Device for Connecting Components of an Aircraft Engine and Method of Using the Same

Abstract

The present invention relates to a device for connecting components of an aircraft engine. The connecting device comprises: a connector adapted to connect a first component and a second component so as to establish a physical transmission link between these components; and means for enabling the monitoring of the connection state, in particular by means of impedance measurements carried out in a circuit formed by components integrated into said connector.

Description

Field of the Invention

[0001] The present invention relates to the field of the assembly of aircraft engine components. The present invention particularly relates to a device for connecting components of an aircraft engine. The present invention also relates to a method of using said connecting device. Background Art

[0002] The prior art particularly includes the documents EP-A1-2003384, EP-A1-2739842 and EP-A2-1512901.

[0003] Recent forecasts indicate that the number of aircraft will double in the next few decades. These forecasts are themselves based on forecasts of increased passenger traffic, the increase in which leads to a doubling of the number of passengers by 2030 and necessarily implies a strong growth in the number of aircraft in circulation.

[0004] To meet this growth, the production and maintenance of aircraft must also increase significantly. The same applies to the engines of aircraft.

[0005] To solve the problems in terms of increasing productivity, one solution being envisaged is to use a "quick" connection system for components. The aim is to obtain simplicity on the assembly line and to save operating time. In particular, this solution consists in replacing components that are normally connected together by bolts, threads or welding with a more modular connecting device that enables rapid attachment.

[0006] Advantageously, the quick connection device makes it possible to dispense with monitoring the tightening torque inherent in the components connected by threads. In fact, in an aircraft, threaded connections mean checking whether the safety limits of the attachment are respected by measuring the tightening torque (for example using a torque wrench).

[0007] Known quick coupling methods use, for example, bayonet connectors or push-pull connectors, which do not require torque monitoring. In addition, these systems are said to be fast because they enable components to be assembled or disassembled more quickly and thus the duration of the assembly / disassembly operation can be shortened compared to conventional attachment.

[0008] These coupling systems are used, for example, in the field of motorsport, and these connection systems enable fluid pipes (such as air, fuel or oil) and cables to be connected.

[0009] In addition, these connection systems also provide additional safety during assembly / disassembly operations. In fact, it is difficult to detect malicious acts of loosening threaded connections with the naked eye. On the other hand, in a quick-connection system, malicious operations on the connector are more easily detectable by the naked eye. Therefore, the use of such a system can reduce the risk of IFSD (In Flight ShutDown) events due to defective connections.

[0010] However, even with a quick-connection system, it can be very time-consuming to verify during assembly and / or maintenance operations whether two components are connected as per the nominal connection (i.e., as expected by the manufacturer of the connection device).

[0011] In addition, non-nominal connections are more likely to occur as a result of incorrect assembly or maintenance operations as well as malicious acts.

[0012] It is known that the torque of threaded fittings can be monitored. This method relies on the dynamic measurement of this torque and the comparison of the gradient of the torque evolution with a predetermined value to identify whether the connection is sufficient. However, this method requires complex measurements and is not applicable to quick connections.

[0013] Patent application EP2739842A1 describes a method for monitoring a locking member. In this case, the monitoring is applicable to locking members of the electric actuator type and thus does not concern the connection between components of a physical transmission link. Summary of the Invention

[0014] The present invention provides a connection device for real-time monitoring of the connection state between connectors included in the connection device and thus the connection state between the components to which the connection device is connected. In other words, the connection device includes components enabling self-diagnosis. In addition, in some embodiments, the connection device can also analyze the time evolution of the connection state and enable better management or even prediction of faults associated with defective connections.

[0015] To this end, according to a first aspect, the present invention relates to a device for connecting components of an aircraft engine, the device comprising: a first connector and a second connector, the first connector and the second connector being adapted to connect a first component and a second component to establish a physical transmission link between the first and second components, characterized in that the connection device further comprises:

[0016] - a transmitting member adapted to generate a determined physical signal;

[0017] - A first transmission member, the first transmission member being adapted to transmit the determined physical signal between at least a first component, a second component, and a third component of the first connector and the second connector;

[0018] - The first component, the first component being included in the first connector, the first component having a determined first impedance with respect to the physical signal;

[0019] - The at least second component and third component, the at least second component and third component being included in the second connector, the at least second component and third component respectively having a determined second impedance and a determined third impedance with respect to the physical signal, the second impedance being different from the third impedance;

