The drainage device of a gas turbine engine with compressor
(57) Abstract:Usage: in the aircraft engine industry. The inventive drainage device comprises a drain tank 1 to the intake opening 2 and which to the input and output pipes pre-supply pump 3 is connected to the fuel injector 4. In line 5 of the fuel discharge installed shut-off valve 6 and valve 7. Perelivnoj element 8 shut-off valve 6 has an actuator in the form of a membrane 9, in the control cavity 10 which is placed the spring 11. The device also includes an air ejector 12, the active nozzle which is connected to the compressor of the engine, the mixing chamber with the tank 1, and the passive nozzle communicated with the control cavity 10 and through a nozzle 13 with a signal hole 14 of the tank 1. Moreover, the hole 14 is located at a level above the intake openings. 1 Il. The invention relates to aircraft engine industry, and more specifically to fuel drainage systems of gas turbine engines (GTE).Known drainage device GTE containing drainage tank, placed in the fuel tank ejector mounted in-line removal of fuel from the tank check valve and located in front of the active nozzle of the ejector solenoid shutoff valve  P is providing shut-off valve is supplied from the button start the engine.A disadvantage of the known device is that, due to the need for accommodation in the drainage tank ejector tank should have sufficient height sizes. In some cases, to install such tanks in the lower points of the engines due to the limited dimensions is not possible, which makes it difficult to use this device on GTE.Closest to the invention to the technical essence and the achieved result is a drainage device GTE containing drain tank connected to the intake opening of the tank and to the input and output pipes of the transfer pump fuel ejector, and managed cutoff (float) and check valves are installed in-line removal of fuel between the tank and the ejector  In this device, when the engine is running fuel is drawn from the tank by the ejector and discharged into the inlet of the transfer pump. Control shut-off valve carried by the float for the fuel level in the tank.A disadvantage of the known drainage device is that the cutoff (float) valve must be placed inside the tank, since the float monitors the fuel level. This leads to higher dimensions tank height and condition aceveda scope of such devices, and difficult because of their unification.These drawbacks are eliminated when using a drainage device having a drain tank with a small height and a more simple design. If the prototype control shut-off valve is carried out using a float placed in the drainage tank, in the inventive device shut-off valve controls the air ejector with the nozzle in the suction line, allowing these elements and shut-off valve be placed separately from the tank and thereby to perform the drainage tank is the minimum size and to simplify its design. These advantages of the proposed device allows you to place drainage tanks in the lowest points of the engine, providing recycling merging of fuel, and to unify the elements located outside the tank, to combine them into a single unit and mounted in any convenient location on the engine.The invention consists in that the drainage device of the CCD containing the drainage tank, fuel injector, connected to the intake opening of the tank and to the input and output pipes of the transfer pump, and installed in-line removal of fuel between the tank and fuel ejector managed Taisto additionally there is an air ejector, active nozzle which is connected to the compressor of the engine, the camera offset to the tank, and the passive nozzle communicated with the control cavity servo and through a nozzle with a signal hole tank located at a level above the intake openings.The drawing shows a diagram of the inventive drainage device.The drainage device comprises a drain tank 1 to the intake opening 2 and which to the input and output pipes pre-supply pump 3 is connected to the fuel injector 4. In line 5 of the fuel discharge installed shut-off valve 6 and valve 7. Diverter element 8 shut-off valve 6 has an actuator in the form of a membrane 9, in the control cavity 10 which is placed the spring 11. The device also includes an air ejector 12, the active nozzle which is connected to the compressor of the engine, the mixing chamber with the tank 1, and the passive nozzle communicated with the control cavity 10 and through a nozzle 13 with a signal hole 14 of the tank 1. The hole 14 is located at a level above the intake openings 2.Drainage device operates as follows.Of the units 15, the fuel is discharged into the tank 1. During engine operation to the active nozzle of the ejector 4 is fed fuel from vychodne 12 creates a vacuum in the control cavity 10, the value of which depends on the fuel or air podkashivayutsya through a nozzle 13. If the fuel level in the tank 1 above the signal holes 14, through