Motor integrated type fluid machine, vertical take-off and landing aircraft, and design method for motor integrated type fluid machine

A motor integrated type fluid machine suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet. The machine includes: a shaft portion provided at a center of a rotation axis; a rotating portion rotating around the shaft portion; an outer peripheral portion provided on an outer periphery of the shaft portion; and an outer peripheral drive motor rotating the rotating portion. The rotating portion includes a hub rotatably supported by the shaft portion, blades provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion having an annular shape along the circumferential direction. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is 50% to 95%.

RELATED APPLICATIONS

The present application is a National Phase of International Application Number PCT/JP2020/036523 filed Sep. 28, 2020 and claims priority to Japanese application Number 2019-238689 filed Dec. 27, 2019.

TECHNICAL FIELD

The present disclosure relates to a motor integrated type fluid machine, a vertical take-off and landing aircraft, and a design method for a motor integrated type fluid machine.

BACKGROUND ART

In the related art, there is known a ring motor including a stator, a rotor, and a plurality of propeller blades (for example, refer to PTL 1). The stator includes a stator support ring, and a plurality of windings that are disposed in a circumferential direction of the stator support ring. A plurality of pitch blades are joined to the stator support ring. The rotor includes a rotor support ring, a plurality of magnetic poles disposed in a circumferential direction of the rotor support ring, and a central hub. The central hub is joined to a portion of the stator. The plurality of propeller blades are joined to the rotor support ring. For this reason, by virtue of the windings and the magnetic poles, the rotor rotates around the central hub joined to the stator, so that the plurality of propeller blades rotate.

CITATION LIST

Patent Literature

SUMMARY OF INVENTION

Technical Problem

Meanwhile, in the case of a motor integrated type fluid machine such as the ring motor of PTL 1, a centrifugal force acts on the rotor support ring when blades are rotated. At this time, since the plurality of magnetic poles are arranged in the circumferential direction on the rotor support ring, a larger centrifugal force acts on each blade due to the mass of the magnetic poles. In this case, the thickness of each blade is increased in order to secure the load capacity of each blade against the centrifugal force, which causes an increase in weight of the motor integrated type fluid machine. In other words, it is difficult to secure the load capacity of each blade against the centrifugal force while suppressing an increase in weight of the motor integrated type fluid machine.

Therefore, an object of the present disclosure is to provide a motor integrated type fluid machine, a vertical take-off and landing aircraft, and a design method for a motor integrated type fluid machine with which it is possible to suitably secure a load capacity against a centrifugal force while suppressing an increase in weight.

Solution to Problem

According to an aspect of the present disclosure, there is provided a motor integrated type fluid machine that suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet, the machine including: a shaft portion that is provided at a center of a rotation axis; a rotating portion that rotates around the shaft portion; an outer peripheral portion that is provided on an outer periphery of the shaft portion; and a motor that rotates the rotating portion. The motor is an outer peripheral drive motor that applies power from the outer peripheral portion to rotate the rotating portion. The rotating portion includes a hub that is rotatably supported by the shaft portion, a plurality of blades that are provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion that is provided on an outer peripheral side of the plurality of blades and has an annular shape along the circumferential direction of the rotation axis. The motor includes a rotor side magnet that is provided in the rotating outer peripheral portion, and a stator side magnet that is provided in the outer peripheral portion to face the rotor side magnet. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is equal to or larger than 50% and equal to or smaller than 95%.

According to another aspect of the present disclosure, there is provided a vertical take-off and landing aircraft including: the motor integrated type fluid machine; and an airframe that is moved by thrust generated from the motor integrated type fluid machine.

According to still another aspect of the present disclosure, there is provided a design method for the motor integrated type fluid machine, the method including: a step of setting the ratio of the rigidity of the rotating outer peripheral portion to the rigidity of the rotating portion; a step of deriving a centrifugal force borne by the plurality of blades based on the ratio between the rigidities; a step of deriving a thickness of the blades based on the derived centrifugal force such that a rigidity, at which the blades withstand the derived centrifugal force, is achieved; and a step of deriving a plate thickness of the rotating outer peripheral portion based on the ratio between the rigidities and the rigidity of the blades such that a rigidity at which the rotating outer peripheral portion withstands a centrifugal force is achieved.

