Method and system to generate power to drive engine auxiliary components

FIELD: engines and pumps.

SUBSTANCE: invention is intended for feeding electric power to equipment from gas turbine engine. The proposed system comprises an electronic control device to control, at least, one parameter containing the data on originating variation in consumed power, a control valve controlled by aforesaid system and feeding air take off the engine operated in transient conditions and a pneumatic device receiving aforesaid taken-off air to actuate the aircraft onboard equipment. The latter can represent an air turbine or generator with built-in pneumatic circuitry.

EFFECT: use of engine pneumatic power to drive aircraft onboard equipment.

33 cl, 10 dwg

 

The technical field to which the invention relates.

The present invention relates to a method and system power equipment from the gas turbine engine. In particular, the present invention provides a hybrid power supply system equipment engine, which provides improved performance characteristics of gas turbine engine.

The level of technology

Removing power from the gas turbine engine is usually produced using mechanical gearbox, which is driven by a PTO shaft that is directly connected to one of the main driving shaft of the engine. The gear set in such a way as to ensure the possibility of accession by any of the equipment driven by the engine, such as fuel pump, oil pump, hydraulic pump, generators, etc. Reducer converts the mechanical energy of the shaft of the gas turbine into mechanical energy of the shaft of the equipment elements.

The high pressure compressor of a gas turbine working in steady state, which corresponds to the one presented in figure 1, the working line 10 growth of air flow through the compressor and relationship pressures by increasing the speed of rotation of the rotor. The range of possible modes of operation of the compressor per Nicene line 12 stop for which maintaining a steady flow of air through the compressor is impossible. Working line 10 of the compressor at a given air flow rate corresponds to smaller values of the ratio of pressures than line 12 stop that provides stability margin for engine operation in unsteady mode. During acceleration of the engine compressor parameters deviate from the working line 10 steady state and change in accordance with the working line 14 of the unsteady regime. In the case of a typical high-pressure compressor working line 14 of the unsteady regime is characterized by lower stability margin in the operating range of the engine parameters. As shown in figure 2, the power consumption of the auxiliary equipment negatively affects the work in the unsteady mode due to the decrease of the available stability margin.

In the known solutions of the energy production equipment for gas turbines provide mechanical means through a few gears and gear shaft attached to the rotor of a high pressure engine. Electric and hydraulic power for aircraft systems, as well as the driving force of oil and fuel pumps engine are installed on the engine mechanical drive equipment. A significant proportion powerfully the tee shaft, taken at the same time, reduces the stability margin of the engine in the transient mode, as shown in figure 2.

There are several solutions that allow operation of the engine in the unsteady mode, taking into account the above constraints. So, may be reduced the speed of acceleration of the engine; however, this reduction may not be compatible with requirements for the safety of the aircraft in emergency circumstances, such as when bending around obstacles. Increase the minimum number of revolutions of the rotor of a high pressure at idle, leading to an increase in thrust at idle, and, consequently, reducing the range of possible values of thrust (thrust at idle, to thrust at maximum power), also allows you to reduce the speed of acceleration and deflection in unsteady mode. However, it can also be compatible with the desired modes of operation of the aircraft, since a higher number of revolutions at idle, it leads to an increase in thrust at idle, which requires more altitude before landing aircraft. With regard to operation at idling associated with the profile of the lower plane and manageability thrust necessary to ensure the safety of the aircraft, the variation of the compressor when operating in the transient mode is, what about the fact, fixed, which leads to the need to reduce the load on the rotor of the high pressure created by the PTO for the equipment operation.

The bleed air from the compressor can be used for removing the working line of the compressor from the line overload. This technology is widely used in the known solutions; however, it is characterized by certain disadvantages, in particular by increasing the level of engine noise and the influence heated to high temperatures of exhaust elements fairing (casing) of the engine.

There is a need for a system which would reduce the mechanical load on the shaft and would allow the systems to absorb and use the energy of the air taken from the compressor at low power.

