JP2001098901A - Turbine and flywheel turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a turbine and a flywheel turbine which can remarkably enhance the output power per unit flow rate and the efficiency, by causing a jet stream to successively impinge upon blades on several stages, which are circumferentially arranged while preventing increase in back pressure in a working fluid passage within the turbine, and outflow of unused working fluid. SOLUTION: A turbine rotor 30 is opposed to a stator 60 supported in a housing 24 having a nozzle 12 and a exhaust port 14, and is formed therein with annular rings 42b, 44b and an annular jet passage 54, and first and second guides 60b, 60b' are arranged in an annular jet passage so as to deflect the jet stream of working fluid into directions toward blades 42b", 44b". With this arrangement, the counter torque of the turbine can be minimized, and the efficiency of the turbine can be enhanced.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine, and more particularly to a turbine and a flywheel turbine that can be used for a water turbine, a steam turbine, and a gas turbine.

[0002]

2. Description of the Related Art Representative steam turbines are disclosed in U.S. Pat. Nos. 5,385,446 and 5,624,235. In these turbines, the stationary blades and the moving blades are arranged in multiple stages in the axial direction, and the working fluid flows out in the axial direction. Generally, the rotor blade has a convex blade outer surface (rear surface)
And a concave blade inner surface, and a working fluid is caused to collide with the blade inner surface to generate a positive torque. At this time,
Since the back surface collides with the working fluid flowing in the axial direction and generates a reaction (negative torque) in the rotating direction of the rotor blade, an output torque is generated on the output shaft that is offset by the positive and negative torques. Moreover,
Since this type of turbine rotates at high speed, the peripheral speed of the turbine rotor increases, and at this time, a strong fluid wall in which the blades and the fluid are integrated in the housing due to a strong centrifugal force is generated. At this time, the back pressure increases and the working fluid becomes difficult to flow in the axial flow direction, and the turbine efficiency is significantly reduced. Furthermore, there are many spaces between the housing and the blades of the turbine rotor, and unused working fluid flows out of these spaces without colliding with the rotor blades, so that the output and efficiency per unit flow rate deteriorate. . For this reason, the volume of the working fluid increases, and the boiler and the heat exchanger become large, which causes an increase in energy cost. In addition, the structure of the turbine is complicated, the number of parts is tens of thousands or more, and the manufacturing cost and the maintenance cost are high.

[0003] US Pat. No. 5,071,312 discloses a turbine in which a number of stationary blades are formed in a circumferential direction of a stator, and a number of moving blades are formed in the circumferential direction of a rotor opposed thereto. . In this turbine, the back surface of the rotor blades collides with the working fluid flowing in the radial direction and counter torque acts on the rotor, so that the output of the rotor is attenuated. Also,
The turbine structure is complicated and the manufacturing cost is high.

Japanese Patent Application Laid-Open No. 4-81,502 discloses a turbine in which a partition is provided on the outer periphery of a rotor to form a circumferential flow path. In this turbine, since a large number of moving blades are directly arranged in the ejection flow path of the working fluid so as to intersect the same, the moving blade itself becomes a wall and the working fluid cannot flow out at high speed in the circumferential direction. At this time, the rotor blade of the turbine rotor and the working fluid are integrated by centrifugal force, and a strong back pressure is generated in the flow path of the working fluid by a strong fluid wall. Moreover, since the working fluid tends to stay in the space between the rotor blades,
When the turbine rotor rotates, the back surface of the rotor blade collides with the working fluid remaining in the space, and a large negative (counter) torque is generated. As described above, the efficiency of the turbine having the above structure is extremely low, and it is difficult to use the turbine for a large engine or a steam turbine.

[0005]

The above-described turbine has a large anti-torque and a remarkable increase in the back pressure in the working fluid flow path, so that the turbine efficiency per unit flow rate decreases,
The turbine structure became complicated and large.

It is an object of the present invention to provide a small, high performance, low cost turbine and flywheel turbine.

Another object of the present invention is to provide a turbine and a flywheel turbine that can be used as a steam turbine, a hydraulic turbine, or a gas turbine.