Advantageous Effects of Invention

According to the aspects of the present disclosure, it is possible to suitably secure a load capacity against a centrifugal force while suppressing an increase in weight.

DESCRIPTION OF EMBODIMENTS

Hereinafter, an embodiment according to the present disclosure will be described in detail with reference to the drawings. Incidentally, the invention is not limited by the embodiment. In addition, the components in the following embodiment include components that can be easily replaced by those skilled in the art, or components that are substantially the same. Further, the components to be described below can be appropriately combined, and when there are a plurality of embodiments, the embodiments can be combined.

EMBODIMENT

A motor integrated type fluid machine according to the present embodiment is an axial fluid machine. The motor integrated type fluid machine is a motor integrated type fan1(hereinafter, also simply referred to as a fan1) that takes in air from a suction port and discharges the air from a discharge outlet, thus to generate thrust. Incidentally, in the present embodiment, the motor integrated type fan1will be described as an application of the motor integrated type fluid machine, and the motor integrated type fluid machine is not particularly limited to the configuration. The motor integrated type fluid machine may be applied, for example, as a motor integrated type thruster such as a propeller which takes in a liquid such as water or seawater from a suction port to inject the liquid from a discharge outlet, thus to generate thrust.

The motor integrated type fan1is provided in, for example, a vertical take-off and landing aircraft such as a helicopter or a drone. The motor integrated type fan1provided in the vertical take-off and landing aircraft generates thrust for lifting an airframe, or generates thrust for controlling the posture of the airframe. Incidentally, the motor integrated type fan1may be applied to, for example, an air cushion vehicle such as a hovercraft. Further, when the motor integrated type fan1is applied as a motor integrated type thruster, the motor integrated type fan1may be applied to ships.

The motor integrated type fan1will be described with reference toFIGS.1to5.FIG.1is a cross-sectional view of a motor integrated type fan according to the present embodiment.FIG.2is a perspective view of a fan blade according to the present embodiment.FIG.3is a partial perspective view showing a part of the fan blade according to the present embodiment.FIG.4is a description view showing a part of the fan blade according to the present embodiment.FIG.5is a graph showing the relationship between a plate thickness and the ratio of the rigidity of a rotating support ring.

The motor integrated type fan1is called a duct-type propeller or a duct fan. The motor integrated type fan1is used, for example, in a horizontal state in which an axial direction thereof is parallel to a vertical direction, and takes in air from an upper side in the vertical direction and discharges the air to a lower side in the vertical direction. Incidentally, the motor integrated type fan1may be used in a vertical state in which the axial direction is parallel to a horizontal direction.

The motor integrated type fan1is a flat fan of which the length in an axial direction of a rotation axis I is shorter than the length in a radial direction of the rotation axis I. The motor integrated type fan1is a fan in which one motor is integrally provided, and includes a shaft portion11, a rotating portion12, an outer peripheral portion13, a motor14, a rolling bearing15, and a guide vane16.

The shaft portion11is provided at the center of the rotation axis I, and is a support system (fixed side). The axial direction of the rotation axis I is an upward and downward direction inFIG.1, and is a direction along the vertical direction. For this reason, a flow direction of air is a direction along the axial direction of the rotation axis I, and the air flows from an upper side toward a lower side inFIG.1. The shaft portion11includes a shaft side fitting portion25that is a portion provided on an upstream side in the axial direction of the rotation axis I, and a shaft body26that is a portion provided downstream of the shaft side fitting portion25.

A hub31of the rotating portion12to be described later is fitted to the shaft side fitting portion25. The shaft side fitting portion25has a cylindrical shape, and is provided to protrude from an end surface on the upstream side of the shaft body26in the axial direction. A space having a columnar shape is formed on a center side of the rotation axis I in the shaft side fitting portion25. A part of the hub31of the rotating portion12is inserted into the space. In addition, an outer peripheral side of the shaft side fitting portion25is surrounded by a part of the hub31of the rotating portion12.

