Aircraft power supply circuit for electrical hardware including anti-icing circuit

FIELD: transport.

SUBSTANCE: set of invention relates to aircraft electric power supply circuit. Proposed circuit comprises power distribution circuit 16 and electric hardware supply circuit 5b, and electric power generator 27 incorporates with aircraft engine to supply anti-icing circuit 5a. Electric hardware comprises nacelle consuming components 5b connected DC voltage distribution with bus 35 connected with voltage converter circuit 34 supplied by distribution circuit 17. Anti-icing circuit 5a comprises, at least, one resistor 61 to dissipate electricity sent back to DC voltage distribution circuit 35 by, at least, some of nacelle consuming components. Aircraft comprises above described power supply circuit.

EFFECT: simplified design, reduced power consumption and power losses.

9 cl, 3 dwg

Prior art

The invention relates to the supply of electricity to the electrical equipment in the engine of the aircraft and/or in the environment.

More specifically, the scope of the invention are aircraft engines, particularly gas turbine engines. In addition, the invention is applicable also in the engines of the helicopters.

The term "electrical equipment in the engine of the aircraft or its environment" is used in this description, covering not only electrical equipment that is used to ensure operation of the engine, and electrical equipment associated with the nacelle of the engine, such as de-icing or anti-icing electrical circuits, such as circuits for de-icing systems gondola (VDR) or actuators intended for use in the system of opening of the engine with a thrust reverser (SOCKT), or Electromechanical actuators for use in the electric circuit of a control system of reverse thrust (SVRS) gas turbine aircraft engine, or even the schema associated with the wing carrying the engine, such as anti-icing or de-icing electric circuit of the wings himself the aircraft.

The traditional scheme for the receipt and distribution of electricity from a gas turbine aircraft engine shown in Fig. 3.

Two generators street 111A, 111b (or larger amount provided for redundancy purposes or to optimize electricity generation, depending on considerations of application) installed on the auxiliary gear 113, which is mechanically connected to a turbine shaft of the engine. Generators street 111A, 111b, as a rule, represent a starter-generator (S/G)containing a synchronous generator, which is connected with excitation and which delivers an AC voltage at a frequency varying depending on the speed of the engine, the site of excitation and synchronous generator driven with ability to work in the synchronous motor during startup of the turbine.

The AC voltage supplied by generators street 111A, 111b, are transmitted on the lines a, 115b in the electrical network 117 for distribution of electricity on Board the aircraft, called the "side chain". Scheme 119 onboard network, connected with lines a, 115b, delivers alternating current (Pet) with an adjustable AC voltage, typically located at 115 volts AC (115 V Pet) or 230 V Pet, one or more tire distribution. Scheme 119 also feeds the inverter 121 voltage, which feeds the river is Guliyeva DC voltage (Pot), as a rule, located at 270 volts DC (In the Pot) or ±270 In the Pot by one or more tires. Voltage circuits 119 and 121, is fed by an electrical load onboard, mainly in the area of the fuselage.

Associated with the engine fully self-contained unit 143 engine management (BUD) powered by generator 127, such as a generator with permanent magnets or an alternator with permanent magnets (GPTM mounted on the gear 113. BUD 143 is also connected to one of the schemes 119, 121, for example, with the circuit 119 variable voltage source of alternating current, guaranteeing its power up until the engine reaches a speed that is sufficient to supply the required electricity through GPTM 127, or in case of refusal PTPM. BUD 143 consumes receive electricity to ensure their components and for excitation of various engine components, such as sensors or probes, actuators or valves steering, which require electric power in limited quantities.

Currently there is a trend towards more and more replacing hydraulic energy to electrical energy for actuating the various elements of the electric the definition of equipment in the engine of the aircraft or its environment. For example, some aircraft are equipped with reverses 147 traction with electric drive. Thus, the circuit includes inverters 133 AC voltage into a DC voltage having inputs connected to the onboard network 117 via lines 145, 149, 151 power supply having outputs connected with such reverses 147 thrust and static equipment such as circuit 153, 155 for removing ice from the engine nacelles and wing carrying the engine.

The electricity network on Board the aircraft for different loads outside of the fuselage by means of supply lines, which must be very reliable and should be isolated lines, weight and volume are significant, cause a risk that the size will be a factor in determining or even prohibiting, if the number of powered equipment increases, and the supply is a source of electrical losses that can not be ignored.

