TW201904383A - Combine harvester - Google Patents

Abstract

The present invention provides a united harvester suppressing the overheating of a waste gas purifying device. The united harvester is provided with a cooler fan (13) which is disposed between an engine (11) and a cooler (12) on a machine frame (2) and is used to inhale external air, and also is provided with a waste gas purifying device (20) used to purify the gas exhausted form the engine (11). The united harvester is constituted to be that: a supporting portion member (40) is disposed on the machine frame (2) and is used to support the waste gas purifying device (20) which is disposed on an opening portion (42a) formed at the upper portion of the supporting member (40); and at least one part of the external air inhaled by the cooler fan (13) passes through the opening portion (42a) to flow toward the waste gas purifying device (20). In addition, the lower side of the opening portion (42a) is provided with an air baffle (43) used to guide the external air inhaled by the cooler fan (13) toward the waste gas purifying device (20).

Description

Combine harvester

The invention relates to a combine harvester.

In conventional combine harvesters, a diesel engine as a drive source is provided on a fuselage frame. For such a combine, in order to meet the exhaust gas regulations that have been intensified in recent years, there is a structure provided with an exhaust gas purification device that purifies exhaust gas discharged from a diesel engine.

The exhaust gas purification device has a structure including a DPF (Diesel Particulate Filter) that removes particulate matter in the exhaust gas, and ammonia and exhaust gas generated from an aqueous urea solution (hereinafter referred to as urea water). Urea SCR (Selective Catalytic Reduction) catalyst that is purified by reacting nitrogen compounds and purifying (see, for example, Patent Document 1). DPF and urea SCR catalysts are housed in cylindrical housings (hereinafter referred to as DPF and urea SCR catalysts including the housing).

Patent Document 1: Japanese Patent Application Publication No. 2016-158591

However, in the conventional combine as described above, a unit for cooling the high-temperature exhaust gas discharged from the diesel engine may not be provided, and the exhaust gas purification device may overheat due to the high-temperature exhaust gas.

The present invention has been made in view of the above circumstances, and an object thereof is to provide a combine that can suppress overheating of an exhaust gas purification device.

In order to solve the above problems and achieve the objective, the present invention adopts the following technical solutions. The invention described in claim 1 is a combine harvester. The combine harvester is provided with a radiator fan 13 for sucking in external air between the engine 11 and the radiator 12 provided on the fuselage frame 2 and the combine harvester. An exhaust gas purifying device 20 for purifying the gas exhausted from the engine 11 is provided, wherein the combined harvesting mechanism is provided with a support for supporting the exhaust gas purifying device 20 on the fuselage frame 2. Member 40, the exhaust gas purifying device 20 is supported on an opening portion 42a formed in an upper portion of the supporting member 40, and at least a part of the external air sucked by the radiator fan 13 faces the exhaust gas through the opening portion 42a The purification device 20 flows.

In the invention according to claim 2, in the combine according to claim 1, the exhaust gas purifying device 20 is disposed behind the engine 11, and is disposed in the opening 42a of the support member 40. An air deflector 43 is provided on the lower side, and the air deflector 43 guides the external air that is drawn into the radiator fan 13 and flows to the rear of the engine 11 to the exhaust gas purification device 20.

In the invention according to claim 3, according to the combine harvester according to claim 1 or 2, the rear side of the engine 11 is provided on the left and right sides of the fuselage frame 2. There is a threshing device 7 for threshing the grain rod. A grain box 8 storing threshing grains is provided on the rear side of the engine 11 on the left and right sides of the fuselage frame 2. The box 8 is provided to be rotatable around the longitudinal axis of the fuselage. The upper part of the exhaust gas purification device 20 is provided with covers 30 a and 30 b formed by dividing left and right.

In the invention according to claim 4, according to the combine of claim 3, the front surface of the exhaust gas purification device 20 is covered by the covers 30a, 30b, and the exhaust gas purification device 20 The back surface side is open.

According to the invention of claim 1, the external air sucked into the body by the radiator fan 13 flows to the exhaust gas purification device 20 side, so that the cooling of the exhaust gas purification device 20 can be promoted and overheating can be suppressed. In addition, an opening portion 42a is formed in the upper portion of the support member 40 that supports the exhaust gas purification device 20, so that at least a part of the external air sucked by the radiator fan 13 flows toward the exhaust gas purification device 20 through the opening portion 42a, which can improve Cooling efficiency of the exhaust gas purification device 20.

According to the invention described in claim 2, in addition to the effects of the invention described in claim 1, the external air sucked by the radiator fan 13 can be more reliably guided to the exhaust gas purification device 20 side. This can promote cooling of the exhaust gas purification device 20 and suppress overheating of the exhaust gas purification device 20.

According to the invention described in claim 3, in addition to the effects of the invention described in claim 1 or 2, for example, if only the cover 30b on the grain box 8 side of the covers 30a and 30b formed by dividing left and right is removed, it is possible to The grain tank 8 is opened from the grain tank 8 side, and maintenance of the exhaust gas purification device 20 is performed. Thereby, work such as maintenance of the exhaust gas purification device 20 becomes easy.

According to the invention described in claim 4, in addition to the effects of the invention described in claim 3, the heat around the exhaust gas purifying device 20 can be efficiently discharged to the machine with the flow of external air sucked by the radiator fan 13. Outside.

An embodiment of the combine of the present invention will be described in detail with reference to the drawings. The present invention is not limited to the above-mentioned embodiment, and various modifications can be made without departing from the gist of the present invention. In addition, the constituent elements in the following embodiments include content that can be easily replaced by a person having ordinary knowledge in the art, or substantially the same content, so-called equivalent range content.

