WO2020096033A2 - タービン装置 - Google Patents
タービン装置 Download PDFInfo
- Publication number
- WO2020096033A2 WO2020096033A2 PCT/JP2019/043818 JP2019043818W WO2020096033A2 WO 2020096033 A2 WO2020096033 A2 WO 2020096033A2 JP 2019043818 W JP2019043818 W JP 2019043818W WO 2020096033 A2 WO2020096033 A2 WO 2020096033A2
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- WIPO (PCT)
- Prior art keywords
- turbine
- compressor
- combustor
- housing
- drive
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
Definitions
- the present invention relates to a turbine device.
- a turbine device is known in which air or the like is applied to the turbine to rotate the turbine, and the rotation of a shaft that rotates in synchronization with the turbine is used for power generation, for example.
- Patent Document 1 discloses an example of such a turbine device.
- the turbine is rotated by the steam supplied through the steam passage. Further, the rotational force of the turbine is transmitted to the gear portion housed in the gear chamber through the turbine shaft connected near the rotation center of the turbine.
- the gear unit is composed of a plurality of gears having different gear ratios.
- the gear part is adapted to change the ratio of rotation of the turbine transmitted through the turbine shaft and transmit it to a generator or the like.
- the present invention has been made in view of the above circumstances, and an object of the present invention is to provide a turbine device that can efficiently use the energy from which a fluid is blown to rotate a turbine.
- the power generation device A disk-shaped drive turbine connected to one end of a drive shaft rotatably supported, A cylindrical turbine housing containing the drive turbine; A combustor connected to the turbine housing for generating combustion gas to be sent to the turbine housing, The direction of the combustion gas blown into the turbine housing is tangential to the outer periphery of the drive turbine.
- the drive turbine has a plurality of blades formed at predetermined intervals along a circumferential direction, and the blade has a dimension with respect to an axial direction of the drive turbine. It is characterized in that the central portion of the width is V-shaped protruding in the rotation direction.
- the central portion in the width direction of the blade has a V-shape protruding in the rotation direction, so that the wind hitting the blade is prevented from escaping outward in the width direction. Therefore, the combustion gas is more efficiently used for rotating the drive turbine, and the drive turbine rotates at a higher speed. Thereby, power generation efficiency and the like can be increased.
- the combustor is tubular, and further includes a compressor unit that is connected to the combustor and sends compressed gas to the combustor, and the compressor unit is the drive shaft.
- the combustor is formed such that the first connecting portion between the combustor and the compressor portion extends in the same direction as the tangential direction of the outer circumference of the impeller.
- the second connecting portion between the combustor and the turbine housing is formed so as to extend in the same direction as the tangential direction of the outer circumference of the turbine housing.
- the first connecting portion between the combustor and the compressor portion is formed so as to extend in the same direction as the tangential direction of the outer circumference of the impeller, so that the compressed gas is efficiently transferred to the combustor. It is sent inside. Further, since the second connecting portion between the combustor and the turbine housing is formed so as to extend in the same direction as the tangential direction of the outer circumference of the turbine housing, the combustion gas is efficiently fed into the turbine housing. As a result, the energy can be efficiently used to rotate the drive turbine, and the power generation efficiency and the like can be increased.
- the compressor sections are adjacent to each other in the axial direction of the drive shaft, and are configured to be symmetrical with respect to each other via a compressor connection section that is a connection section.
- a first compressor section of the first compressor section and a second impeller section of the second compressor section, the bottom surfaces of the first impeller and the second impeller section of the second compressor section are opposed to each other;
- One connecting portion is provided at a position that is an outer periphery of the compressor connecting portion.
- the first compressor section and the second compressor section are configured to be symmetrical with respect to each other via the compressor connecting section which is a connecting section, and the first impeller and the second impeller have bottom surfaces facing each other.
- the first connecting portion is provided at a position that is the outer periphery of the compressor connecting portion, so that only one compressed gas is discharged from the first compressor portion and the second compressor portion.
- FIG. 1 is a diagram showing a turbine device according to an embodiment of the present invention, as viewed from a side surface.
- FIG. 3 is a perspective view showing the same appearance.
- FIG. 3 is an axial sectional view of the same.
- FIG. 3 is a perspective view showing the external appearance of the drive turbine of the same.
- FIG. 3 is a view of the drive turbine as viewed from the outside in the radial direction.
