Piping fault detection in a turbine engine

Abstract

A turbine engine includes a pressurized fluid source, a piping system including a plurality of pipes in fluid communication with the pressurized fluid source, and a piping fault detection system. The piping fault detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is operatively connected to two of the plurality of pipes. Each of the plurality of pipes has at least two pressure sensors operatively connected to it.

Description

[0001] Cross-references to related applications

[0002] This application is a non-provisional application that claims priority to U.S. Provisional Application No. 63 / 334,424, filed April 25, 2022, pursuant to 35 U.S. SC §119(e), the entire contents of which are incorporated herein by reference. Technical Field

[0003] This disclosure relates to the detection of pipeline faults in gas turbine engines. Background Technology

[0004] Gas turbine engines typically consist of a turbine and a rotor assembly. Gas turbine engines, such as turbofan engines, are used for aircraft propulsion. In the case of a turbofan engine, the rotor assembly can be configured as a fan assembly. For various reasons, gas turbine engines typically include pressurized piping that transports fluid from one location to another. Attached Figure Description

[0005] The complete and practical disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0006] Figure 1 This is a cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.

[0007] Figure 2 This is a schematic diagram of a portion of a turbine according to an exemplary embodiment of the present disclosure.

[0008] Figure 3 A schematic diagram of the rear end of a turbine according to an exemplary embodiment of the present disclosure is provided.

[0009] Figure 4 A flowchart of a method for detecting pipeline faults in a pipeline system according to an example embodiment of the present disclosure is provided.

[0010] Figure 5 Example embodiments according to this disclosure are provided. Figure 1 System diagram of the engine controller for a gas turbine engine. Detailed Implementation

[0011] The inventors of this disclosure have found that improvements in the detection of ruptures or breaks in one or more of these pressurized pipes would be beneficial in the art.

[0012] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. Detailed description uses numerals and letter designations to refer to features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to refer to similar or analogous portions of this disclosure.

[0013] The term “exemplary” in this document means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as superior or better than other implementations. Furthermore, all embodiments described herein should be considered exemplary unless specifically stated otherwise. Unless the context clearly specifies otherwise, the singular forms “a,” “an,” and “this” include plural references. The term “at least one” in the context of, for example, “at least one of A, B, and C” means only A, only B, only C, or any combination of A, B, and C.

[0014] To provide cooling, compressed air from the compressor section of the gas turbine engine can be delivered via at least one compressor or exhaust extraction port to one or more cooling or exhaust circuits consisting of various pipes or conduits and connectors. The piping is configured to direct the compressed air to the desired section of the gas turbine engine. Engine requirements dictate that the engine remain operable in the presence of a faulty pipe. To achieve this, the piping system must be over-engineered, resulting in excessive pressure and flow rates throughout the engine system to provide sufficient flow and pressure under faulty pipe conditions. In current designs, each pipe includes a dedicated, independent sensor operatively connected only to that specific pipe to detect a pipe fault in that particular pipe. In this configuration, sensor failure can lead to false faulty pipe alarms.

[0015] This disclosure generally relates to a pipeline fault detection system. In at least one embodiment, the system includes a plurality of pressure sensors, such as, but not limited to, differential pressure sensors. Each pressure sensor is operatively connected to two or more of a plurality of pipelines. The pipeline fault detection system disclosed herein detects pipeline faults based on supply pressure in a compressor or relative to an adjacent pipeline system, rather than indicating a burst pipeline based on feedback from a single sensor. The system disclosed herein provides redundancy in pipeline fault detection systems, thereby eliminating erroneous pipeline fault alarms based on feedback from a single sensor.

[0016] Referring now to the accompanying drawings, where the same numerals throughout the drawings denote the same elements. Figure 1 This is a schematic cross-sectional view of a gas turbine engine 10 according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In one embodiment, the gas turbine engine 10 is a high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." For example... Figure 1As shown, the gas turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline 12 for reference), a radial direction R, and a circumferential direction C extending around the longitudinal centerline 12. Typically, the gas turbine engine 10 includes a fan section 14 and a turbine 16 disposed downstream of the fan section 14.

