Patent Publication Number: US-2022235715-A1

Title: System and method for fault sensing flow components

Description:
FIELD 
     The present disclosure relates generally to systems and methods for detecting fault conditions in flow components such as in gas turbine engines. 
     BACKGROUND 
     Typical aircraft propulsion systems include one or more gas turbine engines. The gas turbine engines generally include a turbomachine, the turbomachine including, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air is provided to an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. The combustion gases are routed from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is then routed through the exhaust section, e.g., to atmosphere. 
     Certain operations and systems of the gas turbine engines and aircraft include fuel systems that deliver fuel and fluid systems that deliver fluids to various components of the engine and may be controlled by engine management systems. Detection and monitoring systems can be used with such fuel systems and fluid systems for monitoring of the systems of the engine. 
     BRIEF DESCRIPTION 
     Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention. 
     In one exemplary embodiment of the present disclosure, a turbomachine for a vehicle is provided. The turbomachine includes a manifold configured to channel a flow of fluid therethrough; a first pressure measurement device in communication with the manifold and configured to determine a first pressure difference (ΔP1); a second pressure measurement device in communication with the manifold and configured to determine a second pressure difference (ΔP2); a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal; and an engine controller operably coupled to the data selector device such that the engine controller receives the single pressure signal indicating a pressure differential of the manifold. 
     In certain exemplary embodiments the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     In certain exemplary embodiments when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     In certain exemplary embodiments when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     In certain exemplary embodiments when the logic circuit determines that only one of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference and the second pressure difference that is within the predetermined pressure range. 
     In certain exemplary embodiments the engine controller, in response to receiving the single pressure signal, compares the single pressure signal to a predetermined range. 
     In certain exemplary embodiments when the engine controller determines the single pressure signal is within the predetermined range, the engine controller detects a positive condition of the manifold, and when the engine controller determines the single pressure signal is outside of the predetermined range, the engine controller detects a fail condition of the manifold. 
     In certain exemplary embodiments the engine controller includes a monitoring system that indicates the positive condition or the fail condition of the manifold. 
     In certain exemplary embodiments the first pressure measurement device includes a first pressure sensor at a first upstream location and a second pressure sensor at a first downstream location, and the second pressure measurement device includes a third pressure sensor at a second upstream location and a fourth pressure sensor at a second downstream location. 
     In certain exemplary embodiments the turbomachine includes a valve disposed in a portion of the manifold, wherein the valve is transitionable between an open position and a closed position. 
     In another exemplary embodiment of the present disclosure, a computing system for a component of a vehicle is provided. The computing system includes a first pressure measurement device in communication with the component and configured to determine a first pressure difference (ΔP1); a second pressure measurement device in communication with the component and configured to determine a second pressure difference (ΔP2); a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal; and a controller having one or more processors and one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, in performing the operations, the one or more processors are configured to receive the single pressure signal indicating a pressure differential of the component. 
     In certain exemplary embodiments the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     In certain exemplary embodiments when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     In certain exemplary embodiments when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     In certain exemplary embodiments when the logic circuit determines that only one of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference and the second pressure difference that is within the predetermined pressure range. 
     In certain exemplary embodiments the one or more processors are further configured to, in response to receiving the single pressure signal, compare the single pressure signal to a predetermined range. 
     In an exemplary aspect of the present disclosure, a method is provided for measuring pressure at a component of a vehicle. The method includes receiving, at a data selector device, two or more signals indicating a first and second pressure difference for the component; generating a single pressure signal from the first and second pressure difference; and receiving, by one or more computing devices, the single pressure signal indicating a pressure differential of the component. 
     In certain aspects the generating the single pressure signal from the first and second pressure difference comprises the data selector device using a logic circuit to generate the single pressure signal and the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     In certain aspects when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     In certain aspects when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     These and other features, aspects and advantages of the present subject matter will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the subject matter and, together with the description, explain the principles of the subject matter. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A full and enabling disclosure of the present subject matter, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: 
         FIG. 1  is a schematic cross-sectional view of an exemplary gas turbine engine in accordance with exemplary embodiments of the present disclosure. 
         FIG. 2  is a perspective view of an exemplary control system and manifold in accordance with exemplary embodiments of the present disclosure. 
         FIG. 3  is a side elevation view of an exemplary control system and manifold in accordance with exemplary embodiments of the present disclosure. 
         FIG. 4  is a rear elevation view of an exemplary control system and manifold in accordance with exemplary embodiments of the present disclosure. 
