Patent Abstract:
An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.

Full Description:
BACKGROUND 
       [0001]    This disclosure relates to gas turbine engines, and more particularly to the thermal protection of electrical components of gas turbine engines. 
         [0002]    Electrical components are by their nature sensitive to temperature and thermal cycling. As a result, it is desired to keep the electrical components relatively cool and within a small temperature range in order to function properly and to extend the useful service life of the electrical components. Many mechanical system components such a pumps, actuators, valves, or the like are driven by electrical motors, and while the mechanical portion of the component may be able to withstand high operating temperatures, the electrical portions of the components, such as a motor, controller and other portions, must be kept relatively cool to maintain their useful service life. In a typical gas turbine engine, a “firewall” is defined that divides a “cold side” of the gas turbine engine where temperatures are typically below 160 degrees Fahrenheit from a “hot side” of the gas turbine engine where operating temperatures are often in the range of about 160 degrees to 600 degrees Fahrenheit or higher. Problems arise when it is desired or necessary to locate a mechanical component with necessary electrical portions such as a motor or a controller on the “hot side” of the firewall. 
       SUMMARY 
       [0003]    In one embodiment, an electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough. 
         [0004]    Additionally or alternatively, in this or other embodiments the electronic module is operably connected to one or more of an electrical controller or an electrical motor located at the second side of the firewall. 
         [0005]    Additionally or alternatively, in this or other embodiments the electronic module is configured to collect data from the mechanical component relating to the service life and/or operation of the mechanical component. 
         [0006]    Additionally or alternatively, in this or other embodiments the data is one or more of operating speeds, temperatures, pressures, flow, vibration, proximity, position, current or operational time of the mechanical component. Any other sensors not listed that measure physical states would also be applicable. 
         [0007]    Additionally or alternatively, in this or other embodiments the mechanical component is one of an actuator or a pump. 
         [0008]    Additionally or alternatively, in this or other embodiments an electrical motor is located at the second side of the firewall and is operably connected to the mechanical component via a coupling extending through the firewall at a coupling opening, separate and distinct from the module opening. 
         [0009]    Additionally or alternatively, in this or other embodiments an electrical controller is located at the second side and is operably connected to the electronic module and the electrical motor to control the electrical motor utilizing input from the electronic module. 
         [0010]    Additionally or alternatively, in this or other embodiments the electronic module is inseparably secured to the mechanical component to remain connected to the mechanical component for the entire service life of the mechanical component. 
         [0011]    Additionally or alternatively, in this or other embodiments the first side has an operating temperature greater than 160 degrees Fahrenheit. 
         [0012]    Additionally or alternatively, in this or other embodiments the firewall is located axially upstream of a high pressure compressor section of the gas turbine engine, the first side located axially downstream of the firewall. 
         [0013]    In another embodiment, an electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electrical motor located at a second side of the firewall, the second side having a lower operating temperature than the first side. The electrical motor is operably connected to the mechanical component via a coupling extending through a coupling opening in the firewall and configured to drive the mechanical component. An electronic module is inseparably connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side and a cover plate installed over the module opening after the electronic module is inserted therethrough. 
         [0014]    Additionally or alternatively, in this or other embodiments the electronic module is operably connected to an electrical controller located at the second side of the firewall. The electrical controller is configured to control the electrical motor utilizing input from the electronic module. 
         [0015]    Additionally or alternatively, in this or other embodiments the electronic module is configured to collect data from the mechanical component relating to the service life and/or operation of the mechanical component. 
         [0016]    Additionally or alternatively, in this or other embodiments the data is one or more of operating speeds, temperatures, pressures, flow or operational time of the mechanical component. 
         [0017]    Additionally or alternatively, in this or other embodiments the mechanical component is one of an actuator or a pump. 
         [0018]    Additionally or alternatively, in this or other embodiments the first side has an operating temperature greater than 160 degrees Fahrenheit. 
         [0019]    Additionally or alternatively, in this or other embodiments the firewall is located axially upstream of a high pressure compressor section of the gas turbine engine, the first side located axially downstream of the firewall. 