FIG. 1 is a schematic left side view of a combine harvester 1 according to an embodiment. FIG. 2 is a schematic plan view of a combine harvester 1 according to an embodiment. In the following description, the front-rear direction, the left-right direction, and the up-down direction in the normal use state of the combine 1 will be described as the front-rear direction, left-right direction, and up-down direction of each part, respectively.

Among them, the "front" side is the traveling direction of the combine 1 during the harvesting operation, the "left" side is the left-hand direction when facing forward, and the "bottom" side is the direction in which gravity acts. In addition, these directions are defined for easy understanding and explanation, and the present invention is not limited by these directions. In addition, hereinafter, the “body” is sometimes referred to as the combine 1.

<Overall Structure of Combine Harvester 1> First, the overall structure of the combine harvester 1 will be briefly described. As shown in FIGS. 1 and 2, the combine harvester 1 includes a fuselage frame 2, a traveling device 3 provided below the fuselage frame 2, an upper portion of the fuselage frame 2, and a front of the fuselage frame 2 described later. Various operating devices, and an operating portion 4 provided on the upper front side of the fuselage frame 2. The operating unit 4 is covered by a driver's cab 4a, and an operator's seat (also referred to as an operator) on which an operator (also referred to as an operator) sits, various operating levers, and measuring instruments are provided inside the driver's cab 4a.

The traveling device 3 includes a pair of left and right crawler tracks 3 a that transmit power by a diesel engine (hereinafter referred to as an engine) 11 (refer to FIG. 3) provided on the fuselage frame 2 and perform rotation. The traveling device 3 travels the body by rotating the crawler 3a. The crawler belt 3a is formed in an annular shape from an elastic body such as rubber. The traveling device 3 includes drive wheels 3b for rotating the crawler belt 3a and tension wheels 3c for applying tension to the crawler belt 3a at both ends of the fuselage in the front-rear direction.

The working device includes, for example, a harvesting device 5 provided in front of the fuselage frame 2; a grain rod conveying device 6 provided on the upper side of the fuselage frame 2 on the left side of the cab 4a; and a threshing device 7 provided on the The upper left and right sides (left side) of the fuselage frame 2; the grain box 8, which is provided on the upper left, right, and other sides (right side) of the fuselage frame 2; and the grain discharge screw conveyor 9, which is arranged in the thresher 7 and Above the grain bin 8.

In the working device, the grain rod conveying device 6 is used to transport the grain rods harvested by the harvesting device 5 toward the threshing device 7, and the grains obtained by threshing and screening by the threshing device 7 are stored in the grain box 8, and The grain discharge screw conveyor 9 discharges the grain stored in the grain tank 8 to the outside of a body, such as a rack of a transport vehicle. The grain tank 8 is configured to be rotatable from a working position on the fuselage frame 2 to a maintenance position outside the fuselage frame 2 around a longitudinal axis (rotation axis) provided on the rear side of the grain tank 8.

The operation section 4 provided on the upper front side of the fuselage frame 2 is provided with the above-mentioned operation seat 4b, various operation levers, measuring instruments, an operation panel, a display capable of displaying various information, and the like. In addition, the manipulation unit 4 may have a so-called cab opening structure provided for each cab 4 a so as to be rotatable toward the outside of the fuselage frame 2.

The harvesting device 5 includes a grass-dividing rod 5a that divides the grain rod in the field, a lifting device 5b that lifts the divided cereal rod, and a cutter that cuts the root of the lifted grain rod. The harvesting device 5 uses the grass-dividing rod 5a to divide the grass rods planted in the field, uses the lifting device 5b to lift the divided cereal rods, and uses the cutter to harvest the raised cereal rods. The grain rod conveying device 6 is provided behind the harvesting device 5 and conveys the grain rods harvested by the harvesting device 5 toward the threshing device 7.

After the threshing device 7 is threshed by the grain raising device, the grains screened by the screening unit are sent to the grain tank 8. The grain tank 8 feeds the stored grains by the conveying screw 50 provided at the bottom to the longitudinal direction as a part of the grain discharge screw conveyor 9 provided behind the grain tank 8 (above the rear part of the fuselage frame 2). The lower part of the screw conveyor 9a. The grain fed to the vertical screw conveyor 9a is fed from the upper part of the vertical screw conveyor 9a to the horizontal screw conveyor 9b, and is discharged from the discharge cylinder 9c provided in the front end part of the horizontal screw conveyor 9b.

An engine room 10 is provided below the cab 4 a on the fuselage frame 2 (see FIG. 4). In the engine room 10, in addition to the engine 11 as a power source, a radiator 12 (see FIG. 4) for cooling the engine 11 and a radiator fan 13 (see FIG. 4) for sucking outside air are housed. Wait. The details of the engine 11, the radiator 12, and the radiator fan 13 housed in the engine room 10 will be described later using FIGS. 3 and 4.

Further, an exhaust gas purification device 20 for purifying the exhaust gas discharged from the engine 11 is provided above the rear side of the engine room 10 and the engine 11 on the fuselage frame 2.

<Exhaust Gas Purification Device 20> Next, the exhaust gas purification device 20 will be described with reference to FIGS. 3 to 6. FIG. 3 is a schematic left side view for explaining the arrangement of the exhaust gas purification device 20. FIG. 4 is a schematic plan view illustrating the arrangement of the exhaust gas purification device 20. FIG. 5 is a schematic front view illustrating a supporting structure of the exhaust gas purification device 20. FIG. 6 is a schematic rear view illustrating the supporting structure of the exhaust gas purification device 20.

