Patent Publication Number: US-11661859-B2

Title: Method for operating a turbo machine

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     The present application claims the benefit of the earliest available effective filing date of U.S. patent application Ser. No. 16/001,369, having a filing date of Jun. 6, 2018 and issued as U.S. Pat. No. 10,822,993, of which is incorporated herein by reference in its entirety. 
     FIELD 
     The present subject matter relates generally to methods for operating a turbo machine based on diagnosing, maintaining, or improving turbo machine engine health, operability, or performance. 
     BACKGROUND 
     Turbo machines, such as gas or steam turbine engines, use information from a specific operating condition to determine engine health, operability, or performance of the turbo machine. However, known methods and systems for determining engine health, operability, or performance are limited such as to provide similar information across multiple engine conditions. Determining engine health, operability, or performance may exclude information that may indicate health, operability, or performance across multiple locations of the engine. As such, there is a need for improved methods and systems for determining engine health, operability, or performance. 
     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. 
     An aspect of the present disclosure is directed to a system for determining performance of a turbine engine. The system includes a plurality of sensors and one or more computing devices executing operations including acquiring, via the plurality of sensors, a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing, via the computing device, the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating, via the computing device, a health condition prediction at the engine based on the compared parameters. 
     In various embodiments, the operations further include acquiring, via a first sensor, a first parameter set based on a first engine operating condition indicating a health condition at a first location of the engine; and acquiring, via the first sensor, a second parameter set based on a second engine operating condition indicating a health condition at a second location different from the first location. 
     In one embodiment, the operations further include acquiring, via a second sensor, a third parameter set based on the first engine operating condition indicating a health condition at the second location; and acquiring, via the second sensor, a fourth parameter set based on the second engine operating condition indicating a health condition at the first location. 
     In another embodiment, the operations further include comparing, via the computing device, the first parameter set, the second parameter set, the third parameter set, and the fourth parameter set to determine a health condition corresponding to a location at the engine. 
     In still another embodiment, the operations further include comparing the parameter sets to determine the health condition at the first location; and comparing the parameter sets to determine the health condition at the second location. 
     In yet another embodiment, the operations further include comparing the first parameter set and the fourth parameter set to determine the health condition at the first location. 
     In still yet another embodiment, the operations further include comparing the second parameter set and the third parameter set to determine the health condition at the second location. 
     In one embodiment, the operations further include determining, via the computing device, one or more locations of a health deterioration contributor via the compared parameter sets. 
     In various embodiments, the operations further include generating, via the computing device, a signal to an operator of the engine indicating an action item for the user/operator to perform. In one embodiment, the operations further include transmitting, via the computing device, the signal indicating an engine manoeuver. In another embodiment, the operations further include transmitting, via the computing device, the signal indicating a maintenance action. In still another embodiment, the operations further include transmitting, via the computing device, the signal indicating an operating limit. 
     In one embodiment, the operations further include operating the engine at a plurality of engine operating condition to generate a quantity of engine operating conditions at a plurality of different operating conditions. 
     Another aspect of the present disclosure is directed to a method for operating an engine based on a health deterioration condition. The method includes acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions, in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters. 
     In one embodiment, the method further includes determining one or more locations of a health deterioration contributor via the compared parameter sets. 
     In various embodiments, the method further includes generating a signal to an operator of the engine indicating an action item for the user/operator to perform. In one embodiment, the method further includes transmitting the signal indicating an engine manoeuver. In another embodiment, the method further includes transmitting the signal indicating a maintenance action. In yet another embodiment, the method further includes transmitting the signal indicating an operating limit. In still another embodiment, the method further includes operating the engine at a plurality of engine operating condition to generate a quantity of engine operating conditions at a plurality of different operating conditions. 
     These and other features, aspects and advantages of the present invention 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 invention and, together with the description, serve to explain the principles of the invention. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A full and enabling disclosure of the present invention, 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 an exemplary schematic cross sectional view of an embodiment of a turbo machine according to an aspect of the present disclosure; 
         FIG.  2    is a flowchart outlining exemplary steps of a method for operating a turbo machine according to an aspect of the present disclosure; 
         FIGS.  3 A- 3 B  are exemplary cross sectional views of a flowpath of the turbo machine according to  FIG.  1    depicting a plurality of engine operating conditions; and 
         FIG.  4    is an exemplary cross sectional view of the flowpath of the turbo machine upstream of the cross sectional views depicted in regard to  FIGS.  3 A- 3 B . 
     
    
    
     Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present invention. 
     DETAILED DESCRIPTION 
     Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents. 
     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 “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. In regard to the figures, such as depicted in regard to  FIG.  1   , “upstream end  99 ” depicts a reference from which fluid flows into an engine  10  and “downstream end  98 ” depicts a reference to which the fluid flows from the upstream end  99 . 
     Generally provided are methods (e.g., method  1000  further described below) and systems (e.g., system  100  further described below) for determining a health condition of a turbo machine (hereinafter, “engine”) at one or more locations at the engine, and operation based on the determined health condition. The system  100  includes a plurality of sensors acquiring data or parameter sets at each engine operating condition. Each acquired parameter set corresponds to or reflects an upstream health condition of the system. The system  100  and method  1000  compares each acquired parameter set from each sensor at two or more engine operating conditions and then combines the parameter sets to determine a location at the engine at which a health deterioration contributor is located. 