[0017] The exemplary turbine 16 shown typically includes an engine cowling 18 defining an annular core inlet 20. The engine cowling 18 surrounds, in a series flow relationship, a compressor section including a turbocharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24; a combustion section 26; a turbine section including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. A high-pressure (HP) shaft 34 (which may additionally or alternatively be a valve core) drives the HP turbine 28 to the HP compressor 24. A low-pressure (LP) shaft 36 (which may additionally or alternatively be a spool) drives the LP turbine 30 to the LP compressor 22. The compressor section, combustion section 26, turbine section, and exhaust nozzle section 32 together define a working gas flow path 37.

[0018] In the depicted embodiment, fan section 14 includes a fan 38 having a plurality of fan blades 40 spaced apart and coupled to disk 42. As shown, the fan blades 40 generally extend outward from disk 42 along a radial direction R. Each fan blade 40 is rotatably coupled relative to disk 42 about a pitch axis P by means of a suitable pitch-changing mechanism 44, which is configured to, for example, uniformly and collectively change the pitch of the fan blades 40. Gas turbine engine 10 also includes a power gearbox 46, and the fan blades 40, disk 42, and pitch-changing mechanism 44 together are rotatable across power gearbox 46 about a longitudinal centerline 12 via LP shaft 36. Power gearbox 46 includes a plurality of gears for adjusting the rotational speed of fan 38 relative to LP shaft 36, so that fan 38 can rotate at a more efficient fan speed.

[0019] Still referencing Figure 1 In an exemplary embodiment, the disc 42 is covered by a rotatable front hub 48 of the fan section 14 (sometimes also referred to as a "rotator"). The front hub 48 has an aerodynamic profile to facilitate airflow through multiple fan blades 40.

[0020] Furthermore, the exemplary fan section 14 includes an annular fan housing or outer nacelle 50 circumferentially surrounding at least a portion of the fan 38 and / or turbine 16. In the illustrated embodiment, the nacelle 50 is supported relative to the turbine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Additionally, a downstream section 54 of the nacelle 50 extends over the outer portion of the turbine 16 to define a bypass airflow passage 56 therebetween.

[0021] However, it should be understood that, Figure 1 The exemplary gas turbine engine 10 depicted is provided by way of example only, and in other exemplary embodiments, the gas turbine engine 10 may have other configurations. For example, although the illustrated gas turbine engine 10 is configured as a ducted gas turbine engine (i.e., including an outer nacelle 50), in other embodiments, the gas turbine engine 10 may be a ducted or non-ducted gas turbine engine (e.g., fan 38 is a non-ducted fan, and outlet guide vanes 52 cantilevered out from the engine cowling 18). Additionally or alternatively, although the illustrated gas turbine engine 10 is configured as a geared gas turbine engine (i.e., including a power gearbox 46) and a variable pitch gas turbine engine (i.e., including a fan 38 configured as a variable pitch fan), in other embodiments, the gas turbine engine 10 may additionally or alternatively be configured as a direct-drive gas turbine engine (such that the LP shaft 36 rotates at the same speed as the fan 38), as a fixed-pitch gas turbine engine (such that the fan 38 includes fan blades 40 that cannot rotate about the pitch axis P), or both. It should also be understood that, in other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may (as appropriate) be incorporated into, for example, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet gas turbine engine.

[0022] During operation of the gas turbine engine 10, a volume of air 58 enters the gas turbine engine 10 through the associated inlet 60 of the nacelle 50 and fan section 14. As the volume of air 58 passes through the fan blades 40, a portion of a first portion of air 62 is directed or delivered into a bypass airflow passage 56, and a second portion of air 64, as indicated by arrow 64, is directed or delivered into the working gas flow path 37, or more specifically, into the LP compressor 22. The ratio of the first portion of air 62 to the second portion of air 64 is commonly referred to as the bypass ratio. The pressure of the second portion of air 64 then increases as it is directed through the HP compressor 24 and into the combustion section 26, where it mixes with fuel and burns to provide combustion gases 66.

