Gas turbine engine actuator

Abstract

A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power supply. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device can operate with the compressor section, the combustion section, the turbine section, or a combination thereof. The actuator is operatively coupled to the actuation device and includes an electric actuator configured to convert electric current into mechanical power. The power supply is configured to supply electric current to the actuator alone or in cooperation with a hydraulic actuator.

Description

Technical Field

[0001] The present disclosure relates to an actuation system for a gas turbine engine. Background Art

[0002] A gas turbine engine generally includes a turbine and a rotor assembly. A gas turbine engine, such as a turbofan engine, can be used for aircraft propulsion. In the case of a turbofan engine, the rotor assembly can be configured as a fan assembly. The fan assembly can include one or more components with variable geometry that can be manipulated by valves and actuators. For example, the geometry of these components can be changed to control surge and rotating stall.

[0003] In existing gas turbine engines, valves and actuators are typically controlled using an actuating fluid (e.g., fuel) to operate each actuator or valve. In conventional hydraulic actuation systems, it may be difficult to control an actuator or valve under certain conditions. For example, hydraulic fluid is typically driven by source pressure, and under extreme operating conditions, the source pressure may be insufficient or completely lost. Therefore, an improved actuation device would be useful. Summary of the invention

[0004] Aspects and advantages of the present disclosure 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 present disclosure.

[0005] In an exemplary embodiment of the present disclosure, a gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power supply. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device can operate with the compressor section, the combustion section, the turbine section, or a combination thereof. The actuator is operatively coupled to the actuation device and includes an electric actuator configured to convert electric current into mechanical power. The power supply is configured to supply electric current to the actuator.

[0006] In an exemplary embodiment of the present disclosure, a hybrid electric / hydraulic actuation system for a gas turbine engine includes an actuation device capable of operating with a section of the gas turbine engine, a hybrid electric / hydraulic actuator, a hydraulic actuation system, and an electric actuation system. The hybrid electric / hydraulic actuator is operatively connected to the actuation device and is partially driven by electricity and partially driven by a working fluid. In this article, partially driven means that the actuator can be driven by electricity all or part of the time, can be driven by the working fluid all or part of the time, and / or can be driven at least part of the time by a combination of electricity and power generated by the working fluid. The hydraulic actuation system includes a working fluid, a working fluid pump configured to pressurize the hydraulic actuation system with the working fluid, and a fluid pipeline connected to the working fluid pump and the hybrid electric / hydraulic actuator and extending between the working fluid pump and the hybrid electric / hydraulic actuator. The electric actuation system includes a power supply, which is configured to supply current to the hybrid electric / hydraulic actuator.

[0007] In an exemplary embodiment of the present disclosure, a method of changing a position of an actuation device in a gas turbine engine includes providing hydraulic power to an actuator operatively coupled to the actuation device to move the actuation device from a first position to a second position, receiving data indicating that the hydraulic power is less than an amount required to move the actuation device from the first position to the second position, and providing electrical power to the actuator to assist in moving the actuation device from the first position to the second position.

[0008] These and other features, aspects and advantages of the present disclosure will be 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 present disclosure and, together with the description, serve to explain the principles of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] A full and enabling disclosure of the present disclosure, including the best mode thereof, is set forth in the specification to those skilled in the art, with reference to the accompanying drawings, wherein:

[0010] Figure 1A is a schematic cross-sectional view of a first gas turbine engine having an electrical power system according to an exemplary embodiment of the present disclosure.

[0011] Figure 1B is a schematic cross-sectional view of a first gas turbine engine having a hybrid electric / hydraulic powertrain according to an exemplary embodiment of the present disclosure.

[0012] Figure 2A is a schematic cross-sectional view of a second gas turbine engine with an electrical power system according to another exemplary embodiment of the present disclosure.

[0013] Figure 2Bis a schematic cross-sectional view of a second gas turbine engine having a hybrid electric / hydraulic power system according to another exemplary embodiment of the present disclosure.

[0014] Figure 3 is a simplified schematic diagram of a hybrid electric / hydraulic actuator according to an exemplary embodiment of the present disclosure.

[0015] Figure 4 is a flow chart of a method of operating an actuator assembly. DETAILED DESCRIPTION

[0016] Reference will now be made in detail to embodiments of the present disclosure, 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. In the drawings and description, like or similar names are used to refer to like or similar parts of the present disclosure.

[0017] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. In addition, unless otherwise specified, all embodiments described herein should be considered exemplary.

[0018] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and not for the purpose of indicating the position or importance of each component.

[0019] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, with respect to a gas turbine engine, the front refers to a position near the engine inlet, and the rear refers to a position near the engine nozzle or exhaust.

[0020] The terms "upstream" and "downstream" refer to the relative directions of the fluid flow in the fluid channel. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction to which the fluid flows.

[0021] The terms “coupled,” “fixed,” “attached,” and the like refer to both direct coupling, fixing, or attachment as well as indirect coupling, fixing, or attachment through one or more intermediate components or features, unless otherwise specified herein.

[0022] The singular forms "a", "an" and "the" include plural forms unless the context clearly dictates otherwise.

[0023] Approximate language used in the entire specification and claims herein is applied to modify any quantitative representation that can allow variation without causing the basic function associated therewith to change. Therefore, by one or more terms, such as "about", "approximately" and "substantially", the modified value is not limited to the specified precise value. In at least some instances, approximate language may correspond to the accuracy of the instrument used to measure the value, or the accuracy of the method or machine used to build or manufacture parts and / or systems. For example, approximate language may refer to within 1, 2, 4, 5, 10, 15 or 20% of the amplitude. These approximate amplitudes may be applicable to any one or two endpoints of a single value, a limited range of values, and / or the range amplitude between the endpoints.