Another object of the present invention is to provide a flywheel turbine capable of obtaining a stable output even with intermittent supply of a working fluid.

[0009]

According to a first aspect of the present invention, a turbine includes a housing having nozzle means for supplying a jet stream of a working fluid in a tangential direction and a discharge port for discharging the working fluid, and a turbine disposed inside the housing. Stator means;
A turbine rotor rotatably housed in a housing adjacent to the stator means, the turbine rotor including an annular jet passage communicating with the nozzle means and the outlet, and an annular ring extending on both sides of the annular jet passage. A first guide for causing the jet stream to impinge on the first stage blade means, the plurality of blade means being provided at intervals in a circumferential direction so that an inner peripheral surface of the annular ring faces the annular jet passage. This is achieved by providing means and second guide means for causing the jet stream ejected from the first stage blade means to impinge on the second stage blade means.

According to a second aspect of the present invention, there is provided a housing having a nozzle means for supplying a jet stream of a working fluid to a flywheel turbine in a tangential direction and a discharge port for discharging the working fluid, and a stator means arranged inside the housing. A flywheel rotatably housed in a housing, the flywheel including a pair of annular rings formed on the outer periphery thereof and an annular jet passage formed therebetween, and each of the annular rings has an inner peripheral surface thereof. A first guide means for deflecting the jet stream to the first-stage blade means, comprising a plurality of stages of blade means formed at intervals in the stator, wherein the stator means is disposed in the annular jet passage close to the nozzle means; Providing a second guide means for deflecting the jet stream ejected from the first-stage blade means to the subsequent-stage blade means Is achieved by

[0011]

In the turbine and flywheel turbine of the present invention, a turbine rotor or a flywheel is rotatably housed in a housing, and an annular jet passage and an annular ring functioning as a flow path of a working fluid are formed in the turbine rotor or the flywheel. By arranging the blade means in the annular ring and arranging the stator means in the annular jet passage, the obstacle of the working fluid in the flow path is eliminated to facilitate the flow of the fluid, and the generation of the anti-torque. To minimize the back pressure of the working fluid,
The entire amount of working fluid in the flow path is made to collide with the blade means so that unused working fluid is not generated, so that turbine efficiency is dramatically improved, and compactness, cost reduction, and energy saving are achieved. Things.

[0012]

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. 1 and 2, the flywheel turbine 10 includes a housing 24 having a nozzle 12 and an outlet 14 for a front stage, a nozzle 16 and an outlet 18 for a middle stage, and a nozzle 20 and an outlet 22 for a rear stage. The nozzles 16, 18, 20 supply a jet stream of working fluid to the housing 24 and the outlets 14, 1
Reference numerals 8 and 22 discharge the working fluid from the housing 24. As shown in FIG. 2, the front outlet 14 is connected to the middle nozzle 16, the middle outlet 18 is connected to the rear nozzle 20, and the working fluid is sequentially expanded at the front, middle, and rear stages,
The expanded fluid is discharged to the next process through the discharge port 22. A turbine rotor 26 formed of a flywheel is connected to an output shaft 28 and rotatably housed in the housing 24. The turbine rotor 26 is composed of first, second and third flywheel rotor disks 30, 32, 34 of which the outer diameter gradually increases in the axial direction. The flange 36 and the press ring 38 are fixed by connecting bolts 40. First rotor disk 30
Constitutes a flywheel composed of divided central disk portions 42, 44. The central disk portions 42, 44 are formed with annular bottom portions 42a, 44a extending in the axial direction, annular rings 42b, 44b, and an annular jet passage 54, respectively. Have been. The annular rings 42b, 44b are spaced apart in the axial direction, and
4 facing the inner peripheral surface 42b ′, 44b ′. The annular rings 42b, 44b are respectively provided with inner peripheral surfaces 42b ', 44
A plurality of blades 42b "and 44b" are formed at equal intervals in the circumferential direction inside b '. As shown in FIG. 3, the blades 42b ", 44b"
A concave portion formed inside the inner peripheral surfaces 42b 'and 44b' of the 44b and opening to the annular jet passage 54, the concave portion has a collision jet portion intersecting the annular jet passage 54 at an acute angle α, The stream is returned to the annular jet passage 54.