- FIG. 3 is a sectional view for explaining the combustor.
- FIG. 3 is a view of the turbine device seen from one end in the axial direction.
- FIG. 3 is a diagram for explaining the discharge of combustion gas.
- FIG. 3 is a perspective view of the same in the axial direction.
- FIG. 6 is an explanatory diagram for explaining the second gear housing of the same.
- FIG. 3 is an explanatory diagram for explaining the first gear housing of the same.
- FIG. 3 is a view of the turbine device seen from one end in the axial direction.
- FIG. 3 is a diagram for explaining a small window portion of the turbine housing of the same.
- FIG. 3 is a diagram for explaining the blower device.
- FIG. 1 shows a turbine device 1 according to the present embodiment, and is a view of the turbine device 1 as seen from a side surface.
- FIG. 2 is a perspective view of the turbine device 1.
- FIG. 3 is an axial sectional view of the turbine device 1. Note that, in FIG. 3, the first impeller 41 and the second impeller 42 are not shown in cross section.
- the turbine device 1 is used, for example, in a generator, a ship engine, a train engine, or the like.
- the turbine device 1 includes a first compressor section 100, a second compressor section 200, a drive shaft 10, and the like.
- the first compressor section 100 includes a first housing 31, a first impeller 41, a first intake section 51, and the like.
- the first compressor unit 100 is a centrifugal compressor.
- the second compressor section 200 also includes a second housing 32, a second impeller 42, a second intake section 52, and the like.
- the second compressor section 200 is a centrifugal compressor.
- the first compressor section 100 and the second compressor section 200 are arranged side by side in the axial direction of the drive shaft 10 and are connected to each other.
- the drive shaft 10 is inserted through the first compressor section 100 and the second compressor section 200.
- the first compressor section 100 and the second compressor section 200 are configured to be symmetrical with respect to each other via a compressor connecting section 400 that is a connecting section (boundary) of each other.
- the axial direction of the drive shaft 10 will be simply referred to as the axial direction.
- a through hole is formed in the first impeller 41 in the axial direction, and the drive shaft 10 is inserted through the through hole.
- a recess is provided in the through hole of the first impeller 41 along the axial direction, and a protrusion that engages with the recess is provided at a position of the drive shaft 10 that faces the recess. The engagement between the concave portion and the convex portion allows the first impeller 41 to rotate in synchronization with the drive shaft 10. It can be said that the first impeller 41 is axially supported by the drive shaft 10.
- the first impeller 41 has a circular outer periphery when viewed in the axial direction.
- a surface of the first impeller 41 which is located on the second compressor section 200 side and is perpendicular to the axial direction, is a bottom surface.
- the end of the first impeller 41 on the side opposite to the bottom surface in the axial direction is the upper end.
- the outer circumference circle (circumscribed circle) at the upper end has a smaller diameter than the outer circumference circle at the bottom surface.
- the first impeller 41 is formed such that the outer diameter gradually increases from the upper end toward the bottom surface.
- a surface formed between the upper end and the bottom surface of the first impeller 41 and inclined with respect to the axial direction is a hub surface.
- the second impeller 42 is formed in the same manner as the first impeller 41, and thus redundant description will be omitted.
- the second impeller 42 has a plurality of blades 42a.
- the first impeller 41 is housed inside the first housing 31.
- the first housing 31 is formed in a shape that covers the first impeller 41 along the outer shape of the first impeller 41.
- the first housing 31 has a bottom portion 31a facing the bottom surface of the first impeller 41, and an end portion on the axially opposite side of the bottom portion 31a is open. In other words, the end of the first housing 31 on the axially opposite side from the bottom 31a is an open end.
- the second housing 32 is formed in the same manner as the first housing 31, and thus redundant description will be omitted.
- the second housing 32 has a bottom portion 32a.
- the first housing 31 and the second housing 32 are connected to each other with the bottom 31a and the bottom 32a facing each other. Further, the bottom portion 31a and the bottom portion 32a are provided with holes 11 through which the drive shaft 10 is inserted.
- a first intake portion 51 having a flow path 51 a is connected to an opening end of the first housing 31.
- the flow path 51 a has a function of taking in gas from the outside in the radial direction of the first taking-in portion 51 and guiding the gas into the inside of the adjacent first housing 31.
- the first intake portion 51 includes a support portion 51b that supports the drive shaft 10 together with the bearing 2.