         FIG. 5  is a top elevation view of an exemplary control system and manifold in accordance with exemplary embodiments of the present disclosure. 
         FIG. 6  is a perspective view of an exemplary control system and manifold in accordance with another exemplary embodiment of the present disclosure. 
         FIG. 7  is a side elevation view of an exemplary control system and manifold in accordance with another exemplary embodiment of the present disclosure. 
         FIG. 8  is a rear elevation view of an exemplary control system and manifold in accordance with another exemplary embodiment of the present disclosure. 
         FIG. 9  is a side elevation view of an exemplary control system and manifold with a wall portion of the manifold hidden in accordance with exemplary embodiments of the present disclosure. 
         FIG. 10  is a top elevation view of an exemplary control system and manifold in accordance with exemplary embodiments of the present disclosure. 
         FIG. 11  provides a block diagram of a control system in accordance with exemplary embodiments of the present disclosure. 
         FIG. 12  is an example controller including a built-in status monitoring system according to exemplary embodiments of the present disclosure. 
         FIG. 13  is a flow diagram of an exemplary method of measuring pressure at a manifold of a vehicle in accordance with exemplary embodiments of the present disclosure. 
         FIG. 14  is an example computing system according to exemplary embodiments of the present disclosure. 
     
    
    
     Corresponding reference characters indicate corresponding parts throughout the several views. The exemplifications set out herein illustrate exemplary embodiments of the disclosure, and such exemplifications are not to be construed as limiting the scope of the disclosure in any manner. 
     DETAILED DESCRIPTION 
     Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. 
     The following description is provided to enable those skilled in the art to make and use the described embodiments contemplated for carrying out the invention. Various modifications, equivalents, variations, and alternatives, however, will remain readily apparent to those skilled in the art. Any and all such modifications, variations, equivalents, and alternatives are intended to fall within the scope of the present invention. 
     For purposes of the description hereinafter, the terms “upper”, “lower”, “right”, “left”, “vertical”, “horizontal”, “top”, “bottom”, “lateral”, “longitudinal”, and derivatives thereof shall relate to the invention as it is oriented in the drawing figures. However, it is to be understood that the invention may assume various alternative variations, except where expressly specified to the contrary. It is also to be understood that the specific devices illustrated in the attached drawings, and described in the following specification, are simply exemplary embodiments of the invention. Hence, specific dimensions and other physical characteristics related to the embodiments disclosed herein are not to be considered as limiting. 
     As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. 
     The terms “forward” and “aft” refer to relative positions within a gas turbine engine, with forward referring to a position closer to an engine inlet and aft referring to a position closer to an engine nozzle or exhaust. 
     The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. 
     The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise. 
     Additionally, the terms “low,” “high,” or their respective comparative degrees (e.g., lower, higher, where applicable) each refer to relative speeds within an engine, unless otherwise specified. For example, a “low-pressure turbine” operates at a pressure generally lower than a “high-pressure turbine.” Alternatively, unless otherwise specified, the aforementioned terms may be understood in their superlative degree. For example, a “low-pressure turbine” may refer to the lowest maximum pressure turbine within a turbine section, and a “high-pressure turbine” may refer to the highest maximum pressure turbine within the turbine section. 
     Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and/or systems. For example, the approximating language may refer to being within a ten percent margin. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. 
     Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. 
     A vehicle of the present disclosure includes a control system that allows for a first pressure measurement device and a second pressure measurement device in communication with a component, e.g., a manifold or other fluid flow component, to each take a pressure reading at an upstream location of the manifold and at a downstream location of the manifold. These pressure readings are indicated in  FIG. 11  at P1, P2, P3, and P4. This allows for the control system to determine a first pressure difference (ΔP1) and a second pressure difference (ΔP2). A data selector device of the control system receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal. An engine controller is operably coupled to the data selector device such that the engine controller receives the single pressure signal indicating a pressure differential of the manifold. In this manner, advantageously, the control system of the present disclosure reduces multiple pressure readings P1, P2, P3, and P4, which each would need to be transmitted to a controller in multiple signals in conventional systems, to a single pressure signal that is sent to the engine controller. Thus, the control system of the present disclosure allows for a single signal to be transmitted to the engine controller thus reducing the space and/or number of channels required of the engine controller. 
