of fuel, according to the invention, the drainage tank with float valve, artery bypass fuel receiving levels of its opening and closing above the level of the intake holes.In the inventive design of the drainage tank with float valve, which is made with the placement of the levels of its opening and closing above the level of the intake openings of the drainage tank, and the highway bypass fuel are connected by one end with the outlet of the fuel pump and the other with a float valve that prevents complete pumping fuel from the drain tank by providing a bypass of the fuel within the system and eliminates the ingress of air at the inlet to the fuel pump, thereby reducing wear of the friction surfaces of the parts.The drawing shows a diagram of the fuel drainage system of the CCD.The system includes a drainage tank 1 is connected to it through the intake port 2 and the fuel system 3 engine line 4 pumping fuel with established therein fuel gear pump 5, the filter 6 and the check valve 7 and line 8 of the bypass fuel. Highway 8 bypass connected at one end with the outlet of the fuel pump 5, and the second float valve 9. The levels of the opening and closing valve 9 is located above the level of the intake port 2. Drain the tank 1 is connected to the mains drain 10 fuel drained from the cavities of the engine and venting 11. the time.From drained cavities of motor fuel through line 10 is discharged into the drain tank 1, which leads to the closure of the float valve 9. When the engine is running the fuel through the intake port 2 enters the highway 4 pumping and is pumped by pump 5 through the filter 6 and the opened check valve 7 in the fuel system 3. Since the float valve 9 is closed, the bypass fuel from the output of the pump 5 in the tank 1 is missing.As pumping of the fuel level in the tank 1 is reduced, and the vacant space is filled with air through line 11 venting. At a certain fuel level float valve 8 opens, starts the bypass fuel line 8 because of the gear pump 5 into the drain tank 1.This leads to a decrease of pressure between the pump, closing the check valve 7 and the termination of fuel discharge from the fuel system 3.By continuing the supply of fuel through line 10 into the drain tank 1, the fuel level will rise and float valve 9 closes again. Disabling of bypass fuel will cause an increase of pressure between the pump 5, the opening of the check valve 7 and the allotment received in the tank 1 fuel in the fuel system 3.If the fuel in Greatski 4 and bypass 8 back into the tank 1.The filter 6 performs cleaning of the fuel supplied from the fuel system, and a check valve 7 prevents the flow of fuel back out of the fuel system into the drain.Thus, the proposed fuel drainage system eliminates the ingress of air at the inlet to the fuel pump and thereby reduce wear of the friction surfaces of the parts, improving the working conditions of the pump and increasing the reliability of the system.Sources of information:
1. The magazine "Aviation industry", 1995, N 7-8, page 22, Fig.5B.2. RF patent N 826780, F 02 C 3/24, 1993 Fuel drainage system gas turbine engine that includes a drain tank connected to it via the suction hole line pumping fuel pump, highway bypass of the fuel, characterized in that the drain tank with float valve, artery bypass fuel are connected by one end with the outlet of the fuel pump and the other with float valve, made with the placement of the levels of its opening and closing above the level of the intake holes.
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.
FIELD: mechanical engineering; engines.
SUBSTANCE: invention is designed for draining fuel leaks from manifold and returning fuel into engine fuel system. Proposed device contain drain tank connected with drain fuel source, ejector with working nozzle, outlet and receiving chamber, drain tank shutoff valve, float installed in drain tank and connected with shutoff valve. Constant pressure valve connected with ejector outlet is installed at inlet of ejector working nozzle. Throttling needle with spring and piston is installed in working nozzle of ejector. One space of piston being connected with drain space and the other, with ejector outlet.
EFFECT: prevention of cavitation in ejector and getting of air into fuel system.
FIELD: mechanical engineering.
SUBSTANCE: invention relates to devices and methods of combustion of fuel-air mixture in air-jet engines, small-size gas-turbine engines and gas-turbine plants. Proposed low-pressure nozzle contains annular atomizing edges, body accommodating central air swirler, channel to feed fuel with auger swirler, and outer air swirler arranged on nozzle body. Channel to supply swirled high-pressure air is arranged around fuel feed channel. Two-tier jet outer air swirler is provided with outer and inner inclined holes, air vortex stabilizer and annular outer and inner atomizing edges. Method of fuel atomizing by low-pressure nozzle comes to delivery of fuel and pressure feeding of air through central swirler and outer swirler. Fuel is fed between two swirler air flows formed by central swirler and channel to supply swirler high-pressure air. Flows of air and fuel getting to annular atomizing edges of nozzle form finely dispersed fuel air-mixture. Drops of mixture are atomized by air jets of outer swirler first on its inner annular atomizing edge, and then on outer edge. Said peculiarities of proposed invention increase payload capacity of aircraft, reduce exhaust of harmful substances.