- a second intake portion 52 having a flow path 52a is connected to an opening end of the second housing 32.
- the second loading section 52 is formed in the same manner as the first loading section 51, and thus redundant description will be omitted.
- the second intake portion 52 includes a support portion 52b that supports the drive shaft 10 together with the bearing 2. It can be said that the drive shaft 10 is rotatably supported by the support portion 51b of the first intake portion 51 and the support portion 52b of the second intake portion 52.
- a cylindrical turbine housing 60 is connected to an end of the first intake portion 51 on the axially opposite side from the side connected to the first housing 31.
- a drive turbine 70 is housed inside the turbine housing 60.
- the drive turbine 70 is connected to an end of the drive shaft 10 and is rotatable integrally with the drive shaft 10.
- the drive turbine 70 is fixed to the drive shaft 10 by being fastened with the nut member 9 (shown in FIG. 2).
- FIG. 4 is a perspective view showing the appearance of the drive turbine 70.
- FIG. 5 is a view of the drive turbine 70 as viewed from the outside in the radial direction.
- the drive turbine 70 includes a disk-shaped rotating plate 71, a plurality of blades 72 standing on the outer peripheral side surface of the rotating plate 71, a shaft hole 73, and the like.
- the shaft hole 73 is formed so that the end portion of the drive shaft 10 can be inserted therein.
- a plurality of blades 72 are provided at predetermined intervals along the circumferential direction.
- the blade 72 is a thin plate member and is formed to have a V shape. As shown in FIG.
- the blade 72 has a substantially center of the width S directed toward the turbine rotation direction (arrow Z direction shown in FIG. 4). Has a protruding shape.
- FIG. 3 It returns to FIG. 3 and demonstrates.
- One end of the combustor 80 is connected.
- the other end of the combustor 80 is connected to the outer peripheral surface of the turbine housing 60.
- a first connecting portion 81 an end portion of the combustor 80 having a pipe shape (tubular shape) on the side of the first compressor portion 100 and the second compressor portion 200 is referred to as a first connecting portion 81.
- the end portion of the combustor 80 on the turbine housing 60 side is referred to as a second connecting portion 82.
- the first connecting portion 81 is tangential to the outer periphery of the first housing 31 on the bottom 31a side (the bottom 32a side of the second housing 32), that is, the outer periphery of the bottom surface side of the first impeller 41 (bottom surface side of the second impeller 42). Is a portion extending in substantially the same direction as the tangential direction of.
- the second connecting portion 82 is a portion provided so as to extend in a direction substantially the same as the tangential direction of the outer circumference of the turbine housing 60.
- the first compressor section 100 compresses the gas sucked through the first intake section 51 by the rotation of the first impeller 41, and sends the compressed gas to the combustor 80.
- the second compressor section 200 is configured to compress the gas sucked through the second intake section 52 by the rotation of the second impeller 42 and send the compressed gas to the combustor 80.
- the first connecting portion 81 is provided with an intake port for taking in the compressed gas sent from the first compressor unit 100 and an intake port for taking in the compressed gas sent from the second compressor unit 200. The first connecting portion 81 collects the compressed gas taken in through the two inlets into one and sends it out to the combustor 80.
- a spark plug 83 and a fuel pump 84 are attached to the combustor 80.
- the fuel pump 84 is provided to inject fuel such as gasoline into the combustor 80.
- the fuel injection amount can be controlled by a fuel pump control device (not shown).
- gasoline is injected from the fuel pump 84, a mixed gas of compressed gas and gasoline is created inside the combustor 80.
- the spark plug 83 spark plug
- spark plug is provided for spark ignition of the mixed gas.
- combustion occurs, and the combustion gas is sent to the inside of the turbine housing 60 via the second connecting portion 82.
- FIG. 9 is a perspective view of the axial sectional view shown in FIG.
- the first impeller 41 and the second impeller 42 are adapted to rotate in the direction of arrow F.
- the compressed gas is discharged in the same direction as the tangential direction of the outer periphery of the first impeller 41 and the second impeller 42 on the bottom surface side, but the first connecting portion 81 is provided so as to be in the same direction as the tangential direction. There is. Therefore, the first connecting portion 81 can efficiently and smoothly take in the compressed gas.
- the second connecting portion 82 is provided so as to be in the same direction as the tangential direction of the outer circumference of the turbine housing 60. Therefore, the second connecting portion 82 can efficiently and smoothly send the combustion gas into the turbine housing 60.