Disclosure of inventions

Thus, the problem to which the present invention is directed, is to offer the system in which the pneumatic energy can be used to produce power for actuation of the equipment installed on Board the aircraft, at the same time ensuring the advancement of the working line of the compressor of the gas turbine relative to a line compressor overload (increased stability margin).

Another problem to which the present invention is directed, is pre the Appendix how to use the pneumatic energy of the engine to actuate the equipment, installed on Board the aircraft, at the same time ensuring the advancement of the working line of the compressor of the gas turbine relative to a line compressor overload (increased stability margin).

The objectives are achieved by a system and method according to the present invention.

In accordance with this invention features a hybrid power supply system equipment of the engine. The system generally includes means for monitoring at least one parameter containing information about the beginning of the change of the power consumption, money supply air taken from the engine when it is operating in unsteady mode depending on the specified at least one controlled parameter, and pneumatic means for receiving the selected air and energy production for the actuation of equipment installed on Board the aircraft. Controls include electronic control engine that receives at least one incoming signal of starting the change of the power consumption.

Electronic engine control contains a stand-alone digital engine management system.

Money supply selected contain air control valve, open or adjustable signal is a stand-alone digital engine management system.

The control gate is made with collateral in its open position, the intake air taken from the compressor high pressure specified by the engine, these pneumatic tools.

The system further comprises a feedback circuit to transmit a signal representing the state of the valve, the electronic control device.

Pneumatic tools provide the generator with integrated Pneumatics for the production of electricity from order to actuate at least one of the elements selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

Pneumatic tools provide the generator with built-in pneumatic system for supplying mechanical energy to the gearbox with the purpose of actuating at least one of the elements selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

Pneumatic tools contain an air turbine mounted on the gearbox, to supply mechanical energy to the gearbox with the purpose of actuating at least one of the elements equipped with the I, selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

Pneumatic tools contain an air turbine connected to the shaft of the gearbox through a system of shafts and gears, and air turbine is arranged to supply mechanical energy to the gearbox with the purpose of actuating at least one of the elements selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

Pneumatic tools contain an air turbine connected to the gearbox, and also include a generator coupled to the gearbox and driven by an air turbine.

Pneumatic tools contain an air turbine and a generator driven by an air turbine to supply energy to at least one system installed on Board the aircraft.

Pneumatic tools are designed to increase the process stability margin of the high pressure compressor of the gas turbine engine.

In addition, in accordance with the present invention proposes a method of power supply equipment of the gas turbine engine. The method in General comprises the step of controlling at least one parameter containing information about the beginning of the change of the power consumption, stage bleed air from the engine when it is running in transient mode is performed depending on the specified at least one controlled parameter, and the stage of submission of selected air to pneumatic tools production of energy for actuation of the equipment installed on Board the aircraft.

On the phase control signal to change consumption in aircraft power from the control panel in the Autonomous digital engine management system.

On the phase control signal to change the power consumption of the electricity generator and offline digital engine management system.

On the phase control signal representing a change in torque of the drive shaft and indicating the change of the power consumption in Autonomous digital engine management system.

On the phase control signal corresponding to the load on at least one electricity generator, Autonomous digital engine management system.

At the stage of controlling served at least one signal representing the change in consumption is Amnesty, in the electronic control device, during air sampling signal from the electronic control device on the control valve that supplies a flow of air taken from the high pressure compressor of the gas turbine engine, these pneumatic tools.

Submit feedback signal representing the state of the valve, the electronic control device.

At the stage of filing serves selected air generator with integrated Pneumatics, intended for the supply of energy to actuate the at least one piece of equipment connected to the gearbox.

Generate electricity through a generator with built-in pneumatic and serves electricity to at least one item of equipment.

Produce mechanical energy of rotation of the shaft by means of a generator with a built-in pneumatic and serves the mechanical energy of rotation of the shaft on the gearbox for the drive system of energy transfer order to actuate the at least one piece of equipment.

At the stage of filing serves selected air to the air turbine is installed on the gearbox, to produce mechanical energy of rotation of the shaft in order to actuate at least one piece of equipment through the transmission system.