[0023] Combustion gas 66 is directed through HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a sequential stage of HP turbine stator blades 68 connected to the turbine housing and HP turbine rotor blades 70 connected to the HP shaft 34, thereby causing the HP shaft 34 to rotate to support the operation of HP compressor 24. Combustion gas 66 is then directed through LP turbine 30, where a second portion of the thermal and kinetic energy is extracted from the combustion gas 66 via a sequential stage of LP turbine stator blades 72 connected to the turbine housing and LP turbine rotor blades 74 connected to the LP shaft 36, thereby causing the LP shaft 36 to rotate to support the operation of LP compressor 22 and / or the rotation of fan 38.

[0024] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of turbine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it is directed through the bypass airflow passage 56 before exiting the fan nozzle exhaust section 76 of gas turbine engine 10, also providing propulsive thrust. HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through turbine 16.

[0025] Figure 2 yes Figure 1 A schematic diagram of a portion of the turbine 16 of the gas turbine engine 10. (As shown in the diagram) Figure 1 and Figure 2 As shown, cooling of various sections of turbine 16 is provided via compressed air 80, which is drawn from or released from a pressurized fluid source such as high-pressure compressor 24. Turbine 16 includes one or more draw-out ports 82 fluidly connected to high-pressure compressor 24. In an exemplary embodiment, one or more draw-out ports 82 may be located near an intermediate stage of high-pressure compressor 24.

[0026] The piping system 84 is used to deliver compressed air 80 to other sections of the turbine 16, such as, but not limited to, the high-pressure turbine 28, to provide cooling to various hot gas path components and / or casing components. The piping system 84 includes multiple pipes or conduits 86 (…). Figure 2 Only one pipe 86 is shown in the diagram to fluidly connect the corresponding extraction port 82 to one or more inlet ports 88 of the high-pressure turbine 28. In a non-limiting embodiment, a series of fluidly connected pipes, conduits, connectors, etc., providing a flow path between the corresponding extraction port 82 and one or more inlet ports 88 may define a single or independent cooling circuit 90.

[0027] like Figure 2As shown, a check valve 92, such as a pneumatic check valve, can be installed within the conduit 86. The check valve 92 allows compressed air 80 to flow from the high-pressure compressor 24 with minimal pressure loss, but restricts reverse flow, thereby preventing hot air from flowing back into the high-pressure compressor 24. The check valve 92 also minimizes external losses of cooling / pressurizing / purifying air in the event of a conduit failure. In a particular embodiment, the cooling circuit 90 does not include the check valve 92.

[0028] Figure 3 Exemplary embodiments according to this disclosure are provided. Figure 1 A schematic diagram of the rear end of the turbine 16 of the gas turbine engine 10. (See diagram below.) Figure 3 As shown, the piping system 84 includes multiple cooling loops 90. (Return to reference) Figure 2 It shows a single cooling circuit 90 and a corresponding pipe 86, each cooling circuit 90 having a furthest downstream end 91 defined as close to the final / last flow outlet 93 of the corresponding cooling circuit 90.

[0029] like Figure 3 As shown, turbine 16 includes a pipe fault detection system 100 or system 100. System 100 includes at least one pressure sensor or sensor 102, such as, but not limited to, a differential pressure sensor or transducer operatively connected to pipes 86 of two adjacent cooling circuits 90. In this way, pressure sensor 102 is operatively connected to both pipes 86.

[0030] In a particular embodiment, system 100 includes N D 86 and N pipes S 102 sensors. In some embodiments, the number of pipes N D Equal to the number of sensors N S For example, for Figure 3 In the embodiment shown, system 100 includes four pipes 86(a), 86(b), 86(c) and 86(d) and four sensors 102(a), 102(b), 102(c) and 102(d).