[0020] - At least one first connection element, the at least one first connection element being included in the first connector and associated with the first component, and the at least one first connection element being adapted to establish a connection link with at least one second connection element and a third connection element, wherein the at least one second connection element and a third connection element are included in the second connector and are respectively associated with the second component and the third component;

[0021] - A detection member, the detection member being adapted to measure at least one characteristic representative of the determined physical signal circulating in the first component, the second component, and the third component;

[0022] - A second transmission member, the second transmission member being adapted to transmit measurement data from the detection member to a first processing member;

[0023] - A first processing member, the first processing member being adapted to receive measurement data from the detection member and generate an information representative of the connection state between the first part and the second part of the aircraft engine based on the measurement data; and

[0024] - A display member, the display member being adapted to display an information representative of the connection state between the first part and the second part of the aircraft engine.

[0025] The device according to the present invention may include one or more of the following features used individually or in combination:

[0026] - The physical transmission link is a fluid transmission link, or an electrical signal transmission link, or an optical signal transmission link;

[0027] - The determined physical signal is an electrical signal or an optical signal;

[0028] - The characteristic representation of a determined physical signal includes impedance, the intensity of the physical signal, or the amplitude of the physical signal;

[0029] - The first, second, and third connection elements of the connector are provided on separate parts of the connector such that the establishment of a connection link between two connection elements depends on the corresponding position of the connector;

[0030] - Information representing the connection state between the first and second components is included in the following information:

[0031] - No connection, corresponding to the non - establishment of a connection link between the first connection element of the connector and the second or third connection element;

[0032] - Insufficient connection (défaut), corresponding to the connection link established between the first connection element of the first connector and the second connection element of the second connector; and,

[0033] - Nominal connection, corresponding to the connection link established between the first connection element of the first connector and the third connection element of the second connector;

[0034] - The display member is included in the connector, or in the aircraft engine, or in a device unloaded from the aircraft engine;

[0035] - The device further includes:

[0036] - A second processing member, which is adapted to process information representing the connection state between the first and second components of the aircraft engine obtained continuously to determine the time evolution of the connection state between the first and second components of the aircraft engine; and,

[0037] - A memory, which is adapted to store information representing the connection state between components of the aircraft engine.

[0038] According to a second aspect, the invention also relates to a method of using a connection device according to the first aspect, the method comprising the following steps:

[0039] - Transmit at least one physical signal;

[0040] - Transmit the physical signal between the transmitting member, the first component of the first connector, and the component of the second connector that is connected to the first component through the first and second or third connection elements when a connection link is established; and

[0041] - Measuring at least one characteristic representative of the physical signal being transmitted;

[0042] - Generating an information representative of the connection state between the first and second components of the aircraft engine based on the measurement data; and,

[0043] - Displaying the information representative of the connection state between the first and second components of the aircraft engine.

[0044] The method according to the present invention may further include the following steps:

[0045] - Processing the information representatives of the connection state between the first and second components of the aircraft engine obtained continuously to determine the time evolution of the connection state between the first and second components of the aircraft engine; and,

[0046] - Storing the information representatives of the connection state between the first and second components of the aircraft engine in a memory. Description of the Drawings

[0047] The present invention will be better understood and other details, features and advantages thereof will become more apparent by reading the following description of non - limiting examples and referring to the drawings, in which:

[0048] Figure 1 is a schematic diagram of an embodiment of a connection device according to the present invention;

[0049] Figure 2 is a schematic diagram of another embodiment of a connection device according to the present invention;

[0050] Figure 3 is a schematic diagram of yet another embodiment of a connection device according to the present invention;

[0051] Figure 4 is a schematic diagram of the steps of an embodiment of a method according to the present invention;

[0052] Figure 5 is a schematic diagram of the steps of another embodiment of a method according to the present invention.

[0053] Elements having the same function in different embodiments have the same reference numerals in the drawings. Detailed Description of the Embodiments

[0054] Now reference will be made to Figure 1 、 Figure 2 and Figure 3 to describe an embodiment of a connection device according to the present invention.

[0055] The connecting device 101 is used to connect two components of the aircraft engine 100 (not shown in the figure). In particular, the device 101 includes a first connector 102 and a second connector 103, and the first connector and the second connector are adapted to connect the first component and the second component so as to establish a physical transmission link between the two components. For example, these connectors are respectively attached to pipes, cables or optical fibers. Therefore, the so-called physical transmission link refers to, for example, a link for transmitting fluids, a link for transmitting electrical signals or a link for transmitting optical signals.