     In one embodiment, the sensors may define temperature probes (e.g., exhaust gas temperature or EGT probes) measuring a circumferential temperature profile or pattern factor around a flowpath of the engine. Each engine operating condition defines one or more of a different fluid (e.g., air, fuel, fuel-air mixture, or combustion gas) flow rate, pressure, temperature, vorticity, circumferential swirl, boundary condition, or another physical or chemical property of the fluid, or combinations thereof. Each change in engine operating condition may be based on one or more of a flight condition such as start, idle, takeoff, climb, cruise, or descent (or equivalent operating condition in other turbo machine configurations), a change in vane schedule (e.g., vane angle), bleed schedule (e.g., amount open or close of a bleed valve), rotor speed, ambient air condition (e.g., temperature, pressure, density, etc., of air entering the engine), fuel-air ratio, or health deterioration contributor (e.g., degradation, wear, or damage, rotor to shroud clearances, malfunctions, etc.), or combinations thereof. Still further, in one example, the health condition defining a fault location may reflect wear, damage, or degradation at a location in the engine (e.g., the location being one or more fuel nozzles upstream of the sensor defining the EGT probe). As such, each change in engine operating condition results in the sensor acquiring a parameter set (e.g., temperature profile at the flowpath) reflecting a different location (e.g., fuel nozzle) with each change in engine operating condition. More specifically, higher power engine operating conditions may result in a different circumferential swirl of fluid in contrast to lower power engine operating conditions such that the sensor acquires the parameter set reflecting a different fuel nozzle or plurality of fuel nozzles based on each change in engine operating condition. 
     As each parameter set from the sensor reflects a different fuel nozzle(s) at each engine operating condition, the system and method compares and combines the parameter sets from each of the engine operating conditions to determine the location of the health deterioration contributor (e.g., damaged, deteriorated, or otherwise malfunctioning fuel nozzle). 
     For example, a plurality of sensors S acquires a plurality of parameter sets P based on each engine operating condition E in which each sensor determines a health condition at location L upstream of the sensors S. More specifically, in one embodiment, a first sensor S 1  acquiring a first parameter set P 1 E 1 S 1  based on a first engine operating condition E 1  may indicate a health condition of a first fuel nozzle at location L 1 . However, the first sensor S 1  acquiring a second parameter set P 1 ′E 2 S 1  based on a second engine operating condition E 2  (i.e., different from the first engine operating condition E 1 ) may indicate a health condition of a second fuel nozzle at location L 1 ′ (i.e., more generally, not the first fuel nozzle at location L 1 ). Still further, the second parameter set P 1 ′E 2 S 1  may further indicate the health condition of the second fuel nozzle at location L 1 ′ relative to the second engine operating condition E 2  but not relative to the first engine operating condition E 1 . As such, a user or operator of the engine is aware of the health condition at L 1  relative to E 1  and the health condition at L 1 ′ relative to E 2 . However, the user is not aware of the health condition at L 1  relative to E 2  and the health condition at L 1 ′ relative to E 1 . 
     As such, the system  100  and method  1000  further acquires, via a second sensor S 2 , a third parameter set P 1 ′E 1 S 2  based on the first engine operating condition E 1  indicating a health condition of the second fuel nozzle at location L 1 ′. Still further, the second sensor S 2  acquires a fourth parameter set P 1 E 2 S 2  based on the second engine operating condition E 2  indicating a health condition of the first fuel nozzle at location L 1 . 
     The method  1000  and system  100  compares the parameter sets and determines the health condition at L 1  based on P 1 E 1 S 1  and P 1 E 2 S 2 . The method and system further compares the parameter sets and determines the health condition at the fuel nozzle at location L 1 ′ based on P 1 ′E 2 S 1  and P 1 ′E 1 S 2 . As such, the method and system determines the health condition of the engine at the fuel nozzle at location L 1  relative to engine operating conditions E 1  and E 2 , and further the health condition at location L 1 ′ relative to engine operating conditions E 1  and E 2 . 
     As such, the method  1000  and system  100  generally described herein enables more precise determination of the health condition within the engine. For example, the method and system described herein may determine, via the plurality of sensors defining EGT probes, a faulty fuel nozzle upstream of the sensors at one or more engine operating conditions. For example, the fuel nozzle may define faulty operation at a low power condition (e.g., startup, ground idle, etc.) but not at a higher power condition (e.g., cruise, climb, takeoff, etc.). The method and system described herein may determine specifically the location of the faulty fuel nozzle and/or which engine operating conditions at which the fuel nozzle defines faulty behavior. 
     Although described in regard to fuel nozzles, it should be appreciated that the method  1000  and system  100  described herein may be utilized to determine a location(s) at the engine at which a health deterioration contributor is present. For example, such as previously described, the methods and systems described herein may determine which one or more of a plurality of fuel nozzles defines a faulty condition (e.g., damage, wear, deterioration, blockage, etc.), and/or at which engine operating conditions the fault in present (e.g., start, ground idle, flight idle, cruise, approach, climb, takeoff, etc., or corresponding conditions in other turbo machine configurations). As another example, the method and system may define which one or more of a fixed or variable vane is faulty (e.g., mis-positioned, damaged, worn, etc.), or a bleed valve faulty operation. As yet another example, the method and system may define generally a circumferential, radial, and/or axial location within the engine at which a fault in the flowpath is present (e.g., blockage, foreign or domestic object damage, coating or material loss, etc.). 
