Turbine engine comprising system for controlling pitch of propeller blades

Abstract

An example turbine engine includes a propeller including blades rotatable about a centerline axis to vary a pitch of the blades; and a blade pitch control system, the blade pitch control system comprising: a fan pitch actuation system coupled to the blade, the fan pitch actuation system movable to rotate the blade from a first pitch angle to a second pitch angle based on an amount of hydraulic fluid pumped into the fan pitch actuation system; the energy accumulator is used for storing hydraulic fluid; and a valve coupled to the output of the accumulator and to the input of the fan pitch actuation system, the valve automatically providing hydraulic fluid from the accumulator to the fan pitch actuation system based on the control signal.

Description

Technical Field

[0001] This disclosure generally relates to a turbine engine, and more specifically, to a turbine engine including a system for controlling the pitch of propeller blades. Background Technology

[0002] Turbine engines (such as turbofan engines and turboprop engines), like those used on aircraft, typically consist of a propeller / fan and a gas turbine engine that drives the propeller / fan to generate thrust. In some configurations, the propeller / fan has variable-pitch blades. Therefore, the blade pitch can be changed at different stages of operation. Attached Figure Description

[0003] The specification with reference to the accompanying drawings sets forth a complete and feasible disclosure of the currently described techniques for those skilled in the art, including its best mode, wherein:

[0004] Figure 1 This is a schematic cross-sectional view of an example turboprop engine, in which the examples disclosed herein can be implemented.

[0005] Figure 2 include Figure 1 Side view of the propeller blades of a turboprop engine at three different pitch angles.

[0006] Figure 3 The following diagram illustrates the implementation. Figure 1 Automatic blade pitch control fan pitch actuation system.

[0007] Figure 4 The following diagram illustrates the implementation. Figure 1 An alternative to the fan pitch actuation system for automatic blade pitch control.

[0008] Figure 5 The following diagram illustrates the implementation. Figure 1 An alternative to the fan pitch actuation system for automatic blade pitch control.

[0009] Figure 6 The following diagram illustrates the implementation. Figure 1 An alternative to the fan pitch actuation system for automatic blade pitch control.

[0010] Figure 7A The first position is shown. Figure 3-6 Cross-sectional view of the fan blade pitch actuation system.

[0011] Figure 7B The second position is shown. Figure 3-6 Cross-sectional view of the fan blade pitch actuation system.

[0012] Figure 8It shows Figure 3-6 An alternative implementation of the fan pitch actuation system.

[0013] Figure 9 This is a flowchart illustrating example machine-readable instructions and / or operations that can be made, instantiated, and / or executed by programmable circuitry to achieve... Figure 1 Fully digital engine control.

[0014] Figure 10 This is a block diagram of an example processing platform that includes programmable circuitry configured to perform, instantiate, and / or execute example machine-readable instructions and / or perform... Figure 9 Example operations to implement Figure 1 Fully digital engine control.

[0015] These figures are not drawn to scale. Instead, the thickness of areas may be enlarged in the figures. Generally, the same reference numerals will be used throughout the figures and accompanying written description to refer to the same or similar parts. Unless otherwise stated, connection references (e.g., attachment, joint, connection, and engagement) should be interpreted broadly and may include intermediate members between assemblies of elements and relative movement between elements. Therefore, a connection reference does not necessarily imply that two elements are directly connected and have a fixed relationship with each other. A statement that any part is in "contact" and / or "directly in contact" with another part means that there is no intermediate part between the two parts. Detailed Implementation

[0016] Reference will now be made in detail to embodiments or examples of the currently described technology, one or more of which are illustrated in the accompanying drawings. Each example is provided by way of explanation of the currently described technology and not for limitation thereof. Indeed, it will be apparent to those skilled in the art that various modifications and variations can be made to the currently described technology without departing from the scope or spirit of the technology. For example, features shown or described as part of an embodiment or example may be used with another embodiment or example to produce yet another embodiment or example. Therefore, the currently described technology is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0017] When describing elements of various embodiments of this disclosure, the articles “a,” “an,” “the,” and “described” are intended to indicate the presence of one or more of that element. As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and do not imply the location or importance of the components. The terms “comprising,” “including,” and “having” are intended to be inclusive, meaning that additional elements may be present in addition to those listed. Because the terms “connected to,” “linked to,” etc., are used herein, an object (e.g., a material, element, structure, component, etc.) may be connected to or linked to another object, regardless of whether the object is directly connected to or linked to the other object, or whether there are one or more intermediate objects between the object and the other.

[0018] The terms “upstream” and “downstream” refer to the relative directions of fluid flow within a fluid path. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction in which the fluid flows. As used herein, the terms “axial” and “longitudinal” refer to directions parallel to the centerline axis of the gas turbine engine (e.g., core turbine engine, turbomachinery, etc.), while “radial” refers to a direction perpendicular to the axial direction, and “tangential” or “circumferential” refers to directions perpendicular to both the axial and radial directions. Thus, as used herein, “radially inward” refers to the radial direction from the outer periphery of the gas turbine engine toward the centerline axis of the gas turbine engine, and “radially outward” refers to the radial direction from the centerline axis of the gas turbine engine toward the outer periphery of the gas turbine engine.

[0019] "Comprising" and "including" (and all their forms and tenses) are used herein as open-ended terms. Therefore, whenever a claim uses any form of "comprising" or "including" (e.g., including, comprising, having, etc.) in a preamble or in any type of claim statement, it should be understood that additional elements, terms, etc., may be present without exceeding the scope of the corresponding claim or statement. As used herein, the phrase "at least" is open-ended when used as a transitional term, for example, in the preamble of a claim, as are the terms "comprising" and "including". The term "and / or", when used, for example, in the form of A, B, and / or C, refers to any combination or subset of A, B, and C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the operation or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the operation or execution of processes, instructions, actions, activities and / or steps, the phrase “at least one of A or B” is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B.

[0020] As used herein, singular references (e.g., “a,” “an,” “first,” “second,” etc.) do not exclude multiple entities. As used herein, the term “a” or “an” refers to one or more of that entity. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, while individual features may be included in different examples or claims, these may be combined, and inclusion in different examples or claims does not imply that combining features is impractical and / or disadvantageous.

[0021] Some turbine engines used on aircraft, such as turboprop engines, ductless fan (UDF) engines, and high-bypass turbofan engines, have variable-pitch blades or rotor blades. Specifically, the pitch (e.g., angle) of the blades relative to the incoming airflow can be changed during engine operation. This allows the turbine engine to achieve optimal operation at various stages of flight. These types of engines include blade pitch control systems to control the blade pitch. The blade pitch control system is hydraulically actuated. In the event of hydraulic system failure and / or engine shutdown during flight, it is desirable for the blades to move to a certain pitch position, called a feathering position, where the blades generate minimal (e.g., minimum) drag or resistance. In some cases, the feathering position corresponds to a position or angle where the blades are substantially aligned (e.g., ±5°) with the direction of the incoming airflow.

[0022] This document discloses an example blade pitch actuation system having a hydraulic and / or pneumatic system as fault protection to move the blades to one or more positions / angles (e.g., one or more feathering positions / angles) in the event of a failure of the blade pitch control system and / or engine shutdown. The hydraulic system includes a hydraulic accumulator with configurable solenoid valves. The solenoid valves are controlled based on triggers to transfer fluid from the hydraulic accumulator to the fan pitch actuation system (FPAS). The FPAS controls the pitch of the propeller blades based on the fluid flowing into and / or out of the FPAS. Thus, the hydraulic system passively controls the FPAS to change the propeller blade pitch in response to triggers (e.g., power failure, actuation failure, and / or any other trigger).

[0023] The pneumatic system includes a pressurized pneumatic chamber filled with a pressurized gas (e.g., nitrogen). The pressurized pneumatic chamber is sealed and provides a constant bias force in the feathering position. Therefore, the pressurized pneumatic chamber is always loaded during normal operation of the blade pitch control system. However, in the event of hydraulic system failure and / or engine shutdown, the pressurized pneumatic chamber operates passively to move the blades to the feathering position.

[0024] Compared to conventional technologies, the examples disclosed herein use a compact and less complex system to passively move propeller blades to predetermined positions (e.g., full feathering, partial feathering, no feathering, etc.) without active control. The examples disclosed herein reduce the hazardous risks associated with feathering failure due to power loss, pitch control unit (PCU) malfunction, pressure loss, etc.

[0025] Referring now to the accompanying drawings, in which the same numbers throughout the drawings denote the same elements. Figure 1This is a schematic cross-sectional view of an example turbine engine 100 that can be combined with the various examples disclosed herein. In this example, the turbine engine 100 is a turboprop engine, referred to herein as turboprop engine 100. However, the principles of this disclosure are also applicable to other types of engines, such as turbofan engines (e.g., high-bypass turbofan engines, low-bypass turbofan engines), ductless fan (UDF) engines (sometimes referred to as propeller fans), and / or other types of engines having propellers with variable-pitch blades or impellers (e.g., fans, propellers, etc.). Furthermore, the examples disclosed herein can also be used in conjunction with other types of applications, such as electric fans or wind turbines with variable-pitch fans.

