JP2021168635A - Combine harvester - Google Patents

Abstract

To provide a combine harvester capable of increasing a capacity of a fuel tank without changing a shape and arrangement of a threshing device and a grain tank.SOLUTION: There is provided the combine harvester comprising: a threshing device 4 for thresh processing the harvested crops; a grain tank 5 arranged laterally side by side to the threshing device 4 and stores the grain obtained by the threshing device 4; and a fuel tank 10 arranged in a space between the threshing device 4 and the grain tank 5. A downward-narrowing section 5U having a downward-narrowing shape in a machine body lateral direction below the grain tank 5. The fuel tank 10 includes a first section arranged in a state entering in a lower space 5S below the downward-narrowing section in the space, and a second section arranged in the rearward of the first section and projecting behind a rear end of the grain tank. The second section overlaps the grain tank in a rear view so that the cross sectional shape of the second section is larger than the first section in the rear view.SELECTED DRAWING: Figure 3

Description

The present invention relates to a combine equipped with a fuel tank.

Conventionally, the threshing device and the grain tank are provided side by side, and the fuel tank is a constricted lower part provided at the lower part of the grain tank in the space between the threshing device and the grain tank. There was a combine harvester provided in a state of entering the lower space below the constriction (see Patent Document 1).

Japanese Unexamined Patent Publication No. 2016-049095

Further, in the configuration of Patent Document 1, the fuel tank has a shape corresponding to the shape of the lower space of the lower constriction portion and is arranged in the lower space of the lower constriction portion. Although it was possible to effectively utilize the space below the lower constriction of the lower constriction provided at the bottom, the cross-sectional shape of the fuel tank when viewed from the rear is almost the same shape at any point in the front-rear direction of the aircraft. It was formed in. Furthermore, in order to increase the capacity of the fuel tank, it was necessary to change the shape and arrangement of the threshing device and the grain tank.

Therefore, in view of the above problems, it is an object of the present invention to provide a combine capable of increasing the capacity of the fuel tank.

The combine of the present invention includes a threshing device for threshing harvested crops, a grain tank provided side by side with the threshing device and storing grains obtained by the threshing device, and the threshing device. A fuel tank provided in a space between the grain tank and the fuel tank is provided, and a lower constriction portion having a lower constriction shape in the left-right direction of the machine body is provided at the lower part of the grain tank, and the fuel tank is provided with a lower constriction portion. The first portion provided in the space so as to enter the lower space below the lower constriction portion, and the first portion provided behind the first portion and projecting rearward from the rear end portion of the grain tank. The second portion overlaps with the grain tank in the rear view so that the cross-sectional shape in the rear view is larger than that in the first portion.

According to the present invention, by arranging the first portion of the fuel tank so as to enter the lower space below the lower constriction portion, the lower space can be effectively utilized and the second portion of the fuel tank can be effectively utilized. However, since the cross-sectional shape in the rear view is larger than that of the first part, the shape and arrangement of the grain removing device and the grain tank are not changed, and the cross-sectional shape is rearward of the rear end of the grain tank. It will be possible to increase the capacity of the fuel tank by utilizing an existing space.

In the present invention, it is preferable that a chamfered portion is provided at the upper corner portion of the second portion, and the refueling portion for refueling the fuel tank extends from the chamfered portion.

According to this configuration, when connecting the refueling part to the fuel tank in the manufacturing process of the fuel tank, the refueling part is simply connected to the chamfered part to the flat chamfered part formed in the upper corner part. This process makes it possible to easily manufacture a fuel tank provided with a refueling unit. Further, since the refueling unit is provided so as to extend from a position lower than the upper surface portion of the fuel tank, the height of the refueling position is lowered as compared with the case where the refueling unit is provided on the upper surface portion of the fuel tank. It becomes possible.

In the present invention, it is preferable that the refueling portion extends obliquely upward from the chamfered portion.

According to this configuration, since the refueling section is extended diagonally upward, it is possible to prevent the inconvenience that the refueled gasoline or the like smoothly flows into the fuel tank and the gasoline or the like stays in the refueling section. Further, the refueling section may be connected so as to extend in a direction close to the direction perpendicular to the surface of the chamfering section, and when connecting the refueling section to the fuel tank in the fuel tank manufacturing process, precision is required. Since no fuel tank is required, it is possible to easily manufacture a fuel tank provided with a refueling unit.

In the present invention, the upper corner portion of the second portion is provided with a recessed portion recessed toward the inside of the fuel tank, and the refueling portion for refueling the fuel tank is provided from the recessed portion. It is preferable that it is extended.