The shaft body26has a substantially conical shape that is tapered from the upstream side toward a downstream side in the axial direction. For this reason, an outer peripheral surface of the shaft body26is a surface that approaches an inner side from an outer side in the radial direction as the surface extends from the upstream side toward the downstream side in the axial direction. An internal space in which a device can be installed is formed inside the shaft body26. Examples of the device include a control device, a camera and the like. In addition, an end portion on the radial inner side of the guide vane16to be described later is connected to the outer peripheral surface of the shaft body26.

As illustrated inFIGS.1and2, the rotating portion12is a rotating system (rotating side) that rotates around the shaft portion11. The rotating portion12is provided on an inlet side, into which air flows, with respect to the shaft portion11in the axial direction of the rotation axis I. The rotating portion12includes the hub31, a plurality of blades32, and a rotating support ring33.

The hub31is provided upstream of the shaft portion11in the axial direction, and is rotatably fitted to the shaft side fitting portion25. The hub31includes a hub body35that is a portion provided on the upstream side in the axial direction, and a hub side fitting portion36that is a portion provided downstream of the hub body35. The hub body35is formed such that an end surface on the upstream side is a hemispherical surface having a predetermined radius of curvature. The hub side fitting portion36has a shape complementary to that of the shaft side fitting portion25. The hub side fitting portion36includes a central shaft36aprovided at the center of the rotation axis, and a cylindrical portion36bthat has a cylindrical shape and is provided on an outer peripheral side of the central shaft36a. The central shaft36ais inserted into the space of the shaft side fitting portion25, the space being formed at the center of the rotation axis. The cylindrical portion36bis provided to protrude from an end surface on the downstream side of the hub body35in the axial direction. The cylindrical portion36bis disposed to surround an outer periphery of the shaft side fitting portion25. At this time, the rolling bearing15is provided between an inner peripheral surface of the shaft side fitting portion25and an outer peripheral surface of the central shaft36aof the hub31.

Then, a surface extending from an end surface of the hub body35to the outer peripheral surface of the shaft body26via an outer peripheral surface of the cylindrical portion36bis a surface that is smooth without a step.

The plurality of blades32are provided to extend from the hub31toward the radial outer side, and are provided side by side at predetermined intervals in a circumferential direction. Each of the blades32has an airfoil shape and the length thereof in a direction in which a pressure surface and a suction surface face each other is the thickness thereof. The plurality of blades32are made of a composite material. Incidentally, in the present embodiment, the plurality of blades32are made of a composite material; however, the material is not particularly limited, and the plurality of blades32may be made of, for example, a metallic material.

The rotating support ring33is formed in an annular shape centered on the rotation axis I. The rotating support ring33is connected to an outer peripheral side of the plurality of blades32in the radial direction of the rotation axis I. A radial outer end portion of each blade32is fixed to an inner peripheral surface of the rotating support ring33via a joining fitting42. In addition, a permanent magnet45of the motor14to be described later is held at the outer peripheral surface of the rotating support ring33.

The rotating portion12is configured such that the hub31, the plurality of blades32, and the rotating support ring33are integrally joined to each other, and rotates around the hub31. In addition, as will be described in detail later, the permanent magnet45of the motor14is integrally held at the rotating portion12, so that a fan blade rotor41in which the rotating portion12and the permanent magnet45are integrated with each other as shown inFIG.2is formed.

The outer peripheral portion13is provided outside the shaft portion11in the radial direction, and is the support system (fixed side). The outer peripheral portion13is a duct that is formed in an annular shape, and is caused to generate thrust by the rotation of the rotating portion12. In the outer peripheral portion13(hereinafter, referred to as the duct13), an opening on the upstream side in the axial direction of the rotation axis I is a suction port38, and an opening on the downstream side is a discharge outlet39. In addition, the duct13has a shape in which when the rotating portion12rotates, air is suctioned from the suction port38, and the suctioned air is discharged from the discharge outlet39to generate thrust. Specifically, an inner peripheral surface of the duct13on the downstream side of the rotating portion12is a surface that is widened from the suction port38side toward the discharge outlet39side.