     Furthermore, it should be appreciated that the method  1000  and system  100  described herein may be utilized to compare and combine a plurality of parameter sets acquired via a plurality of sensors over a plurality of engine operating conditions to determine a health condition at a plurality of locations at the engine. As such, system may generally include a quantity N of sensors S in which N&gt;1. The system and method may further include operating the engine at a quantity X of engine operating conditions in which X&gt;1. The system and method further determines the health condition at each of a quantity of locations less than or equal to N. 
     Additionally, or alternatively, the system  100  and method  1000  described herein may include determining the location L of the health condition over a circumferential, radial, and/or axial range at the engine. As such, in one embodiment locations L and L′ may partially overlap. In another embodiment, locations L and L′ are non-overlapping. 
     Although generally described herein as methods  1000  and systems  100  for determining a health condition of the engine, it should be appreciated that “health condition”, “health condition prediction”, “health deterioration contributor”, etc. may further refer to performance and/or operability conditions, predictions, or deterioration contributors. For example, the health condition may further indicate one or more locations at the engine affecting engine operability or performance, including, but not limited to, rotating stall or surge, deteriorated emissions performance (e.g., increased unburned hydrocarbons, smoke, carbon monoxide, carbon dioxide, oxides of nitrogen, etc.), decreased lean or rich blowout stability, increased engine or combustion dynamics, etc. 
     Each sensor S of the plurality of the sensors is perceptible over a measurement range R within the engine, such as to measure the parameter set P. The measurement range R is a function of at least a predetermined distance U and a coefficient C based on an engine operating condition E. The predetermined distance U may generally define a circumferential, radial, or axial distance, or combinations thereof (e.g., three-dimensions) within the flowpath through which the fluid flows and at which the sensor S may perceive, detect, or otherwise measure the parameter set P at a baseline or nominal condition. For example, the predetermined distance U may generally define a maximum distance or range along the circumferential, radial, or axial distance, or combinations thereof, within the flowpath at which parameter set P may be measured given an ideal condition. In one example, such an ideal condition may generally define an ambient condition. In another example, the ideal condition may generally define a baseline steady state condition of the engine during operation. Such a baseline steady state condition may include a minimum or a maximum steady state operating condition of the engine. 
     Changes in engine operating condition E, such as particularly changes in flow condition, alter or otherwise change the measurement range R of the plurality of sensors S based on changes in engine operating condition E. In various embodiments, changes in engine operating condition E define the coefficient C based on each engine operating condition E multiplied to the predetermined distance U such as to alter the measurement range R based on engine operating condition E. For example, in one embodiment, the coefficient C is greater than zero and less than or equal to 1.0. Therefore, the measurement range R may alter based on a function of R=F(C X , E X ). 
     Each sensor S defines the measurement range R as a function of at least the engine operating condition E and the predetermined distance U. Each sensor S thereby measures, calculates, or otherwise acquires parameter set P across range R relative to each engine operating condition E. Stated alternatively, each parameter set P reflects a different range R relative to each engine operating condition E. As such, the system and method described herein enables combining the plurality of parameter sets P corresponding to different engine operating conditions E to determine the health condition at each location L at the engine. 
     For example, referring to  FIGS.  3 A- 3 B , exemplary cross sectional views of an exemplary turbo machine (hereinafter, “engine  10 ”) are generally provided. In regard to  FIG.  3 A , the sensor S 1  defines a measurement range RE 1 S 1  based on a first engine operating condition E 1 , a predetermined distance U, and a first coefficient C 1  based on the engine operating condition E 1 . In regard to  FIG.  3 B , the sensor S 1  defines a measurement range RE 2 S 1  based on a second engine operating condition E 2 , the predetermined distance U, and a second coefficient C 2  (i.e., different from the first coefficient C 1 ) based on the engine operating condition E 2 . 
     Referring to  FIG.  3 A , each sensor S through N quantity of sensors (e.g., S 1 , S 2 , S 3  . . . , S(N−1), SN) defines the measurement range R based on the first engine operating condition E 1 , the predetermined distance U, and the first coefficient C 1  based on the first operating condition E 1 . For example, sensor S 1  defines measurement range RE 1 S 1 ; sensor S 2  defines measurement range RE 1 S 2  (not shown); up to sensor SN defining measurement range RE 1 SN. 
     Referring to  FIG.  3 B , each sensor S from S 1  through SN defines the measurement range R based on the second engine operating condition E 2 , the predetermined distance U, and the second coefficient C 2  based on the second operating condition E 2 . For example, sensor S 1  defines measurement range RE 2 S 1 ; sensor S 2  defines measurement range RE 2 S 2  (not shown); up to sensor SN defining measurement range RE 2 SN. 
     It should be appreciated that each sensor S defines the measurement range R at each engine operating condition E such that the measurement range R at X quantity of engine operating conditions at sensor S 1  is REXS 1 ; at sensor S 2  the measurement range REXS 2 ; up to sensor SN defining measurement range REXSN. 
     Referring now to the drawings,  FIG.  1    is a schematic partially cross-sectioned side view of the engine  10  as may incorporate various embodiments of the present invention. The engine  10 , or portions thereof, may be included in the system  100  for determining health deterioration at the turbo machine, and a location of the health deterioration. Although generally depicted herein as a turbofan configuration, the engine  10  shown and described herein may further define a steam turbine engine or gas turbine engine generally, including, but not limited to, turboprop, turboshaft, or turbojet configurations, or in other embodiments, a duct burner, ramjet, scramjet, etc. configuration of Brayton cycle machine. As shown in  FIG.  1   , the engine  10  has a longitudinal or axial centerline axis  12  that extends there through for reference purposes. In general, the engine  10  may include a fan assembly  14  and a core engine  16  disposed downstream of the fan assembly  14 . 
