A method for contactless communication between a fixed reference frame and a rotating reference frame by encoding electrical signals.

Abstract

A data communication method for a de-icing system for a turbine engine is disclosed. The turbine engine includes a fixed reference frame and a rotating reference frame. The system includes a non-contact rotating power transformer (RTU), the primary side of which is constrained by the fixed reference frame, and the secondary side of which is constrained by the rotating reference frame. The fixed reference frame includes an ice protection and control unit (IPC) and a power supply device (DC / AC) for supplying AC power to the primary side. The IPC transmits commands to the DC / AC to adjust the level of power supplied to the primary side. The rotating reference frame includes a propeller (1) and a switch, with a plurality of resistors fixed to the propeller. The switch is used to sequentially distribute the power supplied to the secondary side to the resistors. The protection and control unit (IPC) is programmed to transmit switching commands to the switch via the power supply unit (DC / AC) and the transformer (RTU) by issuing instructions (Ic1, Ic2, Ic3, Ic4, Ic5, Intl) to the power supply unit (DC / AC) to encode the voltage wave sequence (To) applied to the primary side. The switch is programmed to decode the voltage wave sequence (To) recovered on the secondary side.

Description

Technical Field

[0001] This invention relates to a method for communication between a fixed reference frame and a rotating reference frame, such as the stator and rotor of a machine. More particularly, this invention relates to communication between reference frames of an aircraft turbine engine for the electric de-icing of a propeller.

[0002] Existing technology Because aircraft are affected by changes in humidity and temperature, at least some parts of an aircraft may be covered in ice. This is the case, for example, with the propellers of an aircraft's turbine engine.

[0003] To prevent or reduce ice formation, the propeller blades and cone are equipped with heating pads in areas exposed to ice. These pads operate via an electrothermal effect, based on a network of resistors integrated into the propeller.

[0004] Various embodiments exist for powering an electrothermal de-icing system for transmitting power and control between a stationary part and a rotating part to power a turbine engine propeller.

[0005] Some embodiments propose transmitting power and control via contact.

[0006] For example, according to document US 8,120,228 B2, the transmission of electricity and control is performed between the stator brushes and the rotor rails, with the rotor carrying the propeller. This embodiment is attractive due to its simplicity, but it has the disadvantage of limited lifespan due to friction between the brushes and the rails. This may be acceptable for military aircraft requiring frequent maintenance. This embodiment is less suitable or not suitable at all for use in commercial civilian aircraft, especially for situations involving heavy daily commuting. In fact, the maintenance and operating costs would be too high.

[0007] As an alternative, the embodiments propose contactless transmission of power and control.

[0008] For example, it is known to perform transmission via magnetic induction by superimposing a low-energy, high-frequency signal for control onto an electrical signal used for electrothermal effects. This embodiment is attractive, especially because it occupies very little space. However, implementing this embodiment is complex due to constraints related to managing interference between the two superimposed signals on the one hand, and the risk of the transmitted data being altered on the other. The reliability of this embodiment cannot be guaranteed given the numerous sources of interference: transient effects related to load switching in the rotary control unit, large air gaps, and air gap variations due to radial and axial displacement of the movable part relative to the fixed part.

[0009] Another example of magnetic induction transmission of power and control signals uses a second-stage rotary transformer specifically designed for transmitting control signals. This is expensive, bulky, and difficult to install on a turbine engine.

[0010] Another example of power and control transmission implements the capacitive effect. This embodiment is suitable for applications where the transformer is equipped with its own bearings, thus having a small air gap (approximately one millimeter), and is also controlled.

[0011] Disclosure of the present invention The present invention seeks to overcome the above-mentioned disadvantages and has the overall objective of improving power transmission and control between a fixed reference frame and a rotating reference frame, particularly for aircraft turbine engines.

[0012] In particular, this invention seeks to optimize the sequence of power supply to multiple resistors used for de-icing propeller blades. Furthermore, the invention aims to achieve a long service life and limit maintenance interventions in the turbine engine. The invention also seeks to simplify power and control transmission by reducing or even eliminating interference and alterations. Another objective of this invention is to simplify the structure of the turbine engine. Another objective is to limit manufacturing and operating costs. Finally, the invention aims to be specifically suited for turbine engines with large-diameter rotating sections, such as one meter or even larger.

