CN1004566B - Fluid-controlled rotary machine - Google Patents

Abstract

A rotating machine that uses fluids in various ways, such as an air compressor, pumps for liquids, hydraulic or air motors, internal combustion engines (diesel type or other). It has a cylindrical rotor with a recessed interior at one end, which houses in tight-fitting and sealing relationship a stationary cylindrical strut for mounting a plurality (usually a pair) of rotating blades. The rotor is provided with a plurality of corresponding cavities which are threaded to receive respective blade portions which enter and pass through corresponding cavities to compress or propel the particular fluid concerned according to the specific properties of the machine. Various means are provided for maintaining the synchronous rotation of the blades and rotor.

Description

fluid controlled rotating machinery

The present invention relates to fluid-acted rotary machines, such as air compressors and pumps, and fluid-acted rotary machines, such as internal combustion engines and air or hydraulic motors.

A machine of this type is disclosed in my U.S. Patent No. 3,477,414, issued November 11, 1969, entitled "Rotary Machine Using Fluid". Among them, there are a pair of rotating blades on opposite sides of a central rotor, the tips of the blades pass through corresponding cavities provided on the central rotor, and the effect of this pair of blades is to gradually change the cavity between the opposing blade surfaces The volume of the part, so as to achieve the purpose of the specific machine concerned. Since then, so-called "single-screw" air compressors utilizing the same principle have been developed and marketed. Among them, a pair of circular, rimless multi-spoked wheel blades replaced the slender blades shown in my patent, and a threaded helical rotor replaced the binary blade shown in my patent. Cavity rotor. All of this is demonstrated by the Chicago Pneumatic Tool Company's commercial literature reporting on its "single propeller" air compressors.

The present invention constitutes an improvement over my patented and "single propeller" machines. The blades now lie one above the other on corresponding parallel axes in a fixed cylindrical support of the rotor. The inner surface of the rotor is provided with cavities to receive the light ends of the corresponding blades. The blades and rotors can be different from the so-called "single propeller" type air compressors shown in my patent or mentioned above.

Through such modifications, completely unexpected results were obtained. The volume of fluid being transferred at any given time is much greater than it would be without retrofitting, resulting in a more compact and lighter machine per unit volume of fluid being transferred. In the case of an internal combustion engine, that means extraordinary tightness and lightness per horsepower and access to far more torque. This machine combines the advantages of a piston engine (variable volume) and a turbine (high-speed rotary motion). In addition, this mechanical energy is integrated with an electric machine to produce another beneficial use, and can be made into the form of an artificial heart.

This application is a continuation-in-part of my similarly titled Applied Application No. 628406, filed July 6, 1984, which discloses additional implementations that are presently contemplated as the best mode of carrying out the invention example.

In the attached picture:

1 is a top plan view of an air compressor secured to and extending in cantilever form from a vertical post in accordance with the present invention.

FIG. 2 is a front elevational view of the air compressor of the garden 1. FIG. The rotor cavities, vanes, and coupling gears hidden behind in the compression half-circle working position are indicated by dotted lines.

Fig. 3 is a horizontal sectional view along line 3-3 of Fig. 2, and the range of the lower blades is indicated by dashed lines.

Figure 4 is a similar sectional view without the vane drive mechanism showing the relative position of the vanes at the end of the subsequent quarter duty cycle.

Figure 5 is a view comparable to Figure 4 but showing the relative positions of the vanes at the end of one compression cycle and the beginning of the next compression cycle.

Figure 6 is a vertical sectional view taken along line 6-6 of Figures 2 and 3 with the cylindrical blade strut removed, showing the shape of the cavity and the corresponding blade location.

Figure 7 is a similar sectional view showing the same relative position of the rotor cavity and blades for the subsequent quarter of the duty cycle, with the other rotor cavity just visible.

Figure 8 is a similar cross-sectional view showing the respective relative positions of the rotor and the vanes at the end of one compression cycle and the beginning of the next compression cycle.

Figure 9 is a side view of the machine from the left of Figure 1, with the rotor removed to reveal the upper blades during breaks, the inner inlets for the air flow and the outlet channels for the compressed air, which are themselves indicated by dotted lines.