- the combustor 80 is provided so as to extend obliquely with respect to the axial direction of the drive shaft 10.
- the position of the second connecting portion 82 is a position that is moved by a predetermined amount in the rotation direction of the drive turbine 70 with respect to the position of the first connecting portion 81.
- FIG. 7 is a diagram of the turbine device 1 viewed from one end in the axial direction (the drive turbine 70 side).
- a blowout guide portion 61 that restricts the direction of the flow of the combustion gas sent from the combustor 80 is provided.
- a plurality of blowout guide portions 61 are provided at positions corresponding to the second connecting portions 82 of the combustor 80.
- the blow-out guide portion 61 is a plate-shaped portion that is erected on the inner peripheral surface of the turbine housing 60 along the axial direction, and its angle is substantially the same as the tangential direction of the outer periphery of the drive turbine 70 (rotating plate 71). They are formed to be the same. As a result, the combustion gas guided by the blow-out guide portion 61 efficiently hits the blades 72 of the drive turbine 70, and the drive turbine 70 rotates smoothly.
- the angle of the blowout guide portion 61 is substantially the same as the tangential direction of the outer circumference of the rotating plate 71, but the angle of the blowout guide portion 61 is the tangential line of the outer circumference of the entire drive turbine 70 including the blades 72. It may be substantially the same as the direction.
- a thin plate member having a small window portion 63 may be further provided at the tip of the blowing guide portion 61.
- the small window portion 63 is an opening provided to allow the combustion gas to pass therethrough, and is provided at a position facing the apex of the V-shape of the blade 72 of the drive turbine 70 and the area around it.
- the vanes 72 are V-shaped to prevent the combustion gas hitting the vanes 72 from escaping outward in the width direction. As a result, the combustion gas is efficiently captured by the blades 72, and the rotation of the drive turbine 70 is promoted.
- FIG. 8 is a diagram for explaining the discharge of combustion gas.
- the combustion gas hitting the blades 72 is discharged to the outside in the axial direction with respect to the axial direction, and is discharged to the inside in the axial direction.
- the turbine housing 60 is provided with an exhaust guide portion 62 for exhausting the combustion gas exhausted inward in the axial direction to the outside.
- a plurality of discharge guide portions 62 are provided on the inner peripheral surface side of the turbine housing 60 and at a position between the adjacent blow-out guide portions 61.
- the discharge guide portion 62 has a folded-back portion having a U-shaped cross section on the side opposite to the discharge port in the axial direction (that is, on the axially inner side).
- the combustion gas discharged toward the inner side in the axial direction by hitting the blades 72 has its flow direction reversed by the folded portion of the discharge guide portion 62 and is guided to the outer side in the axial direction.
- the combustion gas hitting the blades 72 does not hinder the rotation of the drive turbine 70, and the drive turbine 70 rotates more smoothly.
- the gear housing 300 is connected to an end of the second intake portion 52 opposite to the side where the second housing 32 is connected.
- the gear housing 300 includes a first gear housing 310 and a second gear housing 320.
- FIG. 10 is a sectional perspective view for explaining the inside of the second gear housing 320.
- the second gear housing 320 accommodates the drive shaft 10, the small diameter gear 121, the large diameter gear 122, the bearing 5 (shown in FIG. 3), the oil pump 123, and the like.
- the small-diameter gear 121 is inserted through the drive shaft 10 and rotates in synchronization with the drive shaft 10.
- the oil pump 123 also includes a pump shaft 123a. As shown in FIG. 3, the pump shaft 123 a is installed inside the second gear housing 320 so as to be rotatable via the bearing 5.
- the large diameter gear 122 is inserted through the pump shaft 123 a and meshes with the small diameter gear 121.
- the large diameter gear 122 is adapted to rotate as the small diameter gear 121 rotates.
- the large diameter gear 122 is adapted to rotate in synchronization with the pump shaft 123a.
- the inner rotor and the outer rotor are rotated as the pump shaft 123a is rotated, whereby oil is sucked, discharged, and pressure-fed.
- the oil pump 123 for example, supplies oil to the bearing 2 (see FIG. 3) that supports the drive shaft 10.
- the oil filter 124 in FIG. 10 is attached to remove foreign matter contained in the oil.
- FIG. 11 is a cross-sectional perspective view for explaining the inside of the first gear housing 310.
