The fuel injection system turbojet engine aircraft

 

The invention relates to the field of aircraft engine industry, in particular, to systems fuel injection turbojet engine aircraft. The fuel injection system turbojet engine aircraft contains hydraulically connected by their inputs from the hydraulic pump supply tank of an aircraft motor centrifugal pump and mounted on its shaft in front of him additional screw pump, hydraulically connected with the pump fuel tanks of the aircraft, and input this connection, in the form of tubing placed over the outer surface of the screw wheel in the area of the output area. Motor centrifugal pump connected to the engine via a hydrodynamic torque Converter, which his shaft kinematically connected to the motor shaft and motor shaft of a centrifugal pump and has regulatory authority - the power servopiston associated with the controller of the fuel supply to the injectors of the main combustion chamber, and the inner cavity of the hydrodynamic Converter is connected to the input and output of the motor of the centrifugal pump. Pressure cavity motor of the centrifugal pump is connected to R Rainey combustion chamber. The invention reduces the heater fuel system fuel injection turbojet engine and fuel tanks of the aircraft, thereby improving system reliability and reducing thermal signature of the aircraft. 5 C.p. f-crystals, 2 Il.

The invention relates to the field of aircraft engine industry, in particular, to systems fuel injection turbojet engine aircraft.

A known fuel injection system turbojet engine of the aircraft, containing hydraulically connected by their inputs from the hydraulic pump supply tank of an aircraft motor centrifugal pump connected to its shaft with the motor shaft and communicated its pressure cavity with the regulator fuel supply to the injectors of the main combustion chamber, and mounted on the shaft of motor enrobing pump pump, hydraulically associated with exit nozzles hydraulic pump supply tank of an aircraft [1].

In this system toplivopitanija engines is bukovymi the pumps paging and swapping, the entrance to the turbine which is connected with the engine-driven pump, chastoty rotation of its rotor. Resulting in a slight drop in fuel consumption for the engine and a small change of frequency of rotation of the rotor in flight can experience large heating fuel in fuel tanks and fuel injection system in the engine, resulting in improved mass handling system and a reduction in the reliability of its work.

Task to be solved by the claimed invention is directed, is the reduction in heating fuel systems fuel injection turbojet engine and fuel tanks of the aircraft, allowing to increase the service life of structural elements of the system and thereby improve the reliability of its work, and also allows to reduce the heat radiation from the elements of the fuel injection system of the engine and fuel tanks of the aircraft, thereby reducing thermal signature of the aircraft.

The task is solved in that the fuel injection system turbojet engine of the aircraft, containing hydraulically connected by their inputs from the hydraulic pump supply tank of an aircraft motor centrifugal pump connected to its shaft with the motor shaft and communicated its pressure cavity with the regulator under the pump, hydraulically connected with the nozzles of the hydraulic pump supply tank of an aircraft, an additional pump is made of screw and installed before the motor centrifugal pump, the inlet of its hydraulic connection with the nozzles of the hydraulic pump supply tank is placed over the outer surface of the screw wheel in the area of the output section, and the motor centrifugal pump connected to the engine via a hydrodynamic torque Converter with input and output shafts, kinematically connected respectively to the motor shaft and motor shaft of the centrifugal pump, and with the regulator associated with the controller of the fuel supply to the injectors of the main combustion chamber, moreover, the internal cavity of the hydrodynamic Converter is connected to the input and output of the motor of the centrifugal pump, with the pressure cavity motor of the centrifugal pump is connected with the controller of the fuel supply to the injectors afterburner combustion chamber.

In addition, an additional pump may be hydraulically connected to hydraulic pumps in the tanks pumping fuel the aircraft, and the entrance of this hydraulic connection is combined with the input guy who inogo centrifugal pump can also be connected with the inner cavity of hydropneumatically through channels made in the output shaft of hydropneumatically.