Figure 10 is a view corresponding to Figure 6, but showing an alternative arrangement of inlets and passages (shown in phantom) in the airflow which pass through the rotor instead of the cylindrical blade struts. This arrangement would be employed if the elongated blades and binary cavities of the previous figures were replaced by multi-spoke rimless wheels and corresponding multivariate cavities.

Figure 11 is a view largely equivalent to Figure 3, but showing an example of an internal combustion engine according to the invention, the combustion chambers of which are shown in dashed lines.

Fig. 12 is a side view equivalent to Fig. 9, but of the example of the internal combustion engine of Fig. 11, the combustion chambers of which are indicated by dotted lines.

Figure 13 is a side view similar to Figure 12, but viewed from the right of Figure 1 rather than the left.

Figure 14 is a top plan view of Figures 11-13 with the seal ring installed.

Figure 15 is a vertical sectional view of Figure 14 taken along line 15-15.

Figure 16 is a view similar to Figure 14 but showing an example of elongated blades synchronized without gears.

Figure 17 is a schematic two-dimensional view of the cylindrical inner surface of a rotor suitable for use with the blade of Figure 16, showing the cavity of the rotor.

Figure 18 is a horizontal section through the axis similar to Figure 3 but showing a presently preferred embodiment of the invention in the form of an air compressor.

Figure 19 is a vertical sectional view of Figure 18 taken along line 19-19.

FIG. 20 is a schematic perspective view of a sealing arrangement for a combustion engine having the compressor blade arrangement of FIGS. 18 and 19. FIG.

Figure 21 is a view similar to Figure 4 but showing a presently preferred embodiment. Where the blades are circular so as to occupy the maximum volume of the corresponding compression chamber, the drive mechanism is similar to that of Figures 18 and 19.

FIG. 22 is a two-dimensional schematic diagram similar to FIG. 17 but corresponding to the example of FIG. 21 .

Fig. 23 is a view similar to Fig. 11 showing an inboard engine used as an aircraft engine.

Fig. 24 is a view corresponding to Fig. 23, but shows that the air compressor of Figs. 18 and 19 is added to the structure of Fig. 23, the rotors are connected and started together, and the combination of this motor and air compressor can be used as a belt A jet engine combustor with a diverging nozzle (not shown) or a stationary compressor.

Figure 25 is a view similar to Figure 24, but corresponding only to the portion of the air compressor of Figure 24 which is used as the rotor portion of an electric motor and functions as a motor drive.

Fig. 26 is a view corresponding to Fig. 11, showing the machine as an electric motor incorporated into an engine as the driving means of the generator.

Fig. 27 is a view corresponding to Fig. 20, showing the configuration of seal rings used for the respective rotors in the examples of Figs. 11, 23, 24, 25 and 26.

Figure 28 is a cross-sectional view through the axis of an artificial heart in which the present invention is embodied as a pump device.

In the form of the invention illustrated in Figures 1-9, an air compressor is mounted in the form of a cantilever beam by a vertical support structure 15 of any suitable configuration and held stationary during operation. However, the air compressor can be installed in a variety of ways depending on how it will be used.

As shown, the mounting bracket 16 extends in any suitable manner from where it is secured to a stationary cylindrical blade strut 17, see FIGS. 2 and 9 . The strut carries a rotatable rotor 18 in sealing relationship with the strut, one end of which is recessed inwardly to receive the cylindrical blade strut. After the rotor is mounted on the blade strut 17, the compression ring 16a is fastened to the rotor 18 to hold the rotor on the strut. As shown, the opposite end of the rotor 18 is completely covered by the end cover plate 20a, but this is not a prerequisite.

The sealing is conveniently achieved by mixing the oil vapor with the sucked air in the usual manner, but if the rotor 18 is driven at high speed (approximately 20,000 R.P.M), such sealing may not be necessary. In the case where an effective seal is required, the elongated sealing strip S shown in Figure 9 acts as a known piston ring, which can run along the opposite sides of the compressed air outlet 19 and inlet 29 that run through the place. Install and cover both ports.