         [0020]    In yet another embodiment, a gas turbine engine includes a high pressure compressor, a combustor in operable communication with the high pressure compressor and a firewall located axially upstream of the high pressure compressor. The firewall defines a first side axially downstream of the firewall and a second side axially upstream of the firewall, the second side having a lower operating temperature than the first side. An electromechanical system includes a mechanical component located at the first side, and an electrical motor located at the second side. The electrical motor is operably connected to the mechanical component via a coupling extending through a coupling opening in the firewall and configured to drive the mechanical component. An electronic module is inseparably connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side. A cover plate is installed over the module opening after the electronic module is inserted therethrough. 
         [0021]    Additionally or alternatively, in this or other embodiments the electronic module is operably connected to an electrical controller located at the second side of the firewall, the electrical controller configured to control the electrical motor utilizing input from the electronic module. 
         [0022]    Additionally or alternatively, in this or other embodiments the electronic module is configured to collect data from the mechanical component relating to the service life and/or operation of the mechanical component. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0023]    The subject matter which is regarded as the present disclosure is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: 
           [0024]      FIG. 1  illustrates a schematic cross-sectional view of an embodiment of a gas turbine engine; 
           [0025]      FIG. 2  illustrates a schematic view of an embodiment of a component arrangement at a firewall of a gas turbine engine; 
           [0026]      FIG. 3  illustrates a schematic perspective view of an embodiment of a component connection arrangement at a firewall of a gas turbine engine; 
           [0027]      FIG. 4  illustrates a schematic view of another embodiment of a component connection arrangement at a firewall of a gas turbine engine; and 
           [0028]      FIG. 5  illustrates another schematic view of the embodiment of  FIG. 4 . 
       
    
    
     DETAILED DESCRIPTION 
       [0029]      FIG. 1  is a schematic illustration of a gas turbine engine  10 . The gas turbine engine generally has includes fan section  12 , a low pressure compressor  14 , a high pressure compressor  16 , a combustor  18 , a high pressure turbine  20  and a low pressure turbine  22 . The gas turbine engine  10  is circumferentially disposed about an engine centerline X. During operation, air is pulled into the gas turbine engine  10  by the fan section  12 , pressurized by the compressors  14 ,  16 , mixed with fuel and burned in the combustor  18 . Hot combustion gases generated within the combustor  18  flow through high and low pressure turbines  20 ,  22 , which extract energy from the hot combustion gases. 
         [0030]    In a two-spool configuration, the high pressure turbine  20  utilizes the extracted energy from the hot combustion gases to power the high pressure compressor  16  through a high speed shaft  24 , and the low pressure turbine  22  utilizes the energy extracted from the hot combustion gases to power the low pressure compressor  14  and the fan section  12  through a low speed shaft  26 . The present disclosure, however, is not limited to the two-spool configuration described and may be utilized with other configurations, such as single-spool or three-spool configurations. 
         [0031]    Gas turbine engine  10  is in the form of a high bypass ratio turbine engine mounted within a nacelle or fan casing  28  which surrounds an engine casing  30  housing a engine core  32 . A significant amount of air pressurized by the fan section  12  bypasses the engine core  32  for the generation of propulsive thrust. The airflow entering the fan section  12  may bypass the engine core  32  via a fan bypass passage  34  extending between the fan casing  28  and the engine casing  30  for receiving and communicating a discharge flow F 1 . The high bypass flow arrangement provides a significant amount of thrust for powering an aircraft. 
         [0032]    The engine casing  30  generally includes an inlet case  36 , a low pressure compressor case  38 , and an intermediate case  40 . The inlet case  36  guides air to the low pressure compressor case  38 , and via a splitter  42  also directs air through the fan bypass passage  34 . 
         [0033]    The gas turbine engine  10  further includes a firewall  44 , defined to separate a relatively high temperature portion of the gas turbine engine  10 , where operating temperatures may be in the range of 160 degrees to 600 degrees Fahrenheit or higher, from a relatively low temperature portion of the gas turbine engine  10 , where operating temperatures are less than about 160 degrees Fahrenheit. In the embodiment of  FIG. 1 , the firewall  44  is located between the low pressure compressor  14  and the high pressure compressor  16 , separating a cold side  46  of the gas turbine engine  10  where operating temperatures are less than about 160 degrees Fahrenheit, from a hot side  48  of the gas turbine engine  10 , where operating temperatures may be in the range of 200 degrees to 600 degrees Fahrenheit or higher. The hot side  48  includes engine areas and components axially downstream of the firewall  44 , while the cold side  46  includes engine areas and components axially upstream of the firewall  44 . 
