JP6478744B2 - Rotorcraft - Google Patents

Description

  The present invention relates to a rotary wing machine, and more particularly, to a rotary wing machine including a gas generator and an electric machine that can selectively function as an electric motor or a generator.

  2. Description of the Related Art A rotary wing machine including a gas generator and an electric machine that can selectively function as an electric motor or a generator is known.

  As a related technique, Patent Document 1 describes a helicopter turbine engine including a gas generator and a free turbine. The turbine engine described in U.S. Pat. No. 6,053,836 includes an electric motor / generator mechanically coupled to the shaft of the gas generator and a generator coupled to the shaft of the free turbine. An electric motor / generator mechanically coupled to the gas generator shaft assists in accelerating the turbine engine. An electric motor / generator mechanically coupled to the gas generator shaft extracts rotational kinetic energy from the gas generator shaft during deceleration of the turbine engine. An electric motor / generator mechanically coupled to the gas generator shaft assists in the deceleration of the turbine engine by extracting rotational kinetic energy. A generator coupled to the shaft of the free turbine supplies power to the electric motor / generator via the power storage unit.

  Patent Document 2 describes a turbine engine including a reversible electric machine. The turbine engine described in Patent Document 2 includes a gas generator, a shaft of the gas generator, a free turbine, a shaft of the free turbine, and a reversible electric machine (electric motor / generator). The shaft of the gas generator is connected to the reversible electric machine via the first stoppable coupling means. The reversible electric machine rotates the shaft of the gas generator when the turbine engine is started. That is, the reversible electric machine transmits rotational torque to the shaft of the gas generator. On the other hand, the rotational torque of the shaft of the gas generator is not transmitted to the reversible electric machine due to the presence of the first stoppable coupling means. The free turbine shaft is also connected to the reversible electric machine via the second stoppable coupling means. A reversible electric machine generates electric power by the rotation of a free turbine. The generated electric power is supplied to electric equipment mounted on the helicopter. On the other hand, the reversible electric machine cannot drive the free turbine due to the presence of the second stoppable coupling means.

Special table 2010-523879 Special table 2011-515619

  An object of the present invention is to provide a rotorcraft capable of applying a rotational torque to a main power transmission mechanism between a free turbine and a main rotor.

  These objects and other objects and benefits of the present invention can be easily confirmed by the following description and the accompanying drawings.

  Hereinafter, means for solving the problem will be described using the numbers and symbols used in the embodiments for carrying out the invention. These numbers and symbols are added with parentheses for reference in order to show an example of the correspondence between the description of the claims and the mode for carrying out the invention. Accordingly, the claims should not be construed as limiting due to the bracketed description.

  A rotorcraft according to some embodiments includes a gas generator (10) that generates combustion gas, a free turbine (20) that is driven by the combustion gas from the gas generator (10), and a main rotor (30), a main power transmission mechanism (40) that mechanically connects the free turbine (20) and the main rotor (30), and a first electric machine that selectively functions as an electric motor or a generator ( 50), the first power transmission mechanism (53) for mechanically connecting the main power transmission mechanism (40) and the first electric machine (50), and the operation of the first electric machine (50). And a control device (70). The controller (70) can execute an assist mode in which the first electric machine (50) applies a rotational torque to the main power transmission mechanism (40). In the assist mode, the first electric machine (50) functions as the electric motor.

  In the rotorcraft, the control device (70) automatically activates the assist mode in response to a state signal indicating the state of the rotorcraft or a state signal indicating the state of the gas generator (10). May be executed automatically.

  In the rotary wing machine, the control device (70) may execute the assist mode in response to an increase in a flow rate of fuel supplied to the gas generator (10).

  In the rotary wing machine, the control device (70) may execute the assist mode in response to an increase in pitch angle of the main rotor (30).

  In the rotary wing machine, the control device (70) may be capable of executing a braking mode in which the first electric machine (50) applies a braking force to the main power transmission mechanism (40). In the braking mode, the first electric machine (50) may function as the generator.

  In the rotary wing machine, the control device (70) may execute the braking mode in response to a decrease in the pitch angle of the main rotor.

  In the rotary wing machine, the control device (70) may be capable of executing a start mode for starting the gas generator. In the start mode, the main rotor may be in a rotation stopped state.

  In the rotorcraft, in the start mode, the first electric machine (50) may function as the electric motor.

  In the rotorcraft, the control device (70) may control the operation of the gas generator (10). The control device (70) may be capable of executing an air standby mode. In the air standby mode, the control device (70) stops the operation of the gas generator (10) or maintains the gas generator (10) in an idling state. May be controlled. In the air standby mode, the first electric machine (50) may function as the electric motor.

  In the rotorcraft, the control device (70) may execute the air standby mode in response to a failure of the gas generator (10).

  In the rotary wing machine, the control device (70) may be capable of executing a rotation speed maintaining mode for maintaining a rotation speed of the main rotor (30). In the rotation speed maintaining mode, the control device (70) responds to an increase in the rotation speed of the main rotor (30) so that the first electric machine (50) functions as the generator. One electric machine (50) may be controlled. In the rotation speed maintaining mode, the control device (70) responds to a decrease in the rotation speed of the main rotor (30) so that the first electric machine (50) functions as the electric motor. One electric machine (50) may be controlled.

  The rotorcraft may further include a tail side electric motor (180) and a tail rotor (170) driven by the tail side electric motor (180). The controller (70) may control the operation of the tail side electric motor (180). The controller (70) may control the operation of the tail-side electric motor (180) so that the tail rotor is maintained in a rotation stop state during execution of the start mode.

  In the rotary wing machine, the control device (70) may start the tail-side electric motor (180) when switching from the start mode to the assist mode.

  The rotary wing machine does not have to have a pitch angle changing mechanism of the tail rotor (170).

  In the rotorcraft, the second electric machine (55) that selectively functions as an electric motor or a generator, the main power transmission mechanism (40), and the second electric machine (55) are mechanically connected. A second power transmission mechanism (58) may be further provided. The main power transmission mechanism (40) includes a clutch (120), an upstream power transmission mechanism (44) disposed between the clutch (120) and the free turbine (20), and the clutch (120). And a downstream power transmission mechanism (46) disposed between the main rotor (30) and the main rotor (30). The first power transmission mechanism (53) may be mechanically connected to the downstream power transmission mechanism (46). The second power transmission mechanism (58) may be mechanically connected to the upstream power transmission mechanism (44). The controller (70) may control the operation of the second electric machine (55).

  A rotorcraft according to some embodiments includes a gas generator (10) that generates combustion gas, a free turbine (20) that is driven by the combustion gas from the gas generator (10), and a main rotor (30), a main power transmission mechanism (40) that mechanically connects the free turbine (20) and the main rotor (30), and a first electric machine that selectively functions as an electric motor or a generator ( 50), a first power transmission mechanism (53) mechanically connecting the main power transmission mechanism (40) and the first electric machine (50), and a first functioning selectively as an electric motor or a generator. And a second power transmission mechanism (58) for mechanically connecting the main power transmission mechanism (40) and the second electric machine (55). The main power transmission mechanism (40) includes a clutch (120), an upstream power transmission mechanism (44) disposed between the clutch (120) and the free turbine (20), and the clutch (120). And a downstream power transmission mechanism (46) disposed between the main rotor (30) and the main rotor (30). The first power transmission mechanism (53) is mechanically connected to the downstream power transmission mechanism (46), and the second power transmission mechanism (58) is mechanically connected to the upstream power transmission mechanism (44). Connected to.

  According to the present invention, it is possible to provide a rotary blade machine capable of applying a rotational torque to a main power transmission mechanism between a free turbine and a main rotor.

FIG. 1 is a schematic diagram showing a connection relationship between a gas generator and a main rotor. FIG. 2 is a schematic side view schematically illustrating a helicopter in some embodiments. FIG. 3 is a schematic side view schematically illustrating a helicopter in some embodiments. FIG. 4 is a functional block diagram schematically illustrating the configuration of a helicopter according to some embodiments. FIG. 5 is a table showing an example of a state realized by the start mode. FIG. 6 is a graph schematically showing the relationship between the fuel flow rate, the pressure in the combustion chamber, and the surge line. FIG. 7 is a table showing an example of a state realized by the assist mode or the braking mode. FIG. 8 is a table showing an example of a state realized by the air standby mode. FIG. 9 is a table showing an example of a state realized by the rotation speed maintenance mode. FIG. 10 is a functional block diagram schematically illustrating the configuration of a helicopter according to some embodiments. FIG. 11 is a table showing an example of a state realized by the start mode. FIG. 12 is a table showing an example of a state realized by the assist mode or the braking mode. FIG. 13 is a table showing an example of a state realized by the air standby mode. FIG. 14 is a table showing an example of a state realized by the rotation speed maintenance mode.

  Hereinafter, the rotorcraft in the embodiment will be described with reference to the accompanying drawings. In the following description, an example where the rotorcraft is a helicopter will be described. However, the rotary wing aircraft in the embodiment is not limited to a helicopter. The rotorcraft may be a VTOL aircraft (Vertical Take-Off and Landing Aircraft), a compound helicopter, a multicopter, or the like. In addition, the rotorcraft in the embodiment may be a manned aircraft or an unmanned aircraft.