[0026] like Figure 1 As shown, the turboprop engine 100 includes a gas turbine engine 102 (which may also be referred to as a core turbine engine or turbomachinery) and a propeller 104 comprising a plurality of blades 106 (sometimes referred to as rotors or wheel blades). The propeller 104 may include any number of blades 106. The gas turbine engine 102 is disposed downstream of the propeller 104 and drives the blades 106 of the propeller 104 to generate forward thrust. Figure 1 As shown, the turboprop engine 100 and / or gas turbine engine 102 define a longitudinal or axial centerline axis 108 extending therethrough for reference. Figure 1 It also includes annotated direction diagrams for the axial direction A, radial direction R, and circumferential direction C. Generally, as used herein, the axial direction A is a direction extending approximately parallel to the centerline axis 108, the radial direction R is a direction extending orthogonally outward or inward toward the centerline axis 108, and the circumferential direction C is a direction extending concentrically around the centerline axis 108. Furthermore, as used herein, the term "forward" refers to the direction along the centerline axis 108 in the direction of motion of the turboprop engine 100, for example, in... Figure 1 From the center to the left, while the term "backward" refers to the opposite direction along the centerline axis 108, for example, in Figure 1 From the center to the right.

[0027] The gas turbine engine 102 includes a generally tubular outer casing 110 (which may also be referred to as an intermediate casing) defining an annular inlet 112. The outer casing 110 of the gas turbine engine 102 may be formed from a single casing or multiple casings. The outer casing 110 surrounds, in series flow relationship, a compressor section having a turbocharger or low-pressure compressor 114 (“LP compressor 114”) and a high-pressure compressor 116 (“HP compressor 116”), a combustion section 118 (which may also be referred to as a combustor 118), a turbine section having a high-pressure turbine 120 (“HP turbine 120”) and a low-pressure turbine 122 (“LP turbine 122”), and an exhaust section 124. The gas turbine engine 102 includes a high-pressure shaft or spool 126 (“HP shaft 126”) which is drivably coupled to the HP turbine 120 and the HP compressor 116. The gas turbine engine 102 also includes a low-pressure shaft or spool 128 (“LP shaft 128”) which is drivably coupled to the LP turbine 122 and the LP compressor 114. The LP shaft 128 is also coupled to the propeller shaft or shaft 130 (sometimes referred to as the fan shaft). Blades 106 are coupled to and extend radially outward from the propeller shaft 130. In this example, blade 106 is a variable-pitch blade. Thus, the pitch of blade 106 can be varied during operation of the turboprop engine 100 to improve efficiency and achieve certain flow characteristics during different phases of flight. An example system for varying the pitch of blade 106 is disclosed in more detail herein. In some examples, the LP shaft 128 may be directly coupled to the propeller shaft 130 (i.e., a direct-drive configuration). In alternative configurations, the LP shaft 128 may be coupled to the propeller shaft 130 via a reduction gear 132 (i.e., an indirect-drive or gear-driven configuration). While in this example the gas turbine engine 102 includes two compressors and two turbines, in other examples the gas turbine engine 102 may include only one compressor and one turbine.

[0028] like Figure 1As shown, during operation of the turboprop engine 100, intake air 140 enters the propeller 104 and is accelerated by the blades 106. A first portion 142 of the air 140 flows along the exterior of the gas turbine engine 102, while a second portion 144 of the air 140 flows into the inlet 112 of the gas turbine engine 102 (and thus into the LP compressor 114). One or more successive stages of the LP compressor rotor blades 148 and LP compressor stator blades 146, coupled to the LP shaft 128, progressively compress the second portion 144 of the air 140 flowing through the LP compressor 114 on its way to the HP compressor 116. Subsequently, one or more successive stages of the HP compressor rotor blades 152 and HP compressor stator blades 150, coupled to the HP shaft 126, further compress the second portion 144 of the air 140 flowing through the HP compressor 116. This provides compressed air 154 to the combustion section 118, where it mixes with fuel and burns to provide combustion gases 156.

[0029] Combustion gas 156 flows through HP turbine 120, where one or more successive stages of HP turbine rotor blades 160 and HP turbine stator blades 158, coupled to HP shaft 126, extract a first portion of kinetic and / or thermal energy. This energy extraction supports the operation of HP compressor 116. Combustion gas 156 then flows through LP turbine 122, where one or more successive stages of LP turbine rotor blades 164 and LP turbine stator blades 162, coupled to LP shaft 128, extract a second portion of thermal and / or kinetic energy from it. This energy extraction causes LP shaft 128 to rotate, which supports the operation of LP compressor 114 and / or propeller shaft 130. Combustion gas 156 then exits gas turbine engine 102 through exhaust section 124. Combustion gas 156 mixes with a first portion 142 of air 140 to generate propulsive thrust.

[0030] Along with the turboprop engine 100, the gas turbine engine 102 serves a similar purpose and experiences a similar environment in land-based gas turbines, as well as turbofan engines and turbojet engines, where the ratio of the first portion 142 to the second portion 144 of air 140 is different. In each engine, a reduction device (e.g., reduction gear 132) can be included between any shaft and spool. For example, reduction gear 132 may be disposed between the LP shaft 128 and the propeller shaft 130.

[0031] Figure 1 The turboprop engine 100 includes an automatic blade pitch control system 170. Figure 1The automatic blade pitch control system 170 is a system that automatically and / or passively changes the pitch of blade 106 in response to a trigger. The trigger may be related to a fault and / or failure. Therefore, the automatic blade pitch control system 170 can automatically adjust the pitch of blade 106 after a fault or error to automatically reduce air resistance, thereby reducing the hazards associated with the fault or error. The trigger can be one or more signals from Full Authority Digital Engine Control (FADEC) 180. For example, in response to a power outage or error, FADEC 180 can be powered by a backup power source and / or battery and output one or more control signals to the automatic blade pitch control system 170 to cause the automatic blade pitch control system 170 to change the pitch of blade 106. The automatic blade pitch control system 170 may include hydraulic and / or pneumatic systems for automatically and passively controlling the pitch of blade 106. (The following is in conjunction with...) Figure 2-5 The automatic blade pitch control system 170 is further described.

[0032] FADEC 180 is a controller and / or computing system that controls various aspects of engine performance. FADEC 180 can detect and / or determine errors related to power failure, low pressure, propeller PCU malfunction, and / or any other situation requiring automatic and / or passive adjustment of the pitch of blade 106. FADEC 180 outputs one or more control signals to the automatic blade pitch control system 170 to change the pitch of blade 106 (e.g., from a fine or coarse pitch to a feathered pitch). In some examples, FADEC 180 can utilize engine characteristics and / or flight and / or user / manufacturer preferences to determine the applied pitch angle of blade 106. For example, FADEC 180 can automatically feather blade 106 based on a triggering event. For example, when an error occurs during takeoff or landing, FADEC 180 can trigger a first pitch angle (also called a first pitch) of blade 106, and when an error occurs during normal flight, FADEC 180 can use a second pitch angle (also called a second pitch) of blade 106. Furthermore, the FADEC 180 can control the pitch adjustment speed of blade 106 based on engine characteristics and / or flight and / or user / manufacturer preferences.

[0033] Figure 2 include Figure 1 Side view of the propeller 104 blades 106 of the turboprop engine 100 at three different pitch angles and / or positions (e.g., fine pitch, coarse pitch, and feathering). Figure 2In the example, the low angle of blade 106, also known as the fine pitch, is an angle less than 90 degrees (e.g., 30 degrees) relative to the plane of rotation (e.g., corresponding to line A). A pitch with a low angle corresponds to a first drag level (e.g., high drag). The high angle of blade 106, also known as the coarse pitch, is an angle greater than the low angle but less than 90 degrees (e.g., 60 degrees) relative to the plane of rotation. A pitch with a high angle corresponds to a second drag level (e.g., medium drag). The feathering angle of blade 106, also known as the feathering pitch, is an angle of 90 degrees to the plane of rotation. A pitch with a feathering angle corresponds to a third drag level (e.g., low drag). Although... Figure 2 In the example, the feathering pitch is 90 degrees. As mentioned above, the feathering angle can vary from 90 degrees to approximately ±5°. As described above, the automatic blade pitch control system 170 can adjust the pitch from a first angle (e.g., low and / or high) to a second angle (e.g., high and / or feathering) based on a trigger. The amount of pitch control and / or the speed of pitch control can be based on user / manufacturer preferences and / or on the characteristics of the flight and / or turboprop engine 100.

[0034] Figure 3 It shows what can be used to implement Figure 1 An example blade pitch controller 300 is provided for an automatic blade pitch control system 170. The blade pitch controller 300 includes an example accumulator 301, example valves 302, 306, 307, 316, and 318, example control coils 304 and 320, example connectors 308, 312, and 317, an example fan pitch actuation system (FPAS) 310, an example pressure reducing valve 314, and an example reservoir 322.

[0035] Figure 3 The accumulator 301 is a hydraulic energy storage container for storing fluid. The accumulator 301 functions as a pressure vessel to allow fluid (e.g., via valves 302, 306 (when open) and connector 308) to flow into (e.g., be pumped into) the FPAS 310, causing the blades 106 to change pitch. The fluid can be water-based, oil-based, silicon-based, synthetic hydrocarbon-based, and / or any other type of hydraulic fluid.