In addition, in FIGS. 3 to 6, for convenience of explanation, each part such as the cab 4 a is appropriately omitted in accordance with the drawings. 3 and 4, the engine 11, the radiator 12, and the radiator fan 13 in the engine room 10 will be described first, and then the exhaust gas purification device 20 will be described using FIGS. 3 to 6.

As shown in FIGS. 3 and 4, a radiator on the right side of the engine 11 on the fuselage frame 2, which is the outside of the fuselage, is provided at a predetermined interval from the engine 11 to cool the cooling water supplied to the engine 11. 12. A radiator fan 13 that draws outside air into the engine room 10 is provided between the engine 11 and the radiator 12. In addition, in the engine room 10, a dust exhaust fan for exhausting internal air from the engine room 10 is also provided on the left side of the radiator fan 13 as the inside of the fuselage, and the radiator 12 and the engine room are provided. Provided between the hoods 10a are an oil cooler that cools the oil supplied to the hydraulic cylinder that raises and lowers the harvesting device 5 (see FIG. 1), a fuel cooler that cools the fuel supplied to the engine 11, and an intermediate A cooler that cools the combustion mixed gas supplied to the engine 11.

In addition, when the above-mentioned radiator fan 13 is driven to rotate by the driving force of the engine 11, the external air is sucked into the engine room 10 through the filter body as a perforated steel plate installed in the engine room cover 10a and is sent to the core of the radiator 12 It is possible to cool the heat sink 12 inside. In addition, when the rotation of the radiator fan 13 is stopped and the dust exhaust fan is rotated, the internal air is exhausted to the outside of the fuselage through the filter of the engine room cover 10a, so that the dust adhering to the outer surface of the filter can be dispersed and The removal can maintain the suction efficiency of the radiator fan 13 to the outside air.

The radiator fan 13 is, for example, a propeller fan, and a center portion is mounted on a rotating shaft, and has a blade (propeller) extending in a radial direction from the center portion. The external air sucked by the radiator fan 13 also diffuses backward due to interference with the engine 11 and flows to the rear of the engine 11. The dust exhaust fan is, for example, a propeller fan, and a center portion is mounted on a rotating shaft, and has a blade (propeller) extending radially from the center portion. In order to prevent the radiator fan 13 from reducing the intake efficiency of the outside air, the dust exhaust fan is formed so that the outer diameter of the blade is smaller than the outer diameter of the blade of the radiator fan 13. In addition, in order to reduce the number of parts of the drive unit that drives the radiator fan 13 and the dust exhaust fan and efficiently utilize the space in the engine room 10, it is preferable to adopt the following structure: the angle of the blades of the radiator fan 13 and the dust exhaust fan The angle of the blades is formed to be the opposite angle, and the two fans are alternately driven to rotate in the same direction.

As described above, the engine room 10 is provided below the cab 4 a on the fuselage frame 2 (in front of the grain tank 8 on the fuselage frame 2). Above the rear side of the engine 11 on the fuselage frame 2, an exhaust gas purification device 20 for purifying the exhaust gas of the engine 11 is provided. As shown in FIGS. 3 and 4, a threshing device 7 is provided on the rear of the engine 11 and on the left side of the upper part of the fuselage frame 2, and the right side of the upper part of the fuselage frame 2 is opposed to the threshing device 7 in the left-right direction. A grain box 8 is provided.

As described above, at least a part of the external air sucked by the radiator fan 13 flows to the rear of the engine 11, and the exhaust gas purifying device 20 is disposed at a position where the external air contacts. That is, the external air that is sucked into the fuselage by the radiator fan 13 and interferes with the engine 11 and diffuses and flows to the rear contacts the exhaust gas purification device 20.

According to the above structure, the external air drawn into the body by the radiator fan 13 contacts the exhaust gas purification device 20 in addition to the engine 11, so that the cooling of the exhaust gas purification device 20 can be promoted and the exhaust gas purification device 20 can be suppressed. overheat.

The exhaust gas purification device 20 is provided between the threshing device 7 and the grain tank 8. In addition, the exhaust gas purification device 20 is provided so as to be partially accommodated in a recessed portion 8 a formed on a side surface (left side surface) of the grain tank 8 opposite to the threshing device 7.

The exhaust gas purification device 20 is connected to an exhaust pipe 11 a connected to the engine 11. In addition, since the exhaust gas purification device 20 is disposed above the rear side of the engine 11 as described above, the exhaust gas purification device 20 is not easily affected by vibration from a vibration source such as the traveling device 3 or the engine 11.

The exhaust gas purification device 20 includes a DPF 21 that removes particulate matter in the exhaust gas, and a urea SCR catalyst 22 that converts ammonia generated by hydrolysis of urea water and nitrogen oxides in the exhaust gas after passing through the DPF 21 to convert Into harmless nitrogen. The DPF 21 and the urea SCR catalyst 22 are respectively housed in cylindrical housings. In addition, the reference numerals in the figures are marked on these respective cases.

For the DPF 21, on the honeycomb carrier carrying the catalyst (Pt), the soluble organic components (SOF: Soluble Organic Fraction) and nitrogen compounds (NO _X) component oxide, and particulate matter to be collected by filtration. The DPF 21 is formed of, for example, a honeycomb-shaped unit structure and an outer wall surrounding the unit structure, wherein the unit structure is composed of a honeycomb carrier and a plurality of partition walls, and has a plurality of through holes. Polygonal cross section.