The system can also include a heat sink fuel cooling, and the entrance to the radiator fuel cooling can be hydraulically connected to an output section of a screw pump, and the input of this hydraulic connection is placed over the outer surface of the screw-wheel, and the output of the radiator fuel cooling can be connected to the input of the motor of the centrifugal pump through channels made in the shaft of the pump.

In the requested fuel injection system turbojet engine aircraft elements of propulsion fuel supply system with toplevelbase equipment, including regulators fuel in the main and afterburner the motor circuit, the elements of the fuel system of the aircraft, consisting of systems pumping of fuel from a supply tank and pump the fuel out of the tanks, and the elements of the fuel radiator cooling systems combined into a single integrated system managed by the controller of the fuel supply to the main motor circuit in accordance with a control algorithm turbojet engine that allows you to provide a comprehensive optimum matching of cardinality is p> Installation before motor centrifugal pump screw wheel placed in the area of the output area on the outer surface of the entrance of its hydraulic connection with the nozzles of the hydraulic pump supply tank allows the selection of fuel under pressure generated by a screw wheel, proportional to the magnitude of the fuel flow to the engine, thus enabling the supply of fuel from a supply tank to the centrifugal pump with simultaneous pumping fuel from the tank pump in tank depending on the flow rate of fuel to the engine. With the reduction of fuel consumption by the engine is reduced pumping and pumping fuel from the tank into the tank, resulting in reduced heat generation in the fuel tanks.

The centrifugal pump on the output shaft of the hydrodynamic Converter, the input shaft is kinematically connected to the motor shaft, and having a regulatory authority associated with the controller of the fuel supply to the injectors of the main combustion chamber, provides for each desired mode of operation of the engine fuel supply to the input of the motor of the centrifugal pump with a minimum excess pressure relative to the pressure of the fuel, potrebi is part of a centrifugal pump with controls fuel supply to the nozzles of the main and afterburner combustion chamber provides increased disposable pressure drop afterburner fuel while reducing its heating at high altitude afterburner. In addition, when the engine is turned off afterburner provides the same amount of fuel pressure at the entrance to each of these controls, resulting in faster transition time of the engine in the afterburning mode.

The presence of additional hydraulic connection of the pump with hydraulic pumps in the tanks pumping fuel aircraft and placement of the sign of this relation together with the inlet of the hydraulic connection of additional pump hydraulic pump supply tank of an aircraft allows you to adjust the pace of fuel from tanks pumping rate of fuel feed to the engine from a supply tank. This type of work provides only very slight changes of position of the centre of gravity of the aircraft during the development of fuel in flight.

The system radiator fuel cooling, the output of which is connected to the input of the motor of the centrifugal pump, and an input connected with an output section of an additional pump, provides transportation principal amount of hot drains from sinks fuel cooling at the entrance to the centrifugal pump and then to the nozzles of the main combustion chamber of the engine, except getting hot discharge pump with an internal cavity hydropneumatically through channels made in the output shaft of hydropneumatically, allows to transport fuel, heated hydraulic energy losses in structural elements hydropneumatically, at the entrance to the motor of the centrifugal pump and then to the nozzles of the main combustion chamber of the engine.

In Fig. 1 shows a fuel injection system turbojet engine of the aircraft of Fig.2 presents the requirements for centrifugal and additional pumps.

The fuel injection system turbojet engine aircraft contains installed on an aircraft fuel tank 1 system swap fuel tanks and 2 system pumping fuel in the supply tank 1, which is equipped with hydraulic pumps 3 and 4. As hydraulic pumps mainly used hidrocarbonetos, but in some cases can be installed, for example, the jet pumps.