[0036] Figure 3Valve 302 is a valve that controls the flow of hydraulic fluid from accumulator 301 to FPAS 310. Valve 302 includes an input 351 (e.g., connection, input connection, inlet, inlet connection, etc.) and an output 352. Input 351 (e.g., via a pipe, hose, tube, etc.) is connected to output 350 of accumulator 301 (e.g., connection, output connection, outlet, outlet connection, etc.), and output 352 (e.g., via a pipe, hose, tube, etc.) is connected to input 354 of valve 306. When valve 302 is closed, fluid will not be released from accumulator 301. However, when valve 302 is open, fluid will flow from accumulator 301 to valve 306 via valve 302. In some examples, valve 302 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 302 may control the force of fluid flow based on the position of valve 302 (e.g., the degree of partial opening of valve 302). The wider the valve is opened, the stronger the force of the fluid flow, which corresponds to the vane 106 adjusting to a position (e.g., the feathering position) more quickly.

[0037] Valve 302 can be via Figure 3 The control coil 304 is used for control. The control coil 304 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1 The FADEC 180. When an electrical signal passes through the control coil 304, the control coil 304 generates a magnetic field that can open or close the valve 302. Therefore, the FADEC 180 can control the valve 302 by sending a signal to the control coil 304. For example, in response to a trigger event, the FADEC 180 outputs a first signal (e.g., a low voltage, a high voltage, or a pulse width modulation (PWM) voltage, depending on the characteristics of the valve 302) to open the valve 302 (e.g., partially or fully open). If there is no trigger event, the FADEC 180 can output a second signal different from the first signal (e.g., opposite to the first signal) to close the valve 302.

[0038] Figure 3 Valve 306 is configured to control the flow rate and / or pressure of the liquid from accumulator 301. Figure 1 The speed at which the blade 106 adjusts the pitch. For example, valve 306 may be a flow restrictor valve configured to regulate flow rate and / or pressure to one or more preset values. Valve 306 has an input 354 (e.g., connection, input connection, inlet, inlet connection, etc.) connected to an output 352 of valve 302 via a pipe, hose, tube, etc., and an output 356 (e.g., connection, output connection, outlet, outlet connection, etc.) connected to a first input 358 of connector 308. One or more preset values ​​may be based on user / manufacturer preferences and / or may be based on the characteristics of the flight and / or turboprop engine 100.

[0039] Figure 3 The featherer valve 307 is a valve that controls the pitch of the blades 106 based on commands from the pilot or autopilot system. The featherer valve 307 can output fluid at a specific rate and / or pressure to allow the FPAS 310 to regulate. Figure 1 The pitch of blade 106. In the event of errors, accidents, malfunctions, etc., the feathering valve 307 may not work or become uncontrollable. Therefore, valves 302, 306, 316, and 318 can be controlled to automatically and / or passively adjust the pitch of blade 106 to mitigate emergencies, as further described below.

[0040] Figure 3 Connector 308 provides a connection from accumulator 301 and / or featherer valve 307 to FPAS 310. Connector 308 includes a first input 358 (e.g., via a pipe, hose, tube, etc.) connected to output 356 of valve 306, a second input 362 (e.g., via a pipe, hose, tube, etc.) connected to output 361 of featherer valve 307, and an output 360 connected to input 364 of FPAS 310. Connector 308 allows fluid from accumulator 301 and / or featherer valve 307 to flow into FPAS 310. As described above, during normal operation, featherer valve 307 can be... Figure 1 The FADEC 180 controls the pitch of the blade 106 (e.g., based on pilot control or autopilot control). On the other hand, the accumulator 301 automatically and / or passively controls the pitch of the blade 106 in response to triggers (e.g., user requests after the FADEC identifies an error). Therefore, connector 308 connects the output 361 of feather valve 307 to the output of valve 306 to FPAS 310, such that either feather valve 307 or accumulator 301 can control FPAS 310.

[0041] Figure 3 The FPAS 310 is a hydraulically based system that converts hydraulic pressure into mechanical force based on the amount of hydraulic fluid pumped into the FPAS 310 to regulate... Figure 1The FPAS 310 has an input 364 (e.g., connection, input connection, inlet and inlet connection, etc.) connected to an output 360 of a connector 308 (e.g., via a pipe, hose, tube, etc.), a first output 366 (e.g., output connection, connection, outlet, outlet connection, etc.) connected to an input 370 of a connector 312 (e.g., via a pipe, hose, tube, etc.), and a second output 368 (e.g., connection, output connection, etc.) connected to an input 384 of a connector 317 (e.g., via a pipe, hose, tube, etc.). The FPAS 310 has a movable portion that adjusts (e.g., rotates) the pitch of the blades 106 in a first direction (e.g., from a lower angle, such as 30 degrees) toward a higher angle (e.g., 80-100 degrees) when fluid is pushed into the input 364 via the connector 308. As fluid exits from the first output 366 toward the input 370 of connector 312, FPAS 310 adjusts the pitch of blade 106 in a second direction (e.g., from a higher angle to a lower angle). Furthermore, FPAS 310 can be locked in one position based on fluid inflow into FPAS 310 and fluid outflow from the second output of FPAS 310 into connector 317. FPAS 310 is further described below with reference to Figures 7-9.

[0042] Figure 3 Connector 312 provides a connection from FPAS 310 to pressure reducing valve 314 and / or valve 316. Connector 312 includes an input 370 (e.g., via a pipe, hose, tube, etc.) connected to a first output 366 of FPAS 310, a first output 372 (e.g., via a pipe, hose, tube, etc.) connected to an input 376 of pressure reducing valve 314, and a second output 374 (e.g., via a pipe, hose, tube, etc.) connected to an input 380 of valve 316. Connector 312 allows fluid to flow from FPAS 310 to pressure reducing valve 314 and / or valve 316. As described above, FPAS 310 outputs fluid to move blade 106 from a first pitch to a second pitch.

[0043] Figure 3 The pressure reducing valve 314 maintains the fluid pressure from FPAS 310 below a threshold level (e.g., 2000-2500 psi). The pressure reducing valve 314 includes an input 376 (e.g., via a pipe, hose, tube, etc.) connected to an output 372 of connector 312 and an output 378 (e.g., via a pipe, hose, tube, etc.) connected to reservoir 322. The pressure reducing valve 314 reduces the pressure of the fluid to prevent pressure-induced damage when fluid is allowed to flow into reservoir 322.

[0044] Figure 3Valve 316 is configured to control the feathering speed by controlling the flow rate through connector 317. For example, valve 316 may be a flow restrictor valve configured to regulate the flow rate and / or pressure of fluid from connector 312 to one or more preset values. Valve 316 has an input 380 connected (e.g., via a pipe, hose, tube, etc.) to a second output 374 of connector 312 and an output 382 connected to a second input 388 of connector 317.

[0045] Figure 3 Connector 317 provides a connection from FPAS 310 and / or valve 316 to valve 318. Connector 317 includes a first input 384 (e.g., via a pipe, hose, tube, etc.) connected to a second output 368 of FPAS 310, a second input 388 (e.g., via a pipe, hose, tube, etc.) connected to an output 382 of valve 316, and an output 386 (e.g., via a pipe, hose, tube, etc.) connected to an input 390 of valve 318. Connector 317 allows fluid from FPAS 310 and / or valve 316 to flow to valve 318.

[0046] Figure 3 Valve 318 is a valve that controls the flow of hydraulic fluid from FPAS 310 into reservoir 322. Valve 318 includes an input 390 (e.g., via a pipe, hose, tube, etc.) connected to an output 386 of connector 317 and an output 392 (e.g., via a pipe, hose, tube, etc.) connected to reservoir 322. When valve 318 is closed, fluid will not be released from FPAS 310. However, when valve 318 is open, fluid from FPAS 310 will flow into reservoir 322. Reservoir 322 stores (e.g., via valve 318 and / or pressure reducing valve 314) the fluid flowing from FPAS 310. In some examples, valve 318 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 318 may control the force of fluid flow based on the position of valve 318 (e.g., based on the amount of opening of valve 318). The wider the valve is opened, the stronger the force of the fluid flow, which corresponds to the vane 106 adjusting to a position (e.g., the feathering position) more quickly.

[0047] Valve 318 can be via Figure 3 The control coil 320 is used for control. The control coil 320 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1The FADEC 180. When an electrical signal passes through the control coil 320, the control coil 320 generates a magnetic field that can open or close the valve 318. Therefore, the FADEC 180 can control the valve 318 by sending a signal to the control coil 320. For example, in response to a triggering event (e.g., pressure loss, power loss, fault, error, etc.), the FADEC 180 outputs a first signal (e.g., depending on the characteristics of the valve 318, low voltage, high voltage, or PWM voltage) to open the valve 318 (e.g., partially or fully open). If there is no triggering event, the FADEC 180 can output a second signal (e.g., opposite to the first signal) different from the first signal to close the valve 318.

[0048] Figure 4 It shows what can be used to implement Figure 1 An example of an automatic blade pitch control system 170 is a blade pitch controller 400. The blade pitch controller 400 includes... Figure 3 The example includes an accumulator 301, example valves 302 and 318, example control coils 304 and 320, example connectors 308 and 312, an example fan pitch actuation system (FPAS) 310, an example pressure reducing valve 314, and an example reservoir 322. The blade pitch controller 400 includes an example power system, and more specifically, an uninterruptible power supply (UPS) 402, an example valve 406, and an example control coil 408. Figure 4 Also includes Figure 1 FADEC 180.