[0024] Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein include the endpoints, and the endpoints are independently combinable with each other.

[0025] In a hydraulic actuation system, the ability to provide power to move an actuating device is driven by source pressure. As described above, in some hydraulic actuation systems, the hydraulic fluid may be fuel. In this case, the fuel is provided via a fuel pump that generates a source pressure that is directly related to the amount of fuel required or needed by the gas turbine engine. For example, in an aborted takeoff event or other event that reduces the output power of the gas turbine engine, the fuel pressure may drop rapidly and may lead to a situation where the power from the fuel system to drive the actuator and move the actuating device is less than the air power acting on the actuating device. For example, when the actuating device is a variable bleed valve or a variable stator vane, the air power acting on these components may be greater than the power available from the fuel system to move these components. In this case, the variable bleed valve may be prevented from opening at the desired rate, and the variable stator vane may be prevented from moving to the desired position, putting the compressor of the gas turbine engine in danger of stalling.

[0026] Embodiments in the present disclosure propose a hybrid electric / hydraulic system using a generator (and / or an external battery or power source) on the low-pressure shaft and / or high-pressure shaft of a multi-shaft turbofan engine. The hybrid electric generator system is used to: drive the electric system of the actuator; provide boost power to valves and actuators under extreme operating conditions; and / or provide backup power to the hybrid hydraulic / electric actuator in the event of a loss of hydraulic pressure. The hybrid hydraulic / electric system has a combination of hydraulic and electrical sources to extract power from, thereby always providing the power required to drive the actuation system. Benefits of the proposed hybrid electric / hydraulic system of generators include: more consistent electrical loads in situations where the air force acting to move the actuator is greater than the available hydraulic power, and reduced hydraulic fluid lines, thereby reducing the complexity and weight of the engine structure.

[0027] Reference now Figure 1A , provides a cross-sectional view of an exemplary embodiment of a gas turbine engine that may incorporate one or more inventive aspects of the present disclosure. In particular, Figure 1A The exemplary gas turbine engine of FIG. 1 is configured as a single non-ducted rotor engine 10 that defines an axial direction A, a radial direction R, and a circumferential direction C. Figure 1A As can be seen, the engine 10 takes the form of an open rotor propulsion system and has a rotor assembly 12 that includes an array of airfoils arranged about a centerline 14 of the engine 10 , and more particularly, includes an array of rotor blades 16 arranged about a central longitudinal axis 14 of the engine 10 .

[0028] In addition, as will be explained in detail below, the engine 10 also includes a non-rotating bucket assembly 18 positioned rearward of the rotor assembly 12 (i.e., non-rotating relative to the central axis 14), the bucket assembly 18 including an array of airfoils also arranged about the central axis 14, and more particularly, including an array of buckets 20 arranged about the central axis 14. The rotor blades 16 are typically arranged in an equally spaced relationship about the central axis 14, and each blade has a root 22 and a tip 24 and a span defined therebetween. Similarly, the buckets 20 are also typically arranged in an equally spaced relationship about the centerline 14, and each blade has a root 26 and a tip 28 and a span defined therebetween. The rotor assembly 12 also includes a hub located forward of the plurality of rotor blades 16.

[0029] In addition, the engine 10 includes a turbine 30 having a core (or high pressure / high speed system) 32 and a low pressure / low speed system. It is understood that, as used herein, the terms "speed" and "pressure" are used interchangeably with respect to the high pressure / high speed system and the low pressure / low speed system. In addition, it is understood that the terms "high" and "low" are used in the same context to distinguish between the two systems and are not meant to imply any absolute speed and / or pressure values.

[0030] The core 32 generally includes a high-speed compressor 34, a high-speed turbine 36, and a high-speed shaft 38 extending between and connecting the high-speed compressor 34 and the high-speed turbine 36. The high-speed compressor 34, the high-speed turbine 36, and the high-speed shaft 38 may be collectively referred to as the high-speed spool of the engine. In addition, a combustion section 40 is located between the high-speed compressor 34 and the high-speed turbine 36. The combustion section 40 may include one or more structures for receiving a mixture of fuel and air and providing a flow of combustion gases through the high-speed turbine 36 for driving the high-speed spool.

[0031] The low-speed system also includes a low-speed turbine 42, a low-speed or low-pressure compressor or supercharger 44, and a low-speed shaft 46 extending between and connecting the low-speed compressor 44 and the low-speed turbine 42. The low-speed compressor 44, the low-speed turbine 42, and the low-speed shaft 46 may be collectively referred to as the low-speed spool 55 of the engine. Although the engine 10 is described as having the low-speed compressor 44 located forward of the high-speed compressor 34, in some embodiments, the compressors 34, 44 may be in a staggered arrangement. In addition, or in other words, although the engine 10 is described as having the high-speed turbine 36 located forward of the low-speed turbine 42, in some embodiments, the turbines 36, 42 may also be similarly in a staggered arrangement.