     It is contemplated that the control system of the present disclosure can use an integrated differential pressure sensor array that measures static pressure differences through a component or manifold for detecting broken pipe conditions in fluid flow systems of a turbomachine or other components of other vehicles. It is envisioned that redundant differential pressure measurements across a manifold or other flow component provide robust detection of failed flow components, e.g., piping systems, and control logic of the control system requires positive indication from both pressure measurement devices to output an alarm signal or error message. It is also contemplated that control logic of a monitoring system of the present disclosure provides an alarm signal or error message to indicate fail conditions of a flow component, e.g., a manifold. For example, in exemplary embodiments, control logic of the control system requires positive indication from both pressure measurement devices to output an alarm signal. It is envisioned that an alarm system of the monitoring system may include a continuous signal with multiple alarm levels. For example, different indicators may be used to indicate different levels of the fail condition, e.g., high, medium, and low. The system of the present disclosure also provides for redundant differential pressure measurements combined into a single signal to reduce false positives. 
     For example, the logic circuit of the data selector device of the present disclosure is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. In exemplary embodiments, when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. In exemplary embodiments, when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. In exemplary embodiments, when the logic circuit determines that only one of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference and the second pressure difference that is within the predetermined pressure range. 
       FIG. 1  provides a schematic cross-sectional view of an exemplary turbomachine as may incorporate various embodiments of the present disclosure. Particularly,  FIG. 1  provides an aviation high-bypass turbofan engine or gas turbine engine  10 . The turbofan  10  of  FIG. 1  can be mounted to an aerial vehicle, such as a fixed-wing aircraft, and can produce thrust for propulsion of the aerial vehicle. For reference, the turbofan  10  defines an axial direction A, a radial direction R, and a circumferential direction. Moreover, the turbofan  10  defines an axial centerline or longitudinal axis  12  that extends therethrough for reference purposes. In general, the axial direction A extends parallel to the longitudinal axis  12 , the radial direction R extends outward from and inward to the longitudinal axis  12  in a direction orthogonal to the axial direction A, and the circumferential direction extends three hundred sixty degrees (360°) around the longitudinal axis  12 . 
     The turbofan  10  includes a core gas turbine engine  14  and a fan section  16  positioned upstream thereof. The core engine  14  includes a tubular outer casing  18  that defines an annular core inlet  20 . The outer casing  18  further encloses and supports a booster or low pressure compressor  22  for pressurizing the air that enters core engine  14  through core inlet  20 . A high pressure, multi-stage, axial-flow compressor  24  receives pressurized air from the LP compressor  22  and further increases the pressure of the air. The pressurized air stream flows downstream to a combustor  26  where fuel is injected into the pressurized air stream and ignited to raise the temperature and energy level of the pressurized air. The high energy combustion products flow from the combustor  26  downstream to a high pressure turbine  28  for driving the high pressure compressor  24  through a high pressure spool  30  or a second rotatable component. The high energy combustion products then flow to a low pressure turbine  32  for driving the LP compressor  22  and the fan section  16  through a low pressure spool  34  or a first rotatable component. The LP spool  34  is coaxial with the HP spool  30  in this example embodiment. After driving each of the turbines  28  and  32 , the combustion products exit the core engine  14  through an exhaust nozzle  36  to produce propulsive thrust. 
     The fan section  16  includes a rotatable, axial-flow fan rotor  38  that is surrounded by an annular fan casing  40 . The fan casing  40  is supported by the core engine  14  by a plurality of substantially radially-extending, circumferentially-spaced outlet guide vanes  42 . In this way, the fan casing  40  encloses the fan rotor  38  and a plurality of fan blades  44 . A downstream section  46  of the fan casing  40  extends over an outer portion of the core engine  14  to define a bypass passage  48 . Air that passes through the bypass passage  48  provides propulsive thrust as will be explained further below. In some alternative embodiments, the LP spool  34  may be connected to the fan rotor  38  via a speed reduction device, such as a reduction gear gearbox in an indirect-drive or geared-drive configuration. Such speed reduction devices can be included between any suitable shafts/spools within the turbofan  10  as desired or required. 
     During operation of the turbofan  10 , an initial or incoming airflow, represented by arrow  50 , enters the turbofan  10  through an inlet  52  defined by the fan casing  40 . The airflow  50  passes through the fan blades  44  and splits into a first air flow (represented by arrow  54 ) that moves through the bypass passage  48  and a second air flow (represented by arrow  56 ) which enters the LP compressor  22  through the core inlet  20 . 