According to this configuration, the capacity of the fuel tank and the height position of the refueling portion can be easily adjusted by adjusting the depth of the recessed portion at the time of designing. Further, since the refueling unit is provided so as to extend from a position lower than the upper surface portion of the fuel tank, the height of the refueling position is lowered as compared with the case where the refueling unit is provided on the upper surface portion of the fuel tank. It becomes possible.

In the present invention, the fuel tank is made of resin, the upper portion in the first portion is formed in a flat shape, and the upper corner portion on the side of the grain tank in the first portion is the lower constricted portion. The upper portion of the second portion is formed in an inclined shape along the inclined shape of the first portion, has a left-right width extending to the upper portion of the first portion and the upper corner portion in the left-right direction, and is the same as the upper portion of the first portion. It is preferable that the shape is continuous and flat.

According to this configuration, the upper corner portion on the grain tank side in the first portion is formed in an inclined shape along the inclined shape of the lower constriction portion, so that the shape of the first portion is the lower constriction of the grain tank. The shape is such that the space below the constriction can be used efficiently. Further, the upper part of the second part has a left-right width extending to the upper part of the first part and the upper corner part on the side of the grain tank in the left-right direction, so that the left-right width of the upper part of the second part is the upper part of the first part. The configuration is larger than the left and right width. As a result, it is possible to increase the capacity of the fuel tank. Furthermore, the upper part of the first part and the upper part of the second part are formed in a continuous flat shape to have a simple shape, and since the fuel tank is made of resin, it is possible to facilitate manufacturing. Become.

In the present invention, the fuel tank is wound around a fixing band while being mounted on the airframe frame, and is fastened and fixed to the airframe frame by the fixing band. The fuel tank is made of resin, and the fuel tank is made of resin. It is preferable that a band groove into which the fixed band enters is formed in the first portion and the second portion.

According to this configuration, the fuel tank that is stably supported by the airframe frame is fixed to the airframe frame by winding the fixing band, so that the fuel tank is fixed in a more stable state and further fixed. Since the band is tightened so as to enter the band groove, it is possible to prevent the fixed band from shifting in the fuel tank. Further, since the fuel tank is made of resin, even if the fuel tank has a complicated shape as described above, it can be easily manufactured.

In the present invention, the bottom of the fuel tank is provided with a bulging portion that bulges downward, and the bulging portion is provided with a supply port for supplying fuel inside the fuel tank to the engine. It is preferable to have it.

According to this configuration, the capacity of the fuel tank can be further increased by providing the expansion portion at the bottom of the fuel tank. Further, since the supply port is provided at the lowest position of the fuel tank, the fuel in the fuel tank can be used up to the end, and the fuel in the fuel tank can be used efficiently.

In the present invention, the fuel tank is mounted and supported on the fuselage frame at the rear part of the fuselage, and the fuel tank is mounted and supported on the fuselage frame in a state parallel to the first frame and the first frame. A second frame provided is provided, and a mounting portion to be mounted on the first frame is provided at a portion corresponding to the first frame in the peripheral portion of the bulging portion at the bottom portion. The bulging portion is dropped between the first frame and the second frame in a state where the lowermost end of the bulging portion is located within the vertical width of the first frame and the second frame. It is preferable to have.

Since the expansion portion has a structure that expands downward of the fuel tank, it is provided at a position close to the ground and easily colliding with an obstacle such as a rock. According to the present invention, the bulging portion is located between the first frame and the second frame provided in the airframe frame, and the bottom portion of the expanding portion is the first frame and the second frame. Since it is located above the lower end portion, the expansion portion is protected by the first frame and the second frame in the event of a collision with an obstacle from either the horizontal direction or the downward direction.

In the present invention, a protective plate located below the bulging portion and protecting the bulging portion is provided, and the protective plate is provided at the lower end portion of the first frame and the lower end portion of the second frame. It is preferable that the first frame and the second frame are supported in a stretched state.

According to this configuration, the protective plate is firmly supported and fixed by being supported by the first frame and the second frame provided in the airframe. Further, as compared with the case where the protective plate is not provided, the expansion portion is configured to be firmly protected in the event of a collision with an obstacle from below.

In the present invention, the fuel tank is mounted and supported on the airframe frame, and is mounted on the airframe frame, behind the bulge portion, and overlaps with the bulge portion in a rear view, along the left and right directions of the airframe. It is preferable that an extending horizontal frame is provided.

According to this configuration, the horizontal frame makes it possible to prevent the collision between the obstacle and the bulging portion when the aircraft is moving backward.

In the present invention, a fuel auxiliary machine is provided in a region behind the grain tank and on the side of the fuel tank, the bulging portion is provided at the bottom of the second portion, and the fuel tank is provided. A refueling unit for refueling the fuel tank is provided on the upper part of the second portion, and the supply port is a side portion of the bulging portion on the side where the fuel auxiliary machine is located with respect to the fuel tank. Therefore, it is preferable that the fuel auxiliary machine extends along the horizontal direction toward the side where the fuel auxiliary machine is located with respect to the fuel tank.