[0032] Still refer to Figure 1A , the turbine 30 is generally enclosed in a cowling 48. In addition, it will be appreciated that the cowling 48 at least partially defines an inlet 50 and an exhaust port 52, and includes a turbomachinery flow path 54 extending between the inlet 50 and the exhaust port 52. For the illustrated embodiment, the inlet 50 is an annular or 360 degree axisymmetric inlet 50, located between the rotor blade assembly 12 and the fixed or stationary vane assembly 18, and provides a path for the incoming atmospheric air to enter the turbomachinery flow path 54 (and the compressor 44, 34, the combustion section 40, and the turbine 36, 42) in the radial direction R inside the guide vanes 28. Such a location may be advantageous for various reasons, including management of icing performance and protecting the inlet 50 from various objects and materials that may be encountered during operation. However, in other embodiments, the inlet 50 may be positioned at any other suitable location, for example, behind the vane assembly 18, arranged in a non-axisymmetric manner, etc.

[0033] As shown, the rotor assembly 12 is driven by the turbine 30, and more specifically, by the low speed spool 55. More specifically, Figure 1A The engine 10 in the illustrated embodiment includes a power gearbox 56, and the rotor assembly 12 is driven by the low-speed spool 55 of the turbine 30 through the power gearbox 56. In this manner, the rotating rotor blades 16 of the rotor assembly 12 can rotate about the axis 14 and generate thrust to propel the engine 10, and thus the aircraft associated therewith, in the forward direction F. The power gearbox 56 can include a gear set for reducing the rotational speed of the low-speed spool 55 relative to the low-speed turbine 42, so that the rotor assembly 12 can rotate at a slower rotational speed than the low-speed spool 55.

[0034] As briefly mentioned above, the engine 10 includes a bucket assembly 18. The bucket assembly 18 extends from the cowling 48 and is positioned rearwardly of the rotor assembly 12. The buckets 20 of the bucket assembly 18 may be mounted on a stationary frame or other mounting structure and do not rotate relative to the central axis 14. For reference purposes, Figure 1A The forward direction is also depicted by arrow F, which in turn defines the front and rear parts of the system. Figure 1A As shown, the rotor assembly 12 is located in front of the turbine 30 in a "puller" configuration, and the exhaust port 52 is located behind the guide vanes 28. As can be appreciated, the vanes 20 of the vane assembly 18 can be configured to clean up the airflow from the rotor assembly 12 (e.g., reduce swirl in the airflow) to improve the efficiency of the engine 10. For example, the size, shape, and configuration of the vanes 20 can be designed to apply a reactionary swirl to the airflow from the rotor blades 16 so that in the downstream direction behind the two rows of airfoils (e.g., blades 16, vanes 20), the degree of swirl of the airflow is greatly reduced, which can translate into an improved level of induced efficiency.

[0035] Still refer to Figure 1A It is desirable that the rotor blades 16, the vanes 20, or both include a pitch variation mechanism so that the airfoils (e.g., blades 16, vanes 20, etc.) can be rotated independently or in conjunction with each other relative to a pitch axis of rotation. Such pitch variation can be used to vary thrust and / or swirl effects under various operating conditions, including adjusting the magnitude or direction of thrust generated on the rotor blades 16, or providing a thrust reversal feature, which may be useful under certain operating conditions (e.g., when landing an aircraft), or it may be desirable to adjust at least in part the acoustic noise generated by the rotor blades 16, the vanes 20, or from the aerodynamic interaction of the rotor blades 16 relative to the vanes 20. More specifically, in Figure 1AIn the embodiment of the present invention, the rotor assembly 12 is depicted as having an actuator 58. In this example, the actuator 58 is a pitch change mechanism for rotating the rotor blades 16 about their respective pitch axes 60. The blade assembly 18 is depicted as having an actuator 62, which in this example is a pitch change mechanism for rotating the blades 20 about their respective pitch axes 64.

[0036] Actuators 66, 68 and 70 are also included in Figure 1A (and Figure 1B ) In one example, each of the actuators 58, 62, 66, 68, and 70 individually represents a combination of an actuating device and an actuator that drives the movement of the actuating device. Figure 1A The actuating devices represented by actuators 66, 68, and 70 in the drawings may include one or more variable bleed valves, variable stator vanes, variable inlet guide vanes, variable outlet guide vanes, compressor discharge pressure bleed valves, turbine clearance control systems, recirculation valves, bleed valves, and throttle valves. In this manner, it is understood that the actuating device may generally be any variable geometry component of the engine 10 for modifying airflow through the turbomachinery flow path 54 or around the turbine 30, or an airflow valve of the engine 10 for modifying the amount of airflow bled from the turbomachinery flow path 54 or over the turbine 30, or the amount of airflow provided to the turbomachinery flow path 54 or over the turbine 30.

[0037] Still reference Figure 1A , generator 72 and generator 74 are shown mounted on engine 10. In particular, generator 72 may be a high-speed generator mounted on high-speed turbine 36 (e.g., high-pressure turbine). Generator 74 may be a low-speed generator mounted on low-speed turbine 42 (e.g., low-pressure turbine).

[0038] However, it is understandable that Figure 1A The exemplary single rotor non-ducted engine 10 depicted in FIG. 1 is merely an example, and in other exemplary embodiments, the engine 10 may have any other suitable configuration, including, for example, any other suitable number of shafts or spools, turbines, compressors, etc.; fixed pitch blades 16, 20, or both; a direct drive configuration (i.e., the gearbox 56 may not be included); etc. For example, in other exemplary embodiments, the engine 10 may be a three-spool engine with a medium speed compressor and / or turbine. In such a configuration, it will be understood that the terms "high" and "low" used herein with respect to speeds and / or pressures of turbines, compressors, or spools are terms of convenience for distinguishing components, but do not require any particular relative speeds and / or pressures, nor do they exclude other compressors, turbines, and / or spools or shafts.