     The pressure of the second airflow  56  is progressively increased by the LP compressor  22  and then enters the HP compressor  24 , as represented by arrow  58 . The discharged pressurized air stream flows downstream to the combustor  26  where fuel is introduced to generate combustion gases or products. The combustion products  60  exit the combustor  26  and flow through the HP turbine  28 . The combustion products  60  then flow through the LP turbine  32  and exit the exhaust nozzle  36  to produce thrust. Moreover, as noted above, a portion of the incoming airflow  50  flows through the bypass passage  48  and through an exit nozzle defined between the fan casing  40  and the outer casing  18  at the downstream section  46  of the fan casing  40 . In this way, substantial propulsive thrust is produced. 
     As further shown in  FIG. 1 , the combustor  26  defines an annular combustion chamber  62  that is generally coaxial with the longitudinal centerline axis  12 , as well as an inlet  64  and an outlet  66 . The combustor  26  receives an annular stream of pressurized air from a high pressure compressor discharge outlet  69 . A portion of this compressor discharge air (“CDP” air) flows into a mixer (not shown). Fuel is injected from a fuel nozzle  68  to mix with the air and form a fuel-air mixture that is provided to the combustion chamber  62  for combustion. Ignition of the fuel-air mixture is accomplished by a suitable igniter, and the resulting combustion gases  60  flow in an axial direction A toward and into an annular, first stage turbine nozzle  72 . The nozzle  72  is defined by an annular flow channel that includes a plurality of radially-extending, circumferentially-spaced nozzle vanes  74  that turn the gases so that they flow angularly and impinge upon the first stage turbine blades of the HP turbine  28 . For this embodiment, the HP turbine  28  rotates the HP compressor  24  via the HP spool  30  and the LP turbine  32  drives the LP compressor  22  and the fan rotor  38  via the LP spool  34 . 
     Referring to  FIG. 1 , a control system or computing system  100  of the present disclosure may be in communication with a downstream section  46  of the fan casing  40  that extends over an outer portion of the core engine  14  to define a bypass passage  48 . It is also contemplated that the control system  100  of the present disclosure may in communication with any other components of the core engine  14  that are configured to channel a flow of fluid or fuel therethrough. 
       FIGS. 2-14  illustrate exemplary embodiments of the present disclosure. Referring to  FIGS. 2-5 , in an exemplary embodiment, a control or computing system  100  that may be used with the exemplary gas turbine engine  10  shown in  FIG. 1 . The computing system  100  is part of a system including a manifold or component  102  of a turbomachine  104 . The manifold  102  is configured to channel a flow of fluid  106  therethrough. It is contemplated that the manifold  102  of the present disclosure may be any component of the core engine  14  that is configured to channel a flow of fluid or fuel therethrough. The flow of fluid  106  travels through the manifold  102  from an upstream portion  108  to a downstream portion  110 . 
     Referring to  FIGS. 2-5 and 11 , in an exemplary embodiment, the control system  100  includes a first pressure measurement device  112 , a second pressure measurement device  114 , a data selector device  116 , and an engine controller  118 . 
     In exemplary embodiments, the first pressure measurement device  112  is in communication with the manifold  102  and is configured to determine a first pressure difference (ΔP1). For example, the first pressure measurement device  112  includes a first pressure sensor  120  at a first upstream location  122  and a second pressure sensor  124  at a first downstream location  126 . The first pressure sensor  120  is configured to determine a first pressure reading P1 upstream of a portion of a component  128  or specific location of the manifold  102 , e.g., it is also contemplated that the component may be a valve  250  ( FIGS. 6-10 ) as described in detail below, and the second pressure sensor  124  is configured to determine a second pressure reading P2 downstream of the component  128  or specific location of the manifold  102 , e.g., it is also contemplated that the component may be a valve  250  ( FIGS. 6-10 ) as described in detail below. The first pressure reading P1 and the second pressure reading P2 are used to determine the first pressure difference (ΔP1) at a portion of the manifold  102 . 
     In exemplary embodiments, the second pressure measurement device  114  is in communication with the manifold  102  and is configured to determine a second pressure difference (ΔP2). For example, the second pressure measurement device  114  includes a third pressure sensor  130  at a second upstream location  132  and a fourth pressure sensor  134  at a second downstream location  136 . The third pressure sensor  130  is configured to determine a third pressure reading P3 upstream of a portion of a component  128  or specific location of the manifold  102 , e.g., it is also contemplated that the component may be a valve  250  ( FIGS. 6-10 ) as described in detail below, and the fourth pressure sensor  134  is configured to determine a fourth pressure reading P4 downstream of the component  128  or specific location of the manifold  102 , e.g., it is also contemplated that the component may be a valve  250  ( FIGS. 6-10 ) as described in detail below. The third pressure reading P3 and the fourth pressure reading P4 are used to determine the second pressure difference (ΔP2) at a portion of the manifold  102 . In exemplary embodiments, it is envisioned that the first pressure measurement device  112  and the second pressure measurement device  114  may include pressure transducers, sensors, or other sensing components. It is envisioned that the control system  100  and manifold  102  of the present disclosure is a cavity off-take elbow that can have a plenum to elbow static pressure difference measured and monitored by the control system  100  of the present disclosure. In other exemplary embodiments, the control system  100  of the present disclosure can measure and monitor static pressure differences of any cavity, flow regions, or components of a vehicle. 