The item of equipment is Oia contains the generator, attached to the gearbox, and the mechanical energy of rotation of the shaft produced by the air turbine is passed to the generator.

At the stage of filing serves selected air to the air turbine connected to the gearbox at least one shaft, for producing mechanical energy of rotation of the shaft in order to actuate at least one piece of equipment through the transmission system.

At the stage of filing serves selected air to the air turbine and transmit the energy from the air turbine to the generator to power at least one system of the aircraft.

The energy produced by these pneumatic means are used to actuate at least one of the following items of equipment: generator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

Stage bleed air and the stage of submission of selected air exercise with a decrease in the consumption of mechanical energy of rotation of the rotor of a high pressure engine and lowering operating line of the compressor, thereby providing the possibility of a transfer in unsteady mode with improved stability margin.

Output output the selected air through these pneumatic among the ETS to reduce the temperature and velocity of the exhaust stream, thereby reducing exhaust noise and improving compatibility with the elements of the fairing of the engine.

Release the selected air from these pneumatic tools under the fairing.

Stop filing selected air after passing through the point of minimum stability margin in the boost feature.

Brief description of drawings

Other features of the hybrid system power equipment engine according to the present invention, as well as other objectives and advantages of the invention set forth in the following detailed description and the accompanying drawings, in which used digital signs corresponding to similar elements. In the drawings:

- figure 1 shows a graph illustrating the working line and line overloads gas turbine engine,

- figure 2 shows a graph of the dependence of the stability margin thrust from gas turbine engine,

- figure 3 schematically depicts the architecture of the hybrid system power equipment engine according to the present invention,

- figure 4 schematically depicts a first variant implementation of the hybrid system power equipment engine according to the present invention,

- figure 5 schematically depicts a second variant implementation of the hybrid system power equipment engine really invented the Yu

- 6 schematically depicts a third alternative implementation of the hybrid system power equipment engine according to the present invention,

- 7 schematically depicts a fourth variant of the implementation of the hybrid system power equipment engine according to the present invention,

- Fig schematically depicts a fifth variant of the implementation of the hybrid system power equipment engine according to the present invention,

- figure 9 schematically depicts a sixth variant of the implementation of the hybrid system power equipment engine according to the present invention,

figure 10 presents a view in section of a pneumatic device that is used in different variants of implementation of the hybrid system power equipment engine according to the present invention.

The implementation of the invention

The present invention is directed to a system that simultaneously provides a reduction of the mechanical load on the shaft and allows the systems to absorb and use the energy of the air taken from the compressor at low power. Engine operation in the transient regime can be improved or optimized by combining several known components of control and power. In the system of the present invention installed on DWI is the motor power system can operate using only mechanical energy in normal operating conditions in a steady mode and to use a combination of pneumatic and mechanical energies at work in unsteady mode. In the framework of the present description, the term "transient mode" means any change in the power consumption that occurs with the change of power consumption by the engine due to the change in its status or change consumption of mechanical energy or electricity-related status of any piece of equipment. In some flight regimes using a combination of pneumatic and mechanical energy may be desirable when working in steady state. The inclusion of air bleed from the compressor allows to reduce the working line, which increases the stability margin (point b In figure 1). Selected air is directed into the pneumatic device, which reduces the mechanical power from the rotor shaft of the high pressure gas turbine engine. The decrease in mechanical power leads to lower operating line of the compressor, which causes an additional increase of the stability margin to change parameters in unsteady mode, as illustrated by the line 18 in figure 1.

Figure 3 schematically shows the architecture of a hybrid system power equipment engine according to the present invention. The drawing shows a motor 40 that contains the compressor 90 high pressure, is connected with the shaft motor. Power is transmitted from the shaft 92 of the rotor to the gearbox 46 through the shaft of the power takeoff (not shown). The gear 46 is used to generate power for items of equipment such as starters/generators 52, and possibly other devices such as another generator (not shown). The system also includes a pneumatic device 42, described below, which is used for supplying power to the gear 46, and/or driven equipment. In addition, as described below, the device 42 receives the air taken from the compressor 90 or other parts of the motor 40 when the engine is in transient mode to reduce the load on the shaft 92 of the rotor and, consequently, increase the stability margin of the engine.