The exhaust gas purification device 20 has a function of a DOC (Diesel Oxidation Catalyst) that efficiently oxidizes nitric oxide in the DPF 21, and has a reduction catalyst using a selective catalyst of ammonia generated from urea water in the urea SCR catalyst 22. Features.

The exhaust gas purification device 20 converts nitric oxide in the exhaust gas into nitrogen dioxide in the DPF 21, and in a pipe connecting the outlet of the DPF 21 and the inlet of the urea SCR catalyst 22, sprays urea water on the nitrogen dioxide, Nitrogen dioxide is converted into water and nitrogen to remove nitrogen oxides (NO _x ) from the exhaust gas. The purified exhaust gas flows in the tail pipe 44 and is discharged to the outside.

According to the above configuration, the urea SCR catalyst 22 is installed in the exhaust gas purification device 20 to purify nitrogen compounds (NO _X ) in the exhaust gas, so that the exhaust gas of the engine 11 can be efficiently purified.

Here, other devices provided as peripheral equipment of the exhaust gas purification device 20 on the body frame 2 will be briefly described. On the fuselage frame 2, as a peripheral device of the exhaust gas purifying device 20, a medicating component (hereinafter referred to as DM) 23, a supplying component (hereinafter referred to as SM) 24, a urea water tank 25 (see FIGS. 11 and 12), and the like are provided.

The DM 23 is a urea water injection unit of the urea SCR catalyst 22. The DM 23 is provided, for example, on a pipe connecting an outlet of the DPF 21 and an inlet of the urea SCR catalyst 22. The SM 24 is a pump that transports urea water from the urea water tank 25 to the DM 23. The SM 24 is preferably provided at a position spaced upward with respect to the fuselage frame 2, for example. In addition, the SM 24 is preferably provided separately from the DPF 21 and the urea SCR catalyst 22.

By arranging the SM 24 separately from the fuselage frame 2 in this way, it is possible to suppress transmission of vibration from the vibration source to the SM 24, and to suppress damage to the SM 24 and the like. In addition, the SM 24 is disposed separately from the DPF 21 and the urea SCR catalyst 22, so that the SM 24 is not easily affected by the heat generated by the DPF 21 and the urea SCR catalyst 22.

The urea water tank 25 (see FIGS. 11 and 12) stores urea water supplied to the urea SCR catalyst 22. The urea water tank 25 is preferably provided separately from the engine 11. By disposing the urea water tank 25 separately from the engine 11, the urea water tank 25 is not easily affected by heat (exhaust heat) from the engine 11, and deterioration of the urea water can be suppressed. The arrangement of the urea water tank 25 in the present embodiment will be described later using FIGS. 11 and 12.

The DPF 21 and the urea SCR catalyst 22 as the exhaust gas purifying device 20 are arranged side by side in the front-rear direction and the left-right direction with the direction of the imaginary central axis of the cylindrical case. In addition, the respective cylindrical cases of the DPF 21 and the urea SCR catalyst 22 of the exhaust gas purification device 20 are connected in a parallel state and are unitized.

According to the above-mentioned structure, since the DPF 21 and the urea SCR catalyst 22 are unitized, the exhaust gas purification device 20 can be configured compactly, and can be easily mounted on a support member 40 described later.

The exhaust gas purification device 20 is provided between the threshing device 7 and the grain tank 8 on the fuselage frame 2. Specifically, while the position of the grain tank 8 is fixed to the working position (the position during normal use) on the fuselage frame 2, a part of the exhaust gas purification device 20 enters the grain tank 8 and faces the thresher 7. In the recessed portion 8a formed on the surface (left side surface). In the above case, the DPF 21 is configured to be separated from the grain tank 8, and the urea SCR catalyst 22 is configured to enter and be accommodated in the recessed portion 8a.

In this way, the DPF 21 is arranged separately from the grain tank 8 so that straw chips or dust cannot easily accumulate in the grain tank 8 at a position close to the DPF 21 at a high temperature.

In addition, a cover 30 covering the upper part of the exhaust gas purifying device 20, that is, the DPF 21 and the urea SCR catalyst 22 is provided on the upper part of the exhaust gas purifying device 20. The cover 30 will be described later using FIG. 7.

As shown in FIGS. 5 and 6, on the fuselage frame 2, the exhaust gas purification device 20 (DPF 21 and urea SCR catalyst 22) is supported by the support member 40 from below. The support member 40 has a frame structure (frame combination structure), and includes a plurality of leg portions 41 and a mounting portion 42. A plurality of (three in this embodiment) leg portions 41 are erected on the fuselage frame 2. The mounting portion 42 forms an upper portion of the support member 40 on an upper portion of the plurality of leg portions 41. The exhaust gas purification device 20 is placed on the mounting portion 42. The mounting portion 42 will be described later using FIGS. 8 to 10 and the like.

In addition, a shielding plate 41 a is provided on a side surface of the support member 40. The shielding plate 41a shields a part of the side surface of the support member 40 which is a frame structure. Specifically, the shielding plate 41 a shields between the leg portion 41 and the leg portion 41 on the upper portion of the support member 40.

According to the above configuration, it is possible to suppress the diffusion of external air that is sucked into the radiator fan 13 and flows to the rear side, and the external air can be brought into contact with the exhaust gas purification device 20 in a concentrated manner. This can promote cooling of the exhaust gas purification device 20 and suppress overheating of the exhaust gas purification device 20.