[0039] Additionally, or alternatively, in other exemplary embodiments, any other suitable gas turbine engine may be provided. For example, in other exemplary embodiments, the gas turbine engine may be a turboshaft engine, a turboprop engine, a turbojet engine, etc. Additionally, for example, although the engine is depicted as a single non-ducted rotor engine, in other embodiments, the engine may include a multi-stage open rotor configuration, and various aspects of the disclosure described below may be incorporated therein. Additionally, still in other exemplary embodiments, the engine 10 may be configured as a ducted turbofan engine (e.g., see Figure 2A-2B ).

[0040] about Figure 1A , it can be appreciated that the engine is integrated with the electric actuation system 100. The electric actuation system 100 generally includes a load sharing bank 102 and a power source 104. Moreover, for the illustrated embodiment, the load sharing bank 102 of the electric actuation system 100 is in electrical communication with the power source 104 and the actuators 58, 62, 66, 68, and 70. In this example, the actuators 58, 62, 66, 68, and 70 and the generators 72 and 74 can be considered to be part of the electric actuation system 100.

[0041] The load sharing bank 102 may generally be any device capable of receiving power and distributing such power in a desired manner. For example, the load sharing bank 102 may include an electrical controller, power electronics, switches, etc. to perform such functions. In addition, in some embodiments, the load sharing bank may further store some power as an electrical energy storage unit.

[0042] It is worth noting that although Figure 1B A single load sharing bank 102 is provided in the exemplary embodiment, but in alternative exemplary embodiments, the electric actuation system 100 may additionally or alternatively include multiple load sharing banks, such as multiple electrical controllers, so that one or more actuators are powered from a separate load sharing bank.

[0043] In at least some exemplary embodiments, the power source 104 may include one or more batteries. Additionally or alternatively, the power source 104 may include one or more supercapacitor arrays, one or more ultracapacitor arrays, or both. Additionally or alternatively, the power source 104 may be one or both of the generators 72, 74, or further may be a generator driven by a separate gas turbine engine (e.g., a gas turbine engine that generates thrust or an auxiliary power unit).

[0044] In at least some embodiments, the power supply 104 can be configured to provide at least 5 kilowatts (kW) of energy to the electric actuation system 100, such as at least 50 kilowatts, such as at least 250 kilowatts, such as at least 300 kilowatts, such as at least 350 kilowatts, such as at least 400 kilowatts, such as at least 500 kilowatts, such as up to 5 megawatts (MW), such as up to 10 megawatts (MW). In addition, the power supply 104 can be configured to provide such power for at least two minutes, such as at least three minutes, such as at least five minutes, such as up to one hour. Moreover, still in other embodiments, the power supply 104 can be configured to provide such power for any other suitable duration, such as continuously during operation of the engine 10.

[0045] In a rejected takeoff event, the engine 10 decelerates rapidly from takeoff power to idle speed at a very fast rate. This presents a challenge to the stability margin of the low speed compressor 44. In a rejected takeoff event, it is desirable to open the variable bleed valve (e.g., the actuation device represented by actuator 66) as quickly as possible to prevent stalling of the low speed compressor 44.

[0046] In existing hydraulic actuation systems, the hydraulic working fluid is typically driven by a source pressure. In the case of a fuel-based hydraulic system, the fuel is provided via a fuel pump, and the source pressure is directly related to the amount of fuel provided to the combustion section 40 of the engine 10. For example, in an aborted takeoff event or other event that reduces the output power of the engine 10, the fuel pressure may drop rapidly and may result in a situation where the power from the fuel system to drive the actuator and move the actuating device is less than the air force acting on the actuating device. For example, when the actuating device is a variable bleed valve or a variable stator vane, the air force acting on these components may be greater than the power available from the fuel system to move these components. In this case, the variable bleed valve may be prevented from opening at a desired rate, and the variable stator vanes may be prevented from moving to a desired position, putting the compressor of the gas turbine engine at risk of stalling.

[0047] exist Figure 1A (and Figure 2A , discussed below), it will be appreciated that when, for example, a rejected takeoff flag is triggered or other data indicative of a rejected takeoff is received, the electric actuation system 100 can be activated and deployed to provide the required power to the actuators (e.g., actuators 66, 68, 70) to move the actuation devices of these actuators in the desired manner. Continuing with this example, the electric actuation system 100 can provide power for the maximum rate of opening of the variable bleed valve of, for example, actuator 66. The electric actuation system 100 makes a determination or takes action when determining the maximum electrical load required in this case, and the load sharing bank 102 provides this power to the actuators.

[0048] Some benefits of the electric actuation system 100 may include reducing or eliminating hydraulic fluid lines in the engine 10, thereby reducing the structural complexity and weight of the engine 10. With the electric actuation system 100, in situations where the air power acting to move any actuator 58, 62, or 66-70 is high compared to the available hydraulic power, the resulting electrical load is more consistent. In addition, the voltage slew rate of the fuel hydraulic actuator may be limited by the available power of the supply pump of the hydraulic system. With the electric actuation system 100, faster voltage slew rates may be achieved by extracting power from the turbine via the generator 72 or 74 or extracting power from an external source (e.g., power source 104).