[0056] In addition, one of the two connectors can be male, the other can be female, or both are of the same type, as long as the two connectors can establish a connection that allows the establishment of a physical transmission link. In addition, the connectors are preferably threadless. In other words, the connecting device is a so-called quick-connect device, and its connectors are, for example, bayonet or push-pull connectors.

[0057] In particular, the connecting device according to the present invention enables self-diagnosis of the connection state it provides. This ability is based on a set of components included in the connecting device.

[0058] The transmitting member 104 is adapted to generate a determined physical signal. Such a physical signal can be, for example, an electrical signal or an optical signal. The transmitting member 105 is adapted to transmit the said signal under discussion between the components of the connectors 102 and 103.

[0059] More specifically, the first component 106 included in the first connector 102 has a first determined impedance Z106 with respect to the said physical signal. "With respect to the said physical signal" means that depending on whether the signal emitted by the transmitting member 104 is an electrical signal or an optical signal, this impedance can be electrical or optical.

[0060] The second component 107 and the third component 108 included in the second connector 103 respectively have a second impedance Z107 and a third impedance Z108 with respect to the said physical signal. The second impedance Z107 is different from the third impedance Z108.

[0061] Therefore, in the example shown, the physical signal emitted by the transmitting member 104 circulates between different components (i.e., components 106, 107 and 108) via the transmitting member 105. In addition, those skilled in the art will understand that the number of components included in these connectors, and particularly in the second connector, can be greater than two.

[0062] The first connection element 109 included in the first connector 102 is associated with the first component and is adapted to establish connection links with the second connection element 110 and the third connection element 111, wherein the second connection element and the third connection element are themselves associated with the second component and the third component, respectively. In other words, the first connection element can establish a connection link with the second connection element 110, with the third connection element 111, or with neither of these connection elements. In this way, the physical signal transmitted only flows through the first component, through the first and second components, or through the first and third components, depending on which connection elements are actually connected.

[0063] In addition, the first connection element, the second connection element, and the third connection element of the connector can be provided on separate parts of the connector such that the establishment of a connection link between two connection elements depends on the corresponding position of the connector. In other words, the signal flows in different circuits (i.e., has different characteristics), depending on whether the connector is more or less well connected. Thus, in Figure 1 the example shown, the establishment of a connection link between the connection elements 109, 110, and 111 depends on the insertion of the first connector 102 into the second connector 103. This situation can correspond, for example, to the use of a "push-pull" type connector.

[0064] In another example, as Figure 3 shown, the connectors 102 and 103 have a circular cross-section, and the corresponding connection elements of the two connectors 102 and 103 are provided on separate radial parts of these connectors. In this way, whether a connection link is established depends on the relative angular position of each connector. This situation can correspond, for example, to the use of a bayonet connector.

[0065] The detection member 112 is adapted to measure at least one characteristic representative of a determined physical signal flowing through the first component, the second component, and the third component. For example, the characteristic representative of the physical signal can be impedance, the intensity of the physical signal, or the amplitude of the physical signal. In particular, this characteristic varies depending on whether a connection link is established between different connection elements and thus depending on the components through which the signal flows. In this way, this characteristic can be used to determine the connection state between two connectors and thus the connection state between two parts of the motor.

[0066] The transmission member 113 is adapted to transmit measurement data from the detection member to the processing member 114, and the processing member in turn is adapted to receive such data and generate an information representative of the connection state between the first part and the second part of the aircraft engine based on such data. In a particular embodiment, the information representative of the connection state between the first part and the second part can be:

[0067] - No connection, corresponding to no connection link being established between the first connection element and the second or third connection element of the connector (as shown on the left side of Figure 3 );

[0068] - Insufficient connection, corresponding to the connection link established between the first connection element of the first connector and the second connection element of the second connector (as shown in the middle of Figure 3 ); and,

[0069] - Nominal connection, corresponding to the connection link established between the first connection element of the first connector and the third connection element of the second connector (as shown on the right side of Figure 3 ).

[0070] Generally speaking, the establishment of a specific connection link changes the characteristics of the circuit formed by various connection components, which affects the measurements performed by the detection component and is reflected in the information representation generated by the processing component. For example, adding a new impedance with a determined value to the circuit in which the signal circulates causes a modification of the detected impedance, which enables the precise state of the connection to be determined.