a nozzle 13 to the ejector 12 is supplied fuel and the pressure in the cavity 10 such that the spring 11 holds the membrane 9 and overlaps the element 8 in the right (open) position. Under the influence of the vacuum created by the ejector 4, the check valve 7 opens, and from the tank 1 through the suction hole 2 through line 5 is the removal of the fuel and its supply at the inlet of the transfer pump 3. Reducing the level of fuel in the tank is below the signal holes 14 causes the flow through the nozzle 13 to the ejector 12 air instead of fuel. This causes a sharp increase in the vacuum in the cavity 10, the membrane 9 compresses the spring 11 and moves the diverter element 8 shut-off valve 6 to the left (closed) position. Line 5 fuel discharge is blocked or remove fuel from the tank 1 is terminated.If the fuel level in the tank again rises above the openings 14, there is a decrease in the vacuum in the control cavity 10, the opening shut-off valve 6 and the removal of fuel. The air coming into the tank 1 from the ejector 12, is discharged through the opening 16 in the atmosphere is Azad from the fuel system into the tank 1.When the flow of fuel through the nozzle 13 mass flow rate GGTand the differential pressure PGTon the jet connected by the relation
GGTwheretthe density of the fuel;
Pbthe pressure in the tank;
PUPTthe pressure in the control cavity 10 when the flow through the nozzle 13 of the fuel.At low differential pressure mass air flow (GWWthrough a nozzle 13 is also connected with the pressure difference ( PWW) ratio
GWWwhereinthe density of air;
POlathe pressure in the control cavity 10 when the flow through the nozzle 13 of the air.For ejector can be written
GEOLnEOL.Ginwhere GEOLconsumption, environment, sucked by the ejector;
Ginair flow through the active nozzle of the ejector;
nEOLthe coefficient of ejection (Sokolov E. Y. singer, N. M. Inkjet units. M Energy 1970).The coefficient of ejection connected with the pressure at the inlet and outlet of the ejector by the following ratio:
nEOLwhere Rinthe air pressure in front of the active nozzle of the ejector 12;
Psunthe pressure in the cavity of the suction , leads to the reduction of mass flow rate through the nozzle. Indeed, if we assume RWWPGT,in1.2 kg/m2andt780 kg/m3then
22,5 i.e. the mass flow rate of air 22.5 times smaller than the mass flow of fuel. Since GEOLGWW(previously GEOLGVT)in the same time decreases and the flow sucked by the ejector 12. But since Ginconst, it means that decreases the coefficient of ejection, which is possible only (Pbconst, Rinconst) at reduced pressure RVS, i.e., with increasing dilution.Previously it was accepted for PWWPGT. Actually, Rvers< PUGTand RWW> PGT. However, attitudes are always a lot of sensecam attitude and the final result is not changed.From the above it follows that the admission of air instead of fuel through the nozzle 13, the magnitude of the vacuum in the control cavity increases.Thus, the device allows you to place drainage tanks in the lowest points of the engine, providing recycling merging of fuel. Both ejector shutoff and check valves and the nozzle can be manufactured as a single unified unit by placing it in any convenient place on the engine. Tenantable tank shut-off valve with actuator, connected to the fuel injector associated with the fuel pump, characterized in that it comprises an air ejector with active, passive nozzles and the mixing chamber and the nozzle, the actuator shut-off valve is made in the form of a spring-loaded diaphragm, which is located in its management of the cavity, and in the side wall of the tank made the hole, and an active air nozzle of the ejector is connected to the compressor of the engine, a mixing chamber with drainage tank, and the passive nozzle communicated with the control cavity of the actuator and through a nozzle with a hole in the side wall of the tank.
FIELD: power industry.
SUBSTANCE: fuel nozzle comprises a passage for the in-line fuel mixture directed into the combustion chamber, which extends through the fuel injector in the longitudinal direction. Fuel nozzle is, moreover, may comprise a channel for liquid fuel which covers at least part of stream passage. The channel may comprise a plurality of fuel nozzles formed for delivering liquid fuel from the fuel passage to the inline passage. The fuel injector may also include an annular outer casing which surrounds the said channel, forming an insulating air cavity, at least around a portion of mentioned channel. The outer shell may comprise at least one opening for purging, providing communication between the insulating air space and an annular shroud surrounding space. It is also provided with a method of bi-fuel gas turbine engine operation.
EFFECT: invention allows to maintain the temperature of the liquid fuel channel below the temperature of the fuel injector fuel coking.
10 cl, 5 dwg
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