An internal space, which has an annular shape and accommodates the rotating support ring33of the rotating portion12, the permanent magnet45of the motor14, and a coil46of the motor14to be described later, is formed inside the duct13. The duct13holds the coil46thereinside and the permanent magnet45and the coil46face each other in the radial direction, the coil46being provided at a position facing the permanent magnet45held by the rotating portion12. Namely, the duct13functions as a stator.

The motor14is an outer peripheral drive motor that applies power from a duct13side toward the rotating portion12to cause the rotating portion12to rotate. The motor14includes a rotor side magnet provided on a rotating portion12side, and a stator side magnet provided on the duct13side. In the present embodiment, the rotor side magnet is the permanent magnet45, and the stator side magnet is the coil46which is an electromagnet.

The permanent magnet45is provided to be held at the outer peripheral surface of the rotating support ring33, and is disposed in an annular shape in the circumferential direction. In addition, the permanent magnet45is configured such that positive poles and negative poles alternate at predetermined intervals in the circumferential direction. Incidentally, the permanent magnet45may be in a Halbach array. The permanent magnet45is provided at a position facing the coil46in the radial direction of the rotation axis I.

A plurality of the coils46are provided to be held inside the duct13and to face the poles of the permanent magnet45and are provided side by side in the circumferential direction. The coil46is provided at a position facing the permanent magnet45, which is held by the rotating portion12, in the radial direction of the rotation axis I. Namely, the permanent magnet45and the coil46are disposed to face each other in the radial direction of the rotation axis I, which is a radial disposition.

The rolling bearing15is provided between the inner peripheral surface of the shaft side fitting portion25of the shaft portion11and the outer peripheral surface of the central shaft36aof the hub31of the rotating portion12. The rolling bearing15connects the shaft portion11and the rotating portion12while allowing the rotating portion12to rotate with respect to the shaft portion11. The rolling bearing15is, for example, a ball bearing or the like.

The guide vane16is provided to connect the shaft portion11and the duct13. The guide vane16is provided downstream of the rotating portion12in the axial direction of the rotation axis I. Namely, the guide vane16is provided at the position of a downstream portion43of the duct13in the axial direction. A plurality of the guide vanes16are provided side by side in the circumferential direction of the rotation axis I. In addition, the guide vane16has a streamlined shape such as an airfoil shape, and rectifies air, which flows from the rotating portion12, to generate thrust. Incidentally, the shape of the guide vane16is not limited to an airfoil shape, and may be a plate shape.

In the motor integrated type fan1described above, power generated by a magnetic field is applied from the duct13side to the rotating portion12by the motor14, so that the rotating portion12rotates. When the rotating portion12rotates, the motor integrated type fan1suctions air from the suction port38, and discharges the air toward the discharge outlet39. The air discharged from the rotating portion12flows along the inner peripheral surface of the duct13to generate thrust. At this time, the flow of the air is rectified by the guide vanes16, so that thrust is also generated by the guide vanes16.

Next, with reference toFIGS.2to4, the fan blade rotor41in which the rotating portion12and the permanent magnet45are integrated with each other will be described. The fan blade rotor41includes the rotating portion12, the permanent magnet45, and a restraining portion51.

For example, a composite material is used for the restraining portion51, and the restraining portion51is wound around the rotating support ring33and the permanent magnet45from the outside of the rotating support ring33of the rotating portion12and the permanent magnet45. As the composite material, a composite material obtained by causing a resin to infiltrate carbon fiber (for example, a composite material obtained by curing a prepreg) is applied. Further, the composite material may be a sheet-like narrow composite material or a fiber bundle, and is not particularly limited.

As shown inFIG.3, the restraining portion51is wound around the rotating support ring33extending in the circumferential direction and the permanent magnet45in a spiral shape and integrally cured to integrally restrain the rotating support ring33and the permanent magnet45, the rotating support ring33and the permanent magnet45serving as a core. In addition, as shown inFIG.4, the joining fitting42that is joined to a radial outer end portion of each of the blades32is provided on an inner peripheral side of the rotating support ring33and the restraining portion51integrally restrains the rotating support ring33, the permanent magnet45, and the joining fitting42.