[0013] In view of the above, the object of the present invention is a data communication method for a de-icing system of a turbine engine, the turbine engine including a fixed reference frame and a rotating reference frame, the system including a non-contact rotating power transformer, the primary side of the rotating power transformer being subject to the fixed reference frame, and the secondary side of the rotating power transformer being subject to the rotating reference frame; the fixed reference frame including an ice protection and control unit and a power supply device for supplying alternating current to the primary side, the protection and control unit transmitting instructions to the power supply device to adjust the level of power supplied to the primary side; the rotating reference frame including a propeller and a switch, a plurality of resistors being subject to the propeller, the switch being used to sequentially distribute the power supplied to the secondary side to the plurality of resistors.

[0014] The protection and control unit is programmed to transmit a switching command to the switch via the power supply unit and the transformer by giving instructions to the power supply unit to encode the voltage wave sequence applied to the primary side, and the switch is programmed to decode the voltage wave sequence recovered on the secondary side.

[0015] This communication method uses a dedicated channel for power transmission to transmit switching commands. Different values ​​are transmitted through the same channel. This is why the de-icing system has a simple structure, as it does not require a specific channel for transmitting switching commands. The advantages gained include control over quality, overall size, and manufacturing and maintenance costs.

[0016] The voltage waveform sequence has an activation duration, a pre-calibrated fixed interrupt duration, and a variable interrupt duration. The switch identifies and uses these durations to distribute power to these resistors. In this way, the power supply unit with a fixed reference frame acts as a transmitter, and the switch with a rotating reference frame acts as a receiver. This allows management of two variables: the de-icing activation duration and the de-icing cycle duration. The resulting advantage is reliable transmission of switching commands, leading to high de-icing efficiency.

[0017] When the voltage waveform sequence is interrupted, switching is performed by the switch. It follows that the continuity of the waveform sequence keeps the switch in its current state. Very short interruptions in the waveform sequence are sufficient for switching management. Advantageously, this allows for optimal power transfer to the resistor.

[0018] Switching is performed under low current and low voltage, or even zero current and zero voltage. This reduces stress on the switching components and improves energy efficiency by offsetting switching losses. Only conduction losses are considered.

[0019] To monitor and protect the rotating reference frame, the power supply measures the current on the primary side. In practice, the measurement is performed on the fixed reference frame side. This allows the power supply to monitor the system's operation on the rotating reference frame side. An advantage gained is the detection of faults, such as short circuits or open circuits. Another advantage is ease of maintenance through fault identification. Furthermore, the rotating electronics are simplified.

[0020] The power supply unit converts DC voltage to AC voltage. In this case, but not limited to, the DC voltage is higher, which allows power to be supplied to the equipment using a built-in grounding wire. Advantageously, this makes the aircraft equipped with the system used to implement this method lighter.

[0021] The power supply system employs double redundancy. The system uses two power supplies to improve de-icing availability.

[0022] The propeller comprises at least one pair of blades. Preferably, the two blades in a pair are diametrically opposed and heated simultaneously. Therefore, the de-icing action on the two blades is synchronized. This advantageously maintains the dynamic balance of the propeller, even if not all blade pairs are at the same level of de-icing.

[0023] Another object of the present invention is a system for implementing a method of data communication for de-icing of a turbine engine, the turbine engine comprising a fixed reference frame and a rotating reference frame.

[0024] Another objective of the present invention is an aircraft that includes a system for implementing the method.

[0025] Brief description of the attached figures Other objects, features, and advantages of the invention will become apparent upon reading the following description, which is given by way of non-limiting example and with reference to the accompanying drawings, in which: [ Figure 1 [Illustration] is a schematic diagram illustrating the power supply of a de-icing system for a turbine engine according to an example of the present invention. [ Figure 2 The diagram schematically illustrates a propeller comprising twelve blades, used for […]. Figure 1 The de-icing method of the system is implemented for turbine engines. [ Figure 3 ] shows the direction to [ Figure 2 The power supply cycle of a pair of blades of the propeller. [ Figure 4 ] shows as [ Figure 1 ]and[ Figure 2 The principle behind the intermittent de-icing of a propeller, which involves switching from one pair of blades to the next. [ Figure 5 The diagram shows a voltage wave sequence for data communication based on the presented example. Detailed Implementation

[0026] Typically, although not shown, the aircraft is powered by at least one turbine engine, including a propeller.

[0027] The turbine engine includes a fixed reference frame and a rotating reference frame. The fixed reference frame is integrated with the structure of the aircraft, and the rotating reference frame is guided by the fixed reference frame and carries the propeller.