In addition, returning to FIG. 3, the above-mentioned supply unit (SM) 24 is attached to the support member 40. The SM 24 is attached to a support 24 a provided between the leg portion 41 and the leg portion 41 of the support member 40. That is, the support 24 a connects the leg portion 41 and the leg portion 41 of the support member 40. In this way, the leg portion 41 and the leg portion 41 of the support member 40 are connected by the support 24 a for mounting the SM 24, so that the frame rigidity can be improved even in the state of the three-leg structure like the present embodiment. In addition, since the support 24a to which the SM 24 is mounted, there is no need to add structural components in order to increase the rigidity of the frame.

As described above, the support member 40 mounts the DPF 21 and the urea SCR catalyst 22 as the exhaust gas purification device 20 on the mounting portion 42 as the upper portion of the support member 40 to support the exhaust gas purification device 20 with respect to the body frame. 2Separate upwards. The support member 40 is disposed close to the threshing device 7. In this case, it is preferable that the support member 40 and the threshing apparatus 7 are not connected. Accordingly, the support member 40 and the exhaust gas purification device 20 supported by the support member 40 are less likely to be affected by the vibration of the threshing device 7.

In addition, the support member 40 supports the DPF 21 and the urea SCR catalyst 22 as the exhaust gas purification device 20 so as to be disposed above the rear side of the engine 11. That is, the support member 40 arranges the exhaust gas purification device 20 at a position separated from the engine 11 as a source of vibration. In this way, transmission of vibration from the vibration source to the support member 40 and the exhaust gas purification device 20 supported by the support member 40 can be suppressed, and thus damage to the support member 40 and the exhaust gas purification device 20 can be suppressed.

In addition, the support member 40 faces at least a part of the exhaust gas purification device 20 (the urea SCR catalyst 22 in the illustrated example) into the space formed by the recessed portion 8 a of the grain box 8 on the side opposite to the threshing device 7. The exhaust gas purification device 20 is supported. Therefore, the grain tank 8, the threshing apparatus 7, the support member 40, and the exhaust-gas purification apparatus 20 supported by the support member 40 can be arrange | positioned close to the fuselage frame 2. As a result, the body can be made compact.

<Cover 30 of Exhaust Gas Purification Device 20> Next, a cover 30 covering the exhaust gas purification device 20 will be described with reference to FIG. 7. FIG. 7 is a schematic perspective view of a cover 30 covering the exhaust gas purification device 20. As shown in FIG. 7, a cover 30 covering the upper part of the exhaust gas purifying device 20 is provided on the upper part of the exhaust gas purifying device 20 so that straw dust and the like are not deposited on the DPF 21 and the urea SCR catalyst 22 as the exhaust gas purifying device 20.

The cover 30 is formed of a plate-like structural member, and includes one cover (hereinafter referred to as a first cover) 30 a and the other cover (hereinafter referred to as a second cover) 30 b. The first cover 30 a and the second cover 30 b are arranged side by side in the left-right direction of the fuselage in a state where the exhaust gas purification device 20 is installed behind the engine 11. In other words, the cover 30 is formed by being divided in the left-right direction of the body. For example, the first cover 30 a covers the inside (left side) of the body of the exhaust gas purification device 20, and the second cover 30 b covers the outside (right side) of the body of the exhaust gas purification device 20. In the present embodiment, the first cover 30a covers the DPF 21 side, and the second cover 30b covers the urea SCR catalyst 22 side.

According to the above configuration, only by removing the cover (second cover) 30b on the grain box 8 side among the covers 30 formed in the left-right direction, the grain box 8 can be opened from the grain box 8 side and the exhaust gas can be purified. Maintenance of the device 20 (DPF 21 and urea SCR catalyst 22) and the like. Thereby, work such as maintenance of the exhaust gas purification device 20 becomes easy.

As described above, the grain tank 8 is provided so as to be capable of rotating in the left-right direction around a vertical axis (“vertical axis” in the technical solution) provided on the upside of the grain tank 8 (rear portion of the fuselage). As shown in FIG. 7, a recess 31 is formed on the cover 30 at a position on the front side in the front-rear direction of the fuselage and inside the fuselage. The position where the recessed portion 31 is formed is a position close to the rotation locus of the front side edge portion of the grain box 8, and the point of the front side edge portion of the grain box 8 is arranged at the working position (position in normal use) on the fuselage frame 2. The welded portion enters the recessed portion 31.

According to the said structure, when the grain tank 8 is arrange | positioned at a work position, the space other than the spot-welded part which entered into the recessed part 31 can be used for other uses. Specifically, for example, when the combine 1 has a so-called cab specification having a cab 4a, the recessed portion 31 can be used as a space for piping such as an air conditioner. This makes it possible to make each part of the combine 1 the same structure regardless of a specification.

The cover 30 shields the front end portion. As shown in FIG. 7, the cover 30 opens a rear end portion (specifically, a rear end surface) 32. In this way, in a state where the exhaust gas purifying device 20 is installed, the front end portion side on the radiator 12 side is shielded, and the rear end surface 32 on the side opposite to the radiator 12 (see FIG. 4) is opened. The internal air around the exhaust gas purification device 20 is efficiently discharged to the outside of the fuselage according to the flow of the external air sucked by the radiator fan 13 (see FIG. 4).

As shown in FIG. 7, the cover 30 is formed such that the length L of the upper edge 32 a of the rear end surface 32 facing the left-right direction (right) on the outside of the fuselage is longer than the length L facing the other (left) on the inside of the fuselage. The length is long. Specifically, in the left-right direction of the upper edge 32 a of the rear end surface 32 of the cover 30, the one (right) side on the grain box 8 side extends diagonally downward. As a result, it is possible to prevent the internal air generated by the exhaust gas purification device 20 and the engine 11 from directly contacting the grain tank 8, and to protect the painted surface of the grain tank 8.