[0049] In other embodiments, the engine 10 may include a third flow path or third flow extending from the low-speed compressor 44 or the high-speed compressor 34. As used herein, "third flow" refers to a small number of secondary air flows that can increase fluid energy to produce total propulsion system thrust. The pressure ratio of the third flow is higher than the pressure ratio of the main propulsion flow (e.g., a bypass or propeller-driven propulsion flow). Thrust can be generated by a dedicated nozzle, or by mixing the secondary air flow with the main propulsion flow or core air flow, for example, into a common nozzle. In certain exemplary embodiments, the operating temperature of the secondary air flow is lower than the maximum compressor discharge temperature of the engine, and more specifically, can be lower than 350 degrees Fahrenheit (such as lower than 300 degrees Fahrenheit, such as lower than 250 degrees Fahrenheit, such as lower than 200 degrees Fahrenheit, and at least the same as the ambient temperature).

[0050] In certain exemplary embodiments, these operating temperatures may facilitate heat transfer to or from the secondary airflow and the separate fluid flows. In addition, in certain exemplary embodiments, the secondary airflow may contribute less than 50% of the total engine thrust (and at least as much as 2% of the total engine thrust) at takeoff conditions, or more particularly, at sea level, static flight speed, 86 degrees Fahrenheit ambient temperature operating conditions, when operating at rated takeoff power. In addition, in certain exemplary embodiments, various aspects of the secondary airflow (e.g., airflow, mixing or exhaust characteristics), and therefore the above exemplary percentage contributions to total thrust, may be passively adjusted during engine operation or purposefully modified using engine control features (e.g., fuel flow, motor power, variable stators, variable inlet guide vanes, valves, variable exhaust port geometry or flow characteristics) to adjust or optimize overall system performance over a wide range of potential operating conditions.

[0051] Reference now Figure 1B , Figure 1B is a schematic cross-sectional view of engine 10 with a hybrid electric / hydraulic powertrain 88 . Figure 1B The exemplary embodiments may be related to the above Figure 1A The exemplary engine 10 is constructed in substantially the same manner, and the same or similar reference numbers may refer to the same or similar parts. Figure 1B In the illustrated embodiment, the engine 10 is shown as including a hybrid electric / hydraulic actuation system 88, which includes an electric actuation system 100 (having a load sharing bank 102 and a power source 104) and a hydraulic actuation system 90 (having an accessory gearbox 92 (AGB 92), a working fluid pump 94 and fluid lines 96).

[0052] Here, the hydraulic actuation system 90 is combined with the electric actuation system 100 to form a hybrid electric / hydraulic power system 88. Utilizing the hybrid electric / hydraulic power system 88, both the hydraulic actuation system 90 and the electric actuation system 100 are constructed to drive the actuators 58, 62, and 66-70 of the engine 10 individually or cooperatively. For example, the working fluid pump 94 of the hydraulic actuation system 90 is fluidly connected to each actuator 58, 62, and 66-70 via a fluid line 96. In this way, the working fluid pump 94 is constructed to deliver working fluid to each actuator 58, 62, and 66-70 to drive the actuation of each actuator 58, 62, and 66-70. In this example, the working fluid pump 94 is driven by the AGB 92 of the engine 10. However, in other embodiments, the working fluid pump 94 can be driven by any other power source, such as a power supply.

[0053] In one example, and more specifically, in Figure 1BIn the depicted example, the hydraulic actuation system 90 is configured as part of the fuel delivery system. Thus, for the illustrated embodiment, the hydraulic actuation system 90 further includes a fuel line 96A extending to the combustion section 40 to provide a fuel flow to the combustion section 40. During operation of the hybrid electric / hydraulic power system 88, the electric actuation system 100 will provide electric boost to the hydraulic actuation system 90 during at least certain operations. For example, when the fuel pressure drops, the hybrid electric / hydraulic actuation system 88 can provide supplemental power via the electric actuation system 100 to facilitate movement of various actuation devices between the first and second positions despite the relatively low hydraulic pressure / fuel pressure. For example, in this case, the hybrid electric / hydraulic actuation system 88 can provide supplemental power via the electric actuation system 100 to maximize the opening rate of the actuation device of the actuator 66 (e.g., the variable bleed valve) and / or any other actuator 58, 62, 70 or 68. Additionally, the ability of the hybrid electric / hydraulic actuation system 88 to determine which axle to pull power from has the added benefit of modifying the deceleration rate during a rejected takeoff event, which provides additional time for the hybrid electric / hydraulic actuation system 88 to open, for example, a variable bleed valve or modify other variable geometry components (e.g., any actuator 58, 62, 66, 68, or 70).

[0054] An additional benefit of the hybrid electric / hydraulic actuation system 88 is the creation of a layer of redundancy to prevent failure of either the electric actuation system 100 or the hydraulic actuation system 90. If one of the two systems fails, the other can take over and provide the necessary power to the actuators 58, 62, and / or 66-70. In other examples, an operating mode can cause the electric actuation system 100 to provide less than 100% power to the actuators 58, 62, and / or 66-70, and cause the hydraulic actuation system 90 to provide less than 100% power to the actuators 58, 62, and / or 66-70. For example, the electric actuation system 100, the hydraulic actuation system 90, or both can provide 10% to 90% power to the actuators, such as 25% to 75% power. In another example, each of the electric actuation system 100 and the hydraulic actuation system 90 can provide up to 100% power to the actuators 58, 62, and / or 66-70 at different time periods (or at the same time).