[0028] The propeller de-icing system includes a fixed reference frame, a rotating reference frame, and a non-contact rotating electrical transformer (RTU). One primary side of the RTU is constrained by the fixed reference frame, and the secondary side of the RTU is constrained by the rotating reference frame. The transformer RTU is... Figure 1 This is part of a schematic diagram; please refer to the diagram.

[0029] In a non-limiting manner, a rotary transformer (RTU) may include, for example, a radial air gap or an axial air gap. Regardless of its construction, the transformer RTU ensures contactless power transfer between a fixed reference frame and a rotating reference frame. Power is switched from the primary side to the secondary side. The absence of electrical contact increases the lifespan of the transformer RTU and facilitates easier cleaning. In fact, no abrasive dust is generated on the conductive parts.

[0030] The fixed reference system includes an ice protection and control unit (IPC) and a power supply unit (DC / AC) for supplying alternating current to the primary side. The protection and control unit (IPC) transmits commands to the power supply unit (DC / AC) to adjust the power level supplied to the primary side of the transformer RTU.

[0031] In a non-restrictive manner, the system includes two power supply units to improve its availability.

[0032] The turbine engine is connected to the power grid that delivers high-voltage direct current (HVDC), allowing it to be powered using a relatively small power chain. For DC, values ​​of 450 V or 800 V are well-suited. In fact, the primary-side power supply converts DC to AC. Therefore, the voltage available to supply power to the primary side of the transformer RTU is AC, which allows power to be switched to the secondary side via the action of an AC magnetic field.

[0033] The protection and control unit (IPC) transmits commands to the power supply unit (DC / AC) to adjust the power level delivered to the primary side.

[0034] On the other hand, the rotating reference frame includes a propeller, and the resistor is constrained by the propeller. For example, the resistor is made in the form of a heating pad that operates through an electrothermal effect, and these pads are integrated into the blades in areas exposed to ice.

[0035] The rotating reference frame also includes a switch for sequentially distributing electrical energy transmitted to the secondary side to these resistors.

[0036] The protection and control unit (IPC) is programmed to transmit switching commands to the switch via the power supply unit (DC / AC) and the transformer RTU by issuing instructions to the power supply unit (DC / AC) to encode the voltage waveform sequence applied to the primary side. The switch is programmed to decode the voltage waveform sequence transmitted from the primary side to the secondary side. The encoding generates activation and interruption durations within the voltage waveform sequence. Therefore, the voltage waveform sequence carries both electrical power and code for switch operation.

[0037] In the described example, in a non-restrictive manner, such as Figure 2As shown, propeller 1 includes six pairs of blades P1, P2, P3, P4, P5, and P6, each pair of blades being referred to as a segment. The two blades of a segment are diametrically opposed. The blades are evenly distributed around the propeller, having two series of blades P1 to P6. The angle difference between two consecutive blades is 30°, and the angle difference between two blades of a segment is 180°.

[0038] In a non-limiting manner, blades P1 through P6 all have the same structure. These blades all have the same length.

[0039] The power distribution to multiple resistors is performed segment by segment. Two blades in the same segment are powered synchronously. Segments P1 to P6 are powered alternately according to a cycle, for example, sequentially.

[0040] Figure 3 The power supply to the first segment P1 is shown, with a de-icing activation duration D1 along the x-axis Ox, a cycle duration D along the x-axis Ox, and the intensity of the power supply along the y-axis Oy. The duration D1 is variable and depends on the icing conditions. The switch obtains information about the icing conditions intrinsically by adjusting the duration D1.

[0041] Figure 4 The continuous power supply to six pairs of blades or sections P1, P2, P3, P4, P5, and P6 is shown. In a non-restrictive manner, the corresponding de-icing activation durations D1, D2, D3, D4, D5, and D6 along the x-axis Ox are equal. These durations are variable, depending on the icing conditions, and are calculated by the system administrator. The switch intrinsically obtains information about the icing conditions by adjusting the durations D1 to D6. Figure 4 The term D, which refers to the cycle duration, is also mentioned. Activation interruption I separates the two consecutive activation sequences of segment P1 to P6.

[0042] like Figure 5 As shown, the power supply sequence is executed by the switch according to instructions from the ice protection and control unit IPC. The waveform sequence (reference To) delivered to the switch is executed along the x-axis Ox over time, with intensity along the y-axis Oy. The protection and control unit IPC interrupts the waveform sequence To for varying durations.