(Definition of terms)
First, the “free turbine” will be described with reference to FIG. FIG. 1 is a schematic diagram showing a connection relationship between the gas generator 10 and the main rotor 30. The gas generator 10 includes a compressor 12, a shaft 13, a combustor 16, and a high pressure turbine 18. The compressor 12 sends compressed air to the combustor 16. The combustor 16 generates combustion gas by burning a mixed gas of compressed air and fuel. The high pressure turbine 18 is rotationally driven by the kinetic energy of the combustion gas. The rotational torque of the high pressure turbine 18 is transmitted to the compressor 12 through the shaft 13. The compressor 12 compresses air using the rotational force from the shaft 13.

  The free turbine 20 is rotationally driven by the kinetic energy of the combustion gas d that has passed through the high-pressure turbine 18. The rotation of the free turbine 20 is transmitted to the main rotor 30 via the main power transmission mechanism 40. The main power transmission mechanism 40 may include a transmission 90.

  In FIG. 1, reference numeral 19 schematically shows a combustion gas flow path toward the high-pressure turbine 18 or the free turbine 20.

  In the present specification, the “free turbine” means a turbine that is rotationally driven by the kinetic energy of the combustion gas and is not mechanically connected to the compressor 12. The form of the free turbine is not limited to the example shown in FIG. For example, the shaft 13 and the shaft of the free turbine 20 may be coaxial or may not be coaxial.

  In this specification, the “turbine” means a structure for extracting rotational power from the kinetic energy of combustion gas. “Turbine” includes, for example, turbine blades, turbine disks, and the like.

  In this specification, the “rotor” means a rotating body including a rotor blade (rotary blade). The “rotor pitch angle” means the pitch angle of the rotor blade (rotary blade). For example, if the pitch angle of the main rotor increases, the lift force by the main rotor increases.

  In the present specification, the “main rotor” means a rotor capable of generating the largest lift, thrust, or resultant force of lift and thrust among at least one rotor installed in the rotorcraft. Typically, the rotor that supports the gravity of the rotorcraft is the main rotor.

(Matters recognized by the inventor)
The matters recognized by the inventor will be described with reference to FIGS. 2 and 3 are schematic side views schematically showing the helicopter 1 in the embodiment.

  The helicopter 1 includes a fuselage 300, a main rotor 30, and landing gears 400 such as wheels. The helicopter 1 may include a tail rotor 170. The body 300 includes a gas turbine unit 100 including the gas generator 10 and the like, and a power transmission unit 200 including the main power transmission mechanism 40 and the like. The power transmission unit 200 may include a transmission mechanism that transmits power to the tail rotor 170.

  Assume that the helicopter 1 moves up or accelerates (forward acceleration). When the helicopter 1 rises or accelerates, the pitch angle of the main rotor 30 is relatively large. FIG. 2 shows a state in which the pitch angle of the main rotor 30 is a relatively large value (pitch angle = α1). In the state shown in FIG. 2, it is assumed that the helicopter 1 stops rising or stops acceleration. When stopping the helicopter 1 from rising or accelerating, the pitch angle of the main rotor 30 is relatively small. FIG. 3 shows a state in which the pitch angle of the main rotor 30 is a relatively small value (pitch angle = α2 <α1).

  When shifting from the state shown in FIG. 2 (a state where the pitch angle is large) to the state shown in FIG. 3 (a state where the pitch angle is small), the air resistance acting on the main rotor 30 is rapidly reduced. For this reason, the rotation speed of the main rotor 30 increases. And when the rotation speed of the main rotor 30 exceeds a predetermined value, the main rotor 30 may be damaged. Therefore, when the state shown in FIG. 2 (the state where the pitch angle is large) is shifted to the state shown in FIG. 3 (a state where the pitch angle is small), the pitch angle of the rotor cannot be reduced rapidly. Since the pitch angle of the rotor cannot be reduced rapidly, the performance (maneuverability, etc.) of the helicopter 1 is limited.

  Assume that the helicopter is a manned aircraft. The pilot operates to reduce the pitch angle of the rotor in order to stop the helicopter 1 from rising or accelerating. When the number of rotations of the main rotor 30 enters the danger zone (red zone) by decreasing the pitch angle of the rotor, the pilot operates to increase the pitch angle of the rotor. Since this operation is an operation that is contrary to the pilot's intention (intention to stop the ascent of the helicopter 1 or to stop the forward movement), it imposes a heavy burden on the pilot.

  Assume that the helicopter 1 rises or accelerates (forward acceleration) from a steady state. In this case, the helicopter 1 shifts from the state shown in FIG. 3 (the state where the pitch angle is small) to the state shown in FIG. 2 (a state where the pitch angle is large). When shifting from the state shown in FIG. 3 (the state where the pitch angle is small) to the state shown in FIG. 2 (a state where the pitch angle is large), the air resistance acting on the main rotor 30 increases abruptly. For this reason, the rotation speed of the main rotor 30 decreases. And if the rotation speed of the main rotor 30 becomes smaller than a predetermined value, the lift of the helicopter 1 may be insufficient. Therefore, when the state shown in FIG. 3 (the state where the pitch angle is small) is shifted to the state shown in FIG. 2 (a state where the pitch angle is large), the pitch angle of the rotor cannot be increased rapidly. Since the pitch angle of the rotor cannot be increased rapidly, the performance (maneuverability, etc.) of the helicopter 1 is limited.

  Assume that the helicopter is a manned aircraft. The pilot maneuvers to increase the pitch angle of the rotor in order to raise or accelerate the helicopter 1. When the rotational speed of the main rotor 30 enters an insufficient rotational speed region by increasing the rotor pitch angle, the pilot operates to decrease the rotor pitch angle. Since this operation is an operation contrary to the pilot's intention (intention to raise or accelerate the helicopter 1), a large burden of attention is given to the pilot.

  In the turbine engine described in Patent Document 1 (Japanese Patent Publication No. 2010-523879), a motor / generator that assists rotation (acceleration) of the shaft of the gas generator is provided. However, since the motor / generator is not a machine that directly assists the rotation of the shaft of the free turbine (that is, the rotation of the main rotor), the mechanism corresponding to the sudden decrease or increase of the pitch angle is a response. Sex is slow. Moreover, in the turbine engine described in Patent Document 1, a generator is provided on the shaft of the free turbine. However, since the generator does not have a function as a motor, it cannot assist the rotation of the shaft of the free turbine. For this reason, the said generator is not a mechanism corresponding to the above-mentioned rapid increase of the pitch angle.

  In the turbine engine described in Patent Document 2 (Japanese Patent Publication No. 2011-515619), a reversible electric machine (motor / generator) is connected to the shaft of the free turbine via a second stoppable coupling means. . However, the turbine engine cannot assist the rotation of the free turbine shaft because of the presence of the second stoppable coupling means. For this reason, the reversible electric machine is not a mechanism corresponding to the above-described rapid increase in the pitch angle.

(Outline of helicopter)
With reference to FIG. 4, the outline | summary of the helicopter in some embodiment is demonstrated. FIG. 4 is a functional block diagram schematically showing the configuration of the helicopter 1 in some embodiments.

  The helicopter 1 includes a gas generator 10, a free turbine 20, a main rotor 30, a main power transmission mechanism 40, a first electric machine 50, a first power transmission mechanism 53, and a control device 70.

  The helicopter 1 may include a battery 80, a transmission 90 that constitutes a part of the main power transmission mechanism, and the like. The main power transmission mechanism 40 may be provided with a clutch (not shown in FIG. 4; see FIG. 10 if necessary). When the main power transmission mechanism 40 is provided with a clutch, the clutch is provided between the transmission 90 (the mechanical connection between the main power transmission mechanism 40 and the first power transmission mechanism 53) and the free turbine 20. Preferably they are arranged.

(Gas generator 10)
The gas generator 10 includes a compressor 12, a shaft 13, a fuel tank 14, a combustor 16, and a high pressure turbine 18. The compressor 12 is a machine that compresses the supplied air a. The air outlet of the compressor 12 is fluidly connected to the air inlet of the combustor 16. The compressor 12 sends the compressed air b to the combustor 16. A fuel outlet of the fuel tank 14 is fluidly connected to a fuel inlet of the combustor 16 via a fuel control valve 15. The fuel tank 14 sends fuel (FUEL) to the combustor 16. In FIG. 4, the fuel tank 14 is described so as to be surrounded by the gas generator 10. However, FIG. 4 does not necessarily mean that the fuel tank 14 and, for example, the combustor 16 are provided in one chamber. The fuel tank 14 and the combustor 16 may be disposed in different chambers, respectively, and the fuel tank 14 and the combustor 16 may be connected by piping.

  The combustor 16 mixes the supplied fuel (FUEL) and the supplied compressed air. The combustor 16 generates combustion gas by burning the mixed gas. A combustion gas outlet of the combustor 16 is fluidly connected to a combustion gas inlet of a high-pressure turbine 18 (primary turbine). The combustor 16 sends the combustion gas c to the high-pressure turbine 18.