[0055] Figure 2A is a schematic cross-sectional view of a second gas turbine engine according to another exemplary embodiment of the present disclosure. For example, Figure 2A An engine 10 according to another exemplary embodiment of the present disclosure is described in detail. Figure 2A The exemplary embodiments may be related to the above Figure 1A-1BThe exemplary engine 10 and power system 100 are constructed in substantially the same manner, and the same or similar reference numbers may refer to the same or similar components. However, as can be appreciated, Figure 2A In the illustrated embodiment, engine 10 further includes a nacelle 80 (having an inlet 82 and an outlet 84 ) that at least partially circumferentially surrounds rotor assembly 12 and turbine 30 , defining a bypass passage 86 therebetween.

[0056] Here, we provide Figure 2A The ducted fan arrangement of the engine 10 is shown, and the engine 10 includes an electric actuation system 100. Therefore, the same or similar features of the engine 10 with the electric actuation system 100 and the corresponding description thereof also apply to Figure 2A An embodiment of an engine 10 is shown having an electric actuation system 100 .

[0057] Reference now Figure 2B , Figure 2B yes Figure 2A A schematic cross-sectional view of an engine 10 is shown which additionally includes a hybrid electric / hydraulic actuation system 88 having a hydraulic actuation system 90 (including an AGB 92, a working fluid pump 94, and fluid lines 96) and an electric actuation system 100 (including a load sharing bank 102 and a power source 104). Figure 2B The exemplary embodiments may be related to the above Figure 2A The depicted exemplary engine 10 is constructed in substantially the same manner, and the same or similar reference numbers may refer to the same or similar components.

[0058] exist Figure 2A and 2B In the illustrated embodiment, a ducted fan arrangement is shown for engine 10. Figure 1A and 1B Similar to the illustrated embodiment, the hydraulic actuation system 90 and / or the electric actuation system 100 may be used individually or in conjunction to power any of the actuators 58, 62, and 66-70 as needed during operation of the engine 10 (e.g., such as during a rejected takeoff event or when compressor discharge pressure drops).

[0059] Reference now Figure 3 , Figure 3 3 is a simplified schematic diagram of a hybrid electric / hydraulic actuator 300 and shows an electric portion 302, a wire 304, a hydraulic portion 306, an inlet line 308, an outlet line 310, and an actuating member 312. In this example, the hybrid electric / hydraulic actuator 300 may be the above-described Figures 1A-2BThus, the embodiments described herein, i.e., embodiments of the hybrid electric / hydraulic actuator 300, may be applicable throughout Figures 1A-2B Other embodiments described.

[0060] like Figure 3 As shown, the hybrid electric / hydraulic actuator 300 includes an electric portion 302 and a hydraulic portion 306. In one example, the electric portion 302 receives power from the load sharing bank 102 of the electric actuation system 100 via a conductor 304. Similarly, the hydraulic portion 306 can receive working fluid from and deliver working fluid to the working fluid pump 94 via an inlet line 308 and an outlet line 310, respectively. During operation of the hybrid electric / hydraulic actuator 300, the actuating member is driven by one or both of the electric portion 302 and the hydraulic portion 306.

[0061] The hydraulic actuator may be driven by a pump having a limited amount of power that may be reduced when supply pressure is reduced (e.g., fuel from a fuel pump during a power reduction mode of a gas turbine engine). A hybrid electric / hydraulic actuation system 88 (e.g., having a hybrid electric / hydraulic actuator 300 (e.g., representing any of actuators 58, 62, and 66-70) Figure 1B and 2B As shown) has many sources to extract power to always provide the power required to drive the actuation system of the engine 10.

[0062] However, it is understood that the hybrid electric / hydraulic actuator 300 is described in schematic form and is provided by way of example only. In other exemplary embodiments, the hybrid electric / hydraulic actuator 300 may have any suitable configuration for receiving power from a hydraulic system and a power source and converting such received power into movement of an actuating device. For example, in other exemplary embodiments, the hybrid electric / hydraulic actuator 300 may include a hydraulic actuator coupled to an actuating device for moving the actuating device using hydraulic pressure, and a separate electric motor that is separately coupled to the actuating device for moving the actuating device using electricity. Other configurations are also contemplated.

[0063] Reference now Figure 4 , a flow chart of an exemplary method 400 for changing the position of an actuating device in a gas turbine engine is provided. The method 400 may be operated with one or more of the exemplary gas turbine engines described above, and one or more of the actuating devices (actuators) described above.

[0064] The method 400 includes providing hydraulic power to an actuator operatively coupled to an actuating device at (402) to move the actuating device from a first position to a second position. In certain exemplary aspects, the hydraulic system may be incorporated into the fuel system. In such exemplary aspects, providing hydraulic power to the actuator at (402) includes providing a fuel flow to the actuator at (404).

[0065] Method 400 further includes receiving data at (406) indicating that the hydraulic power is less than the amount required to move the actuator from the first position to the second position. The data received at (406) can be any data indicating a pressure reduction in the hydraulic system. For example, in certain exemplary aspects, receiving data at (406) indicating that the hydraulic power is less than the amount required to move the actuator from the first position to the second position includes receiving data at (408) indicating a command to reduce the output power of the gas turbine engine. The data can be data received from an engine controller (such as a full authority digital engine controller (FADEC), or any other suitable controller). Alternatively, the data can include pressure data from the hydraulic system, and / or operating data of the gas turbine engine (e.g., speed, operating temperature and / or pressure, etc.).

[0066] Additionally, or alternatively, the data received at (406) may be data indicating that the actuator has not moved to the second position within a desired amount of time, or data indicating that air power on the actuator is greater than power available from the hydraulic system.