[0031] common as Figure 2 and Figure 3As shown, each sensor 102 is operatively connected via a corresponding pressure connector 104 to two pipes 86 of two adjacent cooling circuits 90, the pressure connector 104 being upstream of and close to the corresponding check valve 92 located within each pipe. Each pipe 86 includes at least two corresponding pressure connectors 104(a) and 104(b). In an exemplary embodiment, the pressure connectors 104 and check valves 92 are located at the downstream end of the corresponding cooling circuit 90, closest to the corresponding inlet port 88. This positioning allows for the detection of pipe faults at any point along a specific cooling circuit 90 upstream of the corresponding pressure connector 104. Figure 3 As shown, each pipe 86 includes at least two pressure fittings 104(a) and 104(b).

[0032] like Figure 3 As shown, each sensor 102 is operatively connected to two pipes 86 of two adjacent cooling circuits 90 via corresponding pressure connectors 104(a) and 104(b). For example, sensor 102(a) is operatively connected to pipes 86(a) and 86(b) of adjacent cooling circuits 90(a) and 90(b) via corresponding pressure connectors 104(a) and 104(b). Sensor 102(b) is operatively connected to pipes 86(b) and 86(c) of adjacent cooling circuits 90(b) and 90(c) via corresponding pressure connectors 104(a) and 104(b). Sensor 102(c) is operatively connected to pipes 86(c) and 86(d) of adjacent cooling circuits 90(c) and 90(d) via corresponding pressure connectors 104(a) and 104(b). Sensor 102(d) is operatively connected to pipes 86(d) and 86(a) of adjacent cooling circuits 90(d) and 90(a) via corresponding pressure connectors 104(a) and 104(b).

[0033] In an exemplary embodiment where sensor 102 is a differential pressure sensor, each sensor 102 is connected via a pressure connector to two pipes in two cooling circuits. Sensor 102 is designed such that each has a piston that is forced in one or opposite directions according to pressure from the corresponding cooling circuit pipe that actuates the piston. The piston may have a spring or a set of springs to hold it in a nominal position, and when the pressure increment on the piston exceeds a certain value, the piston will abut against a set of contacts. This, in turn, shuts off the continuity of the entire circuit. When the pistons of two differential pressure sensors operatively connected to pipes 86 of the two cooling circuits abut against their respective sets of contacts, a fault condition or pipe fault is indicated. When the piston of only one of the two differential pressure sensors operatively connected to the same pipe 86 abuts against its corresponding set of contacts, this can indicate a faulty sensor, rather than a pipe rupture. The value of the pressure increment can be set to target a nominal leak occurring from the pipe without indicating a pipe fault.

[0034] Sensors 102(a), 102(b), 102(c), and 102(d) are each communicatively connected to the engine controller 120 of the gas turbine engine 10, for example, via one or more wired or wireless communication links. In this respect, sensor data can be transmitted from sensors 102(a), 102(b), 102(c), and 102(d) to the engine controller 120.

[0035] In an exemplary embodiment, sensors 102(a), 102(b), 102(c), and 102(d) read the pressure difference or differential pressure between their corresponding adjacent cooling circuits 90(a), 90(b), 90(c), and 90(d). The pressure difference can be transmitted to the engine controller 120, for example, for processing. Once the read pressure difference between the two cooling circuits operatively connected to the two sensors exceeds a predetermined value, the system indicates a pipe fault. For example, one or more processors of the engine controller 120 may receive from sensor 102(a) first data indicating the pressure difference between pipe 86(a) of cooling circuit 90(a) and pipe 86(b) of cooling circuit 90(b), second data indicating the pressure difference between pipe 86(b) of cooling circuit 90(b) and pipe 86(c) of cooling circuit 90(c), third data indicating the pressure difference between pipe 86(c) of cooling circuit 90(c) and pipe 86(d) of cooling circuit 90(d), and fourth data indicating the pressure difference between pipe 86(d) of cooling circuit 90(d) and pipe 86(a) of cooling circuit 90(a).

[0036] In some cases, differential pressure received by one or more processors of engine controller 120 can indicate a pipeline fault. It should be noted that system 100 only needs differential pressure signals from the two sensors received at engine controller 120 to indicate a pipeline fault. In the event of a burst or pipeline fault, two of the four sensors 102(a), 102(b), 102(c), and 102(d) will respond to confirm the pipeline fault.