  The high-pressure turbine 18 is rotationally driven by the kinetic energy of the combustion gas c. The output shaft of the high pressure turbine 18 is mechanically connected to the input shaft of the compressor via the shaft 13. The rotational torque of the high pressure turbine 18 is transmitted to the compressor 12 through the shaft 13. The compressor 12 compresses the air a using the rotational torque received from the shaft 13. The combustion gas d that has passed through the high-pressure turbine 18 moves toward the free turbine 20.

  The configuration of the gas generator is not limited to the configuration of the gas generator 10 shown in FIG.

(Free turbine 20)
The free turbine 20 is rotationally driven by the kinetic energy of the combustion gas d that has passed through the high-pressure turbine 18. The combustion gas e that has passed through the free turbine 20 is discharged to the outside of the helicopter 1. The rotational torque of the free turbine 20 is transmitted to the main rotor 30 via the main power transmission mechanism 40.

(Main power transmission mechanism 40)
In the example illustrated in FIG. 4, the output shaft 22 of the free turbine 20 is mechanically connected to the input shaft 31 of the main rotor 30 via the main power transmission mechanism 40 including the transmission 90. The transmission 90 converts the rotation speed, rotation direction, and the like of the first input shaft 91 and transmits the converted signal to the output shaft 92.

  The transmission 90 may be capable of changing a mechanical connection relationship between the first input shaft 91, the output shaft 92, and a first power transmission mechanism 53 described later. For example, the transmission 90 may be capable of switching the mechanical connection state between the first input shaft 91 and the output shaft 92 to a mechanical non-connection state.

  Alternatively or additionally, the transmission 90 can switch the mechanical connection state between the first input shaft 91 and the first power transmission mechanism 53 to a mechanical non-connection state. Good. Alternatively or additionally, the transmission 90 may be capable of switching the mechanical connection state between the first power transmission mechanism 53 and the output shaft 92 to a mechanical non-connection state.

  Alternatively or additionally, the transmission 90 always places the first input shaft 91 and the output shaft 92 in a mechanically connected state, and always connects the first power transmission mechanism 53 and the output shaft 92 to the machine. May be maintained in a connected state.

  The operation of the transmission 90 (for example, the operation of changing the mechanical connection relationship between the first input shaft 91, the output shaft 92, and the first power transmission mechanism 53) may be controlled by the control device 70 (one point). It may be controlled via a signal line indicated by a chain line g).

  The free turbine 20 and the transmission 90 may be connected via a power transmission mechanism including a shaft, gears, and the like. The transmission 90 and the main rotor 30 may be connected via a power transmission mechanism including a shaft, gears, and the like.

(Main rotor 30)
The main rotor 30 is rotationally driven by rotational torque (driving force) transmitted through the main power transmission mechanism 40. The operation of the main rotor 30 (for example, the pitch angle of the main rotor) may be controlled by the control device 70 (may be controlled via a signal line indicated by a one-dot chain line h).

(First electric machine 50, first power transmission mechanism 53)
The first electric machine 50 has a function of an electric motor and a function of a generator. In other words, the first electric machine 50 is an electric motor having a function of a generator (or a generator having a function of an electric motor). The first electric machine 50 selectively functions as an electric motor or a generator based on a signal from the control device 70 (see a signal line indicated by a one-dot chain line i).

  When using the 1st electric machine 50 as an electric motor, the control apparatus 70 controls operation | movement of the 1st electric machine 50 so that electric power is supplied to the 1st electric machine 50, for example. When using the 1st electric machine 50 as a generator, the control apparatus 70 controls operation | movement of the 1st electric machine 50 so that supply of the electric power to the 1st electric machine 50 is interrupted | blocked, for example.

  The first electric machine 50 is mechanically connected to the main power transmission mechanism 40. In the example shown in FIG. 4, the output shaft 51 (the output shaft of the electric motor or the input shaft of the generator) of the first electric machine 50 is mechanically connected to the second input shaft 52 of the transmission 90. Yes. The first electric machine 50 and the main power transmission mechanism 40 may be connected via a power transmission mechanism including a shaft, gears, and the like.

  When the first electric machine 50 functions as an electric motor, the first electric machine 50 transmits rotational torque (power) to the main power transmission mechanism 40 via the first power transmission mechanism 53. In other words, when the first electric machine 50 functions as an electric motor, the first electric machine 50 assists the rotation of the main power transmission mechanism 40. As a result, the first electric machine 50 assists the rotation (acceleration) of the main rotor 30. When the first electric machine 50 assists the rotation of the main rotor 30, the first power transmission mechanism 53 and the main power transmission mechanism 40 need to be in a mechanically connected state.

  When the first electric machine 50 functions as a generator, the first electric machine 50 generates electric power by receiving rotational torque from the main power transmission mechanism 40 via the first power transmission mechanism 53. In other words, when the first electric machine 50 functions as a generator, the first electric machine 50 applies a braking force to the main power transmission mechanism 40 (main rotor 30). As a result, the first electric machine 50 assists the deceleration of the main power transmission mechanism 40 (main rotor 30). When the first electric machine 50 assists the deceleration of the main rotor 30, the first power transmission mechanism 53 and the main power transmission mechanism 40 need to be in a mechanically connected state.

(Battery 80)
The battery 80 is connected to the first electric machine 50 so as to be able to transmit power (see a power line indicated by a broken line j). When the first electric machine 50 functions as an electric motor, the battery 80 supplies electric power (drive power) to the first electric machine 50. When the first electric machine 50 functions as a generator, the battery 80 receives electric power (generated electric power) from the first electric machine 50. The battery 80 stores the received power. The battery 80 may be connected to the control device 70 through the power line k so as to be able to transmit power. When the battery 80 is connected to the control device 70, the battery 80 can supply power to the control device 70 or an electric device controlled by the control device 70.

(Control device 70)
The control device 70 includes, for example, an arithmetic device including a hardware processor, a storage device, and a communication interface. The control device 70 may be configured by a single computer and accessory devices, or may be configured by a plurality of computers and accessory devices.

  The control device 70 (hardware processor) controls the operation of the main rotor 30 by controlling the operation of the first electric machine 50 by executing a program stored in the storage device. The control device 70 may control the operation of the transmission 90 and the operation of the fuel supply mechanism (the fuel tank 14, the fuel control valve 15, etc.) by executing a program stored in the storage device. In the example illustrated in FIG. 4, the control device 70 controls the operation of the main rotor via the signal line h, controls the operation of the transmission 90 via the signal line g, and performs first electrical operation via the signal line i. The operation of the machine 50 is controlled, and the operation of the fuel supply mechanism (for example, the fuel supply flow rate) is controlled via the signal line m.

  The control device 70 executes a program stored in the storage device, so that a plurality of operation modes (a start mode, an assist mode, a transition mode, a braking mode, an air standby mode, a rotation speed maintaining mode, etc.) described later can be obtained. At least one may be executable.

(Start mode)
The start mode is a mode executed by the control device 70 before the helicopter 1 takes off.

  Before the helicopter 1 takes off, the gas turbine unit 100 (particularly, the gas generator 10) is preferably warmed up. In a general helicopter, when the gas turbine unit 100 is warmed up, power generated by the gas turbine unit 100 is transmitted to the main rotor 30. As a result, the main rotor 30 rotates.

  In the helicopter 1 in some embodiments, the main rotor 30 is in a rotation stopped state in the start mode. A rotation stop state is implement | achieved by making the free turbine 20 and the main rotor 30 into a mechanical non-connection state, for example. The mechanical disconnected state is realized, for example, by bringing the first input shaft 91 and the output shaft 92 of the transmission 90 into a disconnected state.

  In the start mode, the free turbine 20 and the first electric machine 50 are brought into a mechanical connection state. As a result, the rotational torque (power) from the free turbine 20 is transmitted to the first electric machine 50 that functions as a generator. The first electric machine 50 generates power with the transmitted rotational torque. The generated power is stored in the battery 80.

  FIG. 5 is a table showing an example of a state realized by the start mode. In the start mode, the main rotor 30 is in a rotation stopped state. The rotation stop state is not limited to a strict rotation stop state. For example, a state where the main rotor is moving due to wind or vibration is also included in the rotation stopped state.

  In the start mode, the control device 70 sends a control signal to the first electric machine 50 so that the first electric machine 50 functions as a generator. As a result, the first electric machine 50 functions as a generator. In the start mode, in order to reliably realize the stop of the main rotor 30, the mechanical connection relationship between the free turbine 20 and the main rotor 30 is preferably in a non-connected state. For this reason, the control device 70 sends a control signal to the main power transmission mechanism 40 (the transmission 90 of the main power transmission mechanism) so that the free turbine 20 and the main rotor 30 are not mechanically connected.

  In the start mode, the mechanical connection relationship between the free turbine 20 and the first electric machine 50 is preferably in a connected state. By setting the free turbine 20 and the first electric machine 50 in a connected state, the free turbine 20 does not run idle, and the kinetic energy of the free turbine can be recovered as electric energy. Therefore, the control device 70 sends a control signal to the main power transmission mechanism 40 (the transmission 90 of the main power transmission mechanism) so that the free turbine 20 and the first electric machine 50 are in a mechanical connection state.