In addition, as described above, one side (right side) of the upper edge 32 a of the rear end surface 32 of the cover 30 extends obliquely downward, so the opening area on the other side (left side) on the opposite side in the left-right direction is larger. That is, the outside of the fuselage of the rear end surface 32 of the cover 30 is widened. This makes it possible to efficiently discharge the internal gas to the outside of the fuselage.

In addition, the cover 30 may be formed so that the upper surface may be inclined toward the rear direction. As a result, the opening area of the rear end portion 32 is increased, so that the exhaust of the air (internal air) around the exhaust gas purification device 20 that generates heat to the outside of the fuselage can be promoted. In addition, it is not necessary to add structural components in order to remove air around the exhaust gas purification device 20.

In addition, as shown in FIG. 7, the cover 30 may be partially opened, for example. That is, the hole portion 33 may be formed on the upper surface of the cover 30. The hole portion 33 is preferably formed near the center of the upper surface. In this way, a part of the upper surface of the cover 30 is opened, and when the radiator fan 13 is reversed, air (internal air or external air) can be easily sucked into the cover 30, and a short time inversion of the radiator fan 13 can be utilized. The drive efficiently cools the exhaust gas purification device 20.

In addition, a pressure difference sensor that detects a pressure difference between exhaust gas before and after the DPF 21 may be disposed in the hole portion 33 formed in the cover 30. In this way, the pressure difference sensor is arranged in the hole portion 33 through which air (internal air or outside air) passes, so that the pressure difference sensor can be cooled by air, and it can be prevented from being caused by the heat of the pressure difference sensor. Malfunction. In addition, there is no need to add structural components for cooling the pressure difference sensor.

In addition, as described above, the cover 30 shields the front surface of the exhaust gas purification device 20. In the above case, a hole may be formed in a portion of the cover 30 that covers the front surface of the exhaust gas purification device 20. In this way, by forming a hole in the front surface portion of the cover 30, it is possible to introduce wind received during the travel of the fuselage into the cover 30 and to discharge the heated air (internal gas) to the outside of the fuselage.

As shown in FIG. 7, a plate-shaped protective cover 34 may be further disposed on the upper surface of the cover 30. As described above, by disposing the protective cover 34, for example, even when the worker contacts the cover 30, the worker can be prevented from being burned, and the safety can be improved. Moreover, since the protective cover 34 functions as a decorative cover, the designability of an external appearance can be improved.

The protective cover 34 is made of a different member from the cover 30. In the above-mentioned case, a fixing portion such as a welding nut is provided on the upper surface of the cover 30, and the protective cover 34 is fixed at a distance from the cover 30, so that heat cannot be easily transmitted from the cover 30 to the protective cover 34. In addition, a structure for preventing heat from being easily transmitted to the protective cover 34 can be obtained inexpensively, and it is not necessary to add a structural member.

A hole 43 a may be formed in the protective cover 34. The hole 43a may form a plurality of small-diameter holes. The plurality of holes 43 a may be formed on the entire surface of the plate-shaped protective cover 34, or may be formed only on a part of the surface. Thus, by forming the hole 43a in the protective cover 34, weight reduction can be achieved, and the protective cover 34 (hot air) can be provided with an exhaust function.

As shown in FIG. 7, a tail pipe 44 is provided at the rear of the exhaust gas purification device 20, which is connected to the urea SCR catalyst 22 and discharges the purified exhaust gas sent from the urea SCR catalyst 22 to the outside of the fuselage. In a state where the exhaust gas purifying device 20 is installed, the tail pipe 44 is mounted so that the exhaust gas outlet 44a is disposed at the upper part of the fuselage and the exhaust gas outlet 44a faces rearward. The tail pipe 44 is provided at a connection portion connected to the urea SCR catalyst 22 with a jet-type suction unit 45 for sucking air into the tail pipe 44. By providing the jet-type air intake portion 45, external air is introduced into the tail pipe 44 by a jet-type effect, and the temperature of the exhaust gas can be reduced.

The injection type air intake unit 45 is disposed in the exhaust gas purification device 20 at a rear portion of the exhaust gas purification device 20 on the side opposite to the radiator 12 (see, for example, FIG. 4) side. In this way, the injection-type air intake portion 45 is arranged on the side opposite to the radiator 12 side, so that the air is sucked in along the flow direction of the air (outside air) from the radiator 12. Therefore, the surrounding area of the exhaust gas purification device 20 can be promoted. The air flows, and the hot air (internal air) can be efficiently discharged.

The connection portion 44 b of the tail pipe 44 and the urea SCR catalyst 22 is an insertion structure including a plurality of insertion portions. In this way, by providing a plurality of insertion portions, when the tail pipe 44 is assembled, the tail pipe 44 can be temporarily placed in a mounted state. In addition, since the number of man-hours is also reduced, assembling the tail pipe 44 is facilitated, and productivity can be improved.

<Placement part 42 of support member 40> Next, the above-mentioned placement part 42 which forms the upper part of the support member 40 is demonstrated with reference to FIG. 8-10, and another figure. 8 and 9 are schematic plan views illustrating the support member 40 for explanation. FIG. 10 is a schematic enlarged plan view illustrating the support member 40 for explanation. The exhaust gas purification device 20 supported by the support member 40 is also shown in FIG. 8, and only the support member 40 is shown in FIG. 9. In addition, FIGS. 8 to 10 show the plane of the mounting portion 42 when the support member 40 is viewed in a plan view.