[0049] exist Figure 4 In the example, Figure 3 Valve 316 was replaced by valve 406, the output of which is connected to reservoir 322 instead of... Figure 3 Connector 317. However, the output of valve 406 can be connected to connector (e.g., Figure 3 Connector 317) to allow fluid to flow into valve 318. Figure 4Valve 406 is a valve that controls the flow of hydraulic fluid from FPAS 310 (e.g., via connector 312) into reservoir 322. Valve 406 includes an input 450 (e.g., via a pipe, hose, tube, etc.) connected to a second output 374 of connector 312 and an output 452 (e.g., via a pipe, hose, tube, etc.) connected to reservoir 322. When valve 406 is closed, fluid from FPAS 310 will not flow through valve 406 to reservoir 322. However, when valve 406 is open, fluid from FPAS 310 will flow through valve 406 into reservoir 322. In some examples, valve 406 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 406 can control the force of fluid flow based on the position of valve 406 (e.g., the degree of partial opening of valve 406). The greater the valve is open, the stronger the force of fluid flow. The faster the fluid flows, the faster the blades 106 adjust to a position (e.g., a feathering position). For example, doubling the flow rate may cause the blades to move into position at twice the speed.

[0050] Valve 406 can be via Figure 3 The control coil 408 is used for control. The control coil 408 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1 The FADEC 180. When an electrical signal passes through the control coil 408, the control coil 408 generates a magnetic field that can open or close the valve 406. Therefore, the FADEC 180 can control the valve 406 by sending a signal to the control coil 408. For example, in response to a triggering event (e.g., indication of pressure loss, power loss, fault, error, etc.), the FADEC 180 outputs a first signal (e.g., depending on the characteristics of the valve 406, low voltage, high voltage, or PWM voltage) to open the valve 406 (e.g., partially or fully open). If there is no triggering event, the FADEC 180 can output a second signal different from the first signal (e.g., opposite to the first signal) to close the valve 406.

[0051] Figure 4 It also includes a UPS 402 to power the FADEC 180 regardless of power failure. The UPS 402 can operate as a backup power source. Therefore, in response to a power failure, the FADEC 180 can still send signals to valves 302, 318, and 406 to control the FPAS 310 to change the pitch of blade 106. As described above, the FADEC 180 can output control signals (e.g., one or more PWM signals) to example control coils 304, 320, and 408 to control valves 302, 318, and 406, thereby controlling the rate at which the pitch of blade 106 changes (e.g., to feathering pitch).

[0052] Figure 5 It shows what can be used to implement Figure 1 An example blade pitch controller 500 is provided for the automatic blade pitch control system 170. The blade pitch controller 500 includes... Figure 3 The example includes accumulator 301, example valves 302 and 318, example control coils 304 and 320, example connectors 308 and 312, example fan pitch actuation system (FPAS) 310, example pressure reducing valve 314, and example reservoir 322. The blade pitch controller 500 also includes an example power system, more specifically... Figure 4 The uninterruptible power supply (UPS) 402, the example valve 406, and the example control coil 408. Figure 5 Also includes Figure 1 FADEC 180. Figure 5 The blade pitch controller 500 also includes example hydraulic sources 502 and 508, example valves 504 and 510, and example control coils 506 and 512.

[0053] Figure 5 A hydraulic source 502 supplies hydraulic fluid used within the turboprop engine 100. The hydraulic source 502 includes an input 550 connected (e.g., via pipes, tubes, hoses, etc.) to a reservoir 322 and an output 552 connected to an input 554 of a valve 504. When fluid is depleted or below a threshold, the hydraulic source 502 collects fluid already stored in the reservoir 322 and supplies fluid to components of the turboprop engine 100, including the accumulator 301. Therefore, when fluid is low, the FADEC 180 can control the valve 504 to refill the accumulator 301.

[0054] Figure 3 Valve 504 is a valve that controls the flow of hydraulic fluid from hydraulic source 502 into accumulator 301. Valve 504 includes an input 554 (e.g., via a pipe, hose, tube, etc.) connected to an output 552 of hydraulic source 502 and an output 556 (e.g., via a pipe, hose, tube, etc.) connected to accumulator 301. When valve 504 is closed, fluid from hydraulic source 502 will not flow to accumulator 301. However, when valve 504 is open, fluid from FPAS 310 will flow into accumulator 301. In some examples, valve 504 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 504 can control the force of fluid flow based on the position of valve 504 (e.g., the degree of partial opening of valve 504). The greater the valve is open, the stronger the force of fluid flow into accumulator 301.

[0055] Valve 504 can be via Figure 5 The control coil 506 is used for control. The control coil 506 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1The FADEC 180. When an electrical signal passes through the control coil 506, the control coil 506 generates a magnetic field that can open or close the valve 504. Therefore, the FADEC 180 can control the valve 504 by sending a signal to the control coil 506. For example, in response to a triggering event (e.g., the fluid volume in the accumulator 301 is below a threshold), the FADEC 180 outputs a first signal (e.g., depending on the characteristics of the valve 504, low voltage, high voltage, or PWM voltage) to open the valve 504 (e.g., partially or fully open). If there is no triggering event, the FADEC 180 can output a second signal different from the first signal (e.g., opposite to the first signal) to close the valve 504.

[0056] Accumulator 301 is initially charged via the hydraulic power unit of each engine and controlled by solenoid valves or even simple check valves. As described above, upon triggering events (e.g., in-flight shutdown (IFSD) and hydraulic power failure), accumulator 301 is released to... Figure 1 The blades 106 are positioned to different pitches (e.g., feathering pitch). After the fluid in accumulator 301 is depleted beyond a threshold amount, FADEC 180 can adjust valve 504 to restore fluid to accumulator 302 and / or add fluid to accumulator 302. However, in the event that turboprop engine 100 requires in-flight restart, hydraulic source 502 may not be available to restore fluid to accumulator 301. Therefore, in response to in-flight restart, the hydraulic power unit of a second engine (e.g., a second turboprop engine implemented in an aircraft for a second propeller with second blades) can be used to recharge accumulator 301.

[0057] Figure 5 Hydraulic source 508 is a hydraulic source from another engine of the aircraft. For example, the aircraft may have a first engine on the left wing and a second engine on the right wing. If the first engine is restarting, hydraulic source 508 of the second engine can be used to restore fluid in accumulator 301 of the first engine. Hydraulic source 508 includes an input 558 and an output 560. Input 558 may be connected (e.g., via a pipe, tube, hose, etc.) to the reservoir of the second engine, and output 560 is connected to input 562 of valve 510. When depleted or below a threshold and / or when hydraulic source 502 is unavailable, hydraulic source 508 collects fluid already stored in the reservoir of the second engine and supplies fluid to components of the first engine, including accumulator 301. Therefore, when the pressure in accumulator 301 is below a threshold amount, FADEC 180 can control valve 510 to refill accumulator 301.

[0058] Figure 5Valve 510 is a valve that controls the flow of hydraulic fluid from hydraulic source 508 into accumulator 301. Valve 510 includes an input 562 and an output 564. Input 562 (e.g., via a pipe, hose, tube, etc.) is connected to output 560 of hydraulic source 508, and output 564 (e.g., via a pipe, hose, tube, etc.) is connected to accumulator 301. When valve 510 is closed, fluid from hydraulic source 508 will not flow to accumulator 301. However, when valve 510 is open, fluid from FPAS 310 will flow into accumulator 301. In some examples, valve 510 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 510 may control the force of fluid flow based on the position of valve 510 (e.g., the degree of partial opening of valve 510). The greater the valve is open, the stronger the force of fluid flow into accumulator 301.

[0059] Valve 510 can be via Figure 3 The control coil 512 is used for control. The control coil 512 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1 The FADEC 180. When an electrical signal passes through the control coil 512, the control coil 512 generates a magnetic field that can open or close the valve 510. Therefore, the FADEC 180 can control the valve 510 by sending a signal to the control coil 512. For example, in response to a triggering event (e.g., fluid in the accumulator 301 falling below a threshold and / or in-flight shutdown of the turboprop engine 100), the FADEC 180 outputs a first signal (e.g., low voltage, high voltage, or PWM voltage, depending on the characteristics of the valve 510) to open the valve 510 (e.g., partially or fully open). If there is no triggering event, the FADEC 180 can output a second signal different from the first signal (e.g., opposite to the first signal) to close the valve 510.

[0060] Figure 6 It shows what can be used to implement Figure 1 An example of an automatic blade pitch control system 170 is a blade pitch controller 600. The blade pitch controller 600 includes... Figure 3 The example includes valve 318, control coil 320, connectors 308 and 312, fan pitch actuation system (FPAS) 310, pressure reducing valve 314, and reservoir 322. The blade pitch controller 600 also includes... Figure 4 Example valve 406 and example control coil 408. Figure 6 The blade pitch controller 600 also includes an example pneumatic tank 602, an example pneumatic-hydraulic converter 604, an example valve 606, and an example control coil 608.