Figure 4 illustrates a first variant implementation of the hybrid system power equipment engine according to the invention. As discussed above, the system 30 may be used to control the operation of gas turbine engine or other equipment of the aircraft in steady-state or transient mode. The system 30 uses pneumatic or electronic device 32 controls. In a preferred embodiment of the invention, the device 32 may be a standalone digital engine control system (FADEC); however, in alternative variationbetween device 32 may be a pneumatic control device, which receives the sensor signal on the need to reduce the torque of the gearbox and delivers the pneumatic energy to the device pneumatic turbo drive. The device 32 may regulate operation of the motor in steady or unsteady mode by changing the fuel and may be any known device FADEC. The device 32 may also control the selection of air from the compressor of the engine when operating in unsteady mode. The device 32 receives the information about the power consumed by the generator through the gearbox, using one or more of the following methods of signaling: (1) input signal 34 from the control panel in the cockpit to indicate the change of the power consumption of the aircraft; (2) input signal 37 from the control generator to indicate the change of power consumption; (3) input signal 39 corresponding to the torque change any of the leading shaft, for example the drive shaft of the generator detected by the sensor 41, preferably mounted on the shaft, and indicating the change of the power consumption; and/or (4) input signal 36 corresponding to the change in the power consumption of one or more generators. The incoming signal 36 may be supplied from a device that regulates the power, you who emotively generator or generators, or from sensors that monitor the power output of the generator or generators. Receipt of any of these signals or all of them informs the device about 32 begins to increase or decrease power consumption and, therefore, have occurred or expected transition in unsteady mode.

Upon receipt of the signal about the change of the power consumption device 32 transmits the valve 38 signal, which causes the opening or adjustment state of the valve. When you open the valve 38, the air taken from the engine, for example from a compressor 90 motor 40, which may be a high pressure air compressor, or from another part of the engine 40, is fed into the pneumatic device 42, which may be a generator with integrated Pneumatics. Within the system of the present invention, the signal corresponding to the state of the valve is transmitted to the device 32 through the circuit 44 feedback.

Pneumatic device 42 may be any known device is designed to transmit the mechanical energy of the shaft to the gearbox 46 order to actuate the motors 48 items of equipment, such as fuel pump, oil separator (dealer), generator permanent magnet (PMA), oil pump, hydraulic pump, generators and/or one who does several starters/generators. In an alternative embodiment, the device 42 may be any known device used to produce electricity for motors of one or more of the above items of equipment or other items that consume energy. As the device 42 can be used, for example, but not exclusively, such pneumatic devices, such as an air turbine, an auxiliary pneumatic power unit, blowers, pneumatic starters, pumps and other pneumatic devices that produce power. Electrical or mechanical energy produced by the device 42 and is used to actuate items of equipment, compensates for the additional load on the generators and reduces the power extracted from the rotor shaft of the engine.

Using entering the device 32 management information about the selection of air from the compressor and consumption of electricity from the generator, the device 32 may control the production of pneumatic energy. Manage production of pneumatic energy can reduce the load on the engine and to provide a greater stability margin operating line of the compressor.

In the embodiment according to figure 5 pneumatic device 42' is a controller who's turbine, mounted on the gearbox 46. As an air turbine may be used any known device for generating mechanical energy which is transmitted to the main shaft 50 of the gear 46 using any suitable known means. As shown in the diagram, the air turbine rotates a shaft 50 connected with several items of equipment using any known means of energy transfer, such as a system of shafts with gears. Items of equipment driven thereby, include the starter/generator 52, the fuel pump 54, the separator 56, the generator 58 permanent magnet, oil pump 60 and the hydraulic pump 62. For the person skilled in the art it is obvious that this or a similar system can also be used to actuate other mechanical devices, such as generators.