According to this configuration, since the refueling unit and the supply port are provided in the second portion, the fuel auxiliary equipment such as the fuel filter and the fuel pump and the refueling unit are arranged side by side in a plan view. .. Therefore, in the maintenance work and the refueling work of the fuel auxiliary machine, the worker hardly needs to change the work place, so that the work can be performed efficiently.

Further, since the supply port extends along the horizontal direction toward the side where the fuel auxiliary machine is located, it is possible to simplify the configuration of the piping or the like connecting the supply port and the fuel auxiliary machine. ..

In the present invention, the fuel tank is provided with a first tank structure and a second tank structure divided by a dividing surface along the vertical direction, and the fuel tank is the first tank structure and the first tank structure. The two tank components are connected to each other, and the divided surface passes through the bulging portion, so that the bulging portion is formed between the first bulging body on the side of the first tank structure and the second bulging portion. It is divided into a second bulge on the side of the tank structure, and the width of the first bulge is the first width of the first bulge and the second bulge with the divided surface interposed therebetween. It is configured to be larger than the width of the two bulges, and the bottom of the first bulge and the bottom of the second bulge are formed in an inclined shape that is inclined downward toward the divided surface side. It is preferable that the supply port extends along the horizontal direction from the side portion of the second bulge that is located on the side opposite to the first bulge. ..

According to this configuration, since the fuel tank is composed of a plurality of components, it is possible to more easily manufacture the fuel tank in a large-sized fuel tank as compared with the case where the fuel tank is integrally configured. Further, the divided surfaces of the first tank structure and the second tank structure are formed along the vertical direction so as to pass through the bulging portion, and the bottom portion of the bulging portion is on the side of the dividing surface. It is configured to spread as you go. As a result, the first tank structure and the second tank structure are configured so that the die can be easily removed and the bulging portion can be firmly molded even in, for example, molding with a die or press working.

Further, the inclined surface at the bottom of the first bulge is larger than the inclined surface at the bottom of the second bulge. Therefore, the fuel that has flowed into the bulge mainly flows down on the inclined surface at the bottom of the first bulge and flows into the supply port provided in the second bulge, so that the engine is surely engineered. It becomes possible to supply fuel to.

It is a side view which shows the ordinary type combine. It is a top view which shows the ordinary type combine. It is a rear view which shows the ordinary type combine. FIG. 1 is a cross-sectional view taken along the line IV-IV of FIG. It is a top view which shows the fuel tank. It is a rear view which shows the fuel tank. FIG. 1 is a cross-sectional view taken along the line VII-VII of FIG. It is a perspective view which shows the fuel tank. It is a perspective view which shows the fuel tank.

A mode for carrying out the present invention will be described with reference to the drawings. In the following description, FIGS. 3 to 9 show the direction of the arrow F shown in FIGS. 1, 2, 5, 8, and 9 as "front" and the direction of arrow B as "rear". Let the direction of the arrow L be "left" and the direction of the arrow R be "right". Further, the direction of the arrow U shown in FIGS. 1, 3, 4, 6, and 7 is defined as "up", and the direction of the arrow D is defined as "down".

[About the overall configuration of the ordinary combine]
As shown in FIGS. 1 and 2, the ordinary combine harvester includes a cutting unit 1, a feeder 2, an operating unit 3, a threshing device 4, a grain tank 5, a grain discharging device 6, and an engine E. And have.

The cutting section 1 for cutting the planted grain culms in the field is provided at the front portion of the combine harvester. A feeder 2 and a driving unit 3 are provided on the rear side of the cutting unit 1. The feeder 2 conveys the cut grain culm cut by the cutting unit 1 to the threshing device 4.

The threshing device 4 is located behind the feeder 2. The harvested culm transported by the feeder 2 is threshed by the threshing device 4. The threshing device 4 includes a sorting processing device (not shown) that sorts grains from the processed product obtained by the threshing treatment. Among the grains sorted by the sorting processing device, the first grain is conveyed to the grain tank 5 by the grain raising device 41, and the second grain is transported to the grain tank 5 by the second reduction processing device 42 in the handling room of the threshing device 4 (shown). Is returned to. A culm treatment device 7 is connected to the rear part of the threshing device 4. The culm processing device 7 is configured to shred the culm discharged from the threshing device 4.