Returning to FIGS. 1 and 2, the second rotor disk 32 includes divided central disk portions 46 and 48, annular bottom portions 46a and 48a, annular rings 46b and 48b, and an annular jet passage 56. Similarly, the third rotor disk 34 includes divided central disk portions 50 and 52, annular bottom portions 50a and 52a, and annular rings 50b and 52b.
And an annular jet passage 58. The second and third rotor disks 32, 34 have blades 46b ″, similar to FIG.
48b ″, 50b ″, 52b ″. The annular jet passage 5 of the first to third rotor disks 30, 32, 34
4, 56, and 58 have the flow path cross-sectional areas increasing in the axial direction.

In FIG. 2, the annular jet passages 54, 56, 5 of the first to third rotor disks 30, 32, 34 are provided.
Front, middle and rear stators 60, 62, 64 are arranged in the housing 24 so as to seal the outer periphery of 8.
The stators 60, 62, and 64 have annular stator rings 60a, 62a, and 64a, each of which has an outer diameter that is sequentially increased.
Which are fixedly supported in the housing 24 by suitable means. Annular stator rings 60a, 62a,
64a are annular jet passages 5 near each nozzle.
First guide means 60b, 6 arranged at 4, 56, 58 to deflect the jet stream and impinge on the first stage blade means
2b and 64b, and a second guide means 60b 'for deflecting the jet stream ejected from the first-stage blade means to sequentially collide with the second-stage blade means. As shown in FIG. 3, the first guide means 60b has a wedge shape for directing the jet stream to the blade means on both sides, and the second guide means 60b 'is separated from the inner peripheral surfaces 42b', 44b 'at a predetermined interval. And extends parallel into the annular jet passage 54. The stator 60 further includes an inner peripheral surface 42 of the annular ring.
b ', 44b' are arranged adjacent to each other and the opening degree control means 60b "for periodically changing the opening degree of the jet stream from the first stage blade means is provided. The annular stator rings 60a, 62a, 64a and the rotor are provided. Disk 30, 3
Labyrinth seals 60c, 6
2c, 64c are arranged to prevent leakage of the working fluid from the annular jet passages 54, 56, 58.

Returning to FIG. 1, a guide piece 66 is supported at an intermediate position between the nozzle 12 and the discharge port 14 on the annular stator ring 60 a of the former stage stator 60.
Reference numeral 6 denotes a discharge port 14 which is fitted into the annular jet passage 54 and forcibly removes the working fluid remaining in the annular jet passage 54.
It has the role of eliminating. The guide piece 66 has an introduction surface 66a extending tangentially to one end of the annular jet passage 54 from the inner surface of the nozzle 12 and a curved surface disposed at the other end of the annular jet passage 54 for forcibly discharging the working fluid to the discharge port 14. A guide surface 66b is provided. A labyrinth seal 68 is provided between the vicinity of the center of the guide piece 66 and the bottom of the annular groove 54 to fluidly separate the nozzle 12 and the outlet 14. Although not shown in FIG.
The rear stage stator 64 is also provided with the guide piece as described above.