         [0034]    Referring now to  FIG. 2 , the gas turbine engine  10  includes many mechanical components  50  or devices such as actuators, pumps or the like, and many of these mechanical components  50  utilize electrical components, such as electrical motors  52  and/or electrical controllers  54  to enable or control operation of the mechanical components  50 . It is often desired or necessary to locate such mechanical components  50  at the hot side  48  of the firewall  44 , but care must be taken to protect the electrical components from the high operating temperatures of the hot side  48 . 
         [0035]    Shown in  FIG. 2  is an embodiment of an arrangement in which the mechanical component  50 , such as an actuator or pump, is located at the hot side  48  of the firewall  44 . A coupling  56 , such as a shaft extends from the mechanical component  50  through a coupling opening  58  in the firewall  44  and connects to the electrical motor  52 , located at the cold side  46  of the firewall  44 . A coupling seal  60  may be located at the coupling opening  58  to seal between the coupling opening  58  and the coupling  56  to prevent migration of hot gases from the hot side  48  to the cold side  46  through the coupling opening  58 . The mechanical component  50  includes an electronic module  62  at which collects data relating to the service life and operation of the mechanical component  50  is stored. The data may include recorded operating speeds, temperatures, vibration, proximity, position, current, flow, operational times or the like and may include data measured by one or more sensors  64  at the mechanical component  50 . One skilled in the art will readily appreciate that other data collected may also be stored at the electronic module  62 . The electronic module  62  is inseparably secured to the mechanical component  50  to remain with the mechanical component  50  through the lifespan of the mechanical component  50 . Data collected at the electronic module  62  will remain with the mechanical component  50  even when the mechanical component  50  is removed from the gas turbine engine  10  for service, repair or replacement. 
         [0036]    The electronic module  62  receives power from the electrical controller  54  and converts analog signals from cable  66  into digital signals for transmission to the electrical controller  54  through a controller cable  72 . The electronic module  62  may include any combination of a power conditioning function, processing unit, memory, analog to digital converters, analog interface circuits and a digital bus interface for communication. Other circuits that interface devices in the mechanical component  50  may also be included in the electronic module  62 . 
         [0037]    To protect the electronic module  62  from the high operating temperatures of the hot side  48  and to preserve the integrity of the data collected at the electronic module  62 , the electronic module  62  is located at the cold side  46  during operation of the gas turbine engine  10 . To accomplish this, the electronic module  62  is connected to the mechanical component  50  via a module cable  66 , which permanently joins the electronic module  62  to the mechanical component  50 . With the mechanical component  50  installed at the hot side  48 , the electronic module  62  is passed through a module opening  68  in the firewall  44  from the hot side  48  to the cold side  46 . A cover plate  70 , which may be installed around the module cable  66  or integral to the module cable  66  covers and seals the module opening  68  from the hot side  48  to prevent hot gas egress from the hot side  48  to the cold side  46  via the module opening  68 . Once in place at the cold side  46 , the electronic module  62  is connected to one or more components on the cold side  46  such as the electrical controller  54  via the controller cable  72  to provide communication between the mechanical component  50  and the electrical controller  54  so the electrical controller  54  may provide commands to the electrical motor  52  via motor cable  74  to, for example, adjust output of the electrical motor  52  based on data feedback from the mechanical component  50  and/or the electronic module  62 . While the controller cable  72  and motor cable  74  are illustrated in  FIG. 2 , it is to be appreciated that in other embodiments, the controller cable  72  may be omitted and the electronic module  62  may be directly connected to the electrical controller  54 . Likewise, in some embodiments the electrical motor  52  may be directly connected to the electrical controller  54 , with the motor cable  74  omitted. Also, while the electronic module  62  in the embodiment of  FIG. 2  is connected to the electrical controller  54 , it is to be appreciated that in other embodiments, the electronic module  62  may be connected to the electrical motor  52  or another electrical or mechanical component. Further, the electronic module  62  may be fixed in place to, for example, the cover plate  70 , the firewall  44  or other structure of the gas turbine engine  10 . 