The grain tank 5 is arranged side by side with the threshing device 4. The grains obtained by the threshing treatment in the threshing device 4 are stored in the grain tank 5. The grain tank 5 is provided with an upper rear surface portion 5c above the rear surface of the grain tank 5 and a lower rear surface portion 5d below the rear end surface of the grain tank 5, and the upper rear surface portion 5c is a lower rear surface portion. It is configured to be located behind 5d. As shown in FIG. 3, a lower constriction portion 5U formed in a lower constriction shape in the left-right direction of the machine body is provided in the lower part of the grain tank 5. The lower constriction portion 5U has an inclined surface 5a on the fuel tank 10 side and an inclined surface 5b on the outside of the airframe in the left-right direction of the airframe. 5 It is configured to incline toward the inside.

The grain discharge device 6 is connected to the lower rear portion of the grain tank 5. The grain discharge device 6 includes a vertical transport section 6A for transporting grains upward and a horizontal transport section 6B for laterally transporting grains from the upper end of the vertical transport section 6A and discharging the grains from the discharge port at the tip. It is equipped (see Fig. 1). The vertical transport unit 6A includes a first support column 26a erected from the airframe frame 20 on the left side of the vertical transport unit 6A, and a second support column 26b erected from the airframe frame 20 behind the vertical transport unit 6A. Is supported by. The grains stored in the grain tank 5 are discharged to the outside of the machine by the grain discharging device 6 as needed.

An exhaust port 8a of an exhaust pipe 8 through which exhaust gas from the engine E (see FIG. 1) flows is arranged in the upper part of the space between the threshing device 4 and the grain tank 5. The workbench 9 is provided so as to be located above the exhaust pipe 8 and the exhaust port 8a and to extend in the front-rear direction of the machine body. The workbench 9 is provided over a position corresponding to the front end portion of the threshing device 4 and a position corresponding to the rear end portion of the grain tank 5.

[About the arrangement of fuel tanks]
As shown in FIG. 4, the resin fuel tank 10 is arranged in the space between the threshing device 4 and the grain tank 5 so as to enter the lower space 5S below the inclined surface 5a. As shown in FIG. 5, the fuel tank 10 is provided behind the first portion 10F and the first portion 10F that enter the lower space 5S, and is behind the rear end portion of the lower rear surface portion 5d of the grain tank 5. It is provided with a second portion 10B protruding from the surface.

The front end of the fuel tank 10 is located near the rear end of the case 42a of the second reduction treatment device 42. The first portion 10F is located at the rear end of the workbench 9 and below the exhaust port 8a (see FIG. 1). The rear end portion of the fuel tank 10 projects to the rear side from the rear end portion of the grain tank 5, and is located at substantially the same position as the rear end portion of the airframe frame 20.

[About the configuration of the fuel tank]
The upper portion of the first portion 10F is formed in a flat shape, and the upper portion of the second portion 10B is formed in a flat shape continuous with the upper portion of the first portion 10F. A refueling unit 13 for refueling the fuel tank 10 is provided in the second portion 10B of the upper part of the fuel tank 10.

As shown in FIG. 8, in the fuel tank 10, an inclined surface 10a having an inclined shape along the inclined surface 5a of the grain tank 5 is formed at an upper corner portion on the side of the grain tank 5 in the first portion 10F. On the other hand, the second portion 10B is not formed with an inclined surface such as the inclined surface 10a. Further, the left-right width Wc of the upper part of the second part 10B has the same left-right width as the sum of the left-right width Wa of the upper part of the first part 10F and the left-right width Wb of the upper corner part of the first part 10F in the left-right direction of the aircraft. As shown in FIG. 7, in the rear view, the second portion 10B is formed in a substantially rectangular shape having the same height as the first portion 10F. Therefore, in the rear view, the second portion 10B has a larger cross-sectional shape than the first portion 10F, and when the fuel tank 10 is installed on the airframe, the upper corner portion of the second portion 10B is a grain. It overlaps with the tank 5 in the rear view.

As shown in FIGS. 8 and 9, a fuel sensor mounting portion 17 for mounting a fuel sensor (not shown) for detecting the remaining amount of fuel is provided above the fuel tank 10.

The fuel tank 10 is provided with a first tank configuration 10L and a second tank configuration 10R divided by a dividing surface 10C along the vertical direction, and the fuel tank 10 has a first tank configuration 10L and a second tank configuration. It is configured by connecting the body 10R. On the lower surface portion and the rear surface portion of the fuel tank 10, the divided surface 10C linearly passes through a substantially central portion of the fuel tank 10 in the left-right direction of the airframe. In the upper surface portion of the fuel tank 10, the split surface 10C extends substantially at the center of the fuel tank 10 in the left-right direction from the rear surface portion toward the front surface portion so as to bypass the fuel sensor mounting portion 17 and the inclined surface 10a. It bends to the left and extends toward the front again. Further, the front portion of the fuel tank 10 extends downward. At the upper part of the front surface of the fuel tank 10, the split surface 10C is bent to the right, returns to a substantially central portion in the left-right direction of the airframe, and then extends downward again. With this configuration, the fuel sensor mounting portion 17 is arranged in the second tank configuration 10R.