- a rotation transmission mechanism is provided in the first gear housing 310.
- the rotation transmission mechanism reduces the rotation of the drive shaft 10 and outputs torque proportional to the reduction ratio.
- the rotation transmission mechanism includes a sun gear 111, a planetary gear 112, a ring gear 113, a carrier 114, an output shaft 115, and the like.
- the rotation transmission mechanism is a star-type planetary gear mechanism.
- the sun gear 111 is inserted through the drive shaft 10. As a result, the sun gear 111 rotates in synchronization with the drive shaft 10. Further, the planetary shaft 6 is provided on the bottom portion 311 inside the first gear housing 310. Plural planetary shafts 6 are provided inside the first gear housing 310. The planetary gear 112 is inserted through the planetary shaft 6 together with the bearing 7 and meshes with the sun gear 111. As shown in FIG. 11, a plurality of planetary gears 112 are installed around the sun gear 111. The planetary gear 112 is adapted to rotate with the rotation of the sun gear 111. The planetary gear 112 also meshes with a ring gear 113 described later.
- the ring gear 113 is an internal ring gear.
- a carrier 114 which is an arm, is connected to the surface of the ring gear 113 opposite to the side facing the bottom portion 311.
- a columnar output shaft 115 is provided, one end of which is formed to project toward the outside of the first gear housing 310.
- the output shaft 115 is provided so as to be coaxial with the drive shaft 10. As shown in FIG. 3, the output shaft 115 is rotatably supported by the first gear housing 310 via the bearing 8.
- FIG. 12 is a diagram of the turbine device 1 viewed from one end in the axial direction (on the output shaft 15 side).
- the ring gear 113 serves as a driven shaft and the sun gear 111 serves as a drive shaft, and the ring gear 113 rotates in the direction opposite to the sun gear 111.
- the turbine device 1 includes a blower device 90.
- the blower 90 blows compressed gas into the turbine housing 60 when the power is turned on.
- the direction in which the blower 90 blows out the compressed gas is substantially the same as the direction in which the blowout guide portion 61 guides the combustion gas, that is, the tangential direction of the outer periphery of the drive turbine 70.
- the operation of the turbine device 1 will be described.
- the compressed gas hits the drive turbine 70 and the drive turbine 70 starts rotating.
- the drive turbine 70 rotates
- the drive shaft 10 rotates and the first impeller 41 and the second impeller 42 rotate.
- gas is taken in through the first intake section 51 and the second intake section 52, the gas is compressed, and the compressed gas is transferred to the combustor 80.
- the mixed gas of the compressed gas and the fuel is ignited inside the combustor 80, and the combustion gas is blown into the inside of the turbine housing 60.
- the combustion gas blown into the turbine housing 60 causes the drive turbine 70 to rotate.
- the blower 90 is turned off.
- the rotational speed of the drive turbine 70 can be adjusted by adjusting the fuel injection amount in the combustor 80.
- the direction of the combustion gas blown into the turbine housing 60 is the tangential direction of the outer periphery of the drive turbine 70, the energy for blowing the fluid is efficiently generated. It can often be used to rotate the drive turbine 70. Thereby, power generation efficiency and the like can be increased.
- the turbine device 1 has been described as having both the first compressor section 100 and the second compressor section 200, but it may be configured to have only one of them.