[0061] Figure 6The pneumatic tank 602 (also known as a pneumatic accumulator) is a high-pressure tank that supplies gas to the pneumatic-hydraulic converter 604 when the valve 606 is open. The pneumatic tank 602 includes (e.g., via pipes, hoses, tubes, etc.) an outlet 650 (e.g., output, connection, output connection, outlet connection, etc.) connected to an inlet 652 (e.g., input, connection, input connection, inlet connection, etc.) of the valve 606. Although Figure 6 The pneumatic cylinder 602 stores nitrogen, but the pneumatic cylinder 602 can store different types of gases.

[0062] Figure 6 The pneumatic-hydraulic converter 604 includes a first portion 605 that can be filled with gas from a pneumatic tank 602 and a second portion 607 that is filled with hydraulic fluid. The pneumatic-hydraulic converter 604 includes an input 656 connected (e.g., via a pipe, hose, tube, etc.) to an output 654 of a valve 606 and an output 658 connected to a first input 358 of a connector 308. The pneumatic tank 602, containing high-pressure gas, powers the pneumatic-hydraulic converter 604 (including a double-acting cylinder) and applies force to the second portion 607 (e.g., a chamber containing hydraulic fluid) to allow the hydraulic fluid to flow into the FPAS 310 via the connector 308. When the valve 606 is open, the volume of the hydraulic source in the pneumatic-hydraulic converter 604 is able to fill the volume of the chamber in the FPAS 310 to adjust the pitch of the blades 106.

[0063] Figure 6 Valve 606 is a valve that controls the flow of pneumatic gas from pneumatic tank 602 to pneumatic-hydraulic converter 604. Valve 606 includes an inlet 652 and an outlet 654. The inlet 652 (e.g., via a pipe, hose, tube, etc.) is connected to the outlet 650 of pneumatic tank 602, and the outlet 654 (e.g., via a pipe, hose, tube, etc.) is connected to the input 656 of pneumatic-hydraulic converter 604. When valve 606 is closed, gas is not released from pneumatic tank 602. However, when valve 606 is open, gas from pneumatic tank 602 flows into pneumatic-hydraulic converter 604 via valve 606. In some examples, valve 606 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 606 can control the force of gas flow based on the position of valve 606 (e.g., the degree of partial opening of valve 606). The greater the valve is open, the stronger the force of gas flow, which corresponds to a rapid release of hydraulic fluid into FPAS 310. The faster the hydraulic fluid flows into the FPAS 310, the faster the blades 106 adjust to a position (e.g., feathering position).

[0064] Valve 606 can be via Figure 6 The control coil 608 is used for control. The control coil 608 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1The FADEC 180. When an electrical signal passes through the control coil 608, the control coil 608 generates a magnetic field that can open or close the valve 606. Therefore, the FADEC 180 can control the valve 606 by sending a signal to the control coil 608. For example, in response to a triggering event (e.g., pressure loss, power loss, fault, error, etc.), the FADEC 180 outputs a first signal (e.g., depending on the characteristics of the valve 606, low voltage, high voltage, or PWM voltage) to open the valve 606 (e.g., partially or fully open). If there is no triggering event, the FADEC 180 can output a second signal (e.g., opposite to the first signal) different from the first signal to close the valve 606.

[0065] Figure 7A and 7B It shows Figure 2-6 A cross-sectional view of an example implementation of the FPAS 310 in two positions. Figure 7A The FPAS 310 of 7B includes an example housing 700, an example housing support 702, an example inner shaft 704, an example plug 706, a first example chamber 708, a second example chamber 710, an example pitch locking line 712, an example mechanical pitch locking element 714, an example oil supply bearing assembly 718, an example connector 720, an example spherical bearing 722, an example crankshaft 724, an example arm housing 725 and an example arm 726, and an example pneumatic chamber 727. Figure 7A and 7B It also shows Figure 1 A portion of leaf 106.

[0066] Figure 7A The housing 700 houses the internal components of the FPAS 310. In the example of Figure 7, the housing 700 is cylindrical. However, the housing 700 can correspond to different shapes. The housing 700 is supported by a housing support 702. The inner shaft 704 is a movable shaft that moves from a first position to a second position based on the amount and / or force of fluid and / or gas in the chambers 708 and / or 710. Figure 7A The inner shaft 704 of 7B is hollow. Therefore, the inner shaft 704 includes a plug to prevent fluid from entering the interior of the inner shaft 704. However, the inner shaft 704 may not be hollow.

[0067] Figure 7A The first example chamber 708 can accommodate from Figure 3-5 accumulator 301 and / or Figure 7AThe fluid is obtained (e.g., received) by the pneumatic-hydraulic converter 604 of 7B (e.g., via connector 308). When the fluid is pushed through connector 720, chamber 708 fills, which moves (e.g., pushes) inner shaft 704 outward away from connector 720. As further described below, when inner shaft 704 is pushed outward, blade 106 adjusts the pitch towards feathering. A second example chamber 710 is used when fluid is released to return... Figure 3-6 The reservoir 322 holds fluid. When the fluid is released, the inner shaft 704 can move inward toward the connector 720 if not locked. The closer the inner shaft 704 is to the connector 720, the smaller the pitch angle (e.g., the finer the pitch).

[0068] Figure 7A The pitch locking line 712 contains fluid for locking the position of the inner shaft 704, regardless of the force and / or amount of fluid in the chambers 708, 710. The fluid in the pitch locking line 712 can lock the inner shaft 704 using a mechanical pitch locking element 714, which is controlled by the amount and / or force of the fluid in the pitch locking line 712.

[0069] The oil supply bearing assembly 718 includes a rotary bearing and several flow paths, allowing Figure 2-6 The FPAS 310 rotates and operates under supplied hydraulic pressure. The oil supply bearing assembly 718 is a compartment / shaft with bearings and internal cavities for hydraulic input and output.

[0070] Figure 7A A spherical bearing 722 is attached to the inner shaft 704 via one or more connectors. As the inner shaft 704 moves, the spherical bearing 722 rotates. For example, when the inner shaft 704 moves away from the connector 720, the spherical bearing 722 rotates in a first direction, and when the inner shaft 704 moves towards the connector 720, the spherical bearing 722 rotates in a second direction. The spherical bearing 722 is also connected to a crankshaft 724. The crankshaft 724 twists as the spherical bearing 722 rotates. The crankshaft 724 is connected to one of the blades 106. The spherical bearing 722 and the crankshaft 724 convert the linear motion of the inner shaft 704 into the rotational motion of the blade 106. For example, when the inner shaft 704 moves outward, the spherical bearing 722 and the crankshaft 724 cause the blade 106 to rotate toward the pitch line. When the inner shaft 704 moves inward, the spherical bearing 722 and the crankshaft 724 cause the blade 106 to rotate toward a low-angle pitch (e.g., a fine pitch). The FPAS 310 features a spherical bearing 722 for each blade 106 and a crankshaft 724.

[0071] FPAS 310 also includes an optional pneumatic chamber 727. A pneumatic chamber 727 may be included to use gas to provide additional pressure and / or force to adjust the inner shaft 704. The pneumatic chamber 727 may contain gas that can be used to push the inner shaft 704 outward. The pneumatic chamber 727 may be used as a supplement to and / or replacement of chamber 708. For example, the pneumatic chamber 727 may be used in conjunction with chamber 708 to push the inner shaft 704 out more quickly using both pneumatic and hydraulic pressure. In another example, the pneumatic chamber 727 may be used when a failure associated with the hydraulic system is present. (The following is in conjunction with...) Figure 9 The control of the gas entering the pneumatic chamber 727 is further described.

[0072] Figure 7A The FPAS 310 is shown in the first feathering pitch position. Figure 7B The FPAS 310 is shown in the second fine pitch position.

[0073] exist Figure 7A In the first position, the inner shaft 704 is positioned outward, away from the connector 720. The arm housing 725 is connected to the inner shaft 704 and the arm 726. Therefore, when the inner shaft 704 is pushed outward, the arm housing 725 moves outward (e.g., pulls) the arm 726. The arm 726 is connected to the crankshaft 724. Therefore, when the arm 726 is pushed outward, the crankshaft 724 rotates the blade 106 into a feather pitch.

[0074] exist Figure 7B In the second position, the inner shaft 704 faces inward toward the connector 720. The arm housing 725 is connected to the inner shaft 704 and the arm 726. Therefore, when the inner shaft 704 is pushed inward, the arm housing 725 moves inward (e.g., pushes) the arm 726. The arm 726 is connected to the crankshaft 724. Therefore, when the arm 726 is pushed inward, the crankshaft 724 rotates the blade 106 to a fine pitch.

[0075] Figure 8 It shows the use of Figure 2-7B The pneumatic control components of the FPAS 310. Figure 8 Includes the pneumatic chamber 727 shown in Figure 7. Figure 8 It also includes example pneumatic tank 802, example valve 804 and example control coil 806.

[0076] Figure 8 The pneumatic tank 802 (also known as a pneumatic accumulator) is a high-pressure tank that outputs gas to the pneumatic chamber 727 when the valve 804 is open. The pneumatic tank 802 includes an output 850 connected (e.g., via a pipe, hose, tube, etc.) to an input 852 of the valve 804. Although Figure 6 The pneumatic cylinder 602 stores nitrogen, but the pneumatic cylinder 802 can store different types of gases.