In addition, the restraining portion51is wound around the entire circumference of the rotating support ring33. At this time, the restraining portion51is wound such that portions thereof overlap with each other in the circumferential direction of the rotating support ring33. Namely, regarding the restraining portion51spirally wound in the circumferential direction, one portion of the restraining portion51and the other portion of the restraining portion51, which are adjacent to each other in the circumferential direction, overlap with each other.

Incidentally, as shown inFIG.3, it is difficult for the restraining portion51to integrally restrain the rotating support ring33, the permanent magnet45, and the joining fitting42at a joining part which is at the center of the joining fitting42in the circumferential direction. In this case, the restraining portion51integrally restrains portions of the rotating support ring33and the permanent magnet45that correspond to the joining part of the joining fitting42. Then, the restraining portion51integrally restrains the rotating support ring33, the permanent magnet45, and the joining fitting42at flat plate portions of the joining fitting42, which are on both sides in the circumferential direction. Namely, the restraining portion51may be configured to be divided into a plurality of parts and a configuration in which a restraining portion51that restrains the rotating support ring33and the permanent magnet45at the joining part of the joining fitting42and a restraining portion51that restrains the rotating support ring33, the permanent magnet45, and the joining fitting42at the flat plate portions of the joining fitting42are included may also be adopted. In this case, it is preferable to use the same composite material for the divided restraining portions51.

When the fan blade rotor41as described above rotates, a centrifugal force P1 is applied to the fan blade rotor41. The centrifugal force P1 is distributed to each blade32of the fan blade rotor41and the rotating support ring33, so that a tensile force P2 in the radial direction acts on each blade32of the fan blade rotor41and a hoop stress P3 in the circumferential direction acts on the rotating support ring33of the fan blade rotor41.

Here, the rigidity of the rotating support ring33with respect to the centrifugal force P1 is defined as how the rotating support ring33is difficult to be elongated in the radial direction by the centrifugal force P1 and is a value obtained by dividing the centrifugal force P1 by the degree of elongation in the radial direction. Similarly, the rigidity of the rotating portion12with respect to the centrifugal force P1 is defined as how the rotating portion12is difficult to be elongated in the radial direction by the centrifugal force P1 and is a value obtained by dividing the centrifugal force P1 by the degree of elongation in the radial direction. The rotating support ring33is elongated in the radial direction when the rotating support ring33receives the centrifugal force P1. Similarly, the blades32are elongated in the radial direction when the blades32receive the centrifugal force P1. Since the end portions of the blades32are joined to the rotating support ring33via the joining fitting42, the rotating support ring33and the blades32are the same as each other in degree of elongation in the radial direction. At this time, the centrifugal force P1 is distributed into the tensile force P2 and the hoop stress P3 in accordance with the ratio between the rigidity of the plurality of blades32and the rigidity of the rotating support ring33such that the degree of elongation of the rotating support ring33and the degree of elongation of the blades32are balanced. Specifically, in a case where the ratio of the rigidity of the rotating support ring33is large, the rotating support ring33is difficult to be elongated in the radial direction. For example, when the thickness t2 of each blades32is made small and the thickness t1 of the rotating support ring33in the radial direction is made large, the centrifugal force P1 distributed to the plurality of blades32(that is, the tensile force P2) is made small and the centrifugal force P1 distributed to the rotating support ring33(that is, the hoop stress P3) is made large. On the other hand, in a case where the ratio of the rigidity of the rotating support ring33is small, the rotating support ring33is easily elongated in the radial direction. For example, when the thickness t2 of each blades32is made large and the thickness t1 of the rotating support ring33in the radial direction is made small, the centrifugal force P1 distributed to the plurality of blades32(that is, the tensile force P2) is made large and the centrifugal force P1 distributed to the rotating support ring33(that is, the hoop stress P3) is made small. As described above, the thickness t2 of each blade32and the thickness t1 of the rotating support ring33in the radial direction are in a trade-off relationship and the ratio between the rigidity of the plurality of blades32and the rigidity of the rotating support ring33is set as follows in consideration of the relationship.