Objective and summary of the invention

The objective of the invention is to develop a scheme of electric power that is not characterized by the above mentioned disadvantage and which guarantees the power of many units of electrical equipment in the engine of the aircraft and/or its environment.

the same problem is solved using the circuit of electrical power on an aircraft containing network for distribution of electricity on Board the aircraft and supply the electrical equipment located in the engine of the aircraft or surrounded by the above-mentioned engine, and mentioned electrical equipment contains load gondola connected to the bus of the distribution of the DC voltage, while said bus is connected to the Converter circuit voltage fed mentioned distribution network, and said power supply further comprises a generator of a power supply built into the engine of the aircraft to power the de-icing circuit, and the de-icing circuit contains at least one electrical resistance for dissipating electricity, if possible, returned to the bus voltage distribution DC, at least some of the burdens of a gondola.

Thus, the circuit according to the invention provided with the opportunity to reduce the length of the cable for transmission of electricity in the de-icing circuit. In addition, the cable that transmits electricity from the distribution network electricity on Board the aircraft, may have a small diameter. This gives the possibility to optimize the weight and volume of cables. In addition, de-icing circuit not maladive is no adjustment restrictions, and so the generator power can have a configuration that is simple, is resistant to external influences, compact and causes light weight. In addition, there is no need to have electrical resistance, exclusively intended for the dissipation of electricity, which can be returned to the bus distribution voltage DC electric actuators in the gondola. This further reduces weight and ensures saving of electricity.

Mentioned de-icing circuit mainly connected directly with the mentioned generator power supply for receiving the AC voltage.

Thus, the circuit according to the invention ensures that the de-icing circuit (which is purely resistive) will receive the AC voltage without converting the AC voltage into DC voltage, which ensures the reduction of power losses, and reduced dimensions and weight of the schema.

In accordance with another aspect of the present invention referred to the generator energy supply is a specialized generator with wound rotor.

Therefore, the generator power is simple and resistant to external influences.

Diagram of the main power supply is entrusted includes generator with permanent magnets (alternator with permanent magnets GPTM), mechanically associated with said generator, power supply, and the said generator with permanent magnets is arranged to supply at least one engine control unit (BUD) for electronic control of the engine.

Thus, the generator with permanent magnets (GPTM), feeding the engine control unit (BUD) for electronic control of the engine combined with a generator supplying deicing schema.

Mentioned, at least one engine control unit (BUD) is preferably connected to the said generator with permanent magnets to produce AC voltage. This ensures that the simplification of the circuit.

The mentioned generator with permanent magnets preferably nourishes many ECUs, and the supply of these units is carried out, for example, through the means of mates.

In accordance with the characteristic of the present invention, the generator power is a machine with wound rotor, and the generator with permanent magnets corresponds to the stage with permanent magnets mentioned machine with wound rotor. Thus, you can save on at least one output shaft of the accessory gearbox.

The power supply of predpochtitel is but includes:

input connected to the distribution network of electricity, for receiving the AC voltage, while the said voltage Converter is connected to the said input for converting the AC voltage supplied by a distribution network of electricity in the DC voltage, and

- switch the supply voltage is supplied to the said Converter, bus distribution voltage DC.

Thus, the scheme gives the opportunity to have protected electrical node, located in the vicinity of the engine, to power the loads, the built-in engine or located in its surroundings, thus to guarantee the availability of electricity in the power grid engine has only one connecting link with the electrical network on Board the aircraft. In addition, the Converter may have a size corresponding to all electrical equipment, except for de-icing equipment, which reduces the size of the Converter.

The invention also provides for the creation of an aircraft, comprising the above-described power supply.

Brief description of drawings

The invention is evident from the following description given as a non-restrictive example with reference to alagaesia drawings, on which:

Fig. 1 is a greatly simplified view of the system according to the invention for electrical power equipment and control them in the engine of the aircraft and its environment;

Fig. 2 is a more detailed view of the hardware device to the electrical power supply according to Fig. 1; and

Fig. 3 is described above, is substantially simplified representation of a known scheme for generation and distribution of electricity on an aircraft.

Detailed description of embodiments of the invention

In Fig. 1 presents a schematic diagram of an electrical power supply and control kit 5 items of electrical equipment 5A and 5b in the engine of the aircraft and its environment, in particular, in connection with a gas turbine aircraft engine.

The circuit according to Fig. 1 contains at least one generator 11, such as a starter-generator (S/G)mounted on the accessory gearbox (denoted by position 13), which is mechanically connected to a turbine shaft of the engine (not shown). The AC voltage supplied by the generator (generators) 11-type C/G, is passed through one or more lines 15 in the electrical network 17 for the distribution of electricity on Board the aircraft, referred to as "side chain". Scheme 19 onboard network delivers the one or more tyres RA the distribution of the AC voltage, which, usually, is at the level of 115 In Pet or 230 V Pet and has a frequency that varies depending on the speed of rotation of the shaft of the turbine. Scheme 19 may also exercise the power Converter 21 voltage, which supplies a regulated DC voltage, typically located at 270 In the Pot or ±270 In the Pot by one or more tires. The voltage produced by the circuits 19 and 21, is fed by an electrical load in the zone of the fuselage of the aircraft.