As described in the above embodiment, the air taken from the compressor 90 motor 40 or other parts of the engine 40, served in the air turbine 42' at the opening of the control valve 38 electronic device 32 of the control.

Figure 6 shows a variant of the system shown in figure 5. In this embodiment, the air turbine 42' is not installed on the gearbox 46. Instead, the air turbine 42' is installed in the aircraft separately from the gearbox and mechanical the th energy comes from the air turbine 42' on the shaft 50 through a system of shafts 70 and gear, contains the node 72 bevel gear and drive shaft 74 that is connected with the shaft 50 through the node 76 gear. For the person skilled in the art it is obvious that instead of these elements can also be used other solutions are equivalent to the described embodiment implementation of the present invention.

7 illustrates another variant implementation of the hybrid drive equipment of the engine according to the present invention. In this embodiment, the air turbine 42 is not installed on the gearbox 46. Instead, the air turbine 42 is installed in the aircraft separately from the gearbox. The air taken from the compressor 90 or other part of the gas turbine engine 40, as necessary, enters the air turbine 42 through the valve 38. The valve 38 is actuated or adjusted by the electronic device 32 controls as described above. Air turbine 42 is used to supply energy to the generator 61. Energy may be supplied with air turbine 42 to the generator 61 in the form of mechanical energy of rotation of the shaft or electricity depending on the type of air turbine. The electricity produced by the generator 61, then fed into the system, installed on Board the aircraft, or any additional equipment that consume power for actuation systems and/or equipment is tion. For the person skilled in the art it is obvious that instead of these elements can also be used other solutions are equivalent to the described embodiment of the implementation of the hybrid system power supply equipment according to the present invention.

On Fig presents another variant implementation of the hybrid system power equipment engine according to the present invention. In this embodiment, the air turbine 42 is installed on the end of the gearbox 46. Air turbine 42 rotates the shaft 45, which in turn rotates the shaft 50 and the shaft connected to the different elements of the equipment, including, not excluding the possible presence of other equipment, starters/generators 52, the fuel pump 54, the separator 56, the generator 58 permanent magnet, oil pump 60 and the hydraulic pump 62, through any known transmission or gear system 47. If necessary, the air turbine 42 can be used to power other equipment such as a generator (not shown). As described above, the flow of sampled air in the air turbine 42 is regulated by a valve (not shown)that is opened or operated electronic device 32 control, such as a FADEC system. For the person skilled in the art it is obvious that instead of these elements could also is t to be used other solutions equivalent to the described embodiment of the implementation of the hybrid system power supply equipment according to the present invention.

Fig.9 illustrates another variant implementation of the hybrid system power equipment engine according to the present invention. In this embodiment, the air turbine 42 is installed on the end of the gearbox 46. Air turbine 42 rotates the shaft 45, which provides the mechanical energy of rotation of the shaft generator 61 also mounted on the end of the gearbox 46. The energy produced by the generator 61 may be used to actuate the various elements of the equipment, including, not excluding the possible presence of other equipment, starters/generators 52, the fuel pump 54, the separator 56, the generator 58 permanent magnet, oil pump 60 and the hydraulic pump 62, through any known transmission system (not shown). As described above, the flow of sampled air in the air turbine 42 is regulated by a valve (not shown)that is opened or operated electronic device 32 control, such as a FADEC system. For the person skilled in the art it is obvious that instead of these elements can also be used other solutions are equivalent to the described embodiment of the implementation of a hybrid energy system equipment the project according to the present invention.

Figure 10 presents the pneumatic device 42, which can be used in any of the embodiments of the hybrid system power supply equipment according to the present invention. The device 42 is a device pneumatic turbo drive containing the turbine 80. The device 42 may be optionally attached to the gearbox by means of a flange 82. The mechanical energy produced by the device 42 may be passed through slot 84. A useful feature of this system is that the exhaust stream leaving through the outlet 86 may be taken under the fairing of the engine, an output path, outside the aircraft, in the exhaust system of an internal contour of the engine or in any other place. Another useful distinction is that the transmission output of sampled air through the drive system can reduce the temperature and velocity of the exhaust, resulting in reduced exhaust noise and improves compatibility with the elements of the fairing of the engine.