Hidrocarbonetos 3 in the tank 1 through pipe 5 is hydraulically connected with the centrifugal pump 6 second stage pumping of fuel, kinematically connected through a mechanical gear transmission 7 and a rotor 8 turbojet engine. The output of the hydraulic pump 6 is connected to the SIP. The pump 12 is placed on the shaft 13 of the motor of the centrifugal pump 14, which, in turn, is mounted on the shaft 15 of the turbine 16 hydropneumatically 17 torque. The pump wheel 18 hydropneumatically 17 through a mechanical gear transmission 7 is connected with the rotor 8. In the inner cavity of hydropneumatically 17, namely in circulation 19, set the rotary blades 20, which are United by the regulator hydropneumatically 17 - power servoport 21, connected by communication lines 22 to the controller 23 of the fuel supply 23 to the nozzles 24 of the main combustion chamber of the engine.

Circulation 19 is connected by a channel 25, is made in the output shaft 15 hydropneumatically 17, to the input 26 of the centrifugal pump 14.

The inlet 26 of the pump 14 channels 27, made in the shaft 13 of the pump 14, is also connected with the output hydraulic connection 28 of the radiator 29, 30 fuel cooling power of the cooling system and oil drives generators of the power supply system of the aircraft. Radial clearance 31 between the shaft 13 and the outer diameter of the hydraulic connection 28 is minimal.

Pump 12 has in its housing cavity 32 33 located in the area of its outlet area above darwinulidae of hydrocarbonaceous 3, 4 in the tanks 1, 2. The output of the centrifugal pump 14 by a pipe 35 connected to the controller 23 of the fuel supply to the nozzle 24 of the main combustion chamber and to the controller 36 of the fuel supply to the injectors 37 afterburner combustion engine 9. Before the nozzles 24 and 37 main and afterburner combustion chambers installed sensors measure fuel consumption, 38, 39.

The output of the centrifugal pump 14 channel 40 is associated with a range of circulation 19 hydropneumatically 17.

The system works as follows.

From the rotor 8 turbojet engine 9 through a mechanical gear transmission 7 is driven pump wheel 18 hydropneumatically 17, in which the torque supplied to the rotor 8, is converted into kinetic and potential energy of the fuel flow, filling the circulation 19. The fuel behind the wheel 18 is supplied to the turbine blades 16 hydropneumatically 17, where the energy flow of the fuel is converted into mechanical work on the shaft 15 of the turbine 14, resulting in rotation mounted on this shaft is a centrifugal pump impeller 14 and the screw of the pump impeller 12. Fuel under pressure created by the screw of the pump impeller 12, on the outer surface of this wheel is fed to the input of hydraulic connection 34 with nozzles is of westlea fuel from the tank 1 to the pump 6 and then to the pump 12 with simultaneous pumping fuel from tank 2 to tank 1 and tank 3 to the tank 2.

The pipe 35 of the pump impeller 14 submits under the pressure of the fuel input to the controller 23 of the fuel supply to the nozzle 24 of the main combustion chamber and the entrance to the controller 36 of the fuel supply to the injectors 37 afterburner combustion chamber.

When the engine 9 is disabled, the boost pressure before the regulator 36 has the same value with the fuel pressure regulator 23, resulting in faster transition time of the engine in the afterburning mode with improved flight characteristics of the aircraft in flight while maneuvering.

When changing modes of operation of the engine 9 through the communication lines 22, the controller 23 of the fuel supply at the same time manages power servoport 21, which provides the rotation of the blades 20 in a certain position, resulting in a power turbine 16 hydropneumatically 17 is changed. This leads to changes in speed of the centrifugal pump 14 and the screw pump 12 at a flow rate of fuel to the nozzles 24 of the main combustion chamber changes the pressure created by the pumps 14 and 12, as well as the rate of paging and running out of fuel from the tanks 1, 2.

When fully open the blades 20 of the pump 14 and 12 provide the maximum pressure and provide the highest rate Kimi energy loss in circulation 19 by the operation of the pump turbine wheel 18 16 hydropneumatically 17, occurs at the entrance of the centrifugal wheel 14 through the channels 25 on the inside of the shaft 15 and further goes regulators 23 and 36 to the nozzle 24 and 37.