In accordance with the invention, the power supply has associated with the engine (indicated by item 23), the generator 27 supplies, built-in aircraft engine to power denoted by the position 5A circuit for de-icing systems gondola (VDR) engine, also known as anti-icing, or scheme for removing ice from the wing carrying the engine.

This makes possible the shortening of the length of the cable that supplies electricity in the de-icing circuit 5A. It should be noted that the cable is connected to the resistive de-icing circuit 5A has a diameter that is larger than diameters of the cables connected to other elements of the electrical equipment. Thus, reducing the length of the cable of this type serves to reduce the size and weight of the cables required for the transmission of electricity is icesta to the load, which is external to the fuselage. In addition, since the de-icing circuit 5A is purely resistive, it does not require any particular adjustment limits, and therefore the generator 27 supplies, for example, a generator of the type which has a specialized phase of the rotor, may be a configuration that is simple, is resistant to external influences, compact and has a small weight.

In addition, de-icing circuit 5A can be connected directly to the generator 27 of the power supply to receive the AC voltage. Thus, it is not necessary to have a voltage Converter for converting AC voltage into DC voltage. This serves to reduce power losses and reduce the size and weight of the circuit power supply.

In addition, the generator 27 of the power supply is also connected, at least one block 30 engine control (BUD).

BUD 30 mainly receives the AC voltage from the generator 27 supplies. This generator delivers in BUD 30 AC current which can be adjusted or changed depending on the speed of the engine. In addition, BUD 30 may also be connected with the circuit 19 of the AC voltage line 16, ensuring that matched the existing supply of this scheme until until the engine reaches the speed, which would be sufficient to supply the required electrical energy by generator 27 supplies. In addition, the circuit 19 also nourishes kit 5b electrical equipment corresponding to the loads in the gondola.

In Fig. 2 depicts an implementation option scheme of the electric power supply according to the invention.

In this example, the power supply comprises a generator 28 with permanent magnets (alternator with permanent magnets, PTPM), mechanically associated with generator 27 supplies. The generator 28 with permanent magnets, which is connected with the generator 27 supply is designed to power one or more BUD 30. More specifically, the generator 28 with permanent magnets nourishes few BUD 30 through circuit 31 mates.

As an example, we mention the possibility of saving the output shaft of the auxiliary gearbox, and the generator 27 of the power supply is designed as a machine with wound rotor, and the generator 28 with permanent magnets corresponds to the stage with the permanent magnets of this machine with wound rotor.

In addition, the power supply includes a bus 35 DC high voltage (PTN) for distribution of DC voltage and is protected by the first device 29 of the power supply, forming part of a network of electricity distribution associated with the engine (indicated by item 23).

The device 29 of the power supply has an input 32, the switch 33 and an inverter 34 of the AC voltage to DC voltage.

The input 32 is connected with a network of 17 distribution of electricity, and more specifically with the circuit 19, for receiving the AC voltage. The Converter 34 voltage is connected to the input 32 for converting the AC voltage supplied by a network of 17 distribution of electricity in the DC voltage. In addition, the switch 33 guarantees the supply voltage of the inverter 34 to the bus 35 distribution of DC voltage.

Thus, the generator 27 of the power supply supplies electrical energy from AC to BUD 30, and this energy is adjusted or changed depending on the speed of the engine. In addition, the switch 33 ensures the connection of BUD 30 through the device 29 of the power supply and circuit 31 mates with the circuit 19 of the AC voltage on the line 16 to implement the correct power up until the engine reaches a speed that is sufficient to supply the required electricity by generator 27 supplies.

This configuration allows the t to obtain the protected site electrical power supply. The generator 27 of the power supply takes the AC voltage directly to the equipment 5A for removing ice from the engine nacelle or wing. In contrast, the portion of the electrical equipment which complies with the loads 5b gondola, connected to the bus 35 distribution of DC voltage.

More specifically, de-icing circuit (de-icing circuit) 5A connected (connected) with generator 27 of the power supply through the module 47A supply of de-icing schema (de-icing circuits), which includes the switch and protection device, controlled by the Central unit 51 of the management or BUD 30.