EFFECT: reduced energy losses and expenses.
3 cl, 1 dwg
FIELD: rocketry and aeronautical engineering; fuel systems of flying vehicles.
SUBSTANCE: device proposed for realization of this method includes fuel tanks connected in succession by means of pipe lines; sequence of fuel utilization is estimated by intensity of heating of fuel contained in them.
EFFECT: reduction of temperature at engine plant inlet.
3 cl, 1 dwg
FIELD: metered delivery of fluid medium from supply source to users.
SUBSTANCE: proposed meter includes metering valve sliding in body at working stroke C; this valve has inlet hole for receiving fluid medium from supply source and outlet for discharge of fluid medium to user. Meter is provided with passage for fluid medium for performing washing motion of fluid medium over contact surfaces of valve and body. Passage is formed by helical groove at width L and screw pitch P. Besides that injector is proposed which is fitted with this meter.
EFFECT: avoidance of accumulation of contaminants during flow of fluid medium through meter.
3 cl, 3 dwg
FIELD: mechanical engineering; turbomachines.
SUBSTANCE: proposed fuel injection system contains high-pressure pump for delivering fuel at high pressure from fuel tank, fuel nozzles arranged in combustion chamber of turbomachine and metering device located between said high-pressure pump and fuel nozzles to control rate of fuel getting into fuel nozzles from high-pressure pump. Metering device contains delivery valve operated in accordance with two delivery levels by metering valve to which fuel is delivered from said high-pressure pump. Electrically controlled shutoff valve is provided additionally to cut off fuel delivery to said fuel nozzles.
EFFECT: possibility of limiting heating of fuel and setting optimum dimensions of system components.
5 cl, 2 dwg
FIELD: devices for mixing of fuel components including gaseous and liquid fuel, water vapor and air before their supply to the combustion chamber.
SUBSTANCE: the mixer of fuel components has a fuel supply manifold and a system for preparation of the fuel-containing mixture including a device of multi-point fuel injection. The system for preparation of the fuel-containing mixture is made in the form of a single Venturi tube, the device of multi-point fuel injection installed in the Venturi tube up to its critical section is made in the form of a tore-shaped stream-lined manifold with openings on the outer and inner surfaces. The tore-shaped manifold of multi-point injection is tear-shaped.
EFFECT: simplified and lightened construction of the mixer, reduced friction loss.
2 cl, 2 dwg
FIELD: gas-turbine plants.
SUBSTANCE: system comprises nozzle provided with internal axial space that is terminated by the outlet port for fuel-air mixture at one of its ends. The nozzle has first stage for supplying fuel provided with several first fuel supply openings that enter the internal space, are arranged around the axis of the nozzle, and are connected with the inlet fuel zone through fuel supply passages, and at least one passage for air supply that enters the internal axial space and is connected with the inlet air zone. The nozzle is additionally provided with at least second stage for fuel supply provided with several second fuel supply openings that enter the internal space, are arranged around the axis of the nozzle, and are connected with the inlet fuel zone of the nozzle through the fuel supply passages. The fuel supply passages are in part in coincidence with the fuel supply passages of the first stage.
EFFECT: enhanced quality of fuel-air mixture.
18 cl, 8 dwg
FIELD: mechanical engineering; turbomachines.
SUBSTANCE: fuel system of turbomachine combustion chamber has fuel-feed nozzle providing spraying of fuel in combustion chamber, and mixing-and-deflecting unit arranged symmetrically relative to axis of fuel-feed nozzle and designed to form mixture of fuel oxidizer with fuel and its atomizing in said combustion chamber. Mixing-and-deflecting unit has first swirler and, at least, second swirler arranged with relative displacement along said axis and separated by venture device arranged coaxially relative to fuel-feed nozzle. First swirler is rigidly fastened to said fuel-feed nozzle and is arranged at constant distance from nozzle in radial direction. Distance is chosen so that fuel atomized by fuel-feed nozzle cannot get onto said first swirler.
EFFECT: provision of good atomizing of fuel under all conditions.
5 cl, 5 dwg
FIELD: power engineering.
SUBSTANCE: method comprises injecting compressed air into the system for supplying fuel to the nozzle. The compressed air is injected directly to the fuel injection head downstream of the valves. The injecting is controlled by the signal characteristic for a given stage of operation of the turbine machine. The compressed air is taken at the exit of the compressor, is collected in a tank, and then is injected to the head through the internal pipeline.
EFFECT: enhanced reliability.
12 cl, 8 dwg