  In the start mode, in order to reliably realize the stop of the main rotor 30, the mechanical connection relationship between the free turbine 20 and the main rotor 30 is preferably in a non-connected state. Therefore, the control device 70 sends a control signal to the main power transmission mechanism 40 (the transmission 90 of the main power transmission mechanism) so that the first electric machine 50 and the main rotor 30 are not mechanically connected.

  By maintaining the main rotor 30 in the stopped state in the start mode, the safety of the ground worker is improved during the warm-up operation of the gas turbine. In addition, noise during warm-up operation is reduced.

  The start mode may be started in response to the start of the gas turbine engine (gas generator 10) (may be executed in conjunction with the start). For example, when the control device 70 detects the start of the gas turbine engine, the control device 70 may automatically execute the start mode. Alternatively, the start mode may be executed by a pilot operation after the gas turbine engine is started.

(Assist mode)
The assist mode is a mode that is executed by the control device 70 before the helicopter 1 takes off or during the flight of the helicopter 1.

  First, the surge phenomenon will be described. The surge phenomenon is a phenomenon in which compressed air or the like flows backward toward the compressor when the pressure in the combustion chamber of the combustor 16 becomes higher than the pressure of the compressed air supplied from the compressor 12. FIG. 6 is a graph schematically showing the relationship between the air flow rate Q in the compressor, the pressure P in the combustion chamber, and the surge line.

  FIG. 6 shows the relationship between the air flow rate Q and the pressure P when the gas turbine engine is stopped (STOP (T1)), and the air flow rate Q and the pressure P when the gas turbine engine is idling (IDLE (T2)). The relationship is described. From the idling state (IDLE (T2)), it is assumed that the fuel flow rate is increased in order to accelerate the main rotor. When the fuel flow rate is suddenly increased (when the main rotor is accelerated rapidly), the pressure P in the combustion chamber may exceed a surge line (a line where a surge phenomenon occurs). For this reason, it is difficult for a general helicopter to accelerate the main rotor with a large acceleration.

  In the turbine engine described in Patent Literature 1 (Japanese Patent Publication No. 2010-523879) and the turbine engine described in Patent Literature 2 (Japanese Patent Publication No. 2011-515619), the turbine engine is mechanically coupled to the shaft of the gas generator. The electric motor / generator assists in the acceleration of the turbine engine. However, the turbine engine described in Patent Document 1 and the turbine engine described in Patent Document 2 directly assist the rotation of the shaft of the gas generator by an electric motor, and are free turbines (in other words, main rotors). ) Is not directly assisting rotation. For this reason, the acceleration response of the main rotor by the assist of the electric motor is slow.

  In the helicopter 1 in some embodiments, in the assist mode, the first electric machine 50 directly assists the rotation of the main power transmission mechanism 40 (in other words, the main rotor) between the free turbine 20 and the main rotor 30. To do. For this reason, the acceleration response of the main rotor 30 by the first electric machine 50 (electric motor) is fast.

  In the assist mode, the free turbine 20 and the main rotor 30 are mechanically connected, the first electric machine 50 and the main rotor 30 are mechanically connected, and the first electric machine 50 functions as an electric motor. It is realized by.

  The mechanical connection state between the free turbine 20 and the main rotor 30 in the assist mode is realized by, for example, connecting the first input shaft 91 and the output shaft 92 of the transmission 90 to each other. The mechanical connection state between the first electric machine 50 and the main rotor 30 in the assist mode is realized by, for example, bringing the first power transmission mechanism 53 and the main power transmission mechanism 40 into a mechanical connection state (more Specifically, it is realized by connecting the second input shaft 52 and the output shaft 92 of the transmission 90).

  FIG. 7 shows an example of a state realized by the assist mode. In the assist mode, the main rotor 30 is rotated by the rotational torque (power) from the free turbine 20 and the rotational torque (power) from the first electric machine 50.

  In the assist mode, the control device 70 sends a control signal to the first electric machine 50 so that the first electric machine 50 functions as an electric motor. As a result, the first electric machine 50 functions as an electric motor.

  In the helicopter 1 in some embodiments, in the assist mode, the first electric machine 50 directly assists the rotation of the main power transmission mechanism 40 between the free turbine 20 and the main rotor 30. For this reason, the responsiveness of applying the rotational torque to the main rotor 30 by the first electric machine 50 (electric motor) is fast. For example, it is assumed that the assist mode is executed when the state shown in FIG. 3 (main rotor pitch angle = α2) is shifted to the state shown in FIG. 2 (main rotor pitch angle = α1> α2). To do. In a general helicopter, the rotational speed of the main rotor 30 decreases as the pitch angle of the main rotor 30 increases rapidly. On the other hand, in the helicopter 1 in some embodiments, a decrease in the rotational speed of the main rotor 30 is quickly suppressed by executing the assist mode. For this reason, the risk that the rotation speed of the main rotor is insufficient is reduced.

  Assume that the helicopter 1 is a manned aircraft. In the helicopter 1 in some embodiments, a decrease in the rotational speed of the main rotor 30 is quickly suppressed by executing the assist mode. For this reason, the operation burden on the pilot is reduced.

  The assist mode is in response to a state signal (a signal indicating the state of the helicopter) such as a torque signal indicating a torque acting on the main rotor 30 or a torque angle acting on the main rotor 30 (for example, an increase in the pitch angle). It may be automatically executed. For example, the assist mode may be executed in response to (in conjunction with) an increase in the pitch angle of the main rotor 30. For example, when the control device 70 detects that the increase speed of the pitch angle of the main rotor exceeds a predetermined first threshold value, the control device 70 may automatically execute the assist mode. As an example, the assist mode may be automatically executed in accordance with a pitch angle of the main rotor 30 (for example, an increase in pitch angle) and a torque signal indicating torque acting on the main rotor 30. .

  Alternatively or additionally, the assist mode may be automatically executed in response to a signal indicating the state of the combustor 16. For example, the assist mode is automatically executed in response to the flow rate of fuel supplied to the combustor 16, the rotational speed of the high-pressure turbine 18, the rotational torque of the free turbine 20, the temperature of the combustion gas in the combustor 16, and the like. You may do it. It should be noted that the acquisition of the rotational torque for automatically executing the assist mode may be performed by measuring the rotational torque of the high-pressure turbine 18 instead of measuring the rotational torque of the free turbine 20. . Further, the assist mode may be executed in response to (in conjunction with) an increase in the fuel flow rate supplied to the combustor 16. For example, when the control device 70 detects that the increase rate of the throttle opening (or the increase rate of the fuel flow rate command value) exceeds a predetermined second threshold, the control device 70 automatically assists. A mode may be executed.

  Alternatively or additionally, the assist mode may be executed in response to (in conjunction with) the take-off operation of the helicopter 1. For example, when the control device 70 detects that a take-off operation by a throttle lever operation or the like has been performed in a state where the warm-up operation (start mode) is being executed, the control device 70 automatically enters the assist mode. May be executed.

(Transition from start mode to assist mode)
In the start mode, the main rotor 30 is in a stopped state. When the rotational torque is suddenly applied to the stopped main rotor 30, the main rotor 30 and the like may be damaged. For this reason, when shifting from the start mode to the assist mode, the control device 70 may execute the shift mode between the start mode and the assist mode. In the transition mode, the control device 70 controls the main power transmission mechanism 40 (more specifically, so that the mechanical connection between the free turbine 20 and the main rotor 30 is gradually performed (or smoothly performed). Specifically, a control signal is sent to the transmission 90) of the main power transmission mechanism. In other words, in the transition mode, the control device 70 causes the main power transmission mechanism 40 so that the mechanical connection relationship between the free turbine 20 and the main rotor 30 becomes a complete connection state via the semi-connection state. To send a control signal.

(Braking mode)
The braking mode is a mode that is executed by the control device 70 during the flight of the helicopter 1.

  In the helicopter 1 according to some embodiments, in the braking mode, the first electric machine 50 directly applies a braking force to the main power transmission mechanism 40 (in other words, the main rotor) between the free turbine 20 and the main rotor 30. Is granted. For this reason, the deceleration response of the main rotor 30 by the first electric machine 50 (generator) is fast.

  The braking mode is realized by bringing the first electric machine 50 and the main rotor 30 into a mechanical connection state and causing the first electric machine 50 to function as a generator. In the braking mode, the free turbine 20 and the main rotor 30 may be in a mechanically connected state or in a mechanically disconnected state.

  The mechanical connection state between the first electric machine 50 and the main rotor 30 in the braking mode is realized by, for example, bringing the first power transmission mechanism 53 and the main power transmission mechanism 40 into a mechanical connection state (more Specifically, it is realized by connecting the second input shaft 52 and the output shaft 92 of the transmission 90).

  FIG. 7 shows an example of a state realized by the braking mode. In the braking mode, the rotation kinetic energy of the main rotor 30 performs work for driving the first electric machine 50 (generator), whereby the rotation of the main rotor 30 is decelerated. The rotational kinetic energy of the main rotor 30 is converted into electric energy by the first electric machine 50 (generator), and the converted electric energy is stored in the battery 80. The electrical energy stored in the battery 80 is reused during the flight of the helicopter 1, for example.