Protivoobledinitelnoy scheme also includes at least one electrical resistance 61 to dissipate the electricity that can be returned to the bus 35 distribution of DC voltage, at least some of the loads 5b gondola. Possible return electricity to the bus 35 distribution of DC voltage indicated by the position 63. The dispersion of this electric energy electric resistance 61 becomes possible through the connection 65 between the bus 35 distribution of DC voltage and electric resistance 61.

In addition, the bus 35 feeds module 47b energos is abgene gondola together with the control device, includes main unit 51 of the control.

In this example, modules 47A, 47b of the power supply controls the Central unit 51 controls. It is connected to sensors (not shown)connected at least with some pieces of electrical equipment and connected with BUD 30. Module 47b supply gondola associated with electrical equipment 5b in the gondola.

Module 47b supply gondola contains the inverter 53 and the switching circuit 55. The inverter 53 is used to supply the AC voltage to the electrical equipment 5b, and the AC voltage obtained from the DC voltage supplied by a bus 35, and the switching circuit 55 is used to enable units of electrical equipment 5b. The Central unit 51 of the control module 47b, and in particular the switching circuit 55, ensuring the inclusion of each item of equipment 5b depending on the information received from BUD 30 and/or sensors associated with the equipment 5b.

It should be noted that the power supply may include two generator 27 of the power supply and possibly two bus 35 distribution of DC voltage, for example, the DC bus high voltage (PTN).

Thus, the use of two generators makes it possible to mitigate the failure of one generator, maintaining the thus energy, they are protected through a connection 16 with the network on Board the aircraft, and also makes it possible joint use of the supplied electric energy.

The DC voltage supplied via the bus 35 (or perhaps tires 35), can be adjustable voltage, for example, adjustable to achieve the nominal value 270 In the Pot or ±270 In the Pot, when this regulation is provided by the Converter circuit of the AC voltage to DC voltage. In one embodiment, the DC voltage supplied through the medium tyres (tires) 35, does not require regulation, and then the acceptable range of variation relative to the nominal values, in particular, independent of changes in voltage supplied by the circuit 19.

The invention also provides for the creation of an aircraft that includes an electrical power supply that contains a network of 17 distribution of electricity on Board the aircraft, the supply of electrical equipment 5b, in the engine of the aircraft or in the environment of the engine, and the generator 27 of the power supply built into the engine of the aircraft to supply power to a de-icing circuit 5A.

1. The electrical power on an aircraft containing the network (17) for the distribution system is CTV on Board the aircraft and power electrical equipment (5b), in the engine of the aircraft or surrounded by the above-mentioned engine, wherein the electrical equipment includes load (5b) gondola connected to the bus (35) distribution of DC voltage, these bus (35) connected with the scheme (34) of the voltage Converter fed by the said network (17) distribution, the power supply circuit includes a generator (27) power supply built into the engine of the aircraft to power the de-icing circuit (5A), and de-icing circuit (5A) contains at least one electrical resistance (61 for dissipation of electricity, if possible, returned to the bus (35) distribution of DC voltage, at least some of the burdens of a gondola.

2. The power supply according to claim 1, characterized in that the said de-icing circuit (5A) are directly connected to the said generator (27) the power supply for receiving the AC voltage.

3. The power supply according to claim 1, characterized in that the generator (27) the power supply is a specialized generator with wound rotor.

4. The power supply according to claim 1, characterized in that it comprises a generator (28) with permanent magnets, mechanically associated with said gene is the operator (27) supply moreover, the said generator (28) with permanent magnets is arranged to supply at least one block (30) engine control for electronic control of the engine.

5. The power supply according to claim 4, characterized in that the said at least one block (30) management engine connected to the said generator (28) with permanent magnets to produce AC voltage.

6. The power supply according to claim 4, characterized in that the generator (28) with permanent magnets nourishes many blocks (30) of the motor control, and power of these blocks is provided through the scheme (32) pair.

7. The power supply according to claim 4, characterized in that the generator (27) the power supply is a machine with wound rotor, and referred to the generator (28) with permanent magnets corresponds to the stage with permanent magnets mentioned machine with wound rotor.

8. The power supply according to claim 1, characterized in that it comprises: entrance (32)connected to a network (17) distribution of electricity, for receiving the AC voltage, while the mentioned Converter (34) voltage is connected to the said inlet (32) for converting the AC voltage supplied by the network (17) distribution of electricity, the voltage at the constant current, and the switch (33) for supplying voltage to the mentioned Converter (34), rail (35) distribution of DC voltage.

9. Aircraft, including the electrical power supply according to any one of claims 1 to 8.