     In exemplary embodiments, the data selector device  116  is in communication with the first pressure measurement device  112  and the second pressure measurement device  114 . For example, referring to  FIGS. 2-5 , the data selector device  116  is in communication with the first pressure measurement device  112  via a first signal line  140  and the data selector device  116  is in communication with the second pressure measurement device  114  via a second signal line  142 . It is also contemplated that the data selector device  116  is in communication with the first pressure measurement device  112  and the second pressure measurement device  114  via other communication means such as via a wireless communication system. 
     The data selector device  116  receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal  220 . Importantly, in this manner, a single pressure signal  220  is transmitted to the engine controller  118  as shown in  FIG. 11 . For example, the logic circuit of the data selector device  116  of the present disclosure is configured to determine if the first pressure difference (ΔP1) and the second pressure difference (ΔP2) are within a predetermined pressure range. In exemplary embodiments, when the logic circuit determines that both of the first pressure difference (ΔP1) and the second pressure difference (ΔP2) are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference (ΔP1) and the second pressure difference (ΔP2). In exemplary embodiments, when the logic circuit determines that both of the first pressure difference (ΔP1) and the second pressure difference (ΔP2) are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. In exemplary embodiments, when the logic circuit determines that only one of the first pressure difference (ΔP1) and the second pressure difference (ΔP2) are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference (ΔP1) and the second pressure difference (ΔP2) that is within the predetermined pressure range. It is envisioned that any number of logic circuits can be used, such as an AND logic gate. 
     It is contemplated that the predetermined pressure range can be any desired range or calculated range for a particular flow application for any flow components of a turbomachine  104 . For example, calculations can be made for a particular flow application to determine an appropriate predetermined pressure range. 
     In an exemplary embodiment, the data selector device  116  comprises a multiplexer, although other components are contemplated. For example, the data selector device  116  may be an electronic device, a programmable device or circuit that sends out an electrical signal based on some logic, or a pressure signal device that is able to read an analog pressure gauge and send a pressure signal. 
     In exemplary embodiments, the engine controller  118  is operably coupled to the data selector device  116  such that the engine controller  118  receives the single pressure signal  220  indicating a pressure differential of the manifold  102 ; and in response to receiving the single pressure signal  220 , compares the single pressure signal  220  to a predetermined range. It is contemplated that the engine controller  118  may be any electronic device or other programmable device or circuit that is able to send out an electrical signal. 
     It is envisioned that the engine controller  118  may be coupled to the data selector device  116  via a third signal line  144 . It is also contemplated that the data selector device  116  is in communication with the engine controller  118  via other communication means such as via a wireless communication system. 
     In the control system  100  of the present disclosure, when the engine controller  118  determines the single pressure signal  220  is within the predetermined range, the engine controller  118  detects a positive condition of the manifold  102 . Furthermore, when the engine controller  118  determines the single pressure signal  220  is outside of the predetermined range, the engine controller  118  detects a fail condition of the manifold  102 . It is contemplated that the predetermined range can be any desired range for a manifold  102  or other component of a turbomachine  104  to indicate a positive condition or a fail condition of the component. For example, the measuring of a static pressure difference through such a manifold or other component  102  allows for the detection of, for example, a broken pipe condition in a flow or fuel system of a gas turbine engine  10 . 