(Relationship Between Ratio Between Rigidities and Plate Thickness)

InFIG.5, the horizontal axis corresponds to the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12and the vertical axis corresponds to plate thicknesses. Incidentally, the plate thicknesses include the thickness t1 of the rotating support ring33in the radial direction (ring plate thickness: solid line), the thickness t2 of the blades32(blade thickness: dotted line), and the ring plate thickness+the blade thickness (dashed line). In addition, in the graph ofFIG.5, a thickness on a hub31side of the blades32is adopted as the thickness t2 of the blades32and the thickness t2 of the blades32is the sum of the thicknesses t2 of all blades32. The blade thickness is a value obtained by calculating a thickness required to bear a force borne by the blades32. In addition, the ring plate thickness is a value obtained by calculating a plate thickness required to achieve a desired rigidity ratio with respect to the rigidity of the blades32.

Here, a design method for a motor integrated type fluid machine for deriving the blade thickness and the ring plate thickness when drawing up the graph shown inFIG.5will be described.FIG.6is a flowchart related to a design method for a motor integrated type fan according to the present embodiment. As shown inFIG.6, in this design method, first, step S11in which the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12is set is performed. Next, step S12in which the centrifugal force P1 borne by the blades32is derived is performed based on the ratio between the rigidities set as above. Thereafter, step S13in which the thickness of the blades32is derived such that the blades32have a rigidity enough to withstand the derived centrifugal force P1 is performed. Then, step S14, in which the rigidity of the rotating support ring33is derived based on the rigidity of the blades32and the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12and the plate thickness of the rotating support ring33is derived such that the derived rigidity of the rotating support ring33is achieved, is performed. In this manner, the blade thickness and the ring plate thickness as shown inFIG.5are calculated.

In the present embodiment, the ratio of the rigidity of the rotating support ring33is set such that a plate thickness that is “the ring plate thickness+the blade thickness” is made equal to or smaller than a plate thickness T1, which is a predetermined threshold value. Here, the plate thickness T1 is a plate thickness determined by the weight of the rotating portion12. The plate thickness is set to be equal to or smaller than T1 for suppression of the weight of the rotating portion12. In this case, the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12is set to fall within a range H1 of 50% to 95%. In a case where the ratio of the rigidity of the rotating support ring33is in the range H1, the ratio of the rigidity of the plurality of blades32falls within a range of 5% to 50%. That is, in a case where the ratio of the rigidity of the rotating support ring33is 95%, the ratio of the rigidity of the plurality of blades32is 5% and in a case where the ratio of the rigidity of the rotating support ring33is 50%, the ratio of the rigidity of the plurality of blades32is 50%. In a case where the ratio between rigidities is set as described above, the rotating support ring33can efficiently bear a rigidity. More specifically, in a case where there is a decrease in ratio of the rigidity of the rotating support ring33, the rigidity of the blades32is increased and the weight of the blades32is increased since the blades32need to bear a rigidity. For this reason, in order to suppress an increase in weight of the blades32, the ratio of the rigidity of the rotating support ring33is made equal to or larger than 50%. Meanwhile, in a case where the ratio of the rigidity of the rotating support ring33is made excessively large for suppression of an increase in weight of the blades32, the ring plate thickness of the rotating support ring33is made large, which results in an increase in weight of the rotating support ring33. For this reason, in order to suppress an installation space for the rotating support ring33and an increase in weight of the rotating support ring33, the ratio of the rigidity of the rotating support ring33is made equal to or smaller than 95%.