[0037] Engine controller 120 is configured to indicate a pipe fault (e.g., pipe 86(a)) in response to both first data from sensor 102(a) and second data from sensor 102(d). In other words, two sensors operatively coupled to the same pipe 86 must sense and provide data indicating a pipe fault for the pipe fault detection system to indicate the fault. If a single sensor (e.g., sensor 102(a)) provides a signal indicating a faulty pipe, while sensor 102(b) or 102(d) does not provide a similar indication, it is conceivable that the pipe fault detection system could ignore the signal from sensor 102(a) or otherwise determine that sensor 102(a) is a faulty sensor.

[0038] In this way, system 100 effectively distinguishes between pipe rupture or other fault events and sensor events indicating damage or malfunction. Upon determining that a pipe fault has occurred, one or more processors of engine controller 120 can then generate and transmit an alarm indicating that a pipe fault has occurred. This alarm can be transmitted to, for example, pilots or crew members, maintenance or service personnel, operators of gas turbine engine 10, etc.

[0039] Furthermore, the system 100 disclosed herein provides the capability not only to verify a burst pipe event but also to verify which pipe 86 needs to be inspected for repair. For example, when both sensors 102(a) and 102(d) indicate positive signals, pipe 102(a) can be marked as the pipe to be inspected for repair because both sensors 102(a) and 102(d) have pressure fittings 104(a), 104(b) operatively connected to pipe 102(a). As another example, when both sensors 102(b) and 102(c) indicate positive signals, pipe 102(c) can be marked as the pipe to be inspected for repair because both sensors 102(b) and 102(c) have pressure fittings 104(a), 104(b) operatively connected to pipe 102(c). Therefore, an alarm generated by one or more processors of the engine controller 120 can indicate a specific pipe that needs to be inspected or repaired.

[0040] Figure 4A flowchart of a method 200 for detecting a pipe fault in a piping system, such as a piping system in fluid communication with a pressurized fluid source of a turbine engine disclosed herein, is provided. Method 200 includes a step 202, receiving first data from a first pressure sensor indicating a pressure difference between a first pipe and a second pipe of the piping system, wherein the pressure difference indicates a pipe fault. In step 204, method 200 includes receiving second data from a second pressure sensor indicating a pressure difference between the first pipe and a second or third pipe of the piping system, wherein the pressure difference between the first pipe and the second or third pipe indicates a pipe fault. In step 206, method 200 includes determining a pipe fault in response to receiving the first and second data, or more precisely, in response to both the first pressure sensor indicating a pipe fault and the second pressure sensor indicating a pipe fault.

[0041] In some embodiments, second data from a second pressure sensor indicates the pressure difference between the first and third pipes of the piping system. In other embodiments, second data from a second pressure sensor indicates the pressure difference between the first and second pipes of the piping system.

[0042] In some further embodiments, the turbofan engine includes a compressor section and a turbine section, wherein a first conduit, a second conduit, and a third conduit extend from the compressor section to the turbine section. In other embodiments, the first conduit, the second conduit, and the third conduit each extend between an upstream end and a downstream end, wherein each pressure sensor is operatively in communication with its respective conduit near the downstream end of its respective conduit. Furthermore, in other embodiments, method 200 further includes transmitting an alarm indicating a conduit fault associated with the first conduit. This alarm may be a general alarm indicating that a conduit fault has occurred, or it may specifically indicate that a fault has occurred in the first conduit.

[0043] Figure 5 A system diagram of an engine controller 120 is provided. As shown, the engine controller 120 may include one or more processors 120A and one or more memory devices 120B. The one or more processors 120A may include any processing device, such as a microprocessor, microcontroller, integrated circuit, logic device, and / or other suitable processing device. The one or more memory devices 120B may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives, and / or other memory devices.

[0044] One or more memory devices 120B may store information accessible by one or more processors 120A, including computer-executable or computer-readable instructions 120C executable by one or more processors 120A. Instructions 120C may be any set of instructions that, when executed by one or more processors 120A, cause one or more processors 120A to perform an operation (e.g., an operation to determine a pipeline fault). Instructions 120C may be software written in any programming language or implemented in hardware or firmware. Additionally and / or alternatively, instructions 120C may be executed in logically and / or virtually decoupled threads on processor 120A. Memory device 120B may also store data 120D accessible by processor 120A.