[0077] Figure 8 Valve 804 is a valve that controls the flow of pneumatic gas from canister 802 to pneumatic chamber 727. Valve 804 includes an input 852 and an output 854. Input 852 (e.g., via a pipe, hose, tube, etc.) is connected to output 850 of pneumatic canister 802, and output 854 (e.g., via a pipe, hose, tube, etc.) is connected to a second input 856 of pneumatic chamber 727. When valve 804 is closed, gas is not released from pneumatic canister 802. However, when valve 804 is open, gas from pneumatic canister 802 flows into pneumatic chamber 727 via valve 804. In some examples, valve 804 may be partially open (e.g., in a position between fully open and fully closed). In these examples, valve 804 may control the force of gas flow based on the position of valve 804 (e.g., the degree of partial opening of valve 804). The greater the opening of valve 804, the stronger the force of gas flow, which corresponds to the rapid release of pneumatic gas into FPAS 310. The faster the aerodynamic gas flows into the FPAS 310, the faster the blades 106 adjust to a position (e.g., feathering position).

[0078] Figure 8 Valve 804 can be via Figure 8 The control coil 806 is used for control. The control coil 806 is connected via an electrical connection (e.g., wire, trace, etc.) to... Figure 1 The FADEC 180. When an electrical signal passes through the control coil 806, the control coil 806 generates a magnetic field that can open or close the valve 804. Therefore, the FADEC 180 can control the valve 804 by sending a signal to the control coil 806. For example, in response to a trigger event, the FADEC 180 outputs a first signal (e.g., depending on the characteristics of the valve 804, a low voltage, a high voltage, or a PWM voltage) to open the valve 804 (e.g., partially or fully open). If there is no trigger event, the FADEC 180 can output a second signal different from the first signal (e.g., opposite to the first signal) to close the valve 804.

[0079] Although Figure 1 The implementation is shown in the figure. Figure 1 The example method of FADEC 180, but Figure 1 One or more elements, processes, and / or devices shown may be combined, divided, rearranged, omitted, eliminated, and / or implemented in any other way. Furthermore, Figure 1The example FADEC 180 can be implemented solely by hardware or through a combination of hardware and software and / or firmware. Therefore, for example, the example FADEC 180 can be implemented using programmable circuitry combined with machine-readable instructions (e.g., firmware or software), processor circuitry, analog circuitry, digital circuitry, logic circuitry, programmable processors, programmable microcontrollers, graphics processing units (GPUs), digital signal processors (DSPs), ASICs, programmable logic devices (PLDs), and / or field-programmable logic devices (FPLDs) (such as FPGAs). Furthermore, Figure 1 Example FADEC 180 may include, except Figure 1 One or more elements, processes, and / or devices other than those shown, or in place of them. Figure 1 One or more of the elements, processes and / or devices shown may be included, and / or may include more than one of any or all of the elements, processes and devices shown.

[0080] Figure 9 The diagram illustrates example machine-readable instructions and / or example operations, which can be executed by programmable circuitry to implement and / or instantiate example machine-readable instructions. Figure 1 The FADEC 180 example operations can be implemented and / or instantiated by programmable circuitry. Figure 1 The FADEC 180. Machine-readable instructions can be used by programmable circuits (e.g., in combination with the following). Figure 10 The programmable circuit 1012 shown in the example programmable circuit platform 1000 discussed herein executes one or more executable programs or portions of one or more executable programs, and / or may be one or more functions or portions of functions executed by the example programmable circuit (e.g., FPGA). In some examples, machine-readable instructions cause operations, tasks, etc., to be performed and / or executed in a real-world manner in an automated manner. As used herein, “automation” means without human intervention.

[0081] The program may be embodied in instructions (e.g., software and / or firmware) stored on one or more non-transitory computer-readable and / or machine-readable storage media, such as cache memory, magnetic storage devices or disks (e.g., floppy disks, hard disk drives (HDDs), etc.), optical storage devices or optical discs (e.g., Blu-ray discs, optical discs (CDs), digital versatile discs (DVDs), etc.), redundant arrays of independent disks (RAID), registers, ROM, solid-state drives (SSDs), SSD memory, non-volatile memory (e.g., electrically erasable programmable read-only memory (EEPROM), flash memory, etc.), volatile memory (e.g., any type of random access memory (RAM), etc.), and / or any other storage device or disk. Instructions on non-transitory computer-readable and / or machine-readable media may be programmed and / or executed by programmable circuitry located in one or more hardware devices, but the entire program and / or portions thereof may also be executed and / or instantiated and / or embodied in dedicated hardware by one or more hardware devices other than programmable circuitry. Machine-readable instructions may be distributed across multiple hardware devices and / or executed by two or more hardware devices (e.g., server and client hardware devices). For example, client hardware devices can be implemented by endpoint client hardware devices (e.g., hardware devices associated with human and / or machine users) or intermediate client hardware device gateways (e.g., radio access networks (RANs)) that facilitate communication between the server and the endpoint client hardware devices. Similarly, non-transitory computer-readable storage media can include one or more media. Furthermore, although references... Figure 9 The flowchart shown describes an example program, but many other methods of implementing the example FADEC 180 can also be used. For example, the execution order of the flowchart's boxes can be changed, and / or some of the described boxes can be changed, eliminated, or combined. Additionally or alternatively, any or all of the flowchart's boxes can be implemented by one or more hardware circuits (e.g., processor circuitry, discrete and / or integrated analog and / or digital circuitry, FPGAs, ASICs, comparators, operational amplifiers (op-amps), logic circuitry, etc.) configured to perform the corresponding operations without executing software or firmware. Programmable circuitry can be distributed across different network locations and / or located locally on one or more hardware devices (e.g., a single-core processor (e.g., a single-core CPU), a multi-core processor (e.g., a multi-core CPU, XPU, etc.)). For example, programmable circuitry can be a CPU and / or FPGA located in the same package (e.g., the same integrated circuit (IC) package or two or more separate housings), one or more processors in a single machine, multiple processors distributed across multiple servers in a server rack, multiple processors distributed across one or more server racks, etc., and / or any combination thereof.

[0082] The machine-readable instructions described herein may be stored in one or more of the following formats: compressed format, encrypted format, segmented format, compiled format, executable format, packaged format, etc. As described herein, machine-readable instructions may be stored as data (e.g., computer-readable data, machine-readable data, one or more bits (e.g., one or more computer-readable bits, one or more machine-readable bits, etc.), bit streams (e.g., computer-readable bit streams, machine-readable bit streams, etc.)) or data structures (e.g., as part of instructions, code, code representation, etc.) that can be used to create, manufacture, and / or produce machine-executable instructions. For example, machine-readable instructions may be segmented and stored on one or more storage devices, disks, and / or computing devices (e.g., servers) located in the same or different locations (e.g., in the cloud, on edge devices, etc.) within a network or network set. Machine-readable instructions may require installation, modification, adaptation, updating, combination, supplementation, configuration, decryption, decompression, unpacking, distribution, reallocation, compilation, etc., to make them directly readable, interpretable, and / or executable by computing devices and / or other machines. For example, machine-readable instructions may be stored in multiple parts that are individually compressed, encrypted, and / or stored on separate computing devices, wherein these parts, when decrypted, decompressed, and / or combined, form a set of computer-executable and / or machine-executable instructions that implement one or more functions and / or operations that can together form a program as described herein.

[0083] In another example, machine-readable instructions may be stored in a state readable by programmable circuitry, but require the addition of libraries (e.g., dynamic link libraries (DLLs)), software development kits (SDKs), application programming interfaces (APIs), etc., to execute the machine-readable instructions on a specific computing device or other device. In yet another example, the machine-readable instructions may need to be configured (e.g., stored settings, data input, recorded network addresses, etc.) before they can be executed in whole or in part. Therefore, machine-readable, computer-readable, and / or machine-readable media as used herein may include instructions and / or programs, regardless of their specific format or state.

[0084] The machine-readable instructions described in this article can be represented using any past, present, or future instruction set language, scripting language, programming language, etc. For example, machine-readable instructions can be represented using any of the following languages: C, C++, Java, C#, Perl, Python, JavaScript, Hypertext Markup Language (HTML), Structured Query Language (SQL), Swift, etc.

[0085] As mentioned above, Figure 9Example operations can be implemented using executable instructions (e.g., computer-readable and / or machine-readable instructions) stored on one or more non-transient computer-readable and / or machine-readable media. As used herein, the terms non-transient computer-readable media, non-transient computer-readable storage media, non-transient machine-readable media, and / or non-transient machine-readable storage media are explicitly defined to include any type of computer-readable storage device and / or storage disk, excluding propagation signals and transmission media. Examples of such non-transient computer-readable media, non-transient computer-readable storage media, non-transient machine-readable media, and / or non-transient machine-readable storage media include optical storage devices, magnetic storage devices, HDDs, flash memory, read-only memory (ROM), CDs, DVDs, caches, any type of RAM, registers, and / or any other storage device or storage disk, wherein information is stored for any duration (e.g., over an extended period of time, permanently, temporarily, temporarily buffered, and / or cached). As used herein, the terms "non-transient computer-readable storage device" and "non-transient machine-readable storage device" are defined as including any physical (mechanical, magnetic, and / or electrical) hardware designed to retain information for a period of time, but excluding propagation signals and transmission media. Examples of non-transient computer-readable storage devices and / or non-transient machine-readable storage devices include any type of random access memory, any type of read-only memory, solid-state memory, flash memory, optical disc, hard disk, disk drive, and / or redundant array of independent disks (RAID) system. As used herein, the term "device" refers to a physical structure, such as mechanical and / or electrical equipment, hardware, and / or circuitry, which may or may not be configured with computer-readable instructions, machine-readable instructions, etc., and / or may or may not be manufactured for executing computer-readable instructions, machine-readable instructions, etc.