     The core engine  16  may generally include a substantially tubular outer casing  18  that defines an annular inlet  20 . The core engine  16  further defines one or more flowpaths  70  therethrough. For example, the annular inlet  20  generally defines an opening to the flowpath  70  through which a flow of air  80  is directed to the compressor section  21 , the combustion section  26 , and the turbine section  31 . However, it should be appreciated that engine  10  may further define one or more flowpaths for cooling or other fluid transfer or routing. The outer casing  18  encases or at least partially forms, in serial flow relationship, the compressor section  21  having a booster or low pressure (LP) compressor  22 , a high pressure (HP) compressor  24 , or one or more intermediate pressure (IP) compressors (not shown) disposed aerodynamically between the LP compressor  22  and the HP compressor  24 ; the combustion section  26 ; the turbine section  31  including a high pressure (HP) turbine  28 , a low pressure (LP) turbine  30 , and/or one or more intermediate pressure (IP) turbines (not shown) disposed aerodynamically between the HP turbine  28  and the LP turbine  30 ; and a jet exhaust nozzle section  32 . A high pressure (HP) rotor shaft  34  drivingly connects the HP turbine  28  to the HP compressor  24 . A low pressure (LP) rotor shaft  36  drivingly connects the LP turbine  30  to the LP compressor  22 . In other embodiments, an IP rotor shaft drivingly connects the IP turbine to the IP compressor (not shown). The LP rotor shaft  36  may also, or alternatively, be connected to a fan shaft  38  of the fan assembly  14 . In particular embodiments, such as shown in  FIG.  1   , the LP shaft  36  may be connected to the fan shaft  38  via a power or reduction gear assembly  40  such as in an indirect-drive or geared-drive configuration. However, it should be appreciated that in other embodiments, the engine  10  may define a direct drive configuration without a reduction gear assembly. 
     Combinations of the compressors  22 ,  24 , the turbines  28 ,  30 , and the shafts  34 ,  36 ,  38  each define a rotor assembly  90  of the engine  10 . For example, in various embodiments, the LP turbine  30 , the LP shaft  36 , the fan assembly  14  and/or the LP compressor  22  together define the rotor assembly  90  as a low pressure (LP) rotor assembly. The rotor assembly  90  may further include the fan rotor  38  coupled to the fan assembly  14  and the LP shaft  36  via the gear assembly  40 . As another example, the HP turbine  28 , the HP shaft  34 , and the HP compressor  24  may together define the rotor assembly  90  as a high pressure (HP) rotor assembly. It should further be appreciated that the rotor assembly  90  may be defined via a combination of an IP compressor, an IP turbine, and an IP shaft disposed aerodynamically between the LP rotor assembly and the HP rotor assembly. 
     In still various embodiments, the rotor assembly  90  further includes a bearing assembly  160  enabling rotation of the shaft (e.g., shaft  34 ,  36 ,  38 ) relative to a surrounding grounding or static structure (e.g., outer casing  18 ), such as further shown and described in regard to  FIG.  2   . 
     As shown in  FIG.  1   , the fan assembly  14  includes a plurality of fan blades  42  that are coupled to and that extend radially outwardly from the fan shaft  38 . An annular fan casing or nacelle  44  circumferentially surrounds the fan assembly  14  and/or at least a portion of the core engine  16 . It should be appreciated by those of ordinary skill in the art that the nacelle  44  may be configured to be supported relative to the core engine  16  by a plurality of circumferentially-spaced outlet guide vanes or struts  46 . Moreover, at least a portion of the nacelle  44  may extend over an outer portion of the core engine  16  so as to define a bypass airflow passage  48  therebetween. 
     The engine  10  further includes a plurality of sensors  240  (further referred to as sensors S herein) disposed throughout the engine  10 . The sensors  240  may be mounted onto one or more surfaces at the engine  10 , such as, but not limited to, the nacelle  44  or the outer casing  18 , or generally at the fan section  14 , the compressor section  21 , the combustion section  26 , the turbine section  31 , or the exhaust section  32 . As described in regard to sensors S, the sensors  240  may be configured to acquire parameter sets P such as described in regard to the method  1000  and  FIGS.  2 - 4   . In various embodiments, the sensors  240  may be configured to acquire or calculate vibrations measurement, stress or strain, thrust output, or applied load, pressure, temperature, or rotational speed. Although some exemplary locations are depicted in regard to  FIG.  1   , it should be appreciated that the sensors  240  may be disposed throughout the engine  10  such as generally outlined herein. 
     During operation of the engine  10 , as shown in  FIG.  1   , a volume of air as indicated schematically by arrows  74  enters the engine  10  through an associated inlet  76  of the nacelle  44  and/or fan assembly  14 . As the air  74  passes across the fan blades  42  a portion of the air as indicated schematically by arrows  78  is directed or routed into the bypass airflow passage  48  while another portion of the air as indicated schematically by arrow  80  is directed or routed into the LP compressor  22 . Air  80  is progressively compressed as it flows through the LP and HP compressors  22 ,  24  towards the combustion section  26 , such as indicated schematically by arrows  82 . 