[0045] The engine controller 120 may also include a network interface 120E for communicating, for example, with other components of the system 100 (e.g., via a network). The network interface 120E may include components for connecting to one or more networks, including, for example, transmitters, receivers, ports, controllers, antennas, and / or other suitable components.

[0046] The techniques discussed herein refer to computer-based systems and the actions taken by and the information sent to or from computer-based systems. Those skilled in the art will recognize that the inherent flexibility of computer-based systems allows for numerous possible configurations, combinations, task divisions, and functions among components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0047] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any combined methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0048] The following items provide further details:

[0049] A turbine engine includes a pressurized fluid source, a piping system including a plurality of pipes in fluid communication with the pressurized fluid source, and a piping fault detection system. The piping fault detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is operatively connected to two of the plurality of pipes. Each of the plurality of pipes has at least two pressure sensors operatively connected to it.

[0050] According to any of the foregoing clauses, the turbine engine wherein the plurality of pipes includes N D There are several pipes, and within them, multiple pressure sensors include N. S There are N pressure sensors, and N D equals N S .

[0051] According to any of the preceding clauses, the turbine engine, wherein each of the plurality of pipes extends between an upstream end and a downstream end of the respective pipe, wherein each pressure sensor is operatively connected to two of the plurality of pipes near the downstream ends of two of the plurality of pipes.

[0052] The turbine engine according to any of the preceding clauses, wherein each of the plurality of pressure sensors is a spring-loaded differential pressure sensor.

[0053] The turbine engine according to any of the preceding clauses, wherein the pressurized fluid source is the compressor section of the turbine engine.

[0054] The turbine engine according to any of the preceding clauses, wherein the turbine engine further includes a turbine section, and wherein two of the plurality of pipes extend from the compressor section to the turbine section.

[0055] According to any of the preceding clauses, in a turbine engine, at least one of the plurality of pipes is in fluid communication with at least one airfoil within the turbine section.

[0056] The turbine engine according to any of the preceding clauses, wherein two of the plurality of pipes define a first pipe and a second pipe operatively connected to a first pressure sensor of the plurality of sensors, wherein the first pipe originates from a first cooling circuit and the second pipe originates from a second cooling circuit.

[0057] The turbine engine according to any of the preceding clauses, wherein two of the plurality of pipes define a first pipe and a second pipe, and the plurality of pipes further include a third pipe, wherein the plurality of pressure sensors include a first pressure sensor and a second pressure sensor, wherein the first pressure sensor is operatively connected to the first pipe and the second pipe, and wherein the second pressure sensor is operatively connected to the first pipe and the third pipe.

[0058] The turbine engine according to any of the preceding clauses further includes an engine controller. The engine controller is configured to receive first data from a first pressure sensor indicating a pressure difference between a first pipe and a second pipe, the first data indicating a pipe fault. The engine controller is further configured to receive second data from a second pressure sensor indicating a pressure difference between the first pipe and a second pipe or a third pipe, the second data indicating a pipe fault, and in response to both the first data and the second data indicating a pipe fault, determine a pipe fault associated with the first pipe.

[0059] According to any of the preceding clauses, the turbine engine wherein the second data received from the second pressure sensor indicates the pressure difference between the first and third pipes of the piping system.

[0060] According to any of the preceding clauses, the turbine engine further includes a third pressure sensor, wherein the third pressure sensor is operatively connected to the second and third conduits, and wherein the third pressure sensor is operatively connected to the second and third conduits.

[0061] The turbine engine according to any of the preceding clauses further includes an engine controller configured to receive first data from a first pressure sensor indicating a pressure difference between a first pipe and a second pipe, the first data indicating a pipe fault; and to receive second data from a second pressure sensor indicating no pressure difference between the first pipe and the second pipe or a third pipe, the second data not indicating a pipe fault; and to determine a pressure sensor fault associated with the first pressure sensor in response to the first data indicating a pipe fault and the second data not indicating a pipe fault.