[0086] Figure 9 This is a flowchart illustrating example machine-readable instructions and / or example operations 900, which can be made, instantiated, and / or executed by programmable circuitry to control... Figure 1 and Figure 3-6 Automatic blade pitch control system 170. Figure 9 The example machine-readable instructions and / or example operation 900 begin at box 902, where FADEC 180 determines whether to trigger automatic control of the pitch of blade 106. For example, FADEC 180 may be triggered in the event of an error, malfunction, etc. FADEC 180 may trigger automatic control of the pitch of blade 106 based on an identified problem, where increasing the angle of blade 106 would be helpful and / or save lives. The event that causes FADEC 180 to automatically trigger blade pitch control may be based on pilot and / or manufacturer preferences.

[0087] If FADEC 180 determines that it is unnecessary to trigger automatic blade pitch control (box 902: No), the instruction ends. If FADEC 180 determines that it is necessary to trigger automatic blade pitch control (box 902: Yes), FADEC 180 will determine flight / engine information and / or user / manufacturer preferences for blade pitch control (box 904). For example, FADEC 180 may determine whether the aircraft is ascending, leveling, or descending, information from sensors in the aircraft, information related to engine control, etc. Furthermore, the user and / or manufacturer may define preferences on how to adjust the pitch of blade 160 in response to triggering. At box 906, FADEC 180 determines the blade pitch angle and / or feathering speed based on flight information, engine information, user / manufacturer preferences, and / or trigger type (e.g., the detection event that caused the trigger).

[0088] At frame 908, FADEC 180 outputs one or more control signals to one or more of the control coils 304, 320, 408, 608, and 806 of valves 302, 318, 406, 606, and 804 to change the pitch of blade 106 based on a determined blade pitch angle and / or feathering speed. For example, FADEC 180 can output a high voltage to one or more of the control coils 304, 320, 408, 608, and 806 of valves 302, 318, 406, 606, and 804 to rapidly adjust the pitch of blade 106. However, FADEC 180 can output PWM signals to one or more of the control coils 304, 320, 408, 608, and 806 of valves 302, 318, 406, 606, and 804 respectively to adjust the pitch of blade 106 at a specific speed (e.g., based on user / manufacturer preferences and / or flight / engine characteristics).

[0089] At box 910, FADEC 180 determines whether engine 100 is experiencing an in-flight shutdown. (As mentioned above...) Figure 5 If engine 100 is experiencing an in-flight shutdown, hydraulic source 502 may be unable to refuel accumulator 301. If FADEC 180 determines that engine 100 is not experiencing an in-flight shutdown (box 910: No), FADEC 180 outputs a control signal to control coil 506 to open valve 504, thereby restoring hydraulic fluid in accumulator 301 by providing a path from hydraulic source 502 to accumulator 301 (box 912). If FADEC 180 determines that engine 90 is experiencing an in-flight shutdown (box 910: Yes), FADEC 180 outputs a control signal to control coil 512 to open valve 510, thereby restoring hydraulic fluid in accumulator 301 by providing a path from hydraulic source 508 of the second engine to accumulator 301 (box 914).

[0090] Figure 10 This is a block diagram of an example programmable circuit platform 1000, which is configured to perform and / or instantiate... Figure 9 Example machine-readable instructions and / or example operations to implement Figure 1 The FADEC 180. The programmable circuit platform 1000 can be, for example, a server, computer, controller, self-learning machine (e.g., neural network), or any other type of computing and / or electronic device.

[0091] The programmable circuit platform 1000 illustrated includes a programmable circuit 1012. The programmable circuit 1012 illustrated is hardware. For example, the programmable circuit 1012 can be implemented by one or more integrated circuits, logic circuits, FPGAs, microprocessors, CPUs, GPUs, DSPs, and / or microcontrollers from any desired family or manufacturer. The programmable circuit 1012 can be implemented by one or more semiconductor-based (e.g., silicon-based) devices.

[0092] The programmable circuit 1012 shown in the example includes local memory 1013 (e.g., cache, registers, etc.). The programmable circuit 1012 shown in the example communicates via bus 1018 with main memory 1014, 1016, which includes volatile memory 1014 and non-volatile memory 1016. Volatile memory 1014 may be synchronous dynamic random access memory (SDRAM), dynamic random access memory (DRAM), etc. Dynamic Random Access Memory And / or any other type of RAM device. The non-volatile memory 1016 can be implemented using flash memory and / or any other desired type of memory device. Access to the main memory 1014, 1016 of the illustrated example is controlled by the memory controller 1017. In some examples, the memory controller 1017 can be implemented by one or more integrated circuits, logic circuits, microcontrollers from any desired series or manufacturer, or any other type of circuitry to manage the flow of data into and out of the main memory 1014, 1016.

[0093] The programmable circuit platform 1000 shown in the example also includes interface circuitry 1020. Interface circuitry 1020 can be implemented in hardware according to any type of interface standard, such as an Ethernet interface, a Universal Serial Bus (USB) interface, etc. Interfaces include Near Field Communication (NFC) interfaces, Peripheral Component Interconnect (PCI) interfaces, and / or Fast Peripheral Component Interconnect (PCIe) interfaces.

[0094] In the illustrated example, one or more input devices 1022 are connected to interface circuitry 1020. Input devices 1022 allow users (e.g., human users, machine users, etc.) to input data and / or commands into programmable circuitry 1012. Input devices 1022 can be implemented using, for example, audio sensors, microphones, cameras (still or video), keyboards, buttons, mice, touchscreens, touchpads, and / or voice recognition systems.

[0095] One or more output devices 1024 are also connected to the interface circuitry 1020 of the illustrated example. The output devices 1024 may be implemented, for example, via display devices (e.g., light-emitting diode (LED), organic light-emitting diode (OLED), liquid crystal display (LCD), cathode ray tube (CRT) display, in-place switching (IPS) display, touchscreen, etc.), haptic output devices, and / or speakers. Therefore, the interface circuitry 1020 of the illustrated example typically includes a graphics driver card, a graphics driver chip, and / or graphics processor circuitry, such as a GPU.

[0096] The interface circuit 1020 of the example shown also includes communication devices such as a transmitter, receiver, transceiver, modem, residential gateway, wireless access point, and / or network interface to facilitate the exchange of data with external machines (e.g., any type of computing device) via network 1026. Communication can be performed via, for example, Ethernet connections, digital subscriber line (DSL) connections, telephone line connections, coaxial cable systems, satellite systems, line-of-sight wireless systems, line-of-sight wireless systems, cellular telephone systems, optical connections, etc.

[0097] The programmable circuit platform 1000 illustrated also includes one or more mass storage disks or devices 1028 for storing firmware, software, and / or data. Examples of such mass storage disks or devices 1028 include magnetic storage devices (e.g., floppy disks, drives, HDDs, etc.), optical storage devices (e.g., Blu-ray discs, CDs, DVDs, etc.), RAID systems, and / or solid-state storage disks or devices such as flash memory devices and / or SSDs.

[0098] It can be by Figure 9 The machine-readable instructions 1032 implemented by the machine-readable instructions can be stored in a mass storage device 1028, a volatile memory 1014, a non-volatile memory 1016 and / or stored on at least one removable non-transient computer-readable storage medium (such as a CD or DVD).

[0099] As can be understood from the foregoing, example systems, apparatuses, articles, and methods for controlling the pitch of propeller blades have been disclosed. This document discloses an example blade pitch control system having a hydraulic and / or pneumatic system as fault protection for moving the blades to one or more positions (e.g., one or more feathering positions) to reduce drag in the event of a failure of the blade pitch control system and / or engine shutdown. Therefore, the examples disclosed herein improve the safety of the aircraft in such circumstances. Consequently, the disclosed systems, apparatuses, articles, and methods are correspondingly adapted to one or more improvements in the operation of machines such as computers or other electronic and / or mechanical equipment.

[0100] This document discloses example methods, apparatuses, systems, and articles of manufacture for controlling the pitch of propeller blades. Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0101] A turbine engine includes: a propeller including blades rotatable about a centerline axis to change the blade pitch; and a blade pitch control system including: a fan pitch actuation system coupled to the blades, the fan pitch actuation system being movable to rotate the blades from a first pitch angle to a second pitch angle based on the amount of hydraulic fluid pumped into the fan pitch actuation system; an accumulator storing the hydraulic fluid; and a valve coupled to an output of the accumulator and an input of the fan pitch actuation system, the valve automatically supplying the hydraulic fluid from the accumulator to the fan pitch actuation system based on a control signal.