         [0038]    Referring now to  FIG. 3 , in some embodiments it is desired to protect or isolate the electronic module  62  from high frequency vibrations that occur during operation of the gas turbine engine  10 , which may be transmitted through the firewall  44  or cover plate  70 .  FIG. 3  illustrates a vibration isolation structure  76  to which the electronic module  62  is secured, and connected to the controller cable  72 . The vibration isolation structure  76  includes a connection hub  78  at which the electronic module  62  is connected to, for example, the controller cable  72 . The connection hub  78  is spaced from and connected to the firewall  44 , or other structure of the gas turbine engine  10 , by one or more vibration isolators  80 , such as springs, dampers such as elastomeric dampers, and/or other vibration absorbing or damping element such as an air cylinder/piston arrangement or an oil filled cylinder/piston arrangement. While two vibration isolators  80  are shown in  FIG. 3 , it is to be appreciated that other quantities of vibration isolators  80 , for example, one, three, four or more vibration isolators  80  may be utilized. The vibration isolators  80  are configured such that transmission of gas turbine engine  10  high frequency vibrations from the firewall  44  to the electronic module  62  is reduced or prevented. 
         [0039]    To further prevent vibration transmission to the electronic module  62 , the module cable  66  extending from the cover plate  70  to the electronic module  62  is in a slack condition (not taut) after the electronic module  62  is installed at the connection hub  78  and the cover plate  70  is installed to the firewall  44 . Cable springs  82  may extend from the cover plate to the electronic module  62  to further dampen vibration which may be transmitted through the module cable  68 . 
         [0040]    Another embodiment of a vibration isolation structure  76  is shown in  FIGS. 4 and 5 . The vibration isolation structure  76  includes a housing  84  fixed to the cover plate  70  with, in some embodiments, a seal  86  interposed between the housing  84  and the cover plate  70 . A mounting frame  88  is located in the housing  84  with the electronic module  62  secured to a first leg  90  of the mounting frame  88 . The mounting frame  88  includes a leg  92 , which in some embodiments is perpendicular to the first leg  90 . In some embodiments, the mounting frame  88  is substantially T-shaped. The mounting frame  88  is supported in the housing  84  by one or more vibration isolators  80  connected to the housing  84  and to the mounting frame  88 . The vibration isolators  80  support the mounting frame  88  in the housing  84  while allowing for relative vibratory motion of the mounting frame  88  and electronic module  62  relative to the housing  84  and the cover plate  70 . Gas turbine engine  10  vibrations transmitted through the firewall  44  and cover plate  70  into the housing  84  are dampened by the vibration isolators  80  so transmission to the electronic module  62  is reduced or prevented. To allow for the relative vibratory motion of the cover plate  70  relative to the electronic module  62 , the module cable  66  may have a slack (not taut) condition when the cover plate  70  is installed to the firewall  44  to prevent vibration transmission through the module cable  66  to the electronic module  62 . 
         [0041]    To connect the electronic module  62  to the controller cable  72  or other component, the connection hub  78  is located at the housing  84 , providing a connector  94  for connecting the controller cable  72 . The electronic module  62  is connected to the connector  94  of the connection hub  78  via an intermediate cable  96 , which also may have a slack (not taut) condition to allow for relative vibratory motion between the housing  84  and the electronic module  62 , thus preventing vibration transmission through the intermediate cable  96  to the electronic module  62 . 
         [0042]    The embodiment of  FIGS. 4 and 5 , including the housing  84  with the electronic module  62  located inside of the housing  84 , provides additional protection of the electronic module  62  from damage or contamination, both when installed at the gas turbine engine  10  and when not installed at the gas turbine engine  10 . Further, the housing  84  provides a rigid structure to ensure that when the housing  84  is installed through the firewall  44 , a secure connection is made with the mating component, for example, the controller cable  72 . 
         [0043]    While the present disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the present disclosure is not limited to such disclosed embodiments. Rather, the present disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the scope of the present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments. Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Technology Classification (CPC): 5