     Referring still to  FIG.  1   , the combustion gases  86  generated in the combustion section  26  flows to the HP turbine  28  of the turbine section  31 , thus causing the HP shaft  34  to rotate, thereby supporting operation of the HP compressor  24 . As shown in  FIG.  1   , the combustion gases  86  are then routed to the LP turbine  30 , thus causing the LP shaft  36  to rotate, thereby supporting operation of the LP compressor  22  and rotation of the fan shaft  38 . The combustion gases  86  are then exhausted through the jet exhaust nozzle section  32  of the core engine  16  to provide propulsive thrust. 
     As operation of the engine  10  continues over a quantity of cycles, deterioration of various components generally results through normal wear, or foreign or domestic object debris and damage, or malfunction of the engine  10 . Such deterioration or generally adverse operation of the engine  10  may induce rotating stall, surge, undesired combustion dynamics, undesired pattern factor or hot spots (e.g., temperature peaks across a circumferential and/or axial thermal gradient from the combustion chamber), lean blow out, rich blow out, deteriorating emissions performance (e.g., increased unburned hydrocarbons, carbon monoxide, carbon dioxide, oxides of nitrogen, particulates, etc.), coating or material loss, loss of thrust, loss of operability (e.g., an ability to operate over an intended operational envelope), or loss of performance, etc., or combinations thereof. 
     The engine  10  is configured to operate over a plurality of engine operating conditions, in which each engine operating condition corresponds to an operating mode of the engine. In various embodiments, the engine operating conditions correspond to a startup condition, a light-off condition, a minimum steady state operating condition, a maximum steady state operating condition, one or more intermediate steady state operating conditions between the minimum and maximum steady state operating conditions, or transient conditions between the minimum, maximum, and intermediate steady state operating conditions. Each engine operating condition defines a flow rate, pressure, and/or temperature of fluid within the engine  10  (e.g., engine inlet air  74 , fan bypass air  78 , core inlet air  80 , compressed air  82 , or combustion gases  86  through the flowpath  70 , liquid or gaseous fuel, lubricant, hydraulic fluid, or other flow passages within the engine for heat exchange, pressurization, damping, etc.). Each engine operating condition may further define a circumferential, radial, and/or axial velocity, thermal, or pressure profile or gradient, swirl, turbulent or laminar flow profile of the fluid at the engine  10 . The engine operating condition may generally correspond to the operating condition of the engine  10 . The engine operating condition may further correspond to vane schedules (e.g., variable vane angles), bleed or bypass flow schedules (e.g., amount by which a valve is open or closed to divert a fluid), or deterioration at the engine. 
     As another example, the engine operating condition defines an actual engine operating condition, such as a minimum steady state operating condition (i.e., a minimum flow rate of fuel and/or oxidizer to sustain rotation of the rotor assembly  90  at approximately zero acceleration), a maximum steady state operating condition (i.e., a maximum flow rate of fuel and/or oxidizer to sustain rotation of the rotor assembly  90  at approximately zero acceleration), a transient condition between startup (i.e., acceleration from zero RPM) and the maximum steady state operating condition, or one or more intermediate steady state operating conditions. In various embodiments, such as in relation to aviation gas turbine engines, the engine operating condition may include one or more of a start condition, idle, takeoff, climb, cruise, and descent conditions, or transient conditions therebetween. 
     The engine operating condition may further correlate to a flow condition of the fluid within the flowpath of the engine. The flow condition generally alters, changes, or modulates based on or due to each operating condition of the engine. For example, an axial, radial, or circumferential flow condition of the fluid within the flowpath generally alters relative to each operating condition of the engine. As another example, a thermal gradient, a pressure gradient, or a velocity profile of the fluid within the flowpath alters relative to each operating condition of the engine. As still another example, the velocity profile may alter such as to increase or decrease an axial, radial, and/or circumferential flow rate of the fluid along the flowpath. Stated alternatively, the velocity profile may increase or decrease a magnitude of swirl of the fluid along the axial, radial, and/or circumferential directions within the flowpath. 
     Referring now to  FIG.  2   , embodiments of a method for generating a health condition prediction at a turbo machine engine are generally provided (hereinafter, “method  1000 ”). The embodiments of the method  1000  and a system for utilizing and executing the method (e.g., system  100  in  FIG.  1   ) generally shown and described herein generate a health condition prediction at the engine based at least on comparing acquired parameter sets across a plurality of engine operating conditions from a plurality of sensors (e.g., sensors S in  FIG.  1   ). Embodiments of the method  1000  generally provided herein may be utilized or executed in regard to the system  100  such as shown and described in regard to  FIG.  1   . However, it should be appreciated that the methods and systems shown and described herein may be utilized and executed in regard to turbine engines generally, including, but not limited to, gas turbine engines or steam turbine engines, including turboprop, turboshaft, turbofan, or turbojet configurations, including configurations for land-based or vehicle-based power generation, or land, sea, or aerial vehicles. 
     Embodiments of the methods and systems generally shown and described herein generate a health condition prediction providing an estimation of circumferential, radial, and/or axial location at the engine upstream of the sensors at which a health deterioration contributor or fault may be located. The health deterioration contributor generally includes a circumferential, radial, and/or axial location of damage at the engine, the location of malfunctioning components (e.g., flowpath leakage, flowpath damage such as to result in undesired flow conditions, fuel nozzle malfunction, stator or variable vane malfunction, seal or shroud damage or malfunction, or valve malfunction, leakage, or damage, or combinations thereof). 