[About the configuration of the refueling section]
As shown in FIG. 6, the refueling unit 13 has a tubular portion 13a extending from the upper part of the second portion 10B of the fuel tank 10 and a refueling port 13b provided at the protruding end of the tubular portion 13a. doing. A chamfered portion 10b is formed in the upper corner portion of the second portion 10B on the side of the grain tank 5, and the tubular portion 13a is provided in the chamfered portion 10b. The tubular portion 13a is provided so as to extend obliquely upward from the chamfered portion 10b.

[About the support configuration of the fuel tank]
As shown in FIG. 5, the fuel tank 10 is mounted and supported on the airframe frame 20 at the rear part of the airframe. The fuel tank 10 is fixed to the airframe frame 20 by two front and rear fixing bands 23. The fixing band 23 is a band-shaped member, and the fuel tank 10 is fastened and fixed to the machine frame 21 by winding the fixing band 23 while being mounted on the body frame 20.

A band groove 14 into which the fixed band 23 enters is formed in the first portion 10F and the second portion 10B. The fixing band 23a is wound in the first band groove 14a formed in the first portion 10F, and the fixing band 23b is wound in the second band groove 14b formed in the second portion 10B. A plurality of supports 25 are provided on the machine frame 20, and both ends of the fixing band 23 are fixed to the supports 25 by bolts 31.

The airframe frame 20 is composed of a plurality of front-rear frame bodies 20A and a plurality of lateral frame bodies 20B provided in parallel. In the present embodiment, one of the plurality of front-rear frame bodies 20A is configured as a lower frame 20C that supports the plurality of lateral frame bodies 20B from below.

The fuel tank 10 is mounted and supported on two of the plurality of lateral frame bodies 20B, and the two horizontal frame bodies 20B are the bottom of the first portion 10F of the fuel tank 10 and the first portion of the fuel tank 10, respectively. It is arranged so as to correspond to the bottom of the two parts 10B. The first mounting portion 11 is provided on the portion of the bottom of the first portion 10F that is mounted on one of the lateral frame bodies 20B, and is mounted on the other lateral frame body 20B of the bottom of the second portion 10B. A second mounting portion 12 is provided in the portion. As shown in FIGS. 6 and 7, the first mounting portion 11 and the second mounting portion 12 are respectively mounted and supported on the two lateral frame bodies 20B via the tapered support member 32. There is.

[About the configuration of the bulge]
At the bottom of the second portion 10B, a bulging portion 15 that bulges downward from the fuel tank 10 is provided. The bulging portion 15 has a supply port 16a for supplying the fuel in the fuel tank 10 to the engine E (see FIG. 1) and a return port 16b for returning the return fuel from the engine E to the fuel tank 10 (FIG. 1). 5) and are provided.

As shown in FIG. 6, the dividing surface 10C passes through the bulging portion 15, and the bulging portion 15 is the first bulging body 15L on the side of the first tank component 10L and the second tank component 10R. It is divided into a second bulging body 15R on the side of the above. The first swelling body 15L and the second swelling body 15R are configured such that the width of the first swelling body 15L is larger than the width of the second swelling body 15R with the divided surface 10C interposed therebetween. An inclined surface 15La is provided at the bottom of the first bulging body 15L, an inclined surface 15Ra is provided at the bottom of the second bulging body 15R, and the inclined surface 15La and the inclined surface 15Ra are directed toward the side of the dividing surface 10C. It is formed in an inclined shape with a downward inclination.

A fuel auxiliary machine 30 such as a fuel filter device is provided in a region behind the grain tank 5 and on the side of the fuel tank 10 on the side of the second bulge 15R. The fuel auxiliary machine 30 is supported by the first support column 26a. Of the side portions of the second bulging body 15R, the side portion located on the side opposite to the first bulging body 15L is provided with a port mounting surface 15Rb provided with a supply port 16a, and the supply port 16a is provided with a port mounting surface 15Rb. The fuel tank 10 is provided on the side of the fuel auxiliary machine 30 on the side where the fuel auxiliary machine 30 is located. The supply port 16a is formed so as to extend in the horizontal direction toward the side where the fuel auxiliary machine 30 is located with respect to the fuel tank 10.