[0071] Finally, the display components 115, 116, and 117 are adapted to display an information representation of the connection state between the first and second components of the aircraft engine. In the examples shown in Figure 1 and Figure 2 , the display component 115 is included in the connector 102, the display component 116 is included in the aircraft engine 100 (i.e., not in the connector), and the display component 117 is included in the external device of the aircraft engine.

[0072] Therefore, the display component 115 enables the operator to directly check the connection state on the connector to be connected. The display component 115 can consist of, for example, a simple light-emitting diode (LED) located on the connector, which displays red, orange, or green according to the connection state (i.e., corresponding to no connection, insufficient connection, or nominal connection respectively).

[0073] The display component 116 enables the operator to check the connection state on a specific display of the turbine. In addition, since these components are not integrated into any connector, these components can implement a more complete display, for example, by using a screen or an LED box. In particular, such a display component can display the connection states of multiple pairs of components and thus summarize the states of all connections in the aircraft engine. If necessary, such a display can provide guidance on faulty connection links and take corrective measures. In such an embodiment, the cascade module integrated into the display component aggregates the information from multiple processing units of different connection devices so that these display components can display all this information.

[0074] Finally, the display member 117 enables the connection status to be checked by a consulting member external to the aircraft engine. For example, it can be a smartphone, a tablet, a computer or an augmented reality device (such as glasses for example).

[0075] In particular, the embodiments associated with the display members 116 and 117 enable a "test trigger" method to be adopted for the connecting device. That is, it is a method in which the operations associated with diagnosing the connection status are only activated when the operator desires, rather than on a continuous basis.

[0076] In addition, in all the above embodiments, the information to be displayed is transmitted between all the devices 119 and the display member by a suitable transmission member 118, which can be wired or wireless.

[0077] Generally speaking, thanks to this device, the assembly operation becomes safer by means of a simplified verification of the correct locking of the connectors. It is also beneficial for the maintenance check of the connection link status or the verification of the correct reconnection of the connectors after a maintenance operation. In addition, since it is no longer necessary to check all the connectors in a conventional and time-consuming manner, but only to operate on the connectors that need to be checked (i.e., the connectors whose connection is in a non-nominal state), the maintenance process is facilitated.

[0078] As for the embodiment of the connecting device referred to Figure 2 in addition to monitoring the connection status, it is also intended to enable predictions to be made in order to be able to anticipate the future evolution of the connection status.

[0079] In particular, the processing member 201 is adapted to process the information representative of the connection status between the first and second components of the aircraft engine continuously acquired. This continuously acquired information is used to determine the time evolution of the connection status between the first and second components of the aircraft engine. For example, in a particular embodiment, the processing member 201 includes an algorithm processing module 202 and a reporting module 203, the algorithm processing module being configured to determine the evolution trend of the connection status ("trend monitoring"), and the reporting module being configured to determine a prediction of the future evolution based on the determined trend.

[0080] In addition, the memory 204 is used to store the information representative of the connection status between the components of the aircraft engine continuously acquired.

[0081] Typically, in such an embodiment, the connector may include a plurality of components having different impedances greater than two. In this way, the connection device enables a more accurate tracking of the evolution of the nominal connection state over time towards a non-nominal connection state, and thus better predicts the evolution of the connection state and the possible transition from the nominal state to the non-nominal state. Additionally, this type of prediction not only enables corrective actions to be considered to reconnect the connector to restore the nominal state of the connection state, but also enables the information obtained to be interpreted in terms of connector wear to optimize the conditions for connector replacement.

[0082] Finally, in a particular embodiment, the connection device may include an alarm device 205 integrated with the flight deck of the aircraft to convey an alarm to the user based on the information representative of the connection state.

[0083] Referring to Figure 4 , we will now describe a method for implementing the use of the connection device according to the present invention. The steps of the method are thus performed by referring to the connection device described in Figure 1 , Figure 2 and Figure 3 .

[0084] Step 401 includes: transmitting at least one physical signal, and subsequently, in step 402, transmitting this physical signal between the transmitting member, the first component of the first connector, and the component of the second connector that is connected to the first component via the first connection element and the second connection element or the third connection element when the connection link is established.

[0085] Step 403 includes: measuring at least one characteristic representative of the transmitted physical signal, and step 404 includes: generating information representative of the connection state between the first and second components of the aircraft engine based on this measurement data.

[0086] Finally, step 405 includes: displaying information representative of the connection state between the first and second components of the aircraft engine.