To start the engine 9, the proposed scheme can be provided for installation of electrically driven pump 41 volumetric type, in particular gear with the bypass valve 42. Gear pump 41 through pipes 42 through valve 44, 45 is connected to the output of the centrifugal pump 14. Installation of the pump 41 allows low frequencies of rotation of the rotor 8 to create a high pressure fuel inlet supply regulator 23, a good ignition of the fuel in the combustion chamber at startup, allowing the reduction of the time of engine start. Washing pump 41 is made from a battery on-Board power supply system DC aircraft.

The proposed scheme of operation of the fuel system allows a significant reduction of heating fuel in the tanks, and at the entrance to the centrifugal pump 14 on the most heat-stressed flight modes of the aircraft, especially on the long cruise and modes tall small gas engine. So at cruising speed when the fuel consumption of the turbojet dvigateli fuel in the primary circuit can reduce the fuel pressure at its input 4-5 times, what with simultaneous influence on the power servopiston 21 due to the rotation of the blades 20 leads to a sharp drop of the rotational speed of the centrifugal pump 14 and the screw pump 12, thus reducing heat generation in the fuel according to the cubic dependence on the change of the rotation frequency. Although the efficiency of hydropneumatically 17 these modes decreases, the total power loss in fuel injection pumps and tank pumps cut several times, substantially reducing the heating fuel.

One of the primary features of the proposed system is also installed on most operating modes of the engine of the transportation principal amount of hot drains from sinks fuel cooling at the entrance to the centrifugal pump 14 and then to the nozzles 24 of the main combustion chamber with a guaranteed reduction in the possibility of getting hot dumping fuel in the fuel tanks because of the leakage of hot fuel in the gap 31 is extremely small. The differential pressure between the inlet and outlet of the radiator fuel cooling required for pumping the fuel occurs due to the work of auger wheel pump 12, on the outer surface which creates a pressure exceeding the pressure of the flow near the shaft 13.

Sources of information 1. USSR author's certificate 183606, IPC 6 64 D 37/00, 1966

Claims

1. The fuel injection system of turboreactor the m pump supply tank of an aircraft motor centrifugal pump, connected to its shaft with the motor shaft and communicated its pressure cavity with the regulator fuel supply to the injectors of the main combustion chamber, and mounted on the shaft of motor enrobing pump pump, hydraulically connected with the nozzles of the hydraulic pump supply tank of an aircraft, characterized in that an additional pump is made of screw and installed before the motor centrifugal pump, the inlet of its hydraulic connection with the nozzles of the hydraulic pump supply tank is placed over the outer surface of the screw wheel in the area of the output section, and the motor centrifugal pump connected to the engine via a hydrodynamic torque Converter with input and output shafts, kinematically connected respectively to the motor shaft and motor shaft of the centrifugal pump, and with the regulator associated with the controller of the fuel supply to the injectors of the main combustion chamber, and the inner cavity of the hydrodynamic Converter is connected to the input and output of the motor of the centrifugal pump, with the pressure cavity motor of the centrifugal pump is connected with the supply regulator fuel force associated with hydraulic pumps in the tanks pumping fuel consumption of the aircraft, the input of this hydraulic connection is aligned with the inlet of the hydraulic connection of an additional pump with nozzles hydraulic pump supply tank.

3. The system under item 1 or 2, characterized in that the input of the motor of the centrifugal pump is connected with the inner cavity of hydropneumatically through channels made in the output shaft of hydropneumatically.

4. System according to any one of paragraphs. 1-3, characterized in that it contains a radiator fuel cooling.

5. System according to any one of paragraphs. 1-4, characterized in that the entrance to the heat sink fuel cooling hydraulically connected to an output section of a screw pump, and the input of this hydraulic connection is placed over the outer surface of the screw wheel.

6. System according to any one of paragraphs. 1-4, characterized in that the output of the radiator fuel cooling is connected to the input of the motor of the centrifugal pump through channels made in the shaft of the pump.

 

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