     The method  1000  includes at  1005  acquiring, via a plurality of sensors S, a plurality of parameter sets P each corresponding to a plurality of engine conditions E, in which each parameter set P corresponding to each engine condition E indicates a health condition at a plurality of locations at the engine. 
     In various embodiments, the method  1000  further includes at  1010  acquiring, via a first sensor S 1 , a first parameter set P 1 E 1 S 1  based on a first engine operating condition E 1 , in which the first parameter set P 1 E 1 S 1  indicates a health condition of at a first location L 1  of the engine, such as described above herein. 
     The method  1000  includes at  1020  acquiring, via the first sensor S 1 , a second parameter set P 1 ′E 2 S 1  based on a second engine operating condition E 2 , in which the second parameter set P 1 ′E 2 S 1  indicates a health condition at a second location L 1 ′ (i.e., different from the first location L 1 ) at the second engine operating condition. 
     The method  1000  further includes at  1030  acquiring, via a second sensor S 2 , a third parameter set P 1 ′E 1 S 2  based on the first engine operating condition E 1 , in which the third parameter set P 1 ′E 1 S 2  indicates a health condition at the second location L 1 ′ at the first engine operating condition E 1 . 
     The method  1000  further includes at  1040  acquiring, via the second sensor S 2 , a fourth parameter set P 1 E 2 S 2  based on the second engine operating condition E 2 , in which the fourth parameter set P 1 E 2 S 2  indicates a health condition at the first location L 1  at the second engine operating condition E 2 . 
     The method  1000  further includes at  1050  comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine. In various embodiments, the method  1000  at  1050  further includes at  1051  comparing or combining the first parameter set P 1 E 1 S 1 , the second parameter set P 1 ′E 2 S 1 , the third parameter set P 1 ′E 1 S 2 , and the fourth parameter set P 1 E 2 S 2  to determine a health condition corresponding to a location at the engine. More specifically, the method  1000  may include at  1052  comparing or combining the parameter sets to determine the health condition at the first location L 1 . As such, the step  1052  may include comparing the first parameter set P 1 E 1 S 1  and the fourth parameter set P 1 E 2 S 2 . Still further, the method  1000  may include at  1053  comparing or combining the parameter sets to determine the health condition at the second location L 1 ′. As such, the step  1053  may include comparing or combining the second parameter set P 1 ′E 2 S 1  and the third parameter set P 1 ′E 1 S 2 . 
     Still further, the method  1000  may further include at  1055  determining one or more locations of a health deterioration contributor via the compared parameter sets. For example, the method  1000  at  1055  may generally include comparing the parameter sets (e.g., at steps  1050 ,  1051 ,  1052 ,  1053 ) to determine the location of a fault at the engine, such as further described above and herein. The step at  1055  may include one or more operations or functions combining the parameter sets based on the plurality of engine operating conditions. 
     Additionally, it should be appreciated that the method  1000  at  1005 , or more specifically at  1010 ,  1020 ,  1030 , and  1040 , may include acquiring from each available or operable sensor S (e.g., S 1 , S 2 , S 3  . . . , S(N−1), SN) parameter sets P corresponding to each sensor S at each of the quantity X of engine operation condition E. For example, referring to  FIGS.  3 A- 3 B , at engine operating condition E 1 , sensor S 1  may acquire parameter set P 1 E 1 S 1  indicating a health condition corresponding to a first location L 1 ; sensor S 2  may acquire P 1 ′E 1 S 2  indicating a health condition corresponding to another location L 1 ′; sensor S 3  may acquire P 1 ′E 1 S 3  indicating a health condition corresponding to yet another location L″; through sensor SN acquiring P 1   Y E 1 SN indicating a health condition corresponding to still another location L Y , in which Y is less than or equal to the quantity N of sensors S. Stated alternatively, quantity Y corresponds to the quantity of locations L at the engine at which the health condition acquired by parameter set P is indicative. 
     As still another example, at engine operating condition E 2 , sensor S 1  may acquire parameter set P 1 ′E 2 S 1  indicating a health condition corresponding to a location different from the first location L 1  (e.g., L 1 ′, or not L 1 ); sensor S 2  may acquire P 1 E 2 S 2  indicating a health condition corresponding, at least in part, to the first location L 1 ; sensor S 3  may acquire another parameter set indicating a health condition corresponding to yet another location different from L 1  and L 1 ′; through sensor SN acquiring P 1   Y ′E 2 SN indicating a health condition corresponding to still another location L Y ′ different, at least in part, from L Y . 
     As such, the plurality of sensors S each acquire at each engine operating condition E through quantity X a plurality of parameter sets P each corresponding to different combinations of locations at the engine such as due to changes in measurement range R with each engine operating condition E. Furthermore, the method  1000  at  1050 , or more specifically at  1051 ,  1052 , and  1053 , may include comparing and combining the plurality of parameter sets each indicating different combinations of locations to determine a health condition at the plurality of locations at the engine. The method  1000  at  1055  may further determine the health condition at the engine based on the plurality of parameter sets each indicating different combinations of locations. 
     In various embodiments, the method  1000  further includes at  1060  generating and providing a signal to a user or operator of the engine indicating an action item for the user/operator. For example, the action item may include an engine manoeuver, a maintenance action, or an operating limit. 
