JP2001165074A - Movable blade-type rotary device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a movable blade-type rotary device capable of reducing the rubbing abrasion of a movable blade and its engagement groove, in particular, that of the movable blade, and reduce the feeding of a lubricant. SOLUTION: In this movable blade-type rotary device having a cylinder or a cam ring with an inlet port and a discharge port for the fluid, and a rotor eccentrically mounted in the cylinder or coaxially mounted in the cam ring, and composed of at least one axially extended movable blade and an engagement groove for sliding the blade, the rotor has at least one cut groove on a back wall of the engagement groove when observed from the rotating direction, and the cut groove is opened on a surface of the rotor and continuously extended from an opening end toward a bottom of the engagement groove.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a movable airfoil rotating device, more specifically, a gas compression (pressurizing) and a gas compressor such as a vane type compression device, a vane type blower device, and a vane type vacuum device. The present invention relates to a liquid device for liquid pressurization and liquid feeding, such as a gas device for gas feed / gas decompression and a vane-type hydraulic pump device. In particular, movable blades and movable blade sliding of a rotor over these gas devices and liquid devices in general. The present invention relates to a movable airfoil rotating device that exhibits less rubbing and abrasion of a fitting groove or the like and exhibits excellent operation efficiency.

[0002]

2. Description of the Related Art The movable airfoil rotating apparatus disclosed at the beginning is well known. That is, in the device, a rotor (rotor) having one or more movable blades (vanes) is eccentrically arranged in a cylinder having a fluid suction port and a discharge port, and a vane type hydraulic pump device is provided. Among them, the balanced vane pump device uses a cam ring instead of a cylinder,
A rotor is concentrically disposed inside the rotor, and the movable wings on which centrifugal force acts due to the rotation of the rotors enter and exit from the sliding fitting grooves. A mechanism is provided to repeatedly perform a series of operations of taking in the partitioned vane chamber, compressing and pressurizing the taken-in fluid in the gradually decreasing space of the vane chamber, and discharging the pressurized fluid to the outside via the discharge port.

[0003] Among the movable airfoil rotary devices, gaseous devices are roughly classified into a range of rotation speed, use of movable blade material and lubricant, and no use. A type: 500 to 1000 rotations per minute; Made of metal with lubricant, B type: 500-1000 revolutions per minute, movable wing made of non-metal, using lubricant, C type: 500-1000 revolutions per minute, movable wing made of non-metal, no lubricant Use, D type: 1000-1700 rotations per minute, movable blades are made of metal and use lubricant, E type: 1000-1700 rotations per minute, movable blades are made of non-metal and use lubricant, F type: every minute Generally, the movable wing is made of a nonmetallic material and uses no lubricant. Note that the lubricant mentioned here is a liquid lubricant, a semi-solid grease, and a solid lubricant.
The solid lubricant is used under conditions where semi-solid grease, liquid lubricating oil and the like cannot be used. If liquid lubricating oil is used, adopt the lubrication method.

[0004] In addition, a liquid device among movable airfoil rotating devices,
For example, a vane type hydraulic pump device has a rotation speed of 750 rpm.
Since the maximum discharge pressure is 7 MPa or more at 可 動 1800 revolutions, the movable wing is generally applied with a high-speed tool steel material SKH2 or a metal material having characteristics equivalent to or higher than SKH2.

[0005]

In any of the movable airfoil rotating devices of the above-mentioned type, the movable blades move in and out of the fitting groove of the rotor at a high speed, and the movable blades slide on the inner surface of the cylinder or the inner surface of the cam ring. As one of them, rubbing wear of the movable blade and rubbing wear of the wall surface of the rotor fitting groove inevitably occur as the use period elapses. Since excessive wear of the fitting groove wall requires replacement of the rotor and movable wing, generally,
A material that is more easily worn than the rotor material is applied to the movable wing.

[0006] This type of abrasion wear, especially the abrasion wear of the movable wings, cannot use a lubricant, and therefore the movable wings made of carbon or other non-metallics, which are supposed to serve also as a solid lubricant, themselves. It is unavoidable that a lubricant-free gas system using movable wings is even more serious. However, the problem of frictional wear still exists in gaseous devices using a lubricant, including a gas device that supplies liquid lubricating oil to the movable blades, while also reducing frictional wear at the tip of the movable blade that slides in contact with the inner surface of the cylinder. This is the current situation.