       FIG. 11  provides a schematic view of the control system  100  for a vehicle of the present disclosure. As described herein, importantly, the control system  100  of the present disclosure allows for a first pressure measurement device  112  and a second pressure measurement device  114  in communication with a component, e.g., a manifold  102  ( FIGS. 2-5 ), to each take a pressure reading at an upstream location of the manifold  102  and at a downstream location of the manifold  102 . These pressure readings are indicated in  FIG. 11  at P1, P2, P3, and P4. This allows for the control system  100  to determine a first pressure difference (ΔP1) and a second pressure difference (ΔP2). The data selector device  116  of the control system  100  receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal  220 . The engine controller  118  is operably coupled to the data selector device  116  such that the engine controller  118  receives the single pressure signal  220  indicating a pressure differential of the manifold  102 ; and in response to receiving the single pressure signal  220 , compares the single pressure signal  220  to a predetermined range. In this manner, advantageously, the control system  100  of the present disclosure reduces multiple pressure readings P1, P2, P3, and P4, which each would need to be transmitted to a controller in multiple signals in conventional systems, to a single pressure signal  220  that is sent to the engine controller  118 . Thus, the control system  100  of the present disclosure allows for a single signal to be transmitted to the engine controller  118  thus reducing the space and/or number of channels required of the engine controller  118 . 
     It is contemplated that the control system  100  of the present disclosure can use an integrated differential pressure sensor array that measures static pressure differences through a component or manifold  102  for detecting broken pipe conditions in fluid flow systems of a turbomachine  104  or other components of other vehicles. It is envisioned that redundant differential pressure measurements across a manifold or other flow component provide robust detection of failed flow components, e.g., piping systems, and control logic of the control system  100  requires positive indication from both pressure measurement devices to output an alarm signal or error message. It is also contemplated that control logic of the monitoring system  300  provides an alarm signal or error message to indicate fail conditions of a flow component, e.g., a manifold  102 . For example, in exemplary embodiments, control logic of the control system  100  requires positive indication from both pressure measurement devices to output an alarm signal or error message. It is envisioned that an alarm system of the monitoring system  300  may include a continuous signal with multiple alarm levels. For example, different indicators may be used to indicate different levels of the fail condition, e.g., high, medium, and low. The system of the present disclosure also provides for redundant differential pressure measurements combined into a single signal to reduce false positives. 
     In some exemplary embodiments, all of the components of the control system  100  are onboard the turbofan  10 . In other embodiments, some of the components of the control system  100  are onboard the turbofan  10  and some are offboard the turbofan  10 . For instance, some of the offboard components can be mounted to a wing, fuselage, or other suitable structure of an aerial vehicle to which the turbofan  10  is mounted. 
     Furthermore, referring to  FIG. 12 , the control system  100  of the present disclosure includes a controller  130  having a built-in status monitoring system  300 . The built-in status monitoring system  300  is able to indicate a status of the manifold or other component  102  of a gas turbine engine  10 . For example, the monitoring system  300  indicates the positive condition or the fail condition of the manifold  102 . It is also contemplated that the status monitoring system  300  may be able to provide indication of other states of the manifold  102  or other components of the gas turbine engine  10 . It is contemplated that control logic of the monitoring system  300  provides an alarm signal or error message to indicate fail conditions of a flow component, e.g., a manifold  102 . For example, in exemplary embodiments, control logic of the control system  100  requires positive indication from both pressure measurement devices to output an alarm signal or error message. It is envisioned that an alarm system of the monitoring system  300  may include a continuous signal with multiple alarm levels. For example, different indicators may be used to indicate different levels of the fail condition, e.g., high, medium, and low. 
       FIGS. 6-10  illustrate another exemplary embodiment of the present disclosure. The embodiment illustrated in  FIGS. 6-10  includes similar components to the embodiment illustrated in  FIGS. 2-5 , and the similar components are denoted by a reference number followed by the letter A. For the sake of brevity, these similar components and the similar steps of using control system  100 A ( FIGS. 6-10 ) will not all be discussed in conjunction with the embodiments illustrated in  FIGS. 6-10 . 
     Referring to  FIGS. 6-10 , the control system  100 A of the present disclosure may include a valve  250  disposed in a portion of the manifold  102 A. The valve  250  is transitionable between an open position and a closed position. In this manner, the first pressure sensor  120 A is configured to determine a first pressure reading P1 upstream of the valve  250  and the second pressure sensor  124 A is configured to determine a second pressure reading P2 downstream of the valve  250 . The first pressure reading P1 and the second pressure reading P2 are used to determine the first pressure difference (ΔP1) at a portion of the manifold  102 . Furthermore, the third pressure sensor  130 A is configured to determine a third pressure reading P3 upstream of the valve  250  and the fourth pressure sensor  134 A is configured to determine a fourth pressure reading P4 downstream of the valve  250  ( FIGS. 6-10 ). The third pressure reading P3 and the fourth pressure reading P4 are used to determine the second pressure difference (ΔP2) at a portion of the manifold  102 . 