[Regarding the positional relationship between the bulge and the fuselage frame]
As shown in FIGS. 5 to 8, the airframe frame 20 is provided with a first frame 20Ba located around the bulging portion 15 and a second frame 20Bb provided in parallel with the first frame 20Ba. ing. In the present embodiment, the first frame 20Ba is composed of a sideways frame body 20B corresponding to the second mounting portion 12 of the fuel tank 10, and the first frame 20Ba is formed on the peripheral portion of the bulging portion 15 at the bottom of the fuel tank 10. The configuration is such that the two mounting portions 12 are located. The second frame 20Bb is located behind the bulging portion 15, and the bulging portion 15 is in a state where the lowermost end of the bulging portion 15 is located within the vertical width of the first frame 20Ba and the second frame 20Bb. It is configured to be dropped between the first frame 20Ba and the second frame 20Bb.

The fuselage frame 20 is provided with a horizontal frame 20Bc extending along the left and right methods of the fuselage behind the bulging portion 15 so as to overlap the bulging portion 15 in a rear view. In the present embodiment, the horizontal frame 20Bc is composed of the second frame 20Bb.

In the bulging portion 15, the bulging portion side frame 20Aa provided with the bulging portion contact surface body 20Ab that abuts on the bulging portion 15 on the side facing the side portion provided with the supply port 16a. Is provided. The bulging portion side frame 20Aa is provided so as to extend in the front-rear direction of the machine body. The bulging portion contact surface body 20Ab is supported on the upper portion of the bulging portion side frame 20Aa, extends toward the bulging portion 15, and is formed in a shape corresponding to the side portion of the bulging portion 15. The bulging portion 15 is placed and supported on the bulging portion contact surface body 20Ab.

A protective plate 24 that protects the fuel tank 10 is provided below the bulging portion 15. The protective plate 24 is supported by the first frame 20Ba and the second frame 20Bb in a state extending over the lower end portion of the first frame 20Ba and the lower end portion of the second frame 20Bb. The protective plate 24 makes it possible to prevent a collision with an obstacle from below. Further, even if there is a combustible material below the bulging portion 15, it is protected by the protective plate 24, so that the fire resistance can be improved.

[Another Embodiment]
Hereinafter, another embodiment in which the above embodiment is modified will be illustrated. The following alternative embodiments may be applied to the above embodiments in combination as long as there is no contradiction. The scope of the present invention is not limited to the contents of each embodiment.

(1) In the above embodiment, the second portion 10B has the same height as the first portion 10F in the rear view, and the left-right width Wc of the upper portion of the second portion 10B is the upper portion of the first portion 10F in the left-right direction of the aircraft. Although the configuration having the same left-right width as the sum of the left-right width Wa and the left-right width Wb of the upper corner portion of the first portion 10F has been described as an example, the present invention is not limited to the above embodiment. The second portion 10B may have a larger cross-sectional shape in the rear view than the first portion. For example, the second portion 10B may have a configuration having a height higher than that of the first portion 10F in the rear view. The left-right width Wc of the upper part of the second part 10B has a configuration having a left-right width wider than the sum of the left-right width Wa of the upper part of the first part 10F and the left-right width Wb of the upper corner part of the first part 10F in the left-right direction of the aircraft. You may be.

(2) In the above embodiment, the upper part of the first part 10F and the upper part of the second part 10B are formed in a flat shape, and the upper part of the second part 10B is above the upper part of the first part 10F and the first part 10F in the left-right direction. Although the configuration having a left-right width extending over the corner portion and being formed in a flat shape continuous with the upper part of the first portion 10F has been described as an example, the present invention is not limited to the above embodiment. For example, either or both of the upper portion of the first portion 10F and the upper portion of the second portion 10B may be configured in a shape having no flat surface. Further, the upper part of the first part 10F and the upper part of the second part 10B do not have to be formed in a continuous flat shape, and the upper part of the second part 10B is the upper part of the first part 10F and the upper part of the first part 10F in the left-right direction. It does not have to have a left-right width extending over the upper corner.

(3) In the above embodiment, the configuration in which the chamfered portion 10b is provided at the upper corner of the second portion 10B of the fuel tank 10 and the refueling portion 13 extends from the chamfered portion 10b has been described as an example. The present invention is not limited to the above embodiment. For example, even if the upper corner portion of the second portion 10B is provided with a recessed portion recessed toward the inside of the fuel tank 10, and the refueling portion 13 is provided with a configuration extending from the recessed portion. good. Further, it may have a configuration extending from the upper part of the fuel tank 10, or may be provided in the first portion 10F.

(4) In the above embodiment, the configuration extending obliquely upward from the chamfered portion 10b has been described as an example, but the present invention is not limited to the above embodiment. For example, the tubular portion 13a of the refueling portion 13 may be formed in a crank shape, and the refueling portion 13 does not have the tubular portion 13a and is directly attached to the upper portion of the fuel tank 10, the chamfered portion 10b, or the like. The fuel filler port 13b may be formed.