[0087] In another embodiment of the method described in reference to Figure 5 , the method further includes steps 501 and 502, where step 501 is to process the information representative of the connection state between the first and second components of the aircraft engine obtained continuously to determine the temporal evolution of the connection state between the first and second components of the aircraft engine; step 502 is to store the information representative of the connection state between the first and second components of the aircraft engine in a memory.

Claims

1. A connecting device (101) for connecting components of an aircraft engine (100), the connecting device comprising: A first connector (102) and a second connector (103), the first connector and the second connector being adapted to connect a first component and a second component to establish a physical transmission link between the first component and the second component, wherein the connecting device further comprises: - A transmitting member (104), the transmitting member being adapted to generate a determined physical signal; - A first transmission member (105), the first transmission member being adapted to transmit the determined physical signal between at least a first component, a second component and a third component of the first connector and the second connector; - The first component (106), the first component being included in the first connector, the first component having a determined first impedance with respect to the physical signal; - At least a second component (107) and a third component (108), the at least second component and the third component being included in the second connector, the at least second component and the third component respectively having a determined second impedance and a determined third impedance with respect to the physical signal, the second impedance being different from the third impedance; - At least one first connection element (109), the at least one first connection element being included in the first connector and associated with the first component, and the at least one first connection element being adapted to establish a connection link with at least one second connection element (110) and a third connection element (111), wherein the at least one second connection element and the third connection element are included in the second connector and are respectively associated with the second component and the third component; - A detecting member (112), the detecting member being adapted to measure at least one characteristic representative of the determined physical signal circulating in the first component, the second component and the third component; - A second transmission member (113), the second transmission member being adapted to transmit measurement data from the detecting member to a first processing member; - A first processing member (114), the first processing member being adapted to receive measurement data from the detecting member and generate an information representative of the connection state between the first component and the second component of the aircraft engine based on the measurement data; and - A display member (115, 116, 117), the display member being adapted to display an information representative of the connection state between the first component and the second component of the aircraft engine.

2. The connecting device according to claim 1, wherein, The physical transmission link is a fluid transmission link, or an electrical signal transmission link, or an optical signal transmission link.

3. The connecting device according to claim 1 or 2, wherein The determined physical signal is an electrical signal or an optical signal.

4. The connecting device according to claim 1 or 2, wherein The characteristic representative of the determined physical signal includes impedance, the intensity of the physical signal or the amplitude of the physical signal.

5. The connecting device according to claim 1 or 2, wherein The first connection element of the first connector, and the second and third connection elements of the second connector are provided on separate portions of the first and second connectors such that establishment of a connection link between two of the first, second, and third connection elements depends on the respective positions of the first and second connectors.

6. The connecting device according to claim 5, wherein, Information representative of the connection state between the first and second components is included in the following information: - No connection, corresponding to no connection link being established between the first connection element of the first connector and the second or third connection element of the second connector; - Insufficient connection, corresponding to a connection link being established between the first connection element of the first connector and the second connection element of the second connector; and, - Nominal connection, corresponding to a connection link being established between the first connection element of the first connector and the third connection element of the second connector.

7. The connecting device according to claim 1 or 2, wherein The display member is included in the connector, or in the aircraft engine, or in a device removed from the aircraft engine.

8. The connection device according to claim 1 or 2, further comprising: - A second processing member (201) adapted to process information representative of the connection state between the first and second components of the aircraft engine obtained continuously to determine the time evolution of the connection state between the first and second components of the aircraft engine; and, - A memory (204) adapted to store information representative of the connection state between components of the aircraft engine.

9. A method of using a connection device according to any one of claims 1 to 8, the method comprising the steps of: - Transmitting (401) at least one physical signal; - Transmitting (402) the physical signal between the transmitting member, the first assembly of the first connector, and the assembly of the second connector that is connected to the first assembly via the first and second or third connection elements when a connection link is established; - Measuring (403) at least one characteristic representative of the transmitted physical signal; - Generating (404) information representative of the connection state between the first and second components of the aircraft engine based on the measurement data; And, - Displaying (405) information representative of the connection state between the first and second components of the aircraft engine.

10. The method of use according to claim 9, further comprising the steps of: - Processing (501) information representative of the connection state between the first and second components of the aircraft engine obtained continuously to determine the time evolution of the connection state between the first and second components of the aircraft engine; and, - Storing (502) information representative of the connection state between the first and second components of the aircraft engine in a memory.

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