In the case of a gas device for supplying liquid lubricating oil, if the amount of lubricating oil is increased in order to avoid the problem of abrasion and wear, an oil filter or the like for separating and recovering liquid lubricating oil from the pressurized gas discharged to the outside is provided. In addition to the heavy equipment, not only the equipment cost is increased, but also a lot of trouble is required to reuse the recovered lubricating oil, and sometimes the burn-out failure may occur without noticing the running out of the lubricating oil. In addition, even if the amount of refueling is increased, no significant effect is found in suppressing the abrasion and abrasion of the movable blade wall surface. This is also evident from the fact that the above-mentioned kind of abrasion problem also occurs in liquid devices such as vane type hydraulic pump devices.

In the movable airfoil rotating apparatus, the movable airfoil enters and exits the fitting groove of the rotor at a high speed.
During operation, a rapid volume change occurs between the inner end surface of the movable wing and the bottom surface of the fitting groove. As a result, a resistance force is generated with respect to the movable wing coming and going, and fluid leakage easily occurs between the tip of the movable wing and the inner surface of the cylinder and between the tip of the movable wing and the inner surface of the cam ring, which partition adjacent blade chambers. The efficiency of the moving blades is constantly reduced, and the resistance to the insertion of the moving blades promotes the tip wear of the moving blades.

Accordingly, the inventions according to the first to eighth aspects of the present invention are to solve the above-mentioned problems, and in fact, the wear and tear of the movable wings in both the gas apparatus and the liquid apparatus of the type described above. And the frictional wear of the rotor fitting groove, in particular, the frictional wear of the former can be easily reduced without using an additional device, and the resistance to the movable wings accompanying the moving in and out of the movable wings during operation is reduced. It is an object of the present invention to provide a movable airfoil rotating device that can be reduced to the limit and the operating efficiency of the device can be greatly improved.

[00010]

In order to achieve the above-mentioned object, according to the first aspect of the present invention, there is provided a cylinder having a suction port and a discharge port for a fluid, and a rotor eccentrically located in the cylinder. A cam ring having an elliptical cross-section including a suction port and a discharge port for a fluid, and a rotor having a common axis within the cam ring.
In a movable airfoil rotating device including one or more movable blades extending in the axial direction and a sliding fitting groove, the rotor has one or more cuts in a rear wall of the fitting groove as viewed in the rotational direction. A movable airfoil rotating apparatus comprising a groove, wherein the cut groove is open on the rotor surface and has a configuration extending continuously from the open end toward the bottom of the fitting groove.

According to the first aspect of the present invention, as in the second aspect of the present invention, the cut groove forms a fluid introduction flow path from the open end to the fitting groove bottom in accordance with the rotation of the rotor. And a function of diffusing fluid into the gap between the rotor rotating direction back wall of the fitting groove and the movable wing face facing this through the flow path, and forming a fluid film in the gap. The point has functional features.

According to the first and second aspects of the invention, as in the third aspect of the invention, the cut groove is a straight groove having an inner end near the bottom of the fitting groove. Fit.

[0013] Further, with regard to the inventions described in claims 1 to 3, as in the invention described in claim 4, it is preferable that the cut grooves are arranged to be orthogonal to the opening edges of the fitting grooves. .

According to the invention set forth in claims 1 to 4, as in the invention set forth in claim 5, the area of the back surface of the fitting groove at a plurality of locations divided by the cut groove is defined by both end regions in the rotor axial direction. Have uniform areas with each other,
The area sandwiched by the cut grooves has one of the same or approximate area as the total area of both end areas.

[0015] In the invention according to claims 1 to 5, it is advantageous that the cut groove has a branch groove in the middle of the cut as in the invention described in claim 6.

According to the invention described in the first to sixth aspects, preferably, as in the invention described in the seventh aspect, the cut groove and the branch groove are formed from the bottom of the groove to the back wall of the fitting groove. Has a cross-sectional shape of Suehiro.

According to the invention described in claims 1 to 7, preferably, as in the invention described in claim 8, the cut groove has a chamfer at the open end of the rotor.