1 and 3, the jet flow of the working fluid supplied from the nozzle 12 is divided in two directions by the first guide means 60b of the stator 60, and collides with the first-stage blades 42b ″ and 44b ″ to cause the turbine rotor to rotate. 30 is given a positive rotational torque. First stage blade 42b ", 4
The jet streams respectively ejected from the collision ejection sections 4b "are deflected again by the second guide means 60b 'and collide with the subsequent blades 42b", 44b ". In this manner, the jets flow to the subsequent blades 42b", 44b ". The jet flow expands and collides with each other to give rotational energy to the turbine rotor 30.
Is discharged to In the above process, the turbine rotor 30
Rotates, the inner peripheral surfaces 42b 'and 44b' of each of the blades 42b "and 44b" periodically pass through the aperture control means 60b "of the stator 60. In this case, the blades 42b" and 44b " The impinging jet is closed instantaneously, at which time the jet stream is displaced by the blades 42b ", 44.
b ", the inertia force and the reaction force cause the blade 42
b ", increasing pressure energy within 44b"
A large rotational force is applied to the first stage blades 42b ", 44b". In this state, when the impingement jets of the blades 42b ", 44b" deviate from the opening degree control means 60b "due to the rotation of the turbine rotor 30, the fluid energy accumulated from the first stage blade is jetted into one machine and the second guide means 60
The jet stream is deflected by b ′ so that the subsequent blade 42
b ", 44b". Turbine rotor 30
Is rotated at a low speed every time the impinging portion of the blade passes through the opening degree control means 60b ", and generates a low speed and high torque. At this time, the jet flow in the annular jet passage 54 is sequentially jetted at a high speed in the circumferential direction. The rotor 42 collides in a circumferential direction with the blades 42 b ″ and 44 b ″ of the turbine rotor 30 to apply rotational energy of only positive torque. At this time, the entire amount of the jet stream collides with the blades by the stator 30, so The working fluid discharged from the preceding turbine is sequentially supplied to the middle and subsequent turbines, and the working fluid generates positive torque while expanding in the middle and subsequent turbines. Is not exposed to the annular jet passage, no negative torque is generated, and the centrifugal force is generated in the outflow direction of the working fluid. Back pressure due to the wall of the fluid due does not occur. Moreover, the working fluid for impinging one after another into a plurality of blades in the circumferential direction, the turbine efficiency per unit flow rate is remarkably improved.

FIG. 4 shows a turbine according to a second embodiment of the present invention, and the same reference numerals are used for the same parts as those in FIGS. In FIG. 4, the turbine 70 discharges the nozzle 12 for supplying the working fluid in the counterclockwise direction, the outlet 14 for discharging the working fluid, and the nozzle 16 for introducing the working fluid in the clockwise direction, and the fluid. And a housing 24 having an outlet 18 for the outlet. The outlet 14 communicates with the nozzle 16. The turbine 70 further includes first and second turbine rotors 30 each composed of a flywheel fixedly supported on the first and second output shafts 72 and 74, respectively.
32 and stators 60 and 62. The first output shaft 72 has a flange 72a, to which the rotor disks 42, 44 are connected by bolts 76. Similarly, the output shaft 74 has a flange 74a against which the rotor disks 46, 4
8 is fixed. The second output shaft 74 is formed of a hollow shaft, and thereby the first output shaft 72 is rotatably supported via bearings 84 and 86. The left end of the first output shaft 72 and the outer periphery of the second output shaft 74 are supported by bearings 88 and 90 supported by the housing 24. In FIG. 4, the turbine rotor 32 constituting the clockwise drive unit 94 is shown.
Of the turbine rotor 30 and the guide blade 60b of the stator constituting the counterclockwise driving unit 92, that is, in the clockwise direction. Second
It is arranged to drive the output shaft 74. In the above structure, when the working fluid is supplied from the first nozzle 12 and the second nozzle 16 to the annular jet passages 54 and 56 in the counterclockwise direction and the clockwise direction, respectively, the first and second turbine rotors 30 and 32 move in the opposite directions. It is driven clockwise and clockwise. Therefore, the first and second output shafts 72, 74
Is rotated at low speed and high torque in the directions indicated by arrows CCW and CW, respectively. Accordingly, the turbine 70 is suitable for driving a contra-rotating turboprop of a jumbo jet, a propeller of a helicopter, or a contra-rotating propeller of a ship. In this case, US Pat.
No complicated gear reversing mechanism as disclosed in No. 00 is required, and there are various advantages. And in the case of aircraft,
Even if the engine stops, the flywheel effect allows the propeller to continue rotating for a long time, enabling soft landing and dramatically improving aviation safety.