(5) In the above embodiment, the configuration in which the fuel tank 10 is made of resin has been described as an example, but the present invention is not limited to the above embodiment. For example, it may be made of metal.

(6) In the above embodiment, the fuel tank 10 has been described as an example of a configuration in which the fuel tank 10 is fixed to the airframe frame 20 by two front and rear fixing bands 23, but the present invention is not limited to the above embodiment. For example, the fuel tank 10 may be fixed to the airframe frame 20 by one or three or more fixing bands 23, and the fuel tank 10 and the airframe frame 20 are directly bolted to each other without using the fixing bands 23. It may be a fixed configuration.

(7) In the above embodiment, the configuration in which the band groove 14 into which the fixed band 23 enters is formed in the fuel tank 10 has been described as an example, but the present invention is not limited to the above embodiment, and the fuel tank is not limited to the above embodiment. The band groove 14 may not be formed in 10.

(8) In the above embodiment, the configuration in which the bulging portion 15 is provided at the bottom of the fuel tank 10 and the supply port 16a is provided at the bulging portion 15 has been described as an example, but the present invention has been described above. It is not limited to the form. For example, the fuel tank 10 may be configured not to include the bulging portion 15, and the supply port 16a may be configured to be provided at the bottom or side of the fuel tank 10.

(9) In the above embodiment, the fuel tank 10 has been described as an example of a configuration in which the fuel tank 10 is mounted and supported on the first frame 20Ba and the second frame 20Bb, which are the lateral frame bodies 20B of the airframe frame 20. The present invention is not limited to the above embodiment, and may be provided with a configuration in which the fuel tank 10 is mounted and supported on a plurality of front-rear frame bodies 20A of the body frame 20.

(10) In the above embodiment, the grain tank 5 is provided with an upper rear surface portion 5c on the upper portion of the rear surface of the grain tank 5 and a lower rear surface portion 5d on the lower portion of the rear end surface of the grain tank 5. Although the configuration in which the surface portion 5c is configured to be located on the rear side of the lower rear surface portion 5d has been described as an example, the present invention is not limited to the above embodiment. For example, the upper rear surface portion 5c and the lower rear surface portion 5d may be arranged at the same position in the front-rear direction of the machine body so as to form an integral flat surface.

(11) In the above embodiment, a configuration in which a protective plate 24 for protecting the fuel tank 10 is provided below the bulging portion 15 has been described as an example, but the present invention is limited to the above embodiment. is not it. For example, the protective plate 24 may be configured to protect only the bulging portion 15.

(12) In the above embodiment, the first frame 20Ba, the second frame 20Bb, and the horizontal frame 20Bc are configured by the horizontal frame body 20B, and the configuration composed of the second frame 20Bb has been described as an example. Is not limited to the above embodiment. For example, the first frame 20Ba, the second frame 20Bb, and the horizontal frame 20Bc may be composed of the front-rear frame body 20A, and the horizontal frame 20Bc is composed of a separate body from the second frame 20Bb. May be good.

(13) In the above embodiment, the bulging portion 15 is formed so that the lowermost end of the bulging portion 15 is located within the vertical width of the first frame 20Ba and the second frame 20Bb, and the airframe frame. Of the 20, the configuration in which the horizontal frame 20Bc is provided so as to extend along the left and right methods of the machine body behind the bulging portion 15 has been described as an example, but the present invention is not limited to the above embodiment. The lowermost end of the bulging portion 15 does not have to be located within the vertical width of the first frame 20Ba and the second frame 20Bb, and the horizontal frame 20Bc may not be provided.

(14) In the above embodiment, the fuel auxiliary machine 30 is provided in the region behind the grain tank 5 and on the side of the fuel tank 10, and the supply port 16a is the fuel tank in the side portion of the bulging portion 15. An example of a configuration has been described in which the fuel auxiliary machine 30 extends along the horizontal direction from the side portion on the side where the fuel auxiliary machine 30 is located with respect to the fuel tank 10 toward the side where the fuel auxiliary machine 30 is located with respect to the fuel tank 10. However, the present invention is not limited to the above embodiment. For example, the fuel auxiliary machine 30 may be provided behind the fuel tank 10, and the side portion of the bulging portion 15 other than the side portion on the side where the fuel auxiliary equipment 30 is located with respect to the fuel tank 10. A supply port 16a may be provided at the location.

(15) In the above embodiment, the fuel tank 10 has been described as an example of a configuration including a first tank structure 10L and a second tank structure 10R divided by a dividing surface 10C along the vertical direction. Is not limited to the above embodiment. For example, the divided surface 10C may be formed in the left-right direction or the oblique direction, and the fuel tank 10 may be formed of one or three or more components.

The present invention can be used not only for ordinary combine harvesters but also for head-feeding combine harvesters.