[0102] The turbine engine according to the foregoing clause further includes a controller that outputs the control signal to a control coil, wherein the control signal applied to the control coil causes the valve to open.

[0103] The turbine engine according to any of the foregoing clauses, wherein the valve is a first valve, and wherein the turbine engine further comprises: a connector coupled to the output of the fan pitch actuation system; a pressure reducing valve coupled to the connector; a second valve coupled to the connector; and a reservoir coupled to the pressure reducing valve and the second valve.

[0104] The turbine engine according to any of the foregoing clauses, wherein the control signal is a first control signal, and wherein the turbine engine further includes a controller that outputs a second control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

[0105] The turbine engine according to any of the foregoing clauses further includes a reservoir that stores the hydraulic fluid output from the fan pitch actuation system.

[0106] The turbine engine according to any of the foregoing clauses, wherein the valve is a first valve, and wherein the turbine engine further comprises: a hydraulic source coupled to the reservoir, the hydraulic source receiving hydraulic fluid from the reservoir; and a second valve coupled to the hydraulic source and the accumulator, the second valve, when open, allowing the hydraulic fluid in the hydraulic source to flow into the accumulator.

[0107] The turbine engine according to any of the foregoing clauses further includes a controller that outputs the control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

[0108] The turbine engine according to any of the foregoing clauses, wherein the turbine engine is a first turbine engine and the valve is a first valve, and wherein the turbine engine further comprises: a second valve, the second valve being coupled to a hydraulic source included in the second turbine engine and the accumulator, the second valve, when open, allowing hydraulic fluid from the hydraulic source to flow into the accumulator.

[0109] According to any of the preceding clauses, the turbine engine, wherein the fan pitch actuation system comprises: an inner shaft; and a crankshaft coupled to the inner shaft and the blades, the crankshaft converting linear motion of the inner shaft into rotational motion of the blades; a first chamber receiving the hydraulic fluid that causes the inner shaft to move in a first direction; and a second chamber receiving pneumatic gas that causes the inner shaft to move in the first direction.

[0110] The turbine engine according to any of the foregoing clauses further includes a controller that automatically feathers the blades by sending a signal to a control coil to open the valve.

[0111] An apparatus comprising: a fan pitch actuation system coupled to a propeller blade, the fan pitch actuation system being movable in a first direction to rotate the blade from a first pitch angle to a second pitch angle based on an amount of hydraulic fluid pumped into the fan pitch actuation system; an accumulator storing the hydraulic fluid; a valve coupled to an output of the accumulator and an input of the fan pitch actuation system, the valve, when open, supplying the hydraulic fluid from the accumulator to the fan pitch actuation system based on a control signal; and a controller that: detects a trigger event; and outputs the control signal to open the valve based on at least one of user preference, flight characteristics, or engine characteristics, according to the detected trigger event.

[0112] According to the turbine engine described in the foregoing clause, the triggering event is at least one of a malfunction or an error.

[0113] The turbine engine according to any of the foregoing clauses, wherein the valve is a first valve, and wherein the device further comprises: a connector coupled to the output of the fan pitch actuation system; a pressure reducing valve coupled to the connector; a second valve coupled to the connector; and a reservoir coupled to the pressure reducing valve and the second valve.

[0114] The turbine engine according to any of the foregoing clauses, wherein the control signal is a first control signal, and wherein the device further includes a controller that outputs a second control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

[0115] The turbine engine according to any of the foregoing clauses further includes a reservoir that stores the hydraulic fluid output from the fan pitch actuation system.

[0116] The turbine engine according to any of the foregoing clauses, wherein the valve is a first valve, wherein the device further comprises: a hydraulic source connected to the reservoir, the hydraulic source receiving hydraulic fluid from the reservoir; and a second valve connected to the hydraulic source and the accumulator, the second valve, when open, allowing the hydraulic fluid in the hydraulic source to flow into the accumulator.

[0117] According to any of the preceding clauses, in a turbine engine, wherein the controller outputs the control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

[0118] The turbine engine according to any of the foregoing clauses, wherein the valve is a first valve, and the fan pitch actuation system, the accumulator and the first valve are included in the first engine, wherein the device further includes: a second valve, the second valve being coupled to a hydraulic source included in the second engine and the accumulator, the second valve, when open, allowing hydraulic fluid in the hydraulic source to flow into the accumulator.

[0119] An apparatus includes: an interface circuit that outputs a control signal to a valve to cause the blades of a propeller to automatically change from a first pitch angle to a second pitch angle; machine-readable instructions; and at least one programmable circuit that performs at least one of the following: executing the machine-readable instructions or instantiating the machine-readable instructions to at least: determine at least one of flight information, engine information, or pilot preferences; and generating the control signal based on at least one of the flight information, engine information, or pilot preferences based on a triggering event.

[0120] According to the turbine engine described in the preceding clause, wherein the valve is a first valve, the control signal is a first control signal, and the first valve and the blade are included in the first engine, the at least one programmable circuitry: determines whether an in-flight shutdown has occurred; and at least one of the following: based on the occurrence of the in-flight shutdown, outputs a second control signal to cause a second valve to restore hydraulic fluid from a first hydraulic source of the first engine to an accumulator; or based on the absence of the in-flight shutdown, outputs a third control signal to cause a third valve to restore hydraulic fluid from a second hydraulic source of the second engine to the accumulator of the first engine.

[0121] A method includes outputting a control signal to a valve to cause the propeller blades to automatically change from a first pitch angle to a second pitch angle; determining at least one of flight information, engine information, or pilot preferences; and generating the control signal based on at least one of the flight information, engine information, or pilot preferences, based on a triggering event.

[0122] According to the method described in the foregoing clause, wherein the valve is a first valve, the control signal is a first control signal, and the first valve and the blade are included in a first engine, the method further includes determining whether an in-flight shutdown has occurred.

[0123] The method according to any of the foregoing clauses further includes, based on the occurrence of the in-flight shutdown, outputting a second control signal to cause a second valve to restore hydraulic fluid from the hydraulic source of the first engine to the accumulator.

[0124] The method according to any of the foregoing clauses further includes, based on the absence of the in-flight shutdown, outputting a second control signal to cause a second valve to restore hydraulic fluid from the hydraulic source of the second engine to the accumulator of the first engine.

[0125] Although certain example methods, apparatuses, and articles of manufacture are disclosed herein, the scope of this patent is not limited thereto. Rather, this patent covers all methods, apparatuses, and articles of manufacture that fall fully within the scope of the claims of this patent.

Claims

1. A turbine engine, characterized in that, include: A propeller, the propeller including blades, the blades being rotatable about a central axis to change the pitch of the blades; and The blade pitch control system includes: A fan pitch actuation system, the fan pitch actuation system being coupled to the blade, the fan pitch actuation system being movable to rotate the blade from a first pitch angle to a second pitch angle based on the amount of hydraulic fluid pumped into the fan pitch actuation system; An accumulator that stores the hydraulic fluid; and A valve, connected to the output of the accumulator and the input of the fan pitch actuation system, automatically supplies hydraulic fluid from the accumulator to the fan pitch actuation system based on a control signal.

2. The turbine engine according to claim 1, characterized in that, The device further includes a controller that outputs a control signal to a control coil, wherein the control signal applied to the control coil causes the valve to open.

3. The turbine engine according to claim 1, characterized in that, The valve is a first valve, and the turbine engine further includes: A connector that is connected to the output of the fan pitch actuation system; A pressure reducing valve, which is connected to the connector; A second valve, which is connected to the connector; and A reservoir, which is connected to the pressure reducing valve and the second valve.

4. The turbine engine according to claim 3, characterized in that, The control signal is a first control signal, and the turbine engine further includes a controller that outputs a second control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

5. The turbine engine according to claim 1, characterized in that, It further includes a reservoir that stores the hydraulic fluid output from the fan pitch actuation system.

6. The turbine engine according to claim 5, characterized in that, The valve is a first valve, and the turbine engine further includes: A hydraulic power source, connected to the reservoir, receiving hydraulic fluid from the reservoir; and A second valve, connected to the hydraulic power source and the accumulator, allows hydraulic fluid from the hydraulic power source to flow into the accumulator when the second valve is open.

7. The turbine engine according to claim 6, characterized in that, The device further includes a controller that outputs a control signal to a control coil, wherein the control signal applied to the control coil causes the second valve to open.

8. The turbine engine according to claim 5, characterized in that, The turbine engine is a first turbine engine and the valve is a first valve, and the turbine engine further includes: A second valve is connected to a hydraulic source included in the second turbine engine and the accumulator. When the second valve is open, hydraulic fluid from the hydraulic source flows into the accumulator.

9. The turbine engine according to claim 1, characterized in that, The fan pitch actuation system includes: Inner shaft; and A crankshaft, which connects the inner shaft and the blades, converts the linear motion of the inner shaft into the rotational motion of the blades; A first chamber, the first chamber receiving the hydraulic fluid, the hydraulic fluid causing the inner shaft to move in a first direction; and A second chamber receives pneumatic gas, which causes the inner shaft to move in the first direction.

10. The turbine engine according to claim 1, characterized in that, It further includes a controller that automatically feathers the blades by sending a signal to a control coil to open the valve.

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