[0062] The turbine engine according to any of the preceding clauses, wherein the first conduit includes a first pressure connector and the second conduit includes a second pressure connector, wherein the first pressure sensor is operatively connected to the first conduit via the first pressure connector and operatively connected to the second conduit via the second pressure connector.

[0063] A method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine, the method comprising receiving first data from a first pressure sensor indicating a pressure difference between a first pipe and a second pipe of the piping system, the first data indicating a pipe fault; receiving second data from a second pressure sensor indicating a pressure difference between the first pipe and a second pipe or a third pipe of the piping system, the second data indicating a pipe fault; and determining a pipe fault associated with the first pipe in response to both the first data and the second data indicating a pipe fault.

[0064] The method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine according to any of the preceding clauses, wherein receiving second data from a second pressure sensor includes receiving second data from the second pressure sensor indicating the pressure difference between a first pipe and a third pipe of the piping system.

[0065] The method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine according to any of the preceding clauses, wherein receiving second data from a second pressure sensor includes receiving second data from the second pressure sensor indicating the pressure difference between a first pipe and a second pipe in the piping system.

[0066] The method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine according to any of the preceding clauses, wherein the turbine engine includes a compressor section and a turbine section, and wherein a first pipe, a second pipe, and a third pipe extend from the compressor section to the turbine section.

[0067] A method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine, according to any of the preceding clauses, wherein a first pipe, a second pipe, and a third pipe each extend between an upstream end and a downstream end, and wherein each pressure sensor is operatively connected to the respective pipe near the downstream end of the respective pipe.

[0068] The method for detecting a pipe fault in a piping system in fluid communication with a pressurized fluid source of a turbine engine, as described in any of the preceding clauses, further includes transmitting an alarm indicating a pipe fault associated with a first pipe.

[0069] A non-transitory computer-readable medium includes computer-executable instructions that, when executed by one or more processors of an engine controller associated with a turbine engine, cause the one or more processors of the engine controller to receive, from a first pressure sensor, first data indicating a pressure difference between a first pipe and a second pipe of a piping system of the turbine engine, and first data indicating a piping fault; receive from a second pressure sensor, second data indicating a pressure difference between a first pipe and a second pipe or a third pipe of the piping system, the second data indicating a piping fault; and, in response to both the first data and the second data indicating a piping fault, determine a piping fault associated with the first pipe.

[0070] A non-transitory computer-readable medium comprising computer-executable instructions as described in any of the preceding clauses, wherein second data received from a second pressure sensor indicates the pressure difference between a first pipe and a third pipe of a piping system.

[0071] A non-transitory computer-readable medium comprising computer-executable instructions as described in any of the preceding clauses, wherein second data received from a second pressure sensor indicates the pressure difference between a first pipe and a second pipe of a piping system.

[0072] A non-transitory computer-readable medium comprising computer-executable instructions as described in any of the preceding clauses, wherein the first conduit, the second conduit, and the third conduit are in fluid communication with the compressor of a turbine engine.

Claims

1. A turbine engine, characterized in that, include: Pressurized fluid source; A piping system comprising a plurality of pipes in fluid communication with the pressurized fluid source; and A pipeline fault detection system includes a plurality of pressure sensors, each of the plurality of pressure sensors being operatively connected to two of the plurality of pipelines, and each of the plurality of pipelines having at least two pressure sensors operatively connected to it. Wherein, two of the plurality of pipes define a first pipe and a second pipe, and the plurality of pipes further include a third pipe, wherein the plurality of pressure sensors include a first pressure sensor and a second pressure sensor, wherein the first pressure sensor is operatively connected to the first pipe and the second pipe, and wherein the second pressure sensor is operatively connected to the first pipe and the third pipe, and a third pressure sensor, wherein the third pressure sensor is operatively connected to the second pipe and the third pipe.