     The signal generated at  1060  indicating the engine manoeuver may further include at  1061  transmitting the signal indicating to change the engine operating condition. For example, changing the engine operating condition may include changing acceleration or rotational speed of the engine, changing pressure, temperature, and/or flow rate of fluid within the engine, or changing thrust output. For example, the engine manoeuver may include adjusting a variable vane angle such as to adjust a pressure and/or flow rate of fluid within the engine; adjusting a fuel flow rate or pressure such as to adjust rotational speed and/or pressure, flow rate and/or temperature of fluid within the engine; or modulating a valve (e.g., bleed or bypass valve) such as to adjust a flow rate and/or pressure of fluid within a flowpath, or combinations thereof. The signal indicating the engine manoeuver, or changes thereof, may enable continued or prolonged operation of the engine while mitigating further deterioration of the engine, or decreasing a rate of deterioration of the engine. 
     The signal generated at  1060  indicating the maintenance action may include at  1062  transmitting the signal indicating a circumferential, radial, and/or axial location at the engine at which the maintenance action should be investigated and/or implemented. For example, the location at the engine may indicate a module or stage at a compressor section or turbine section of the engine at which the health deterioration contributor is located; a location along the flowpath at which the health deterioration contributor is located; or a location of along fixed components at which the health deterioration contributor is located. For example, the signal indicating the maintenance action may indicate the location of a leak or a faulty component (e.g., fuel nozzle, vane, valve, manifold, etc.), at which the user/operator should further investigate the location or repair/replace the component at the indicated location. 
     The signal generated at  1060  indicating the operating limit may include at  1063  transmitting the signal indicating a change in engine operation based on the location of the health deterioration contributor. For example, an indicated location of a fault, damage, or defect may further indicate the user/operator of the engine to continue operation at a reduced thrust output, pressure, flow rate, and/or temperature based on the location of the health deterioration contributor. As such, the user/operator may adjust operation of the engine until the health deterioration contributor is remedied via the maintenance action. 
     In various embodiments, the parameter sets P are one or more of a temperature, a pressure, a flow rate, or other calculated or measured parameter of a fluid at the engine. For example, the fluid may include air or combustion gases within a core flowpath, a bypass flowpath, a heat exchange flowpath, a lubricant flowpath, or another flowpath within the engine. As another example, the fluid may include fuel, lubricant, hydraulic fluid, coolant, or another liquid or gaseous fluid within the engine. 
     In still various embodiments, the plurality of sensors S each defines a discrete sensor location at the engine. For example, the plurality of sensors S defines quantity of sensors S 1  through SN, in which N&gt;1. Each sensor S defines a discrete axial, radial, and/or circumferential location of the engine different from each other sensor of the plurality of sensors S. 
     In one embodiment, the plurality of sensors S may be defined along an axial plane of the engine, such as along axial direction A in regard to the engine  10  depicted in  FIG.  1   . For example, each sensor S is separated circumferentially along the flowpath, such as generally depicted in regard to  FIGS.  3 A- 3 B . The sensors S depicted in regard to  FIGS.  3 A- 3 B  generally acquire parameter sets P indicating a location L 1  and L 1 ′ upstream of the sensors S (e.g., depicted in regard to  FIG.  4   ). In other embodiments (not shown), each sensor S is separated radially along the flowpath, or separated in combination radially and circumferentially along the flowpath. As yet another example, each sensor S is separated axially along the flowpath, or separated in combination radially, circumferentially, and axially along the flowpath. 
     It should be appreciated that the system and method described herein may further include at  1003  operating the engine at a plurality of engine operating conditions E such that the sensors S may acquire the parameter sets P described in regard to step  1005 , or more specifically in regard to steps  1010 ,  1020 ,  1030 ,  1040 . Still further, the method  1000  at  1003  may include operating the engine based at least on the transmitted and generated signal (e.g., step  1060 ,  1061 ,  1062 ,  1063 ). For example, the method  1000  at  1003  may include changing the engine operating condition via changing a rotational speed, air or fuel flow rate, pressure, or temperature, an acceleration/deceleration or other rate of change of fluid flow or rotor speed, or a vane or bleed schedule, or combinations thereof. As another example, the method  1000  at  1003  may include changing the engine operating condition such as to enable performance of the maintenance action, such as, but not limited to, commanded shutdown of the engine, or components thereof. 
     Referring back to  FIG.  1   , the system  100  may further include a computing device  210 . In general, the computing device  210  can correspond to any suitable processor-based device, including one or more computing devices. For instance,  FIG.  1    illustrates one embodiment of suitable components that can be included within the computing device  210 . As shown in  FIG.  1   , the computing device  210  can include a processor  212  and associated memory  214  configured to perform a variety of computer-implemented functions. In various embodiments, the computing device  210  may be configured to operate the engine  10 , such as to control the engine  10  to operate at an engine operating condition defining operating conditions of the engine such as further described herein. In still various embodiments, the computing device  210  may be further configured to execute one or more steps or operations of the method  1000  generally described herein. 