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Abstract
Description
回転可能に支持された駆動シャフトの一端に連結された円板状の駆動タービンと、
前記駆動タービンを収容する円筒状のタービンハウジングと、
前記タービンハウジングに連結され、前記タービンハウジングに送る燃焼ガスを発生する燃焼器とを備え、
前記タービンハウジングの内部に吹き出される前記燃焼ガスの向きが、前記駆動タービンの外周の接線方向となっていることを特徴とする。
図1は、本実施形態に係るタービン装置1を示すもので、タービン装置1を側面から見た図である。図2は、タービン装置1の斜視図である。図3は、タービン装置1の軸方向断面図である。なお、図3において、第1インペラ41および第2インペラ42は断面としていない。タービン装置1は、例えば、発電機、船のエンジン、電車のエンジン等に用いられる。
第1インペラ41は、上端から底面に向かうにつれて外径が徐々に大きくなるように形成されている。また、第1インペラ41の上端と底面との間に形成され、軸方向に対して傾斜した面をハブ面とする。第1インペラ41のハブ面には、複数のブレード41aが、第1インペラ41の周方向に沿って所定の間隔ごとに立設されている。
第2インペラ42は、第1インペラ41と同様に形成されているため、重複する説明を省略する。第2インペラ42は、複数のブレード42aを有している。
第2ハウジング32は、第1ハウジング31と同様に形成されているため、重複する説明を省略する。第2ハウジング32は、底部32aを有している。
第2ハウジング32における開口端には、流路52aを有する第2取込部52が連結されている。第2取込部52は、第1取込部51と同様に形成されているため、重複する説明を省略する。第2取込部52は、軸受2とともに駆動シャフト10を支持する支持部52bを備えている。駆動シャフト10は、第1取込部51の支持部51bと、第2取込部52の支持部52bとに、回転可能に支持されているといえる。
図4に示すように、駆動タービン70は、円板状の回転板71、回転板71の外周側面に立設された複数の羽根72および軸孔73等を備えている。軸孔73は、駆動シャフト10の端部を挿入可能に形成されている。羽根72は、周方向に沿って所定の間隔ごとに複数設けられている。羽根72は、薄い板状部材で、V字形状となるように形成されている。図5に示すように、駆動タービン70の軸方向に対する羽根72の寸法を幅Sとすると、羽根72は、幅Sの略中央が、タービンの回転方向(図4に示す矢印Z方向)に向かって突出した形状となっている。
以下、図1および図2に示すように、パイプ状(管状)である燃焼器80における第1コンプレッサー部100および第2コンプレッサー部200側の端部を、第1連結部81とする。また、燃焼器80におけるタービンハウジング60側の端部を、第2連結部82とする。
第1連結部81は、第1ハウジング31の底部31a側(第2ハウジング32の底部32a側)の外周の接線方向、すなわち第1インペラ41の底面側(第2インペラ42の底面側)の外周の接線方向と略同一の向きに延在する部位である。また、第2連結部82は、タービンハウジング60の外周の接線方向と略同一の向きに延在するように設けられている部位である。
図8中に矢印で示すように、羽根72に当たった燃焼ガスは、軸方向に対して軸方向外側に排出されるものと、軸方向内側に排出されるものとがある。タービンハウジング60には、軸方向内側に排出された燃焼ガスを外部に排出するための排出ガイド部62が設けられている。排出ガイド部62は、タービンハウジング60の内周面側であって、隣接する吹出ガイド部61の間となる位置に複数設けられている。排出ガイド部62は、排出口とは軸方向反対側(すなわち軸方向内側)に、断面U字状の折り返し部を有している。このため、羽根72に当たって軸方向内側に排出された燃焼ガスは、排出ガイド部62の折り返し部によって流れの向きが反転され、軸方向外側に導かれるようになっている。これにより、羽根72に当たった燃焼ガスが駆動タービン70の回転を妨げることなく、駆動タービン70がよりスムーズに回転するようになっている。
図10は、第2ギアハウジング320の内部について説明するための断面斜視図である。第2ギアハウジング320には、駆動シャフト10、小径ギア121、大径ギア122、軸受5(図3に示す)、およびオイルポンプ123等が収容されている。
オイルポンプ123では、ポンプシャフト123aが回転することに伴い、インナーロータおよびアウターロータが回転するようになっており、これによりオイルが吸入、吐出され、圧送されるようになっている。オイルポンプ123は、例えば、オイルを、駆動シャフト10を支持する軸受2(図3参照)に供給するようになっている。なお、図10におけるオイルフィルター124は、オイルに含まれる異物を除去するために取り付けられている。
図11は、第1ギアハウジング310の内部について説明するための断面斜視図である。第1ギアハウジング310には、回転伝達機構が設けられている。回転伝達機構は、駆動シャフト10の回転を減じ、減速比に比例したトルクを出力するようになっている。回転伝達機構は、サンギア111、プラネタリギア112、リングギア113、キャリア114および出力シャフト115等を備えている。回転伝達機構は、スター型の遊星歯車機構である。