  In the braking mode, the control device 70 sends a control signal to the first electric machine 50 so that the first electric machine 50 functions as a generator. As a result, the first electric machine 50 functions as a generator.

  In the helicopter 1 in some embodiments, in the braking mode, the first electric machine 50 directly assists the deceleration of the main rotor 30 (deceleration of the main power transmission mechanism 40 between the free turbine 20 and the main rotor 30). . For this reason, the response of braking of the main rotor 30 by the first electric machine 50 (generator) is fast. For example, it is assumed that the braking mode is executed when the state shown in FIG. 2 (the pitch angle of the main rotor = α1) shifts to the state shown in FIG. 3 (the pitch angle of the main rotor = α2 <α1). To do. In a general helicopter, the rotational speed of the main rotor 30 increases as the pitch angle of the main rotor 30 decreases rapidly. In contrast, in the helicopter 1 in some embodiments, an increase in the rotational speed of the main rotor 30 is quickly suppressed by executing the braking mode. For this reason, the risk that the main rotor rotates at a speed exceeding the design limit is reduced.

  Assume that the helicopter 1 is a manned aircraft. In the helicopter 1 in some embodiments, an increase in the rotational speed of the main rotor 30 is quickly suppressed by executing the braking mode. For this reason, the operation burden on the pilot is reduced.

  Assume that the helicopter 1 is a drone. In the helicopter 1 in some embodiments, an increase in the rotational speed of the main rotor 30 is quickly suppressed by executing the braking mode. For this reason, automatic control of the helicopter 1 becomes easier.

  The braking mode may be executed in response to (in conjunction with) a decrease in the pitch angle of the main rotor 30. For example, when the control device 70 detects that the absolute value of the decrease speed of the pitch angle of the main rotor is larger than a predetermined third threshold value, the control device 70 may automatically execute the braking mode. .

(Air standby mode)
The air standby mode is a mode executed by the control device 70 during the flight of the helicopter 1.

  The combustion gas generated by the gas generator 10 is a high-temperature combustion gas. When exhausting high-temperature combustion gas to the outside of the helicopter, the risk that the helicopter 1 is detected by the counterpart infrared detector increases.

  In the helicopter 1 in some embodiments, the emission of combustion gas is stopped or reduced in the air standby mode. As a result, the risk of the helicopter 1 being detected by the counterpart infrared detector is reduced.

(First example of air standby mode)
In the first example of the air standby mode, the control device 70 controls the operation of the gas generator 10 so that the operation of the gas turbine engine (gas generator 10) is stopped. For example, the control device 70 transmits a command (for example, a closing command for the fuel control valve 15) for reducing the fuel flow rate of the fuel sent to the combustor 16 to the gas generator 10, whereby the gas generator 10 It is possible to stop the operation.

  In the air standby mode in the first example, the operation of the gas generator 10 is stopped, the first electric machine 50 and the main rotor 30 are mechanically connected, and the first electric machine 50 functions as an electric motor. Is realized. In the air standby mode, the free turbine 20 and the main rotor 30 may be in a mechanically connected state or may be in a mechanically disconnected state.

  The mechanical connection state between the first electric machine 50 and the main rotor 30 in the air standby mode is realized, for example, by bringing the first power transmission mechanism 53 and the main power transmission mechanism 40 into a mechanical connection state ( More specifically, this is realized by connecting the second input shaft 52 and the output shaft 92 of the transmission 90).

  FIG. 8 (first example) shows an example of a state realized by the air standby mode. In the air standby mode in the first example, the main rotor 30 is rotated by rotational torque (power) from the first electric machine 50 (electric motor).

  In the air standby mode in the first example, the control device 70 sends a control signal to the first electric machine 50 so that the first electric machine 50 functions as an electric motor. As a result, the first electric machine 50 functions as an electric motor.

  In the air standby mode in the first example, the discharge of the combustion gas is stopped. For this reason, the risk that the helicopter 1 is detected by the counterpart infrared detection device is greatly reduced.

  Note that the air standby mode in the first example can be executed even when the gas generator 10 (gas turbine engine) is not in operation. Therefore, for example, in response to a failure of the gas generator 10 (gas turbine engine), in other words, in response to the failure of the gas generator 10 being detected by the control device 70 or the like, the air standby mode is set. It may be automatically executed. In this case, the pilot or helicopter automatic pilot device can make the helicopter 1 make an emergency landing using the air standby mode.

(Second example of air standby mode)
In the second example of the air standby mode, the control device 70 controls the operation of the gas generator 10 so that the gas turbine engine (gas generator 10) maintains the idling state. For example, the control device 70 controls the gas generator 10 (the fuel supply mechanism of the gas generator) so that the fuel having the fuel flow rate corresponding to the idling state is sent to the combustor 16. In the idling state, the flame in the combustion chamber of the combustor 16 is maintained so as not to disappear.

  In the air standby mode in the second example, the operation of the gas generator 10 is maintained in the idling state, the first electric machine 50 and the main rotor 30 are mechanically connected, and the first electric machine 50 is set to the electric motor. It is realized by functioning as In the air standby mode, the free turbine 20 and the main rotor 30 are preferably in a mechanically connected state.

  FIG. 8 (second example) shows an example of a state realized by the air standby mode. In the air standby mode in the second example, the main rotor 30 is mainly rotated by rotational torque (power) from the first electric machine 50 (electric motor). When the free turbine 20 and the main rotor 30 are in a mechanical connection state, the rotation of the main rotor 30 is assisted by the power from the free turbine 20.

  In the air standby mode, the control device 70 sends a control signal to the first electric machine 50 so that the first electric machine 50 functions as an electric motor. As a result, the first electric machine 50 functions as an electric motor.

  In the air standby mode in the second example, emission of combustion gas is suppressed. For this reason, the risk that the helicopter 1 is detected by the counterpart infrared detection device is reduced. Further, in the air standby mode in the second example, the gas generator 10 is maintained in an idling state. For this reason, it is possible to quickly increase the power of the gas turbine engine.

  Note that the air standby mode may be automatically executed when the helicopter is in a hovering state. For example, when the control device 70 detects that the position change rate of the location of the helicopter 1 is smaller than a predetermined fourth threshold, the control device 70 may automatically execute the air standby mode.

  Alternatively or additionally, the air standby mode may be executed in response to an operation by a pilot or a remote operation from outside the helicopter.

(Rotation speed maintenance mode)
The rotation speed maintaining mode is a mode executed by the control device 70 during the flight of the helicopter 1.

  When the rotation speed of the main rotor 30 is reduced, lift and the like may be insufficient. Moreover, when the rotation speed of the main rotor 30 increases, the main rotor may be damaged. For this reason, the pilot operates the helicopter in consideration of the rotational speed range in which the lift and the like are not insufficient and the main rotor is not damaged.

  In the helicopter 1 in the embodiment, the control device 70 executes the rotation speed maintenance mode, so that the pilot can maneuver the helicopter 1 without being aware of the range of the rotation speed of the main rotor. For this reason, the operation burden on the pilot is reduced.

  The rotation speed maintenance mode may be a mode for maintaining the current rotation speed. Alternatively, the rotation speed maintenance mode may be a mode that maintains a rotation speed that is equal to or higher than a predetermined fifth threshold value and equal to or lower than a predetermined sixth threshold value. The fifth threshold value or the sixth threshold value may be a variable that varies depending on the value of the pitch angle of the main rotor.

  In the rotation speed maintaining mode, the free turbine 20 and the main rotor 30 are in a mechanical connection state, the first electric machine 50 and the main rotor 30 are in a mechanical connection state, and the first electric machine 50 is in an electric motor or power generation. This is realized by selectively functioning as a machine.

  FIG. 9 shows an example of a state realized by the rotation speed maintenance mode. In the rotation speed maintenance mode, the main rotor 30 is rotated by the rotation torque (power) from the free turbine 20. Further, in the rotation speed maintenance mode, when the rotation speed of the main rotor increases, the first electric machine 50 functions to decelerate the rotation of the main rotor 30 (in other words, rotation of the main power transmission mechanism 40). In other words, the first electric machine 50 functions as a generator. On the other hand, when the rotational speed of the main rotor decreases in the rotational speed maintenance mode, the first electric machine 50 functions to assist the rotation of the main rotor 30 (in other words, the rotation of the main power transmission mechanism 40). In other words, the first electric machine 50 functions as an electric motor.

  In the rotation speed maintenance mode, the control device 70 responds to the increase in the rotation speed of the main rotor (in response to detection of the increase in the rotation speed) so that the first electric machine 50 functions as a generator. 1 Send a control signal to the electric machine 50. As a result, the first electric machine 50 functions as a generator. In the rotation speed maintaining mode, the control device 70 responds to the decrease in the rotation speed of the main rotor (in response to detection of the decrease in the rotation speed) so that the first electric machine 50 functions as an electric motor. 1 Send a control signal to the electric machine 50. As a result, the first electric machine 50 functions as an electric motor.

  The rotation speed maintenance mode may be executed in response to an operation by a pilot or a remote operation from the outside of the helicopter. Alternatively, the rotation speed maintenance mode may be executed as a default mode during the flight of the rotorcraft.