     In this manner, a control system  100 A of the present disclosure can be used to determine if there is blockage at the valve  250 , e.g., if debris or other contaminants are keeping the valve  250  open when the valve  250  should be closed or if the valve  250  is failing. It is contemplated that the control system  100 A of the present disclosure can also determine by a large change in the differential pressure if the valve  250  is in an open position or a closed position. The system of the present disclosure also provides for redundant differential pressure measurements combined into a single signal to reduce false positives. 
       FIG. 13  provides a flow diagram of an exemplary method ( 400 ) of measuring pressure at a manifold or component of a vehicle in accordance with exemplary embodiments of the present disclosure. For instance, the exemplary method ( 400 ) may be utilized for operating the engine  10  described herein. It should be appreciated that the method ( 400 ) is discussed herein only to describe exemplary aspects of the present subject matter and is not intended to be limiting. In an exemplary embodiment, the method ( 400 ) of measuring pressure at a component of a vehicle includes receiving, at a data selector device, two or more signals indicating a first and second pressure difference for the component; generating a single pressure signal from the first and second pressure difference; and receiving, by one or more computing devices, the single pressure signal indicating a pressure differential of the component. 
     In other exemplary embodiments, at ( 402 ), the method ( 400 ) includes determining a first pressure difference (ΔP1) at the component. Next, at ( 404 ), the method ( 400 ) includes determining a second pressure difference (ΔP2) at the component. 
     At ( 406 ), the method ( 400 ) includes sending the first pressure difference (ΔP1) and the second pressure difference (ΔP2) to a data selector device that uses a logic circuit to generate a single pressure signal. Next, at ( 408 ), the method ( 400 ) includes receiving, by one or more computing devices, the single pressure signal indicating a pressure differential of the component. 
       FIG. 14  provides an example computing system  500  according to example embodiments of the present disclosure. The computing systems (e.g., the controller  118 ) described herein may include various components and perform various functions of the computing system  500  described below, for example. 
     As shown in  FIG. 14 , the computing system  500  can include one or more computing device(s)  510 . The computing device(s)  510  can include one or more processor(s)  510 A and one or more memory device(s)  510 B. The one or more processor(s)  510 A can include any suitable processing device, such as a microprocessor, microcontroller, integrated circuit, logic device, and/or other suitable processing device. The one or more memory device(s)  510 B can include one or more computer-readable media, including, but not limited to, non-transitory computer-readable media, RAM, ROM, hard drives, flash drives, and/or other memory devices. 
     The one or more memory device(s)  510 B can store information accessible by the one or more processor(s)  510 A, including computer-readable instructions  510 C that can be executed by the one or more processor(s)  510 A. The instructions  510 C can be any set of instructions that when executed by the one or more processor(s)  510 A, cause the one or more processor(s)  510 A to perform operations. In some embodiments, the instructions  510 C can be executed by the one or more processor(s)  510 A to cause the one or more processor(s)  510 A to perform operations, such as any of the operations and functions for which the computing system  500  and/or the computing device(s)  510  are configured, operations for electrically assisting a turbomachine during transient operation (e.g., method ( 400 )), and/or any other operations or functions of the one or more computing device(s)  510 . Accordingly, the method ( 400 ) may be a computer-implemented method, such that each of the steps of the exemplary method ( 400 ) are performed by one or more computing devices, such as the exemplary computing device  510  of the computing system  500 . The instructions  510 C can be software written in any suitable programming language or can be implemented in hardware. Additionally, and/or alternatively, the instructions  510 C can be executed in logically and/or virtually separate threads on processor(s)  510 A. The memory device(s)  510 B can further store data  510 D that can be accessed by the processor(s)  510 A. For example, the data  510 D can include models, databases, etc. 
     The computing device(s)  510  can also include a network interface  510 E used to communicate, for example, with the other components of system  500  (e.g., via a network). The network interface  510 E can include any suitable components for interfacing with one or more network(s), including for example, transmitters, receivers, ports, controllers, antennas, and/or other suitable components. One or more external devices, such as fuel control device(s)  150  and electrical control device(s)  120 , can be configured to receive one or more commands from the computing device(s)  510  or provide one or more commands to the computing device(s)  510 . 
     It is contemplated that the turbomachines and methods of the present disclosure may be implemented on an aircraft, helicopter, automobile, boat, submarine, train, unmanned aerial vehicle or drone and/or on any other suitable vehicle. While the present disclosure is described herein with reference to an aircraft implementation, this is intended only to serve as an example and not to be limiting. One of ordinary skill in the art would understand that the turbomachines and methods of the present disclosure may be implemented on other vehicles without deviating from the scope of the present disclosure. 