In General all systems presented in figure 4-9, are as follows.

When you change the steady-state operation of the engine, for example the decrease in engine speed below the recommended upper limit rotation speed of the rotor, or when the change in saving the consumption items of equipment device 32 control gives the command to open the system bleed air from the engine. Selected air enters the pneumatic device 42 and 42', which produces more energy, mechanical or electrical required for operation of the equipment elements. After passing through the point of minimum stability margin acceleration system bleed air from the engine can be closed, which increases the efficiency of the engine.

Hybrid power supply system equipment of the engine according to the present invention can be used with any gas turbine engines, including single-stage, 2-5-cascade and/or three-stage gas turbine engines, but not limited to.

Submitted in accordance with the present invention, a hybrid power supply system equipment engine fully complies with the above objectives, means and advantages. Although the present invention is described in the context of the specific variants of its implementation, for the specialist in this field who reviewed this description, it is evident the possible existence of other alternatives, modifications and variations of its implementation. The present invention encompasses such variations, modifications and variations in accordance with a broad interpretation of the appended claims.

1. The way the power equipment from the gas turbine engine, comprising the steps:
the extraction of the air from the gas turbine engine when it is running in transient mode is performed depending on the specified at least one monitored parameter;
submission of selected air to pneumatic tools production of energy for actuation of the equipment installed on Board the aircraft.

2. The method according to claim 1, characterized in that the phase control signal to change consumption in aircraft power from the control panel in the Autonomous digital engine management system.

3. The method according to claim 1, characterized in that the phase control signal to change the power consumption of the electricity generator and offline digital engine management system.

4. The method according to claim 1, characterized in that the phase control signal representing a change in torque of the drive shaft and indicating the change of the power consumption in Autonomous digital engine management system.

5. The method according to claim 1, characterized in that the phase control signal corresponding to the load on at least one electricity generator, Autonomous digital engine management system.

6. The method according to claim 1, characterized in that the step of controlling served at least one signal representing a change of the power consumption in an electronic control device, during air sampling signal from the electronic control device on the control valve that supplies a flow of air taken from the high pressure compressor of the gas turbine engine, these pneumatic tools.

7. The method according to claim 6, characterized in that serves the feedback signal representing the state of the valve, the electronic control device.

8. The method according to claim 1, characterized in that at the stage of filing serves selected air generator with integrated Pneumatics, intended for the supply of energy to actuate the at least one piece of equipment connected to the gearbox.

9. The method according to claim 8, characterized in that generate electricity through a generator with built-in pneumatic and serves electricity to at least one item of equipment.

10. The method according to claim 8, characterized in that the produced mechanical energy of rotation of the shaft by means of a generator with a built-in pneumatic and serves the mechanical energy of rotation of the shaft on the gearbox for the drive system of energy transfer order to actuate at least one element of the equipment.

11. The method according to claim 1, characterized in that at the stage of filing serves selected air to the air turbine is installed on the gearbox, to produce mechanical energy of rotation of the shaft in order to actuate at least one piece of equipment through the transmission system.

12. The method according to claim 11, characterized in that the piece of equipment contains a generator attached to the gearbox, and the mechanical energy of rotation of the shaft produced by the air turbine is passed to the generator.

13. The method according to claim 1, characterized in that at the stage of filing serves selected air to the air turbine connected to the gearbox at least one shaft, for producing mechanical energy of rotation of the shaft in order to actuate at least one piece of equipment through the transmission system.

14. The method according to claim 1, characterized in that at the stage of filing serves selected air to the air turbine and transmit the energy from the air turbine to the generator to power at least one system of the aircraft.

15. The method according to claim 1, characterized in that the energy produced by these pneumatic means are used to actuate at least one of the following items of equipment: generator, starter and/or alternator, fuel pump, macloud the amplifier generator permanent magnet, oil pump and hydraulic pump.