  In a general helicopter, the number of rotations of the main rotor varies greatly due to the operation of the pitch angle of the main rotor. For this reason, the operation burden on the pilot is large with respect to the operation performed to maintain the rotation speed of the main rotor. On the other hand, in the helicopter 1 in some embodiments, the rotation speed maintenance mode can be executed. For this reason, the operation burden on the pilot is reduced.

(More detailed explanation of helicopter)
With reference to FIG. 10, helicopters 1 according to some embodiments will be described. FIG. 10 is a functional block diagram schematically showing the configuration of the helicopter 1 according to some embodiments. In FIG. 10, members or devices having the same functions as the members or devices described in FIGS. 1 to 9 are given the same drawing numbers or symbols. A repeated description of members or devices having the same drawing number or symbol is omitted.

(Reduction gear 110)
The helicopter 1 may include a speed reducer 110. The reduction gear 110 is arrange | positioned at the part of the main power transmission mechanism 40 located between the transmission 90 and the free turbine 20, for example. The reduction gear 110 transmits the rotational torque (power) from the reduction gear input shaft to the reduction gear output shaft so that the rotation speed of the reduction gear output shaft is smaller than the rotation speed of the reduction gear input shaft.

(Clutch 120)
The helicopter 1 may include a clutch 120. The power transmission mechanism between the clutch 120 and the free turbine 20 is an upstream power transmission mechanism 44, and the power transmission mechanism between the clutch 120 and the main rotor 30 is a downstream power transmission mechanism 46. The clutch 120 can transmit the rotational torque from the upstream power transmission mechanism 44 to the downstream power transmission mechanism 46. On the other hand, the clutch 120 cannot transmit the rotational torque from the downstream power transmission mechanism 46 to the upstream power transmission mechanism 44. For this reason, the main rotor 30 or the downstream power transmission mechanism 46 is not subjected to a braking action by a mechanical element located on the upstream side of the clutch 120.

(Second electric machine 55, second power transmission mechanism 58)
The helicopter 1 may include a second electric machine 55. The second electric machine 55 has a function of an electric motor and a function of a generator. In other words, the second electric machine 55 is an electric motor having a function of a generator (or a generator having a function of an electric motor). The second electric machine 55 selectively functions as an electric motor or a generator based on a signal from the control device 70 (see a signal line indicated by a one-dot chain line n).

  When the second electric machine 55 is used as an electric motor, the control device 70 controls the operation of the second electric machine 55 so that electric power is supplied to the second electric machine 55, for example. When using the 2nd electric machine 55 as a generator, the control apparatus 70 controls operation | movement of the 2nd electric machine 55 so that supply of the electric power to the 2nd electric machine 55 is interrupted | blocked, for example.

  The second electric machine 55 and the upstream power transmission mechanism 44 are mechanically connected. In the example shown in FIG. 10, the output shaft 56 (the output shaft of the electric motor and the input shaft of the generator) of the second electric machine 55 is mechanically connected to the second input shaft 57 of the speed reducer 110. ing. The second electric machine 55 and the upstream power transmission mechanism 44 may be connected via a power transmission mechanism including a shaft, gears, and the like. Note that the second electric machine 55 and the upstream power transmission mechanism 44 may be mechanically connected without using the speed reducer 110.

  When the second electric machine 55 functions as an electric motor, the second electric machine 55 transmits rotational torque (power) to the upstream power transmission mechanism 44 via the second power transmission mechanism 58. In other words, when the second electric machine 55 functions as an electric motor, the second electric machine 55 assists the rotation of the upstream power transmission mechanism 44. As a result, the second electric machine 55 assists the rotation (acceleration) of the main rotor 30.

  When the second electric machine 55 functions as a generator, the second electric machine 55 generates power by receiving rotational torque from the upstream power transmission mechanism 44 via the second power transmission mechanism 58. In other words, when the second electric machine 55 functions as a generator, the second electric machine 55 applies a braking force to the upstream power transmission mechanism 44. As a result, the second electric machine 55 assists the deceleration of the upstream power transmission mechanism 44 (free turbine 20). Note that when the second electric machine 55 assists the deceleration of the free turbine 20, the second power transmission mechanism 58 and the upstream power transmission mechanism 44 need to be in a mechanical connection state.

  The mechanical connection between the second power transmission mechanism 58 and the upstream power transmission mechanism 44 may be detachable by a signal from the control device 70.

(Battery 80)
The battery 80 is connected to the second electric machine 55 so as to be able to transmit power (see a power line indicated by a broken line p). When the second electric machine 55 functions as an electric motor, the battery 80 supplies power (drive power) to the second electric machine 55. When the second electric machine 55 functions as a generator, the battery 80 receives electric power (generated electric power) from the second electric machine 55. The battery 80 stores the received power. The second electric machine 55 and the battery connected so as to be able to transmit power may be the same battery as the battery connected to be able to transmit power to the first electric machine 50, or may be a different battery. Good.

(First electric machine 50)
The first electric machine 50 and the downstream power transmission mechanism 46 (for example, the transmission 90 that constitutes a part of the downstream power transmission mechanism 46) are mechanically connected. The other technical items of the first electric machine 50 are the same as the technical items described with reference to FIGS. 4 to 9, and thus the repeated description is omitted.

(Starter / Generator 130)
The helicopter 1 may include a starter or a generator (generator). In the example described in FIG. 10, the starter and the generator are realized by one electric machine. The starter 130 applies rotational torque (power) to the compressor 12 (for example, a blade of the compressor 12) in response to a signal from the control device 70 (see a signal line indicated by a one-dot chain line q). As a result, supply of compressed air from the compressor 12 to the combustor 16 is started. In the example illustrated in FIG. 10, the starter 130 applies rotational torque (power) to the compressor 12 via the gear box 140.

  After the gas generator 10 is started, the generator 130 generates electric power using the rotational torque (power) received from the shaft 13 or the compressor 12. Power from the shaft 13 or the compressor 12 is transmitted to the generator 130 via the gear box 140. The electric power generated by the generator 130 is used, for example, for air conditioning in a helicopter or for avionics operation.

(Gearbox 140)
The gear box 140 is disposed between the starter / generator 130 and the compressor 12. The gearbox 140 is mechanically connected to the starter / generator 130 and mechanically connected to the compressor shaft (in other words, the shaft 13). The gear box 140 uses the rotational torque (power) supplied from the starter / generator 130 or the rotational torque (power) supplied from the compressor shaft (in the case of using electric power generated using the rotational torque). The auxiliary machine of the gas turbine unit 100 is driven. The auxiliary machines are, for example, a fuel supply pump that supplies fuel from the fuel tank 14 to the combustor 16, a lubricating oil supply pump, a turbine control device 150, and the like.

(Turbine control device 150)
The turbine control device 150 (engine control device) is configured based on a signal (refer to a signal line indicated by a one-dot chain line r) from the control device 70 (high-order control device). To control. For example, the turbine controller 150 controls the operation of the gear box 140. Further, the turbine control device 150 controls the fuel control valve 15 (or fuel supply pump) to adjust the flow rate of fuel supplied from the fuel tank 14 to the combustor 16.

(Exhaust temperature reduction device 160)
The exhaust temperature reduction device 160 is disposed downstream of the free turbine 20 with respect to the flow direction of the combustion gas. The exhaust gas temperature reducing device 160 reduces the temperature of the combustion gas e that has passed through the free turbine 20. By reducing the temperature of the exhaust gas, the risk that the helicopter 1 is detected by the counterpart infrared detector is reduced. Reduction of the temperature of the combustion gas by the exhaust temperature reduction device 160 may be performed by mixing air with the combustion gas. In addition, since the helicopter in some embodiments can execute the above-described air standby mode, the configuration of the exhaust temperature reduction device 160 may be omitted. Alternatively, when the air standby mode is being executed, the exhaust temperature reduction device 160 may be controlled to a non-operating state. By omitting the exhaust temperature reducing device 160 or by disabling the exhaust temperature reducing device 160, the pressure loss of the combustion gas is reduced. As a result, the propulsion efficiency of the helicopter 1 is improved.

(Tail rotor 170, third electric machine 180)
The helicopter 1 may include a tail rotor 170. In the example illustrated in FIG. 10, the tail rotor 170 is driven by rotational torque (power) supplied from the third electric machine 180 (tail-side electric motor). The third electric machine 180 is an electric motor driven by a battery, for example. The battery that drives the third electric machine 180 may be the same battery as the battery 80, or may be a battery different from the battery 80.

  The third electric machine 180 may be an electric machine that selectively functions as an electric motor or a generator. When the third electric machine 180 functions as a generator, the third electric machine 180 generates electric power by the rotational torque received from the tail rotor 170. The generated electric power may be stored in a battery.

  In the example illustrated in FIG. 10, the tail rotor 170 and the third electric machine 180 are mechanically connected via a third power transmission mechanism 182. The operation of the third electric machine 180 is controlled based on a signal from the control device 70 (see a signal line indicated by a one-dot chain line s).