     The technology discussed herein makes reference to computer-based systems and actions taken by and information sent to and from computer-based systems. One of ordinary skill in the art will recognize that the inherent flexibility of computer-based systems allows for a great variety of possible configurations, combinations, and divisions of tasks and functionality between and among components. For instance, 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. 
     Although specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the present disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing. 
     Further aspects of the invention are provided by the subject matter of the following clauses: 
     1. A turbomachine for a vehicle, comprising: a manifold configured to channel a flow of fluid therethrough; a first pressure measurement device in communication with the manifold and configured to determine a first pressure difference (ΔP1); a second pressure measurement device in communication with the manifold and configured to determine a second pressure difference (ΔP2); a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal; and an engine controller operably coupled to the data selector device such that the engine controller receives the single pressure signal indicating a pressure differential of the manifold. 
     2. The turbomachine of any preceding clause, wherein the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     3. The turbomachine of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     4. The turbomachine of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     5. The turbomachine of any preceding clause, wherein when the logic circuit determines that only one of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference and the second pressure difference that is within the predetermined pressure range. 
     6. The turbomachine of any preceding clause, wherein the engine controller, in response to receiving the single pressure signal, compares the single pressure signal to a predetermined range. 
     7. The turbomachine of any preceding clause, wherein when the engine controller determines the single pressure signal is within the predetermined range, the engine controller detects a positive condition of the manifold, and wherein when the engine controller determines the single pressure signal is outside of the predetermined range, the engine controller detects a fail condition of the manifold. 
     8. The turbomachine of any preceding clause, wherein the engine controller includes a monitoring system that indicates the positive condition or the fail condition of the manifold. 
     9. The turbomachine of any preceding clause, wherein the first pressure measurement device includes a first pressure sensor at a first upstream location and a second pressure sensor at a first downstream location, and wherein the second pressure measurement device includes a third pressure sensor at a second upstream location and a fourth pressure sensor at a second downstream location. 
     10. The turbomachine of any preceding clause, further comprising a valve disposed in a portion of the manifold, wherein the valve is transitionable between an open position and a closed position. 
     11. A computing system for a component of a vehicle, comprising: a first pressure measurement device in communication with the component and configured to determine a first pressure difference (ΔP1); a second pressure measurement device in communication with the component and configured to determine a second pressure difference (ΔP2); a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first pressure difference (ΔP1) and the second pressure difference (ΔP2) and uses a logic circuit to generate a single pressure signal; and a controller having one or more processors and one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, in performing the operations, the one or more processors are configured to receive the single pressure signal indicating a pressure differential of the component. 
     12. The computing system of any preceding clause, wherein the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     13. The computing system of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     14. The computing system of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     15. The computing system of any preceding clause, wherein when the logic circuit determines that only one of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to only use the one of the first pressure difference and the second pressure difference that is within the predetermined pressure range. 
     16. The computing system of any preceding clause, wherein the one or more processors are further configured to, in response to receiving the single pressure signal, compare the single pressure signal to a predetermined range. 
     17. A method of measuring pressure at a component of a vehicle, the method comprising: receiving, at a data selector device, two or more signals indicating a first and second pressure difference for the component; generating a single pressure signal from the first and second pressure difference; and receiving, by one or more computing devices, the single pressure signal indicating a pressure differential of the component. 
     18. The method of any preceding clause, wherein the generating the single pressure signal from the first and second pressure difference comprises the data selector device using a logic circuit to generate the single pressure signal, wherein the logic circuit is configured to determine if the first pressure difference and the second pressure difference are within a predetermined pressure range. 
     19. The method of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are within the predetermined pressure range, the logic circuit is configured to determine an average of the first pressure difference and the second pressure difference. 
     20. The method of any preceding clause, wherein when the logic circuit determines that both of the first pressure difference and the second pressure difference are outside of the predetermined pressure range, the logic circuit is configured to generate an error message. 
     This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims. 
     While this disclosure has been described as having exemplary designs, the present disclosure can be further modified within the scope of this disclosure. This application is therefore intended to cover any variations, uses, or adaptations of the disclosure using its general principles. Further, this application is intended to cover such departures from the present disclosure as come within known or customary practice in the art to which this disclosure pertains and which fall within the limits of the appended claims.