4 Grain removal device 5 Grain tank 5U Lower constriction 5S Lower space 10 Fuel tank 10F 1st part 10B 2nd part 10L 1st tank component 10R 2nd tank structure 10C Divided surface 10b Chamfered part 13 Refueling part 14 Band groove 15 bulge 15L 1st bulge 15R 2nd bulge 16a Supply port 20 Airframe frame 20Ba 1st frame 20Bb 2nd frame 20Bc Horizontal frame 21 Airframe frame 23 Fixed band 24 Protective plate 30 Fuel auxiliary machine E engine

Claims (12)

A threshing device that threshes the harvested crops,
A grain tank provided side by side with the threshing device and storing grains obtained by the threshing device, and a grain tank.
A fuel tank provided in the space between the threshing device and the grain tank is provided.
At the bottom of the grain tank, a lower constriction portion having a lower constriction shape is provided in the left-right direction of the machine body.
The fuel tank is provided with a first portion provided in the space so as to enter the lower space below the lower constriction portion, and is provided behind the first portion and is rearward of the rear end portion of the grain tank. With a second part that protrudes into,
The second portion is a combine that overlaps with the grain tank in the rear view so that the cross-sectional shape in the rear view is larger than that in the first portion. A chamfered portion is provided at the upper corner portion of the second portion.
The combine according to claim 1, wherein the refueling unit for refueling the fuel tank is a combine harvester extending from the chamfered unit. The combine according to claim 2, wherein the refueling section extends obliquely upward from the chamfered section. The upper corner portion of the second portion is provided with a recessed portion recessed toward the inside of the fuel tank.
The combine according to claim 1, wherein the refueling unit for refueling the fuel tank extends from the recessed portion. The fuel tank is made of resin and
The upper portion of the first portion is formed in a flat shape, and the upper corner portion on the side of the grain tank in the first portion is formed in an inclined shape along the inclined shape of the lower constriction portion.
The upper portion of the second portion has a left-right width extending to the upper portion of the first portion and the upper corner portion of the first portion in the left-right direction, and is formed in a flat shape continuous with the upper portion of the first portion. The combine according to any one of claims 1 to 4. A fixing band is wound around the fuel tank while it is mounted on the airframe, and the fuel tank is tightened and fixed to the airframe by the fixing band.
The fuel tank is made of resin and
The combine according to any one of claims 1 to 5, wherein a band groove into which the fixed band enters is formed in the first portion and the second portion. The bottom of the fuel tank is provided with a bulge that bulges downward.
The combine according to any one of claims 1 to 6, wherein the bulge portion is provided with a supply port for supplying fuel inside the fuel tank to the engine. The fuel tank is mounted and supported on the fuselage frame at the rear of the fuselage.
The airframe frame is provided with a first frame on which the fuel tank is mounted and supported, and a second frame provided in parallel with the first frame.
A mounting portion to be mounted on the first frame is provided at a portion corresponding to the first frame in the peripheral portion of the bulging portion on the bottom portion.
The bulging portion is dropped between the first frame and the second frame in a state where the lowermost end of the bulging portion is located within the vertical width of the first frame and the second frame. The combine according to claim 7. A protective plate located below the bulge and protecting the bulge is provided.
The combine according to claim 8, wherein the protective plate extends over the lower end portion of the first frame and the lower end portion of the second frame, and is supported by the first frame and the second frame. The fuel tank is mounted and supported on the airframe frame, and is supported.
Any one of claims 7 to 9, wherein the airframe frame is provided with a horizontal frame extending along the left-right direction of the airframe behind the bulge portion so as to overlap the bulge portion in a rear view. The combine described in. A fuel auxiliary machine is provided in the area behind the grain tank and on the side of the fuel tank.
The bulging portion is provided at the bottom of the second portion, and the refueling portion for refueling the fuel tank is provided at the upper part of the second portion.
The supply port is directed from the side portion of the bulging portion on the side where the fuel auxiliary machine is located with respect to the fuel tank toward the side where the fuel auxiliary machine is located with respect to the fuel tank. The combine according to any one of claims 7 to 10, which extends along the horizontal direction. The fuel tank is provided with a first tank structure and a second tank structure divided by a dividing surface along the vertical direction, and the fuel tank includes the first tank structure and the second tank structure. Consists of concatenating
When the divided surface passes through the bulging portion, the bulging portion is divided into a first bulging body on the side of the first tank configuration and a second bulging body on the side of the second tank configuration. Has been
The first bulge and the second bulge are configured such that the width of the first bulge is larger than the width of the second bulge with the divided surface interposed therebetween.
The bottom of the first bulge and the bottom of the second bulge are formed in an inclined shape that is inclined downward toward the side of the dividing surface.
13. The combine described in any one of the items.

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