As shown in FIG. 8, the support member 40 is supported by a unit composed of a DPF 21 and a urea SCR catalyst 22 as an exhaust gas purification device 20 behind the engine room 10 in which the engine 11, the radiator 12, and the radiator fan 13 are housed. On the fuselage frame 2. An exhaust gas purification device 20 is placed on a mounting portion 42 forming an upper portion of the support member 40. As shown in FIG. 9, the mounting portion 42 is provided at a front portion in the recessed portion 8 a of the grain box 8.

As shown in FIGS. 9 and 10, the mounting portion 42 is formed with an opening portion 42 a that opens in a central portion of the mounting portion 42 in a plan view. Therefore, when the mounting portion 42 is viewed from below with the exhaust gas purification device 20 supported by the support member 40, the exhaust gas purification device 20 is exposed from the opening portion 42 a of the mounting portion 42.

According to the above configuration, the mounting portion 42 of the support member 40 is formed with the opening portion 42 a so that the mounting portion 42 does not hinder the flow of the outside air that is drawn into the exhaust fan 20 by the radiator fan 13. Therefore, the cooling efficiency of the exhaust gas purification device 20 can be improved.

In addition, as shown in FIG. 10, an air guide plate 43 is provided below the opening portion 42 a of the mounting portion 42 to guide external air sucked by the radiator fan 13 (see FIG. 9) toward the opening portion 42 a. As shown in FIGS. 6 and 10, the air guide plate 43 is formed into a tapered shape that is gradually extended so as to be continuous with the lower end edge of the opening portion 42 a.

According to the above configuration, it is possible to more reliably bring the external air sucked by the radiator fan 13 into contact with the exhaust gas purification device 20. This can promote cooling of the exhaust gas purification device 20 and suppress overheating of the exhaust gas purification device 20.

<Structure Around Grain Box 8> Next, a structure around the grain box 8 will be described with reference to FIGS. 11 to 15. 11 to 15 are schematic diagrams for explaining the configuration of the periphery of the grain tank 8, respectively. In the following, the structure around the grain tank 8 (the conveying screw 50, etc.) is demonstrated first. Next, the arrangement of the urea water tank 25 will be described using FIGS. 11 and 12, the arrangement of the vibration device 52 will be described using FIGS. 13 and 14, and the arrangement of the inspection port 53 of the grain tank 8 will be described using FIGS. 11 and 15. .

As shown in FIGS. 11 to 15, a conveying screw 50 is provided at the bottom of the grain box 8. The conveying screw 50 conveys the grains stored in the grain box 8 from the front side in the front-rear direction of the grain box 8 to the rear side. It is inserted into the transfer metal piece 51 (refer FIG. 3 and FIG. 4) provided in the back of the grain tank 8. The transfer metal piece 51 feeds the fed grains to a vertical screw conveyor 9 a (see FIG. 1) of the grain discharge screw conveyor 9 connected to the upper portion of the transfer metal piece 51.

The conveyance screw 50 conveys the grain stored in the grain tank 8 to the rear side of the grain tank 8, and conveys it to the delivery metal 51. In addition, it is preferable that the recessed portion 8 a formed in the grain tank 8 bulges inward (right side) to a position facing above the conveying screw 50, or a position beyond the above position. As a result, it is possible to reduce the load such as the weight of the grains stored in the grain tank 8 which is applied to the conveyance screw 50.

As shown in FIGS. 11 and 12, an inclined surface inclined upward from the bottom of the built-in transport screw 50 to the left and right sides is formed on the lower part of the grain box 8. A urea water tank 25 that stores urea water delivered to the urea SCR catalyst 22 of the exhaust gas purification device 20 is disposed in a space below the inclined surface on one side (right side) of the outside of the body. In the above case, the urea water tank 25 is preferably provided such that the water supply port 25a of the urea water faces the rear of the fuselage. With the water supply port 25a of the urea water tank 25 facing rearward, for example, the cover can be removed from the water supply port 25a by hand, and water can be supplied from the carrying case, thereby facilitating the water supply operation to the urea water tank 25.

In addition, the urea water tank 25 is covered with an outer lower cover 8b which is detachably attached to the outer lower part of the grain tank 8. Accordingly, since the urea water tank 25 is protected by the outer lower cover 8b, for example, it is possible to prevent the urea water tank 25 from being contaminated or damaged due to mud or the like caused by the traveling device 3 (see FIG. 1).

As shown in FIGS. 13 and 14, below the recessed portion 8 a in which a part of the exhaust gas purifying device 20 (see FIGS. 3 and 4) is stored in the grain tank 8, the grain conveyed by the conveying screw 50 is prevented from stagnating in A vibration device 52 is provided on the conveyance path. The vibrating device 52 vibrates by hitting an inclined surface on the left side of the lower part of the grain tank 8. In this way, by arranging the vibration device 52 below the recessed portion 8a of the grain box 8, even if the lower surface 8aa of the recessed portion 8a is formed at a gentle inclination angle, the grains are dropped by the vibration. Thereby, the volume of the grain tank 8 can be ensured.

In addition, an inspection port 53 is provided on the upper surface of the grain tank 8. As shown in FIGS. 11, 13, and 15, the inspection port 53 is provided on the side (right side) that is the outer side of the fuselage in the left-right direction compared with the recessed portion 8 a of the grain tank 8. In this way, the inspection port 53 is disposed directly above the recessed portion 8 a, so that when the operator views the inside of the grain box 8 from the inspection port 53, the recessed portion 8 a does not become a blind spot, so that each of the grain boxes 8 can be connected Confirmed in the corner. That is, it is possible to ensure visibility from the inspection port 53.