In addition, in the present embodiment, it is more preferable that the ratio of the rigidity of the rotating support ring33is set such that the plate thickness that is “the ring plate thickness+the blade thickness” is made equal to or smaller than a plate thickness T2 smaller than the plate thickness T1. Namely, in order to further suppress an installation space for the rotating portion12and an increase in weight of the rotating portion12, the plate thickness is set to be equal to or smaller than T2. In this case, the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12is set to fall within a range H2 of 80% to 90%. In a case where the ratio of the rigidity of the rotating support ring33is in the range H2, the ratio of the rigidity of the plurality of blades32falls within a range of 10% to 20%. That is, in a case where the ratio of the rigidity of the rotating support ring33is 90%, the ratio of the rigidity of the plurality of blades32is 10% and in a case where the ratio of the rigidity of the rotating support ring33is 80%, the ratio of the rigidity of the plurality of blades32is 20%.

Further, in the present embodiment, it is more preferable that the ratio of the rigidity of the rotating support ring33is set such that the plate thickness that is “the ring plate thickness+the blade thickness” is minimized. Specifically, the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12is set to be 85% (point H3)±2%. In a case where the ratio of the rigidity of the rotating support ring33is 85%±2%, the ratio of the rigidity of the plurality of blades32is 15%±2%. Incidentally, 85%±2% has been used as the ratio of the rigidity of the rotating support ring33at which “the ring plate thickness+the blade thickness” is minimized since the ratio of the rigidity at which “the ring plate thickness+the blade thickness” is minimized differs slightly depending on the configurations, the sizes, and the materials of components and may not be 85%.

As described above, according to the present embodiment, the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12can be set to fall within the above-described range H1. Accordingly, it is possible to secure a load capacity against the tensile force P2 acting on the plurality of blades32even in a case where the centrifugal force P1 is applied and to secure a load capacity against the hoop stress P3 acting on the rotating support ring33while making the plate thickness that is “the ring plate thickness+the blade thickness” equal to or smaller than the plate thickness T1. Therefore, it is possible to suitably secure the load capacity of the rotating portion12against the centrifugal force P1 while suppressing an increase in weight of the rotating portion12.

In addition, according to the present embodiment, it is possible to make the plate thickness that is “the ring plate thickness+the blade thickness” smaller by setting the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12to fall within the above-described range H2. Therefore, it is possible to reduce the weight of the rotating portion12.

In addition, according to the present embodiment, it is possible to minimize the range of the plate thickness that is “the ring plate thickness+the blade thickness” by setting the ratio of the rigidity of the rotating support ring33to the rigidity of the rotating portion12to be the above-described point H3±2%. Therefore, it is possible to minimize the weight of the rotating portion12.

In addition, according to the present embodiment, the ratio of the rigidity of the plurality of blades32can be made equal to or larger than 5% and equal to or smaller than 50% in accordance with the ratio of the rigidity of the rotating support ring33. For this reason, the ratio of the rigidity of the plurality of blades32can be made appropriate for the ratio of the rigidity of the rotating support ring33. Accordingly, it is possible to make the thickness of the blades32appropriate for the thickness of the rotating support ring33in the radial direction and thus it is possible to suppress an increase in weight of the blades32and to suppress the blade thickness. Therefore, it is possible to increase the degree of freedom in designing the weight and the thickness of the blades32.

In addition, according to the present embodiment, the thickness of the rotating support ring33in the radial direction can be made smaller than the sum of the thicknesses of the plurality of blades32. Therefore, it is possible to suppress an increase in weight of the rotating support ring33.

In addition, according to the present embodiment, it is possible to provide a vertical take-off and landing aircraft in which the motor integrated type fan1having a high durability and having a load capacity against the centrifugal force P1 is mounted in an airframe.

The motor integrated type fluid machine (motor integrated type fan)1and the vertical take-off and landing aircraft described in each embodiment are grasped as follows, for example.