[0018]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIGS. FIG. 1 is a front sectional view of a movable airfoil rotating apparatus according to the present invention, and FIG. 2 is a side sectional view taken along line II-II of the apparatus shown in FIG.
FIG. 7 is a side view and a front view of the rotor of the present invention excluding a movable wing. FIGS. 7 and 8 are IIV-I shown in FIGS.
FIG. 9 is a side view of the back wall of the fitting groove along the IV line.
FIG. 9 is an enlarged sectional view taken along line IX-IX shown in FIG. 8.

In the following, a movable airfoil rotating apparatus having a cylinder having a fluid suction port and a fluid discharge port and a rotor eccentrically located in the cylinder will be described as a representative. The movable airfoil rotating device 1 is eccentrically located in the cylinder 2 and the cylinder 2,
And a rotor 3 that rotates in the direction of arrow R by the rotation of a rotation drive device (not shown). The rotor 3 has a length substantially equal to the entire length of the cylinder 2. The cylinder 2 has a suction port 4 for an external fluid (not shown) and a discharge port 5 for an internal fluid on its inner surface, and a fluid suction hole 6 communicating with the suction port 4 and a fluid discharge port communicating with the discharge port 5. And a hole 7. The fluid referred to herein refers to a gas such as air or another gas and a liquid such as oil, water, or another solution, and the same applies hereinafter.

The rotor 3 includes one or more movable blades 10 extending in the direction of the rotation axis X, and four movable blades 10 in the illustrated example, and a fitting groove 11 for allowing the movable blade 10 to slide in and out of the rotor 3. The movable wing 10 is a quadrangular flat plate. This flat plate has a uniform thickness except for the tip of the movable wing 10,
And has a length approximately equal to the length of

The movable wing 10 has a circular chamfered section or a flat chamfered part on the back side in the rotation direction R at a tip portion which comes into contact with the inner surface of the cylinder 2. It contacts the inner surface of the cylinder 2 with a narrow width less than the thickness of the flat plate. In FIG. 1, for convenience, a movable wing 10 having a chamfer having an arc-shaped cross section and a movable wing 10 having a planar chamfer on the rear side are shown for the tip end shape. However, in practice, they are not mixed and beveled in the same shape. The fitting groove 11 has a length over the entire length of the rotor 3 and the movable wing 1
0 to accommodate the entirety.

Here, referring also to FIGS. 1 to 6, the movable airfoil rotating device 1 is a gas device of the type A to F described above.
It applies to both types and liquid devices,
When viewed in the rotation direction R, the rotor 3 has a rear wall 1 of the fitting groove 11.
2 is provided with one or more, and in the illustrated example, three cut grooves 13 are provided. Each of the cut grooves 13 is configured to open to the surface 3sf of the rotor 3 and to extend continuously from the open end 13oe toward the groove bottom 11bm of the fitting groove 11. 3A to 6A are side views of the rotor 3, and FIG.
FIGS. 6B to 6B are front views of the rotor 3.

The rotor 3 shown in FIG.
For C type and low speed vane type hydraulic pump device,
The rotor 3 shown in FIG. 4 is suitable for the D-type and the high-speed vane type hydraulic pump device described above, which is suitable for using the relatively thick movable blade 10 so that a sufficient centrifugal force acts even at low speed rotation. Yes, it is suitable for using a relatively thin movable wing 10 capable of obtaining an appropriate centrifugal force at high speed rotation.

In the above two examples, the fitting groove 11 extends in the radial direction from the axis X, while the rotor 3 shown in FIG. 4 in that it is inclined toward the surface of the shaft 15 on the rotation direction R side of the rotor 3 and sometimes further outwardly from the surface of the shaft 15. Due to this inclination, the depth of the fitting groove 11 is made deeper than the depth of the fitting groove 11 shown in FIG. 4, so that the movable wing 10 is made of a thinner plate and made of a lower specific gravity metal. Also, an appropriate centrifugal force is applied to the movable wing 10 to maintain the pressing force of the tip of the movable wing 10 against the inner peripheral surface of the cylinder 2. The movable wing 10 used for the rotor 3 shown in FIGS. 3 to 5 has, for example, a non-metallic material such as ceramics, which has a larger specific gravity than carbon or resin, a copper-based material, a non-ferrous material other than the copper-based material, It is made of metal including alloys such as iron.