[0067] The method 400 further includes providing power to the actuator at (410) to assist in moving the actuating device from the first position to the second position. Providing power to the actuator at (410) may include providing power to the actuator from a power source (e.g., from a generator coupled to the gas turbine engine, an electrical energy storage unit, a generator driven by an internal combustion engine other than the gas turbine engine, etc.).

[0068] It will be appreciated that changing the position of the actuator may involve or include expanding, contracting, bending or deforming the actuator in addition to or in lieu of linear or rotational movement, such as displacement, rotation or pivoting.

[0069] This written description uses examples to describe the disclosure, including the best mode, and also to enable any person skilled in the art to practice the disclosed embodiments, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or include equivalent structural elements that do not differ substantially from the literal language of the claims.

[0070] Further aspects are provided by the subject matter of the following clauses:

[0071] A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power supply. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device can operate with the compressor section, the combustion section, the turbine section, or a combination thereof. The actuator is operatively coupled to the actuation device and includes an electric actuator configured to convert electric current into mechanical power. The power supply is configured to supply electric current to the actuator.

[0072] The gas turbine engine actuation system according to one or more of these clauses, further comprising a hydraulic system, and wherein the actuator comprises a hybrid hydraulic-electric actuator operable with the hydraulic system.

[0073] A gas turbine engine actuation system according to one or more of these clauses, wherein the hydraulic system is a fuel delivery system.

[0074] The gas turbine engine actuation system according to one or more of these clauses further includes: an accessory gearbox, which is connected to the gas turbine engine and driven by the gas turbine engine, wherein the hydraulic system is mechanically connected to the accessory gearbox and driven by the accessory gearbox, and the hydraulic system includes: a working fluid; a working fluid pump, which is configured to pressurize the hydraulic system using the working fluid; and a fluid pipeline, which is fluidly connected to the working fluid pump and the actuator and extends between the working fluid pump and the actuator.

[0075] A gas turbine engine actuation system according to one or more of these clauses, wherein said hybrid hydraulic-electric actuator is driven partly by electricity and partly by said working fluid of said hydraulic system.

[0076] The gas turbine engine actuation system according to one or more of these clauses, further comprising a generator coupled to the turbine section, wherein the power source comprises the generator or is configured to receive electrical power from the generator.

[0077] The gas turbine engine actuation system according to one or more of these clauses further comprises a load sharing bank electrically connected to the actuator and the power source, wherein the load sharing bank is configured to receive current from the power source and supply the current to the actuator.

[0078] The gas turbine engine actuation system according to one or more of these clauses further includes: a first generator and a second generator, the first generator and the second generator being configured to supply electricity to the load sharing bank; wherein the turbine section includes a low-pressure turbine section and a high-pressure turbine section; wherein the first generator is connected to the low-pressure turbine section and extracts power from the low-pressure turbine section; and wherein the second generator is connected to the high-pressure turbine section and extracts electricity from the high-pressure turbine section.

[0079] A gas turbine engine actuation system according to one or more of these clauses, wherein the actuation device comprises at least one of a variable bleed valve, a variable stator vane, a compressor discharge pressure bleed valve, or a turbine clearance control system.

[0080] A gas turbine engine actuation system according to one or more of these clauses, wherein the power source comprises an external power source disconnected from any rotating element of the gas turbine engine.

[0081] A hybrid electric / hydraulic actuation system for a gas turbine engine includes an actuation device operable with a section of the gas turbine engine, a hybrid electric / hydraulic actuator, a hydraulic actuation system, and an electric actuation system. The hybrid electric / hydraulic actuator is operatively coupled to the actuation device and is driven in part by electricity and in part by a working fluid. The hydraulic actuation system includes a working fluid, a working fluid pump configured to pressurize the hydraulic actuation system with the working fluid, and a fluid line fluidly connected to and extending between the working fluid pump and the hybrid electric / hydraulic actuator. The electric actuation system includes a power source configured to supply current to the hybrid electric / hydraulic actuator.

[0082] A hybrid electric / hydraulic actuation system according to one or more of these clauses, wherein the electric actuation system further comprises a load sharing bank electrically connected to the actuator and the power source, wherein the load sharing bank is constructed to receive current from the power source and supply the current to the hybrid electric / hydraulic actuator.

[0083] A hybrid electric / hydraulic actuation system according to one or more of these clauses, wherein the electric actuation system further comprises a generator configured to generate electricity from the gas turbine engine and supply the generated electricity to the load sharing bank.

[0084] The hybrid electric / hydraulic actuation system according to one or more of these clauses further includes: wherein the generator includes a first generator and a second generator; wherein the first generator is connected to a low-pressure turbine section of the gas turbine engine and extracts power from the low-pressure turbine section; and wherein the second generator is connected to a high-pressure turbine section of the gas turbine engine and extracts electricity from the high-pressure turbine section.

[0085] A hybrid electric / hydraulic actuation system according to one or more of these clauses, wherein the actuation device comprises at least one of a variable bleed valve, a variable stator vane, a compressor discharge pressure bleed valve, and a turbine clearance control system.

[0086] A hybrid electric / hydraulic actuation system according to one or more of these clauses, wherein the power source comprises an external power source disconnected from any rotating element of the gas turbine engine.

[0087] A method of changing the position of an actuating device in a gas turbine engine, comprising providing hydraulic power to an actuator operatively coupled to the actuating device to move the actuating device from a first position to a second position. Receiving data indicating that the hydraulic power is less than an amount required to move the actuating device from the first position to the second position. Providing electrical power to the actuator to assist in moving the actuating device from the first position to the second position. A method according to one or more of these clauses, wherein the actuating device comprises at least one of a variable bleed valve, a variable stator vane, a compressor discharge pressure bleed valve, or a turbine clearance control system.