16. The method according to claim 1, characterized in that the stage of selection of the air and the stage of submission of selected air exercise with a decrease in the consumption of mechanical energy of rotation of the rotor of a high pressure engine and lowering operating line of the compressor, thereby providing the possibility of a transfer in unsteady mode with improved stability margin.

17. The method according to claim 1, characterized in that the output produced by the selected air through these pneumatic means to reduce the temperature and velocity of the exhaust flow, thereby reducing exhaust noise and improving compatibility with the elements of the fairing of the engine.

18. The method according to claim 1, characterized in that the release of the selected air from these pneumatic tools under the fairing.

19. The method according to claim 1, characterized in that the stop filing selected air after passing through the point of minimum stability margin in the boost feature.

20. Power supply system equipment from the gas turbine engine, comprising:
controls at least one parameter containing information about the beginning of the change of the power consumption;
means to supply air taken from the gas turbine engine when it is running in Postnov VSENSE mode, depending on the specified at least one monitored parameter;
pneumatic means for receiving the selected air and energy production for the actuation of equipment installed on Board the aircraft.

21. The system according to claim 20, characterized in that the control means include electronic control engine that receives at least one incoming signal of starting the change of the power consumption.

22. The system according to item 21, wherein the electronic control unit engine contains a stand-alone digital engine management system.

23. The system according to item 21, wherein the means to supply the selected contain air control valve, open or adjustable signal coming from a stand-alone digital engine management system.

24. The system according to item 23, wherein the control gate is made with collateral in its open position, the intake air taken from the compressor high pressure specified by the engine, these pneumatic tools.

25. The system according to item 23, characterized in that it further comprises a feedback circuit to transmit a signal representing the state of the valve, the electronic control device.

26. The system according to claim 20, characterized in that the said stump is automatic tools provide the generator with integrated Pneumatics for the production of electricity from order to actuate at least one of the items of equipment, selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

27. The system according to claim 20, characterized in that the said pneumatic tools provide the generator with built-in pneumatic system for supplying mechanical energy to the gearbox with the purpose of actuating at least one of the elements selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

28. The system according to claim 20, characterized in that the said pneumatic means include an air turbine mounted on the gearbox, to supply mechanical energy to the gearbox with the purpose of actuating at least one of the elements selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

29. The system according to claim 20, characterized in that the said pneumatic means include an air turbine connected to the shaft of the gearbox through a system of shafts and gears, and air turbine is arranged to supply mechanical energy to the gear C is poured actuate the at least one piece of equipment, selected from the group including alternator, starter and/or alternator, fuel pump, oil separator, generator, permanent magnet, oil pump and hydraulic pump.

30. The system according to claim 20, characterized in that the said pneumatic means include an air turbine connected to the gearbox, and also include a generator coupled to the gearbox and driven by an air turbine.

31. The system according to claim 20, characterized in that the said pneumatic means include an air turbine and a generator driven by an air turbine to supply energy to at least one system installed on Board the aircraft.

32. The system according to claim 20, characterized in that the said pneumatic means is arranged to increase the process stability margin of the high pressure compressor of the gas turbine engine.



 

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Gas-turbine unit // 2245448

FIELD: power engineering.

SUBSTANCE: proposed gas-turbine unit has low-pressure compressor, intermediate air cooler, high-pressure compressor, regenerator, combustion chamber, gas turbine wherefrom spent gas is conveyed to regenerator coupled with exhaust pipe that uses energy of exhaust gases and is provided with nozzle and intake chamber for cooling down atmospheric air arriving from intermediate air cooler. Proportion of exhaust pipe parts is chosen to ensure desired proportion of sizes of gas-turbine components.

EFFECT: enhanced reliability of gas-turbine unit and ability of its off-line operation.

1 cl, 1 dwg

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device contains fastening members and movable member telescopically connected with casing. Movable member is on accessory gear box and secured by pressure flange for displacement along end face of box. Clearance is formed between mating surfaces of flange and movable member.