     As used herein, the term “processor” refers not only to integrated circuits referred to in the art as being included in a computer, but also refers to a controller, microcontroller, a microcomputer, a programmable logic controller (PLC), an application specific integrated circuit (ASIC), a Field Programmable Gate Array (FPGA), and other programmable circuits. Additionally, the memory  214  can generally include memory element(s) including, but not limited to, computer readable medium (e.g., random access memory (RAM)), computer readable non-volatile medium (e.g., flash memory), a compact disc-read only memory (CD-ROM), a magneto-optical disk (MOD), a digital versatile disc (DVD) and/or other suitable memory elements or combinations thereof. In various embodiments, the computing device  210  may define one or more of a full authority digital engine controller (FADEC), a propeller control unit (PCU), an engine control unit (ECU), or an electronic engine control (EEC). 
     As shown, the computing device  210  may include control logic  216  stored in memory  214 . The control logic  216  may include instructions that when executed by the one or more processors  212  cause the one or more processors  212  to perform operations such as described in regard to method  1000 . 
     Additionally, as shown in  FIG.  1   , the computing device  210  may also include a communications interface module  230 . In various embodiments, the communications interface module  230  can include associated electronic circuitry that is used to send and receive data. As such, the communications interface module  230  of the computing device  210  can be used to receive data from the engine  10  (e.g., at one or more of the rotor assembly  90 , the gear assembly  40 , flowpaths at the core engine  16  and/or fan bypass airflow passage  48 , the bearing  160 , or sensor  240  proximate or attached thereto) providing parameter set P, such as, but not limited to, a vibrations measurement (e.g., an accelerometer, a proximity probe, a displacement probe, etc.), stress or strain (e.g., a strain gage), thrust output (e.g., calculated via engine pressure ratio), or applied load (e.g., a load cell), pressure (e.g., a pressure transducer or pressure probe), temperature (e.g., thermocouple), or rotational speed (e.g., a 1/rev signal, a tachometer, or other speed detection device proximate to the rotor assembly  90 ). In addition, the communications interface module  230  can also be used to communicate with any other suitable components of the engine  10 , including any number of sensors S configured to monitor and/or acquire one or more parameter sets P of the engine  10 . 
     It should be appreciated that the communications interface module  230  can be any combination of suitable wired and/or wireless communications interfaces and, thus, can be communicatively coupled to one or more components of the system  100  including the engine  10  via a wired and/or wireless connection. As such, the computing device  210  may operate, modulate, or adjust operation of the engine  10 , acquire parameters via the sensor S, or determine a location of the health deterioration contributor, or other steps such as described in regard to the method  1000 . 
     It should further be appreciated that the system  100  may include a plurality of the computing device  210  configured to collectively, or individually, perform one or more of the operations or steps of the method  1000  generally described herein. For example, one or more computing devices  210  may be configured to operate the engine  10 . Another computing device  210  may be configured to determine the location of the health deterioration contributor. The one or more computing devices  210  may be coupled together via any combination of suitable wired and/or wireless communications interfaces, such as to acquire, transmit, determine, generate, or provide data, calculations, results, instructions, or commands across the one or more computing devices  210 . Such combinations of suitable wired and/or wireless communications interfaces may include, but is not limited to, centralized networks or databases, including those referred to as cloud networks. 
     As such, it should be appreciated that the system  100  may include one or more computing devices  210  in communication from the engine  10  to another computing device  210  located at an aircraft to which the engine  10  is coupled (e.g., cockpit or other aircraft control), or off of the aircraft. For example, the computing device  210  may be located at a ground-, sea-, or space-based facility or apparatus, or another aircraft. 
     Embodiments of the methods and systems shown and described herein enable determining a more precise location at the engine of a health deterioration contributor, such as damage or wear, foreign or domestic object debris, or malfunction, or other operational nonconformance or anomaly. The determined location may be transmitted to a user/operator of the engine such as to adjust operation of the engine due to the deterioration contributor, or to provide targeted maintenance, repair, or replacement of the deteriorated component based on the location of the deterioration contributor provided via the method and system. The determined location may further reduce time lost in troubleshooting, investigating, or otherwise repairing an engine. The determined location may further mitigate damage to the engine during operation via providing real-time troubleshooting during engine operation such as to enable the user/operator to adjust engine operation accordingly. 
     Particular embodiments of the methods and systems generally provided herein may acquire sensor to sensor variation (e.g., from a first sensor S 1  at a first position at the engine and a second sensor S 2  at a second position different from the first position) across variations in engine operating condition (e.g., from a first engine operating condition E 1  and a second engine operating condition E 2 ). For example, the sensor (e.g., sensor S) may define a temperature probe (e.g., exhaust gas temperature or EGT probe) disposed in the turbine section  31  or exhaust section  32 . The method  1000  may improve determining a health deterioration contributor, and a location L thereof, (e.g., fuel nozzle coking, cracking, leakage, etc.) that may result in hot or cold streaks circumferentially, radially, and/or axially within the flowpath  70  via acquiring parameters and comparing sensor to sensor variation at the plurality of engine operating conditions. 
     In other embodiments, the sensor may define a pressure probe disposed at the compressor section  21 , the combustion section  26 , the turbine section  31 , the exhaust section  32 , or the fan section  14 . The method  1000  may improve operation, maintenance, or performance of the engine  10  by improving determination of a health deterioration contributor via acquiring parameters and comparing sensor to sensor variation at the plurality of engine operating conditions. Additionally, or alternatively, the method  1000  may improve operation, maintenance, or performance of the engine  10  by improving a thrust output (e.g., calculated thrust output via engine pressure ratio or EPR) via improving determination of a health deterioration contributor. 
     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.