図11に示すように、プラネタリギア112は、サンギア111の周囲に複数設置されている。プラネタリギア112は、サンギア111の回転に伴い、自転するようになっている。また、プラネタリギア112は、後述するリングギア113とも噛合している。
送風装置90の電源がONになると、圧縮気体が駆動タービン70に当たり、駆動タービン70が回転を開始する。次に、駆動タービン70が回転すると、駆動シャフト10が回転し、第1インペラ41および第2インペラ42が回転する。次に、第1インペラ41および第2インペラ42が回転すると、第1取込部51および第2取込部52を介して気体が取り込まれ、気体が圧縮されて、圧縮気体が燃焼器80に送り込まれる。次に、燃焼器80の内部で圧縮気体と燃料との混合気体が点火され、燃焼ガスがタービンハウジング60の内部に吹き出される。次に、タービンハウジング60の内部に吹き出された燃焼ガスにより、駆動タービン70が回転する。当該燃焼ガスによって駆動タービン70が回転するようになると、送風装置90は電源がOFFとなる。なお、燃焼器80における燃料の噴射量を調整することで、駆動タービン70の回転速度が調節できるようになっている。
41 第1インペラ(インペラ)
42 第2インペラ(インペラ)
60 タービンハウジング
70 駆動タービン
72 羽根
80 燃焼器
81 第1連結部
82 第2連結部
100 第1コンプレッサー部(コンプレッサー部)
200 第2コンプレッサー部(コンプレッサー部)
400 コンプレッサー連結部
Claims (4)
- 回転可能に支持された駆動シャフトの一端に連結された円板状の駆動タービンと、
前記駆動タービンを収容する円筒状のタービンハウジングと、
前記タービンハウジングに連結され、前記タービンハウジングに送る燃焼ガスを発生する燃焼器とを備え、
前記タービンハウジングの内部に吹き出される前記燃焼ガスの向きが、前記駆動タービンの外周の接線方向となっていることを特徴とするタービン装置。 - 前記駆動タービンは、周方向に沿って所定の間隔ごとに形成された複数の羽根を有し、
前記羽根は、前記駆動タービンの軸方向に対する寸法である幅の中央部が、回転方向に向かって突出したV字形状となっていることを特徴とする請求項1に記載のタービン装置。 - 前記燃焼器は管状であり、
前記燃焼器に連結され、前記燃焼器に圧縮気体を送るコンプレッサー部をさらに備え、
前記コンプレッサー部は、前記駆動シャフトに軸支されたインペラを有し、
前記燃焼器は、前記燃焼器と前記コンプレッサー部との第1連結部が、前記インペラの外周の接線方向と同じ向きに延在するように形成されているとともに、前記燃焼器と前記タービンハウジングとの第2連結部が、前記タービンハウジングの外周の接線方向と同じ向きに延在するように形成されていることを特徴とする請求項1または請求項2に記載のタービン装置。 - 前記コンプレッサー部は、前記駆動シャフトの軸方向に隣接し、互いの連結部であるコンプレッサー連結部を介して対称となるように構成された第1コンプレッサー部および第2コンプレッサー部を備え、前記第1コンプレッサー部の第1インペラと、前記第2コンプレッサー部の第2インペラとはそれぞれの底面同士が対向するように配置されているとともに、前記第1連結部が、前記コンプレッサー連結部の外周となる位置に設けられていることを特徴とする請求項3に記載のタービン装置。
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JPH02196136A (ja) * | 1988-12-22 | 1990-08-02 | Saram Ahmed | 内燃機関 |
JP2001020701A (ja) * | 1999-07-01 | 2001-01-23 | Ntn Corp | エアタービン駆動スピンドル装置 |
JP2004019617A (ja) * | 2002-06-19 | 2004-01-22 | Katsumi Asada | 発電装置 |
US7628018B2 (en) * | 2008-03-12 | 2009-12-08 | Mowill R Jan | Single stage dual-entry centriafugal compressor, radial turbine gas generator |
FR2960259B1 (fr) * | 2010-05-19 | 2018-03-23 | European Aeronautic Defence And Space Company Eads France | Compresseur thermodynamique |
JP5004373B1 (ja) * | 2011-10-28 | 2012-08-22 | 佳行 中田 | 回転型内燃機関 |
US8978389B2 (en) * | 2011-12-15 | 2015-03-17 | Siemens Energy, Inc. | Radial inflow gas turbine engine with advanced transition duct |
JP6019794B2 (ja) * | 2012-06-20 | 2016-11-02 | 株式会社豊田中央研究所 | ラジアルタービンロータ、及びこれを備えた可変容量ターボチャージャ |
GB2551181A (en) * | 2016-06-09 | 2017-12-13 | Hieta Tech Limited | Radial flow turbine heat engine |
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