The motor integrated type fluid machine1according to a first aspect is the motor integrated type fluid machine1that suctions a fluid (air) from the suction port38and discharges the suctioned fluid from the discharge outlet39, the machine including: the shaft portion11that is provided at the center of the rotation axis; the rotating portion12that rotates around the shaft portion11; the outer peripheral portion (duct)13that is provided on an outer periphery of the shaft portion11; and the motor14that rotates the rotating portion. The motor14is the outer peripheral drive motor14that applies power from the outer peripheral portion13to rotate the rotating portion12, the rotating portion12includes the hub31that is rotatably supported by the shaft portion11, the plurality of blades32that are provided on an outer peripheral side of the hub31and provided side by side in the circumferential direction of the rotation axis, and the rotating outer peripheral portion (rotating support ring)33that is provided on an outer peripheral side of the plurality of blades32and has an annular shape along the circumferential direction of the rotation axis, the motor14includes the rotor side magnet (permanent magnet)45that is provided in the rotating outer peripheral portion33, and the stator side magnet (coil)46that is provided in the outer peripheral portion13to face the rotor side magnet45, and the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12is equal to or larger than 50% and equal to or smaller than 95%.

According to this configuration, the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12is set to be equal to or larger than 50% and equal to or smaller than 95%. Therefore, it is possible to secure a load capacity against the tensile force P2 acting on the plurality of blades32even in a case where the centrifugal force P1 is applied and to secure a load capacity against the hoop stress P3 acting on the rotating outer peripheral portion33. At this time, the thickness of the rotating outer peripheral portion33in the radial direction and the thickness of the plurality of blades32can be restrained from being large. Therefore, it is possible to suitably secure the load capacity of the rotating portion12against the centrifugal force P1 while suppressing an increase in weight of the rotating portion12.

In the motor integrated type fluid machine1according to a second aspect, the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12is equal to or larger than 80% and equal to or smaller than 90%.

According to this configuration, the sum of the thickness of the rotating outer peripheral portion33in the radial direction and the thickness of the plurality of blades32can be made smaller. Therefore, it is possible to reduce the weight of the rotating portion12.

In the motor integrated type fluid machine according to a third aspect, the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12is 85%±2%.

According to this configuration, it is possible to minimize the range of the sum of the thickness of the rotating outer peripheral portion33in the radial direction and the thickness of the plurality of blades32. Therefore, it is possible to minimize the weight of the rotating portion12.

In the motor integrated type fluid machine according to a fourth aspect, the ratio of the rigidity of the plurality of blades32to the rigidity of the rotating portion12is equal to or larger than 5% and equal to or smaller than 50%.

According to this configuration, the ratio of the rigidity of the plurality of blades32can be made appropriate for the ratio of the rigidity of the rotating outer peripheral portion33. Accordingly, it is possible to make the thickness of the blades32appropriate for the thickness of the rotating outer peripheral portion33in the radial direction and thus it is possible to suppress an increase in weight of the blades32.

In the motor integrated type fluid machine according to a fifth aspect, the plate thickness of the rotating outer peripheral portion33in the radial direction of the rotation axis is smaller than the sum of the thicknesses of the plurality of blades32.

According to this configuration, it is possible to suppress an increase in weight of the rotating support ring33.

A vertical take-off and landing aircraft a sixth aspect includes the motor integrated type fluid machine1described above and an airframe that is moved by thrust generated from the motor integrated type fluid machine1.

According to this configuration, it is possible to provide a vertical take-off and landing aircraft in which the motor integrated type fluid machine1having a high durability and having a load capacity against the centrifugal force P1 is mounted in the airframe.

A design method for a motor integrated type fluid machine according to a seventh aspect includes step S11of setting the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12, step S12of deriving the centrifugal force P1 borne by the plurality of blades32based on the ratio between the rigidities, step S13of deriving the thickness of the blades32based on the centrifugal force P1 such that the rigidity of the blades32, at which the blades32withstand the derived centrifugal force P1, is achieved, and step S14of deriving the rigidity of the rotating outer peripheral portion33based on the ratio between the rigidities and the rigidity of the blades32and deriving the plate thickness of the rotating outer peripheral portion33such that the derived rigidity of the rotating outer peripheral portion33is achieved.

According to this configuration, the rigidity of the blades32based on the ratio of the rigidity of the rotating outer peripheral portion33to the rigidity of the rotating portion12can be achieved. For this reason, it is possible to design the weight of the blades32and the blade thickness such that the rigidity of the blades32is satisfied and thus it is possible to increase the degree of freedom in designing the blades32.

REFERENCE SIGNS LIST