[0088] A method according to one or more of these clauses, wherein providing hydraulic power to the actuator comprises providing a flow of fuel to the actuator.

[0089] A method according to one or more of these clauses, wherein receiving data indicating that the hydraulic power is less than an amount required to move the actuator from the first position to the second position comprises receiving data indicative of a command to reduce the output power of the gas turbine engine.

Claims

1. A gas turbine engine actuation system, characterized in that: include: A gas turbine engine, the gas turbine engine comprising: compressor section; a combustion section disposed in fluid communication with the compressor section and downstream of the compressor section; a turbine section disposed in fluid communication with the compressor section and downstream from the compressor section; and a rotational shaft extending axially along a centerline of the gas turbine engine; an actuation device operable with the compressor section, the combustion section, the turbine section, or a combination thereof; a hybrid hydraulic-electric actuator operatively coupled to the actuating device, wherein the hybrid hydraulic-electric actuator includes an electric actuator configured to convert an electric current into a first mechanical power to mechanically drive the actuating device, wherein the hybrid hydraulic-electric actuator further includes a hydraulic actuator configured to convert a pressure of a fluid into a second mechanical power to mechanically drive the actuating device; and a power source configured to provide current to the electric actuator; The hybrid hydraulic-electric actuator is configurably coupled to the actuating device such that the actuating device is simultaneously driven by the first mechanical power of the electric actuator and the second mechanical power of the hydraulic actuator.

2. The gas turbine engine actuation system according to claim 1, characterized in that: A hydraulic system is further included, and wherein the hybrid hydraulic-electric actuator operates with the hydraulic system.

3. The gas turbine engine actuation system according to claim 2, characterized in that: The hydraulic system is a fuel delivery system.

4. The gas turbine engine actuation system according to claim 2, characterized in that: Further including: an accessory gearbox coupled to and driven by the gas turbine engine, wherein the hydraulic system is mechanically coupled to and driven by the accessory gearbox, the hydraulic system comprising: Working fluid; a working fluid pump configured to pressurize the hydraulic system with the working fluid; and A fluid line is fluidly connected to the working fluid pump and the actuator and extends between the working fluid pump and the hybrid hydraulic-electric actuator.

5. The gas turbine engine actuation system according to claim 1, characterized in that: Further included is a generator coupled to the turbine section, wherein the power source includes the generator or is configured to receive power from the generator.

6. The gas turbine engine actuation system according to claim 1, characterized in that: Further included is a load sharing bank electrically connected to the hybrid hydraulic-electric actuator and the power source, wherein the load sharing bank is configured to receive current from the power source and supply the current to the hybrid hydraulic-electric actuator.

7. The gas turbine engine actuation system according to claim 1, characterized in that: The actuating device includes a variable bleed valve, a variable stator vane, a compressor discharge pressure bleed valve or a turbine clearance control system.

8. The gas turbine engine actuation system according to claim 1, characterized in that: Wherein the power source comprises an external power source disconnected from any rotating element of the gas turbine engine.

9. A hybrid electric / hydraulic actuation system for a gas turbine engine, characterized in that: The hybrid electric / hydraulic actuation system comprises: an actuation device operable with a section of the gas turbine engine; a hybrid electric / hydraulic actuator driven in part by electricity and in part by a working fluid, wherein the hybrid electric / hydraulic actuator is operatively coupled to the actuation device; A hydraulic actuation system, the hydraulic actuation system comprising: Working fluid; a working fluid pump configured to pressurize the hydraulic actuation system with the working fluid to generate a first mechanical power for the hybrid electric / hydraulic actuator; and a fluid line fluidly connected to and extending between the working fluid pump and the hybrid electric / hydraulic actuator; and An electric actuation system, the electric actuation system comprising: a power source configured to provide current to the hybrid electric / hydraulic actuator to generate a second mechanical power; The hybrid electric / hydraulic actuator is configurably coupled to the actuating device such that the actuating device is simultaneously driven by the first mechanical power of the hybrid electric / hydraulic actuator and the second mechanical power of the hybrid electric / hydraulic actuator.

10. The hybrid electric / hydraulic actuation system according to claim 9, characterized in that: The electric actuation system further includes a load sharing bank electrically connected to the hybrid electric / hydraulic actuator and the power source, wherein the load sharing bank is configured to receive current from the power source and supply the current to the hybrid electric / hydraulic actuator.

11. The hybrid electric / hydraulic actuation system according to claim 10, characterized in that: The electric actuation system further includes a generator configured to generate electricity from the gas turbine engine and supply the generated electricity to the load sharing bank.

12. The hybrid electric / hydraulic actuation system according to claim 11, characterized in that: Further including: Wherein, the generator comprises a first generator and a second generator; wherein the first generator is coupled to a low-pressure turbine section of the gas turbine engine and extracts power from the low-pressure turbine section; and Wherein, the second generator is coupled to a high-pressure turbine section of the gas turbine engine and extracts electrical power from the high-pressure turbine section.

13. The hybrid electric / hydraulic actuation system according to claim 9, characterized in that: The actuating device includes a variable bleed valve, a variable stator vane, a compressor discharge pressure bleed valve or a turbine clearance control system.

14. The hybrid electric / hydraulic actuation system according to claim 9, characterized in that: Wherein the power source comprises an external power source disconnected from any rotating element of the gas turbine engine.

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