EFFECT: improved reliability of connection of casing and accessory gear box by providing their rigid connection and sealing of inner spaces.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

FIELD: electricity.

SUBSTANCE: cable bundle (3) positioning and retaining station on the turbojet engine (1) housing (2) includes bundle supports (3) standardized for directions perpendicular to the turbojet engine (1) axis (4) and bundle supports standardised for directions parallel to the turbojet engine (1) axis (4).

EFFECT: reduction of manufacturing cycle cost and time.

14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: invention is intended for feeding electric power to equipment from gas turbine engine. The proposed system comprises an electronic control device to control, at least, one parameter containing the data on originating variation in consumed power, a control valve controlled by aforesaid system and feeding air take off the engine operated in transient conditions and a pneumatic device receiving aforesaid taken-off air to actuate the aircraft onboard equipment. The latter can represent an air turbine or generator with built-in pneumatic circuitry.

EFFECT: use of engine pneumatic power to drive aircraft onboard equipment.

33 cl, 10 dwg

Air engine design // 2355902

FIELD: engine engineering, aviation.

SUBSTANCE: in accordance with the present invention fillet fairing is installed inside bypass channel of the external engine circuit in order to avoid outer thickness of auxiliary mechanisms and gear boxes and to actuate them. The external circuit channel is between engine housing and inner circuit of compressor/engine turbine. The fillet fairing dimensions are enough to accommodate auxiliary mechanisms. At the same time the external circuit channel is correspondingly made axisymmentrical to avoid or compensate any blocking effect from fillet fairing within the channel limits when air flows. In addition the fillet fairing may be provided for placing engine oil tank as well as filter/heat exchanger mechanisms foreseen for engine. Under the above circumstances it is essential that elongated cylindrical engine profile is maintained so that reduced cross section is required allowing for the engine to keep a reduced glider of air craft. As a result acoustic shock waves profile is improved.

EFFECT: elimination of outer thickness when auxiliary mechanisms are placed.

FIELD: engines and pumps.

SUBSTANCE: proposed unit consists of gas turbine and reduction gear accommodated inside container and coupled via transfer shaft, reduction gear output shaft carrying the pump. Input device is arranged between said reduction gear and engine so that device front face wall part seats on reduction gear, while device read face wall part is located on gas turbine engine. Note here that both aforesaid parts are linked up axially and radially by sealed telescopic couplings with the remaining part of input device fixed container. Inlet inspection window is made in input device front face wall. Input device lower wall is made flat and horizontal. In operation, sealed telescopic couplings allow the engine and reduction gear to move relative to input device with no loss in tightness on the latter.

EFFECT: higher reliability, reduced weight and overall dimensions, easier mounting and control.

3 dwg

FIELD: machine building.

SUBSTANCE: unit consists of gear box of gas turbine and of at least one starter/generator mechanically coupled with gear box. The gear box consists of gears with several pinions. The starter/generator contains a generating block with a rotor, forming an inductance coil and stator forming an anchor; further, the stator/generator contains an actuating block with the stator forming the inductance coil and rotor forming an anchor connected to the inductance coil of the generating block. The rotor of the generating block and the rotor of the actuating block are arranged on a common shaft with a pinion engaging the gear of the gear box on both sides of this pinion. The invention facilitates integration of the starter/generator into the gear box of the gas turbine.

EFFECT: reduced volume and dimensions, ensuring easy disassembly.

23 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: auxiliary mechanism drive of two-shaft gas turbine engine comprising high- and low-pressure shafts incorporates first mechanical transmission between high-pressure shaft and drive box, and hydraulic transmission between low-pressure shaft and drive box. Auxiliary mechanisms are arranged in drive box, while hydraulic transmission is mounted to allow auxiliary mechanism drive rpm being equal to high-pressure shaft rpm.

EFFECT: possibility to take off power from high- and low-pressure shafts without varying auxiliary mechanism rpm.

14 cl, 3 dwg

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