As is clear from the above, according to the turbine and flywheel turbine of the present invention, there is no back pressure due to a strong fluid wall in the flow direction of the jet flow, and the jet flow in the circumferential direction is Since the blades sequentially collide with a plurality of blades, the positive torque increases and the turbine efficiency is dramatically improved. Moreover, since the flywheel turbine accumulates rotational energy, it prevents the pulsation of rotation and enables the intermittent supply of working fluid, for example, when the flywheel turbine of the present invention is applied to a gas turbine. Since fuel can be supplied intermittently, the generation of harmful substances in exhaust gas can be reduced, and significant energy savings can be achieved, which greatly contributes to the global environment.

[Brief description of the drawings]

FIG. 1 is a partial sectional view of a flywheel turbine according to a preferred embodiment of the present invention.

FIG. 2 is a partial sectional view taken along line II-II in FIG.

FIG. 3 is a diagram showing a positional relationship between a turbine rotor and a stator shown in FIG. 2;

FIG. 4 is a sectional view of a flywheel turbine according to a second preferred embodiment of the present invention;

[Explanation of symbols]

Reference Signs List 10 flywheel turbine 12, 16, 20 nozzle, 14, 18, 22 outlet, 24 housing, 26 turbine rotor, 28 output shaft, 30, 3
2,34 rotor disk, 36,38 flange,
40 connecting rod, 42, 44, 46, 48, 50, 52
Central disk part, 54, 56, 58 Annular jet passage, 60, 62, 64 Stator

Claims (8)

[Claims] 1. A housing having nozzle means for supplying a jet stream of a working fluid in a tangential direction and a discharge port for discharging a working fluid; stator means disposed inside the housing; An annular jet passage communicating with the nozzle means and the discharge port, and an annular ring extending on both sides of the annular jet passage, and an inner peripheral surface of the annular ring. Is provided with a plurality of blade means formed at intervals in the circumferential direction so as to face the annular jet passage, wherein the stator means includes a first guide means for causing the jet stream to collide with the first-stage blade means, and a first-stage blade means. A turbine provided with a second guide means for causing an ejected jet stream to impinge on a subsequent blade means. 2. The opening degree control according to claim 1, wherein the first guide means is arranged adjacent to the inner peripheral surfaces of the annular rings on both sides, and the opening degree of the jet flow from the blade means is periodically changed. A turbine comprising means. 3. The impingement jet according to claim 1, wherein each of the blade means has a recess opening into the annular jet passage, and the recess has an impingement jet intersecting the jet passage at an acute angle. A turbine that recirculates the jet stream to the annular jet passage. 4. The turbine according to claim 3, wherein the turbine rotor comprises divided first and second rotor disks, each of which has an annular ring and an annular jet passage. 5. The first and second stators according to claim 1 or 2, wherein the stator means comprises an annular stator ring fixed in the housing adjacent the outer periphery of the turbine rotor, the annular stator ring being housed in the annular jet passage. A turbine comprising two guide means. 6. A housing having nozzle means for supplying a jet stream of working fluid in a tangential direction and an outlet for discharging working fluid, stator means disposed inside the housing, and rotatably housed in the housing. A plurality of flywheels, each of which has a pair of annular rings formed on the outer periphery thereof and an annular jet passage formed therebetween, and the annular rings are respectively formed at intervals on an inner peripheral surface thereof. Comprising step blade means,
First guide means for deflecting the jet stream to the first blade means, wherein the stator means is disposed in the annular jet passage close to the nozzle means, and deflects the jet stream ejected from the first blade means to the subsequent blade means A flywheel turbine comprising a second guide means for causing the flywheel to rotate. 7. The flywheel turbine according to claim 6, wherein the flywheel comprises divided first and second rotor disks, each of the rotor disks having an annular ring and an annular jet passage. 8. The method according to claim 6, wherein the nozzle means is adapted to supply first and second tangential jet streams.
And a second nozzle, wherein the stator means are respectively the first nozzle and the second nozzle.
And a first and second stator for deflecting the first and second jet streams, wherein a flywheel is rotatably disposed within the first and second stators, respectively, and the first and second stators respectively comprise a first and a second stator.
And first and second turbine rotors driven to rotate in a second direction, the second turbine rotor having a hollow output shaft, and the first turbine rotor being rotatably housed concentrically in the hollow output shaft. Flywheel turbine with an output shaft.