The rotor 3 shown in FIG. 6 is for the above-mentioned E and F types, and has a remarkably low specific gravity as compared with metal and is easily worn, such as carbon, bakelite, other resins, and fiber reinforcement. Since the movable wing 10 made of resin or the like is used, the aspect is different from the above case, and an appropriate value is set so that the tip of the movable wing 10 is worn as little as possible and the required tip of the movable wing 10 is pressed. Centrifugal force of movable wing 10
Has an arrangement of fitting grooves 11 for providing the same.

The above-described cut groove 13 provided on the back wall 12 of the fitting groove 11 is first formed from the open end 13oe of the cut groove 13 to the groove bottom 11bm according to the rotation of the rotor 3.
To form a fluid introduction channel. Next, through this flow path, the cut groove 13 diffuses the fluid into the gap between the back wall 12 of the fitting groove 11 and the surface of the movable wing 10 facing the same,
A fluid film is formed in this gap. These have the effects described below.

That is, first, when observing the form of wear of the conventional movable wing 10, remarkable rubbing marks are generated on the rear wall 20 of the movable wing 10 that slides facing the rear wall 12 of the fitting groove 11. That is, the front wall of the movable wing 10 hardly shows any rubbing wear marks, or even if rubbing wear marks are found, the degree is very small. This means that the fluid pressure in the front chamber in the rotation direction R of the adjacent chambers is higher than the fluid pressure in the rear chamber, so that the force corresponding to the pressure difference is opposite to the rotation direction R. This is based on acting on the front wall of the movable wing 10 as a force.

As shown in FIG. 1, when the external fluid is sucked into the blade chamber from the suction hole 6 through the suction port 4 with the rotation of the rotor 3 as is apparent from FIG.
Move at high speed from 1 to the outside. At this time, the space between the cut groove 13 and the rear wall of the movable wing 10 exhibits a vacuum state. As a result, the fluid in the blade chamber flows from the opening end 13oe of the cut groove 13 toward the groove bottom 11bm of the fitting groove 11. That is, the notch 13 forms a fluid introduction flow path.

Third, the fluid introduced by the slit 13 diffuses into the gap between the rear wall 12 of the fitting groove 11 and the rear wall 20 of the movable wing 10 against the pressure from the front blade chamber. And
A fluid film is formed in this gap. This fluid film forms a fluid lubricating film between two opposing surfaces of the back wall 12 and the back wall 20, similarly to the fluid lubrication of the bearing.

Fourth, when the blade chamber that has taken in the external fluid heads toward the discharge port 5, the movable blade 10 moves inward from the fitting groove 11 at a high speed. At that time, the back surface of the movable wing 10 moving inward from the wing chamber filled with the high-pressure fluid at a high speed,
The viscous fluid is drawn from the open end 13oe of the cut groove 13 toward the groove bottom 11bm of the fitting groove 11. This retraction operation continues until the movable wing 10 reaches the end of the discharge port 5.

After that, the groove 13 forms a fluid introduction passage, and the introduced fluid is fluid-lubricated between two opposing surfaces of the back wall 12 and the back wall 20. Form a film. By forming these fluid lubricating films,
Rubbing and abrasion of the rear wall 20 of the movable wing 10 is significantly reduced as compared with the conventional apparatus. At the same time, the rubbing wear of the back wall 12 of the fitting groove 11 is greatly reduced.

Fifth, in a gas device for supplying lubricating oil, since the fluid lubricating film plays a role of lubricating oil, the use of lubricating oil is limited only to the suppression of wear of the tip of the movable blade 10. The amount of lubricating oil used can be significantly reduced compared to the conventional case.

Sixth, the space formed between the inner end of the movable wing 10 which moves outward at a high speed and the groove bottom 11bm of the fitting groove 11 has a vacuum state in the conventional apparatus. On the other hand, by providing the cut groove 13 forming the fluid introduction flow path, the fluid can be quickly taken into the space, and the effect of relaxing the vacuum state or preventing the occurrence of the vacuum state can be obtained.

Since the vacuum state acts to push the movable wing 10 back inward, the tip of the movable wing 10 does not sufficiently press the inner surface of the cylinder 2, and as a result, the rotational direction R of the movable wing 10 Fluid in the front tends to leak rearward, and the operating efficiency of the device decreases. Therefore, relaxation of the vacuum state or prevention of the generation of the vacuum state improves the operation efficiency of the apparatus.