Other effects and modifications can be easily derived by those skilled in the art. Therefore, the embodiments with a larger scope of the present invention are not limited to the specific details and typical embodiments shown and described as described above. Therefore, various changes can be made without departing from the scope of the attached patent application and the spirit or scope of the general inventive concept defined by its equivalent.

1‧‧‧ combine harvester

2‧‧‧frame

3‧‧‧ Driving device

3a‧‧‧track

3b‧‧‧Drive Wheel

3c‧‧‧Tightening pulley

4‧‧‧ Control Unit

4a‧‧‧cab

4b‧‧‧Control seat

5‧‧‧ Harvesting device

5a‧‧‧point straw

5b‧‧‧Lifting device

6‧‧‧ Grain rod conveying device

7‧‧‧Thresher

8‧‧‧ Grain Box

8a‧‧‧concave

8aa‧‧‧ lower surface

8b‧‧‧Outer lower cover

9‧‧‧ Grain discharge screw conveyor

9a‧‧‧longitudinal screw conveyor

9b‧‧‧Horizontal Screw Conveyor

9c‧‧‧Discharge tube

10‧‧‧Engine Room

11‧‧‧diesel engine (engine)

11a‧‧‧Exhaust pipe

12‧‧‧ Radiator

13‧‧‧ Radiator Fan

20‧‧‧Exhaust gas purification device

 21‧‧‧ Diesel Particulate Filter (DPF)

22‧‧‧Urea SCR catalyst

23‧‧‧ Dosing Kit (DM)

24‧‧‧Supply Components (SM)

24a‧‧‧Support

25‧‧‧Urea water tank

25a‧‧‧ water inlet

30‧‧‧ cover

30a‧‧‧One side cover (the first cover)

30b‧‧‧The other side's hood (2nd hood)

31‧‧‧ recess

32‧‧‧ rear end (rear end face)

32a‧‧‧ Upper edge

33‧‧‧ Hole

34‧‧‧Protective cover

40‧‧‧ support parts

 41‧‧‧ legs

41a‧‧‧shield

42‧‧‧mounting section

42a‧‧‧ opening

43‧‧‧Air deflector

43a‧‧‧hole

44‧‧‧ tail tube

44a‧‧‧Exhaust

44b‧‧‧Connection Department

45‧‧‧jet suction section

50‧‧‧ transport spiral

51‧‧‧ handover metal parts

52‧‧‧Vibration device

53‧‧‧Checkpoint

FIG. 1 is a schematic left side view of a combine harvester according to an embodiment. Fig. 2 is a schematic top view of a combine harvester according to an embodiment. FIG. 3 is a schematic left side view for explaining the arrangement of the exhaust gas purification device. FIG. 4 is a schematic plan view illustrating the arrangement of the exhaust gas purification device. FIG. 5 is a schematic front view illustrating a supporting structure of the exhaust gas purification device. FIG. 6 is a schematic rear view illustrating the supporting structure of the exhaust gas purification device. FIG. 7 is a schematic perspective view of a cover covering the exhaust gas purification device. FIG. 8 is a schematic plan view (1) for explaining the supporting member. FIG. 9 is a schematic plan view (No. 2) illustrating the supporting member. FIG. 10 is a schematic enlarged plan view illustrating a support member. FIG. 11 is a schematic front view illustrating the structure (part 1) around the grain tank. FIG. 12 is a schematic right side view illustrating the structure (part 1) around the grain tank. FIG. 13 is a schematic front view illustrating the structure (part 2) around the grain box. FIG. 14 is a schematic right side view for explaining the structure (second) of the periphery of the grain tank. FIG. 15 is a schematic plan view for explaining a structure (third) around the grain box.

Claims (4)

A combine harvester is provided with a radiator fan (13) for sucking external air between an engine (11) and a radiator (12) provided on a fuselage frame (2), and the combine harvester The machine is provided with an exhaust gas purifying device (20) for purifying the gas exhausted from the engine (11), and the combine is characterized in that the combine harvesting mechanism is provided on the fuselage frame (2) A support member (40) supported by the exhaust gas purification device (20), the exhaust gas purification device (20) is supported on an opening (42a) formed in an upper portion of the support member (40), and is supported by the radiator fan (13) ) At least a part of the sucked external air flows through the opening portion (42a) toward the exhaust gas purification device (20). The combine harvester according to item 1 of the scope of patent application, wherein the exhaust gas purifying device (20) is disposed behind the engine (11) and below the opening (42a) of the support member (40) An air deflector (43) is provided, and the air deflector (43) will be taken in by the radiator fan (13) and the external air flowing to the rear of the engine (11) is guided to the exhaust gas purification device (20). According to the combine harvester according to item 1 or 2 of the scope of the patent application, wherein the rear side of the engine (11) is provided on the left and right sides of the fuselage frame (2) with a threshing mechanism for the grain rod. A threshing device (7) is provided on the rear side of the engine (11) on the left and right side of the fuselage frame (2) with a grain box (8) for storing threshing grains, and the grain box ( 8) It is provided to be rotatable around the longitudinal axis of the fuselage. The upper part of the exhaust gas purification device (20) is provided with covers (30a, 30b) formed by dividing left and right. The combine according to item 3 of the scope of patent application, wherein the front surface of the exhaust gas purification device (20) is covered by the cover (30a, 30b), and the rear surface side of the exhaust gas purification device (20) is open .