  Alternatively, the tail rotor 170 may be driven by rotational torque received from the gas turbine unit 100. When the tail rotor 170 is driven by a gas turbine engine, it is necessary to dispose a power transmission mechanism between the gas turbine unit 100 and the tail rotor. On the other hand, when the tail rotor 170 is driven by the third electric machine 180 (electric motor), the battery and the third electric machine 180 may be connected by an electric cable. The degree of freedom of design when arranging the electric cable is larger than the degree of freedom of design when arranging the power transmission mechanism. Further, when using an electric cable, it is possible to reduce weight, cost, maintenance burden, and the like as compared with the case where a power transmission mechanism is used.

  Further, when the tail rotor 170 is driven by the third electric machine 180 (electric motor), the rotational speed of the tail rotor 170 can be freely changed by the control device 70. Furthermore, when the third electric machine 180 (electric motor) is used, the responsiveness when changing the rotational speed of the tail rotor 170 is fast. In other words, when the third electric machine 180 (electric motor) is used, the aerodynamic force generated by the rotation of the tail rotor 170 can be changed freely and quickly. For this reason, it becomes possible to omit the pitch angle changing mechanism of the tail rotor of a general tail rotor. As a result, the weight or cost of the helicopter is reduced.

(Each operation mode)
With reference to FIGS. 11 to 14, examples of the start mode, the assist mode, the braking mode, the air standby mode, and the rotation speed maintaining mode of the helicopter 1 in the example illustrated in FIG. 10 will be described.

(Start mode)
In the start mode in the example shown in FIG. 11, the operation of the tail rotor 170 and the operation of the second electric machine 55 are added to the start mode in the example shown in FIG. Operation of the main rotor 30, operation of the first electric machine 50, mechanical connection relationship between the free turbine 20 and the main rotor 30, mechanical connection relationship between the free turbine 20 and the first electric machine 50, first Since the mechanical connection relationship between the electric machine 50 and the main rotor 30 is the same as the example shown in FIG. 5, repeated description is omitted.

  In the start mode, the tail rotor 170 is maintained in a rotation stopped state. The rotation stop state is not limited to a strict rotation stop state. For example, a state where the tail rotor 170 is moving due to wind or vibration is also included in the rotation stopped state.

  The rotation stop state of the tail rotor 170 can be realized by not supplying power to the third electric machine 180 (tail side electric motor). When the third electric machine 180 is an electric machine that selectively functions as an electric motor or a generator, the control device 70 sends a signal that causes the third electric machine 180 to function as a generator. By sending it to the machine 180, it is possible to realize the rotation stop state of the tail rotor 170.

  In the start mode, the second electric machine 55 may function as a generator. That is, in the start mode, the control device 70 may send a signal for causing the second electric machine 55 to function as a generator to the second electric machine 55. Alternatively, in the start mode, the mechanical connection between the second electric machine 55 and the upstream power transmission mechanism 44 may be disconnected.

  In the start mode, the main rotor 30 and the tail rotor 170 are maintained in the rotation stopped state. As a result, the safety of the ground worker is improved during the warm-up operation of the gas turbine. In addition, noise during warm-up operation is reduced.

  The third electric machine 180 (tail-side electric motor) may be started when the start mode is switched to the assist mode (in other words, when the transition mode is executed). When the control device 70 automatically starts the third electric machine 180 when switching from the start mode to the assist mode, an additional operation for starting the tail rotor 170 becomes unnecessary.

(Assist mode, braking mode)
In the assist mode and the braking mode in the example shown in FIG. 12, the operation of the tail rotor 170 and the operation of the second electric machine 55 are added to the assist mode and the braking mode in the example shown in FIG. . Regarding the operation of the main rotor 30, the operation of the first electric machine 50, the mechanical connection relationship between the free turbine 20 and the main rotor 30, and the mechanical connection relationship between the first electric machine 50 and the main rotor 30, Since this is the same as the example described in FIG. 7, repeated description is omitted.

  In the assist mode and the braking mode, the tail rotor 170 is in a rotating state. The rotational state of the tail rotor 170 can be realized by supplying electric power to the third electric machine 180 (tail electric motor). When the third electric machine 180 is an electric machine that selectively functions as an electric motor or a generator, the control device 70 sends a signal that causes the third electric machine 180 to function as an electric motor. By sending it to the machine 180, the rotational state of the tail rotor 170 can be realized.

  In the assist mode, the control device 70 sends a control signal to the second electric machine 55 so that the second electric machine 55 functions as an electric motor. As a result, the second electric machine 55 functions as an electric motor. In the assist mode, the second electric machine 55 applies rotational torque to the upstream power transmission mechanism 44 via the second power transmission mechanism 58. In the assist mode, the main rotor 30 is rotated by rotational torque (power) from the free turbine 20, the first electric machine 50, and the second electric machine 55.

  In the example described in FIGS. 10 and 12, the rotation of the main rotor 30 is assisted by the power from the first electric machine 50 and the second electric machine 55. As a result, the assist force is enhanced.

  In the braking mode, the control device 70 sends a control signal to the second electric machine 55 so that the second electric machine 55 functions as a generator. As a result, the second electric machine 55 functions as a generator. In the braking mode, the second electric machine 55 applies a braking force to the upstream power transmission mechanism 44 via the second power transmission mechanism 58. As a result, the free turbine 20 is decelerated. As a result, the deceleration response of the entire gas turbine engine becomes faster.

  In the braking mode, braking of the main rotor 30 is realized by the first electric machine 50 (generator). The mechanism by which the main rotor 30 is braked is the same as that described above (the description related to FIGS. 4 and 7). Therefore, repeated description is omitted.

(Air standby mode)
In the air standby mode in the example shown in FIG. 13, the operation of the tail rotor 170 and the operation of the second electric machine 55 are added to the air standby mode in the example shown in FIG. 8. Operation of the main rotor 30, operation of the first electric machine 50, mechanical connection relationship between the free turbine 20 and the main rotor 30, mechanical connection relationship between the first electric machine 50 and the main rotor 30, gas generation Since the operation of the device 10 is the same as that of the example shown in FIG. 8, repeated description is omitted.

  In the air standby mode, the tail rotor 170 is in a rotating state. The rotational state of the tail rotor 170 can be realized by supplying electric power to the third electric machine 180 (tail electric motor). When the third electric machine 180 is an electric machine that selectively functions as an electric motor or a generator, the control device 70 sends a signal that causes the third electric machine 180 to function as an electric motor. By sending it to the machine 180, the rotational state of the tail rotor 170 can be realized.

  In the air standby mode, the control device 70 sends a control signal to the second electric machine 55 so that the second electric machine 55 functions as an electric motor. As a result, the second electric machine 55 functions as an electric motor. In the air standby mode, the second electric machine 55 applies rotational torque to the upstream power transmission mechanism 44 via the second power transmission mechanism 58. In the air standby mode, the main rotor 30 rotates mainly by the rotational torque (power) from the first electric machine 50 and the second electric machine 55.

  In the example described in FIGS. 10 and 13, the rotation of the main rotor 30 is realized mainly by the rotational torque (power) from the first electric machine 50 and the second electric machine 55. By providing two electric machines, the power for rotating the main rotor 30 is enhanced. Also, by providing two electric machines, the air standby mode can be executed even when one of the electric machines fails.

(Rotation speed maintenance mode)
In the rotation speed maintenance mode in the example shown in FIG. 14, the operation of the tail rotor 170 and the operation of the second electric machine 55 are added to the rotation speed maintenance mode in the example shown in FIG. Regarding the operation of the main rotor 30, the operation of the first electric machine 50, the mechanical connection relationship between the free turbine 20 and the main rotor 30, and the mechanical connection relationship between the first electric machine 50 and the main rotor 30, Since it is the same as the example described in FIG. 9, repeated description is omitted.

  In the rotation speed maintaining mode, the tail rotor 170 is in a rotating state. The rotational state of the tail rotor 170 can be realized by supplying electric power to the third electric machine 180 (tail electric motor). When the third electric machine 180 is an electric machine that selectively functions as an electric motor or a generator, the control device 70 sends a signal that causes the third electric machine 180 to function as an electric motor. By sending it to the machine 180, the rotational state of the tail rotor 170 can be realized.

  In the rotation speed maintaining mode, the control device 70 controls the second electric machine 55 so that the second electric machine 55 selectively functions as an electric motor or a generator.

  In the rotation speed maintenance mode, the main rotor 30 is rotated by the rotation torque (power) from the free turbine 20. Further, in the rotation speed maintaining mode, when the rotation speed of the main rotor increases, the second electric machine 55 functions to apply a braking force to the upstream power transmission mechanism 44. In other words, the second electric machine 55 functions as a generator. On the other hand, when the rotational speed of the main rotor decreases in the rotational speed maintenance mode, the second electric machine 55 functions to apply rotational torque to the upstream power transmission mechanism 44 (to assist the rotation). In other words, the second electric machine 55 functions as an electric motor.

  In the rotation speed maintaining mode, the control device 70 responds to the increase in the rotation speed of the main rotor (in response to detection of the increase in the rotation speed) so that the second electric machine 55 functions as a generator. 2 Send a control signal to the electric machine 55. As a result, the second electric machine 55 functions as a generator. In the rotation speed maintaining mode, the control device 70 responds to the decrease in the rotation speed of the main rotor (in response to the detection of the decrease in the rotation speed) so that the second electric machine 55 functions as an electric motor. 2 Send a control signal to the electric machine 55. As a result, the second electric machine 55 functions as an electric motor.