The seventh is, on the contrary, the inner end of the movable wing 10 moving inward at a high speed and the groove bottom 11 of the fitting groove 11.
The space formed between the bm and the bm exhibits a high pressure state in the conventional device, but the provision of the cut groove 13 allows the fluid to be quickly discharged from the space, alleviating the high pressure state, or This has the effect of preventing the occurrence of a high pressure state.

This high pressure state strongly presses the movable wing 10 against the inner surface of the cylinder 2, thereby promoting the wear of the tip surface of the movable wing 10 that slides on the inner peripheral surface of the cylinder 2 at high speed. Therefore, the relief of the high-pressure state or the prevention of the occurrence of the high-pressure state alleviates the wear of the tip surface of the movable blade 10.

In order to form a fluid lubricating film as wide as possible around the rotational direction R of the rotor 3, the starting end of the suction port 4 and the ending of the discharge port 5 should be as close as possible, as shown in FIG. Is preferred. The above-described operation and effect provided by the cut groove 13 are the same regardless of whether the fluid is a gas or a liquid.

The details of the cut groove 13 suitably have the following configuration. First, as shown by broken lines in FIGS. 3 to 6, the cut groove 13 has an inner end near the groove bottom 11bm of the fitting groove 11, and as shown in FIGS.
Is a straight groove, and the back side opening edge 1 of the fitting groove 11
It becomes an arrangement orthogonal to 1oe. These contribute to the advantageous formation of the fluid lubricating film and the quick inflow and outflow operations of the fluid.

Next, referring to FIG. 7, the rear wall 1 of the fitting groove 11 is divided into a plurality of locations, in the illustrated example, at four locations where the cut groove 13 is divided.
2, both end regions 12 of the rotor 3 in the X-axis direction.
The area where S ₁ and 12S ₂ are such that (area of 12S ₁ ) ≒ (area of 12S ₂ ), that is, they have uniform areas, and are sandwiched by two adjacent cut grooves 13. 12M, the total area of both end regions 12S _1, 12S _2,
So as to have one area or equivalent and approximate (area 12S ₁₎ + (area of 12S _2), notches 13
Place. Naturally, the areas of the plurality of regions 12M are equal to or close to each other. Such arrangement of the cut grooves 13 contributes to the formation of a uniform distribution of the fluid lubricating film.

Next, referring to FIG. 8, the cut groove 13 has a branch groove 13B in the middle of the cut. This branch groove 13
B, when the pressure difference between the rear wing chamber of the forward wing chamber is relatively large, also regions 12S _1, 12S _2, when a relatively large area of 12M, assisting the uniform distribution formation fluid lubricating film Play a role. The number, the inclination angle, the inclination direction, and the like of the branch grooves 13B may be freely set as appropriate, and the opposing branch grooves 13B may be connected to each other as needed.

Next, referring to FIG. 9, the cut groove 13 and the branch groove 13B are formed so that the back wall 1 of the fitting groove 11 is
2 has a cross-sectional shape of Suehiro. In particular,
The connection with the back wall 12 is preferably formed by an arc having a radius of curvature r. This helps the fluid to smoothly diffuse between two opposing surfaces of the rear wall 12 and the rear wall 20.

Finally, although not shown, the notch 13
It is also preferable to have a chamfer at the open end of the rotor 3. The reason for this is that widening the opening end, which is the fluid intake port of the cut groove 13, is advantageous for fluid introduction even in the rotation process of any rotor 3.

The rotor 3 of the movable airfoil rotating apparatus 1 described above
The configuration is effective in solving the abrasion problem regardless of whether it is applied to a vane type fluid pressurizing device or a fluid depressurizing device, and in practice, a gas such as a vane type compression device, a vane type blower device, or a vane type vacuum device is used. Compression (pressure), gas feed,
It shall be used for all liquid devices for liquid pressurization and liquid feed, such as a gas device for gas decompression and a vane type hydraulic pump device. However, among the vane type hydraulic pump devices, a device called an equilibrium type vane pump follows the description below.