[0043] First, interrupts Ic1, Ic2, Ic3, Ic4, and Ic5 with fixed durations are provided. These interrupts are interpreted by the switch as segment change commands to switch from segment n to segment n+1. Subsequently, an interrupt Intl with a variable duration is provided based on the icing condition. Each interrupt is interpreted by the switch as the end of the power supply sequence for all segments P1 to P6. The duration of this interrupt Intl is adjusted to take into account the duration D of the de-icing cycle. The variable interrupt Intl duration can occur at any time.

[0044] The switch is programmed to restart the de-icing sequence by starting from the first segment P1 when the power is switched back to on.

[0045] Each switching operation, both turning on and off, is performed under low current and low voltage, or even zero current and zero voltage. This reduces stress on components and improves efficiency by eliminating switching losses.

[0046] By mastering the applied cycle, the power supply unit knows the reference value of the section it supplies power at all times. Therefore, by measuring the current on the primary side (fixed side) of the transformer, the power supply unit can ensure monitoring of the rotating reference system; the power supply unit can detect faults in each of sections P1 to P6, such as short circuits or open circuits.

[0047] An alternative embodiment of the described example involves introducing additional encoding of the interrupt duration to transmit segment reference values ​​P1, P2, P3, P4, P5, P6 to the switch. The fixed interrupt durations Ic1, Ic2, Ic3, Ic4, Ic5 are replaced by a set of duration ranges based on the following values.

[0048] Section P1: After the power is turned on, Section P2: Interrupt duration, for example, from 10 ms to 15 ms. Section P3: Interrupt duration, for example, from 20 ms to 25 ms. Section P4: Interrupt duration, for example, from 30 ms to 35 ms. Section P5: Interrupt duration, for example, from 35 ms to 40 ms. Section P6: Interrupt duration, for example, from 45 ms to 50 ms.

[0049] The pause between two cycles has a duration that depends on the change in the cycle.

[0050] Generally speaking, the present invention has the advantage of simplicity, and its implementation is carried out by specific programming at the protection and control unit and the switch.

[0051] Of course, the present invention is not limited to the embodiments and examples of implementation described above, and includes all equivalents falling within the scope of the following claims.

[0052] In particular, different numbers of blades can be provided. Nevertheless, the power supply can use the AC voltage available on the aircraft.

Claims

1. A data communication method for a de-icing system of a turbine engine, the turbine engine comprising a fixed reference frame and a rotating reference frame, the system comprising a non-contact rotating power transformer (RTU), the primary side of the rotating power transformer (RTU) being constrained by the fixed reference frame, the secondary side of the rotating power transformer (RTU) being constrained by the rotating reference frame, the fixed reference frame comprising an ice protection and control unit (IPC) and a power supply device (DC / AC) for supplying alternating current to the primary side, the protection and control unit (IPC) transmitting instructions to the power supply device (DC / AC) to adjust the level of power supplied to the primary side; the rotating reference frame comprising a propeller (1) and a switch, a plurality of resistors constrained by the propeller, the switch being used to sequentially distribute the power supplied to the secondary side to the plurality of resistors, characterized in that, The protection and control unit (IPC) is programmed to transmit switching commands to the switch via the power supply unit (DC / AC) and the transformer (RTU) by issuing instructions (Ic1, Ic2, Ic3, Ic4, Ic5, Intl) to the power supply unit (DC / AC) to encode the voltage waveform sequence (To) applied to the primary side, and the switch is programmed to decode the voltage waveform sequence (To) recovered on the secondary side.

2. The method according to claim 1, wherein, The voltage wave sequence (To) has an activation duration (D1, D2, D3, D4, D5, D6), a pre-calibrated fixed interrupt duration (Ic1, Ic2, Ic3, Ic4, Ic5), and a variable interrupt (Intl) duration.

3. The method according to claim 1 or 2, wherein, During the interruption of the voltage wave sequence, the switching is performed by the switch.

4. The method according to any one of claims 1 to 3, wherein, Switching is performed under low current and low voltage or even zero current and zero voltage.

5. The method according to any one of claims 1 to 4, wherein, The power supply device (DC / AC) measures the current on the primary side to monitor and protect the rotating reference frame.

6. The method according to any one of claims 1 to 5, wherein, The power supply unit (DC / AC) converts direct current voltage to alternating current voltage.

7. The method according to any one of claims 1 to 6, wherein, The power supply unit (DC / AC) is dual redundant.

8. The method according to any one of claims 1 to 7, wherein, The propeller (1) includes at least one pair of blades (P1, P2, P3, P4, P5, P6).

9. A system that implements the method according to any one of claims 1 to 8.

10. An aircraft comprising the system according to claim 9.

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