2. The turbine engine according to claim 1, characterized in that, in, The plurality of pipes includes N D A pipe, wherein the plurality of pressure sensors include N S There are N pressure sensors, and N D equals N S .

3. The turbine engine according to claim 1, characterized in that, in, Each of the plurality of pipes extends between the upstream and downstream ends of a corresponding pipe, wherein each of the plurality of pressure sensors is operatively connected to two of the plurality of pipes near the downstream ends of the two pipes.

4. The turbine engine according to claim 1, characterized in that, in, Each of the plurality of pressure sensors is a spring-loaded differential pressure sensor.

5. The turbine engine according to claim 1, characterized in that, in, The pressurized fluid source is the compressor section of the turbine engine.

6. The turbine engine according to claim 5, characterized in that, in, The turbo engine further includes a turbine section, and wherein two of the plurality of pipes extend from the compressor section to the turbine section.

7. The turbine engine according to claim 6, wherein, At least one of the plurality of pipes is in fluid communication with at least one airfoil within the turbine section.

8. The turbine engine according to claim 1, characterized in that, in, Two of the plurality of pipes define a first pipe and a second pipe operably connected to a first pressure sensor of the plurality of pressure sensors, wherein the first pipe is fluidly connected to a first cooling circuit and the second pipe is fluidly connected to a second cooling circuit.

9. The turbine engine according to claim 1, characterized in that, in, The first pipe includes a first pressure connector and the second pipe includes a second pressure connector, wherein the first pressure sensor is operatively connected to the first pipe via the first pressure connector and operatively connected to the second pipe via the second pressure connector.

10. The turbine engine according to claim 1, characterized in that, Further includes: Engine controller, the engine controller being configured to: Receive first data from the first pressure sensor indicating the pressure difference between the first pipe and the second pipe, the first data indicating a pipe fault; Receive second data from the second pressure sensor, indicating the pressure difference between the first pipe and the second pipe or the third pipe, the second data indicating a pipe fault; and In response to the first and second data indicating a pipeline fault, a pipeline fault associated with the first pipeline is determined.

11. The turbine engine according to claim 10, characterized in that, in, The second data received from the second pressure sensor indicates the pressure difference between the first pipe and the third pipe of the piping system.

12. The turbine engine according to claim 1, characterized in that, Further includes: Engine controller, the engine controller being configured to: Receive first data from the first pressure sensor indicating the pressure difference between the first pipe and the second pipe, the first data indicating a pipe fault; Receive second data from the second pressure sensor indicating that there is no pressure difference between the first pipe and the second pipe or the third pipe, and the second data does not indicate a pipe malfunction; and In response to the first data indicating a pipeline fault and the second data not indicating a pipeline fault, a pressure sensor fault associated with the first pressure sensor is determined.

13. A method for detecting pipeline faults in a pipeline system in fluid communication with a pressurized fluid source of a turbine engine, characterized in that, The method includes: First data indicating the pressure difference between a first pipe and a second pipe in the piping system is received from a first pressure sensor; the first data indicating a pipe fault. Receive second data from a second pressure sensor, indicating the pressure difference between the first pipe and the second or third pipe of the piping system, the second data indicating a pipe fault; and In response to the first and second data indicating a pipeline fault, a pipeline fault associated with the first pipeline is determined. Receiving the second data from the second pressure sensor includes receiving second data from the second pressure sensor that indicates the pressure difference between the first pipe and the third pipe of the piping system.

14. The method according to claim 13, characterized in that, in, Receiving the second data from the second pressure sensor includes receiving second data from the second pressure sensor that indicates the pressure difference between the first pipe and the second pipe of the piping system.

15. The method according to claim 13, characterized in that, in, The turbo engine includes a compressor section and a turbine section, wherein the first pipe, the second pipe and the third pipe extend from the compressor section to the turbine section.

16. The method according to claim 13, characterized in that, in, The first, second, and third pipes each extend between an upstream and a downstream end, and each pressure sensor is operatively connected to the respective pipe near its downstream end.

17. The method according to claim 13, characterized in that, Further includes: An alarm is transmitted indicating a fault in the pipeline associated with the first pipeline.

Images