That is, the balanced vane pump has a configuration in which a cam ring having an elliptical cross section provided with a suction port and a discharge port for a fluid, and a rotor sharing the same axis in the cam ring. This configuration will be briefly described with reference to FIGS. 1 and 2. The balanced vane pump includes a cam ring having a substantially elliptical cross section instead of the cylinder 2,
However, a point that the center axis of the rotor 3 coincides with the center axis of the cam ring is basically different from the movable airfoil rotating apparatus 1 described above. The operating principle of the movable wing 10 is the same. Therefore, duplicate description will be avoided.

[0045]

According to the inventions described in claims 1 to 8 of the present invention, it is possible to perform a simple notching process on the fitting groove of the rotor without using an additional device at an extremely low cost. Compared to the conventional device, it is possible to greatly reduce the rubbing wear of the movable wings and the rubbing wear of the rotor fitting groove, especially the former rubbing wear, and greatly improve the operation efficiency of the device. In addition, it is possible to provide a movable airfoil rotating device capable of significantly reducing the amount of lubricating oil used in a device for supplying lubricating oil.

[Brief description of the drawings]

FIG. 1 is a front sectional view of a movable airfoil rotating apparatus according to the present invention.

FIG. 2 is a side sectional view of the device shown in FIG. 1, taken along the line II-II.

FIG. 3 is a side view and a front view of the rotor of the present invention excluding a movable wing.

FIG. 4 is a side view and a front view of another rotor of the present invention excluding a movable wing.

FIG. 5 is a side view and a front view of another rotor of the present invention excluding a movable wing.

FIG. 6 is a side view and a front view of still another rotor of the present invention excluding a movable wing.

FIG. 7 is a side view of the back wall of the fitting groove along the line IIV-IIV shown in FIGS. 3 to 6;

FIG. 8 is a side view of another fitting groove rear wall along the line IIV-IIV shown in FIGS. 3 to 6;

FIG. 9 is an enlarged sectional view taken along line IX-IX shown in FIGS. 7 and 8;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Movable airfoil rotating device 2 Cylinder 3 Rotor 3sf Rotor surface 4 Suction port 5 Discharge port 6 Fluid suction hole 7 Fluid discharge hole 10 Movable wing 11 Fitting groove 11bm Groove bottom 11oe Fitting groove Back side opening edge 12 Fitting groove back Wall 13 Cut groove 13B Branch groove 13oe Cut groove open end 15 Rotor shaft 20 Moving blade back wall R Rotor rotation direction X axis

Claims (8)

[Claims] 1. A cam ring having an elliptical cross section including a cylinder having a fluid suction port and a discharge port, a rotor eccentrically located in the cylinder, and an elliptical cross-section having a fluid suction port and a discharge port. And a rotor that shares the same axis with the rotor. The rotor includes one or more movable blades extending in the axial direction of the rotor, and a movable airfoil rotor including the sliding fitting groove. In the apparatus, a rotor is provided on a rear wall of the fitting groove as viewed in the rotation direction.
A movable airfoil rotating apparatus comprising: at least one notch groove, wherein the notch groove is open on the rotor surface and continuously extends from the open end toward the fitting groove bottom. 2. The cut groove has a function of forming a fluid introduction flow path from an open end toward the bottom of the fitting groove in accordance with the rotation of the rotor. The movable airfoil rotating apparatus according to claim 1, having a function of diffusing a fluid into a gap between the wall and the movable blade face facing the wall to form a fluid film in the gap. 3. The movable airfoil rotating apparatus according to claim 1, wherein the cut groove is a straight groove having an inner end near the bottom of the fitting groove. 4. The movable airfoil rotating apparatus according to claim 1, wherein the cut groove is arranged to be orthogonal to an opening edge of the fitting groove. 5. With respect to the area of the plurality of fitting groove rear walls divided by the cut groove, both end regions in the rotor axial direction have a uniform area with each other, and a region sandwiched by two adjacent cut grooves is: The movable airfoil rotating device according to any one of claims 1 to 4, wherein the movable airfoil rotating device has one of an area equal to or approximate to a total area of both end regions. 6. The movable airfoil rotating apparatus according to claim 1, wherein the cut groove has a branch groove in the middle of the cut. 7. The movable airfoil rotation according to claim 1, wherein the cut groove and the branch groove have a divergent cross-sectional shape from the groove bottom toward the back wall of the fitting groove. apparatus. 8. The movable airfoil rotating apparatus according to claim 1, wherein the cut groove has a chamfer at an open end of the rotor.