  In addition, the example described in FIGS. 11 and 14 includes the clutch 120. Therefore, the rotational speed of the downstream power transmission mechanism 46 (for example, the downstream shaft) connected to the clutch 120 is higher than the rotational speed of the upstream power transmission mechanism 44 (for example, the upstream shaft) connected to the clutch 120. Is larger, the mechanical connection state between the downstream side power transmission mechanism 46 and the upstream side power transmission mechanism 44 is a non-connection state.

  In the examples described in FIGS. 11 and 14, the maintenance of the rotation speed of the main rotor 30 is realized mainly by the operations of the first electric machine 50 and the second electric machine 55. As described above, in the rotation speed maintenance mode, typically, the main rotor 30 is rotated by the rotational torque from the free turbine 20. On the other hand, the first electric machine 50 and the second electric machine 55 are mainly used for maintaining the rotational speed of the main rotor 30. By providing two electric machines, the adjustment capability for maintaining the rotational speed of the main rotor 30 is enhanced. Further, by providing two electric machines, the rotation speed maintaining mode can be executed even when one of the electric machines breaks down.

  In some embodiments, the rotorcraft is a VTOL aircraft (Vertical Take-Off and Landing Aircraft), a compound helicopter, a multicopter. All rotors other than the main rotor may be driven by an electric motor (or an electric machine having a function of an electric motor and a function of a generator). By adopting a configuration in which all the rotors other than the main rotor are driven by an electric motor (or an electric machine), the weight, cost, and maintenance burden of the rotorcraft are reduced. In addition, the degree of freedom in design is improved.

  Alternatively or additionally, the rotor arranged at a relatively close distance from the gas turbine section is a gas turbine engine (and an electric machine having an electric motor function and a generator function). The rotor that is driven by the electric turbine and disposed at a relatively far distance from the gas turbine section is driven by an electric motor (or an electric machine having the functions of an electric motor and a generator). Also good. In other words, the rotor disposed at a location where the distance from the gas turbine section is equal to or greater than the predetermined seventh threshold is driven by a gas turbine engine (and an electric machine having the functions of an electric motor and a generator). The rotor disposed at a location where the distance from the gas turbine portion is less than the predetermined seventh threshold is driven by an electric motor (or an electric machine having the functions of an electric motor and a generator). It may be. By adopting a configuration in which a rotor arranged at a relatively far distance from the gas turbine section is driven by an electric motor (or electric machine), the weight, cost, and maintenance burden of the rotorcraft are reduced. The In addition, the degree of freedom in design is improved.

  Note that the rotorcraft in some embodiments may be able to execute an operation mode other than the above-described operation modes (assist mode or the like).

  The present invention is not limited to the embodiments described above, and it is obvious that the embodiments can be appropriately modified or changed within the scope of the technical idea of the present invention. Various techniques used in each embodiment or modification can be applied to other embodiments or modifications as long as no technical contradiction arises.

1: Helicopter 10: Gas generator 12: Compressor 13: Shaft 14: Fuel tank 15: Fuel control valve 16: Combustor 18: High pressure turbine 20: Free turbine 22: Output shaft 30: Main rotor 31: Input shaft 40: Main power transmission mechanism 44: upstream power transmission mechanism 46: downstream power transmission mechanism 50: first electric machine 51: output shaft 52: second input shaft 53: first power transmission mechanism 55: second electric machine 56: output Shaft 57: Second input shaft 58: Second power transmission mechanism 70: Control device 80: Battery 90: Transmission 91: First input shaft 92: Output shaft 100: Gas turbine section 110: Reducer 120: Clutch 130: Starter / Generator 140: Gearbox 150: Turbine controller 160: Exhaust temperature reduction device 170: Tail rotor 180: Third electric machine 182: third power transmission mechanism 200: power transmission unit 300: fuselage 400: landing gear

Claims (15)

A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A control device for controlling the operation of the first electric machine;
Comprising
The control device is capable of executing an assist mode in which the first electric machine applies rotational torque to the main power transmission mechanism,
In the assist mode, the first electric machine functions as the electric motor,
The control device executes the assist mode in response to an increase in the flow rate of fuel supplied to the gas generator.
Times Utatetsubasa machine. A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A control device for controlling the operation of the first electric machine;
Comprising
The control device is capable of executing an assist mode in which the first electric machine applies rotational torque to the main power transmission mechanism,
In the assist mode, the first electric machine functions as the electric motor,
The control device executes the assist mode in response to an increase in the pitch angle of the main rotor.
Times Utatetsubasa machine. Wherein the control device, the state signal indicating the state of the rotary wing aircraft, or in response to a state signal indicating the state of the gas generator, according to claim 1 or 2 automatically executes the assist mode Rotorcraft. A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A control device for controlling the operation of the first electric machine;
Comprising
The control device is capable of executing an assist mode in which the first electric machine applies rotational torque to the main power transmission mechanism,
In the assist mode, the first electric machine functions as the electric motor,
The control device is capable of executing a braking mode in which the first electric machine applies a braking force to the main power transmission mechanism,
In the braking mode, the first electric machine functions as the generator,
The control device executes the braking mode in response to a decrease in the pitch angle of the main rotor.
Times Utatetsubasa machine. The controller is capable of executing a start mode for starting the gas generator;
The rotary wing machine according to any one of claims 1 to 4 , wherein the main rotor is in a rotation stopped state in the start mode. A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A control device for controlling the operation of the first electric machine;
Comprising
The control device is capable of executing an assist mode in which the first electric machine applies rotational torque to the main power transmission mechanism,
In the assist mode, the first electric machine functions as the electric motor,
The controller is capable of executing a start mode for starting the gas generator;
In the start mode, the main rotor is in a rotation stop state,
In the start mode, the first electric machine functions as the generator.
Times Utatetsubasa machine. The control device controls the operation of the gas generator;
The control device can execute an air standby mode,
In the air standby mode, the control device controls the gas generator to stop the operation of the gas generator or to maintain the gas generator in an idling state;
The rotary wing machine according to any one of claims 1 to 6 , wherein the first electric machine functions as the electric motor in the air standby mode. A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A control device for controlling the operation of the first electric machine;
Comprising
The control device is capable of executing an assist mode in which the first electric machine applies rotational torque to the main power transmission mechanism,
In the assist mode, the first electric machine functions as the electric motor,
The control device controls the operation of the gas generator;
The control device can execute an air standby mode,
In the air standby mode, the control device controls the gas generator to stop the operation of the gas generator or to maintain the gas generator in an idling state;
In the air standby mode, the first electric machine functions as the electric motor.
Rotorcraft. The rotorcraft according to claim 7 or 8 , wherein the control device executes the aerial standby mode in response to a failure of the gas generator. The control device can execute a rotation speed maintenance mode for maintaining the rotation speed of the main rotor,
In the rotation speed maintenance mode, the control device controls the first electric machine so that the first electric machine functions as the generator in response to an increase in the rotation speed of the main rotor,
The control device controls the first electric machine so that the first electric machine functions as the electric motor in response to a decrease in the rotation speed of the main rotor in the rotation speed maintaining mode. The rotary wing machine as described in any one of thru | or 9 . A tail-side electric motor;
A tail rotor driven by the tail-side electric motor,
The control device controls the operation of the tail side electric motor,
The rotary wing machine according to claim 5 , wherein the control device controls the operation of the tail-side electric motor so that the tail rotor is maintained in a rotation stop state during execution of the start mode. The rotorcraft according to claim 11 , wherein the control device starts the tail-side electric motor when switching from the start mode to the assist mode. The rotorcraft according to claim 11 or 12 , wherein the tail rotor does not have a pitch angle changing mechanism. A second electric machine that selectively functions as an electric motor or generator;
A second power transmission mechanism that mechanically connects the main power transmission mechanism and the second electric machine;
The main power transmission mechanism is
Clutch,
An upstream power transmission mechanism disposed between the clutch and the free turbine;
A downstream side power transmission mechanism disposed between the clutch and the main rotor,
The first power transmission mechanism is mechanically connected to the downstream power transmission mechanism;
The second power transmission mechanism is mechanically connected to the upstream power transmission mechanism;
The rotary wing machine according to any one of claims 1 to 13 , wherein the control device controls an operation of the second electric machine. A gas generator for generating combustion gas;
A free turbine driven by the combustion gas from the gas generator;
The main rotor,
A main power transmission mechanism that mechanically connects the free turbine and the main rotor;
A first electric machine that selectively functions as an electric motor or generator;
A first power transmission mechanism that mechanically connects the main power transmission mechanism and the first electric machine;
A second electric machine that selectively functions as an electric motor or generator;
A second power transmission mechanism that mechanically connects the main power transmission mechanism and the second electric machine;
The main power transmission mechanism is
Clutch,
An upstream power transmission mechanism disposed between the clutch and the free turbine;
A downstream side power transmission mechanism disposed between the clutch and the main rotor,
The first power transmission mechanism is mechanically connected to the downstream power transmission mechanism;
The second power transmission mechanism is mechanically connected to the upstream power transmission mechanism.

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