The rotor 18 has a power input shaft 20 extending from the end of the rotor 18 opposite to the aforementioned end where the shaft is secured by a removable closure cover 20a. Shaft 20 is connected in any suitable manner to starting means, such as an electric motor or other motor (not shown). The rotor has cavities, here shown as binary cavities 21 , which open into rotor cylindrical inner surfaces 18 a which engage the cylindrical surfaces of blade struts 17 .

The vane struts 17 are inwardly recessed to provide a chamber 22 for each vane 23 , where a pair of chambers coincide with a pair of cavities 21 provided by the rotor 18 . The cells 22 are divided by partition walls 17a, as shown in FIGS. 2 and 8 . Vanes 23 and their respective chambers, one above the other, are rotatably mounted on respective stub shafts 24 for rotation relative to each other.

The synchronous rotation of the blades and the synchronization of the rotation of the blades with the rotation of the rotor is due to the interconnection of the gears with the rotor 18, for example by the planetary gears 26 rigidly mounted on the rotor 18 and meshed with the corresponding balance shafts 27 in Figures 1, 2 and 3 The spur gear 25 is connected to the rotor 18 to complete. The balance shaft 27 has a bevel gear 28 that is connected to the corresponding blade short shaft 24 (these gears are preferably helical teeth). This gearing, as a means of synchronizing the blades and rotor, is unnecessary in the "single propeller" embodiment of the machine, where the blades are rimless multi-spoked wheels, as a result of the intermeshing of the sets of blades and rotor cavities themselves It acts as a synchronization device.

The vanes 23 are of any desired elongated configuration and counter-rotate within their respective chambers 22 . Their terminals enter and pass through corresponding cavities 21 . Due to their helical symmetry with respect to the axis of rotation of the rotor, this means that the volume of the cavity parts in front of the turning blades gradually decreases, and the air in these cavity parts is gradually compressed. The longitudinal edges of the vanes are skewed as at 23a so as to coincide with the helical orientation of the longitudinal walls of the corresponding cavities. The terminal portion of the vane that contacts the cavity wall is oil-sealed at low speeds as described above, but does not need to be sealed at high speeds.

As shown in the figure, the power input shaft 20 rotates counterclockwise, which drives the rotor counterclockwise and leads the blades 23 in the direction of the additional arrow, providing a balanced air compression stroke in these directions, so that the corresponding rotor cavity 21 The air in the reduced volume portion 21a is compressed, see FIGS. 6 and 7 .

The air inlets 29 at the cylindrical surface of the blade strut 17 in FIGS. 2 and 9 each have a passage 30 leading to the inlet from an opening 31 at the outwardly facing end of this blade strut. Atmospheric air is drawn into the compressor through these passages, the compressed air is discharged through a similar port 19 into a corresponding similar passage 32, and through the outlet and line 33 (Fig. 1) into a pressure tank ready for use.

The blades 23 rotate continuously, and the machine repeats the compression stroke every half revolution.

Air inlets and channels can be located in the rotor as shown in FIG. 10 . In this figure, an outlet 36 leads to the atmosphere, from which a channel 35 leads to an air inlet 34 of each cavity 21 . Such a device could be used with the elongated bladed example described if desired, but would be necessary for the previously mentioned but not yet described multi-spoke, "single propeller" type construction.

When constructing an internal combustion engine mounted in the same manner as an air compressor, as shown in Figures 11-15, a combustion chamber 37 is formed in the cylindrical blade strut (here marked 38), and, except for the diesel mode In addition, a spark plug 39 is installed to ignite the fuel mixture compressed in this combustion chamber. A fuel mixture is fed from a suitable carburetor through an external inlet 40 at the exposed end of the cylindrical vane strut and from there through passage 41 to internal inlet 42 . In diesel mode, the spark plugs are replaced by ordinary fuel injectors, and the size of the combustion chamber is appropriately reduced.

For the purpose of facilitating sealing as the vanes pass through the cavities 44 of their respective rotors 45, each vane 43 is preferably constructed as shown in FIGS. 14 and 15 . Each vane is made of two circular edge beveled portions 46 in planar contact with each other, edge to edge and joined by a central circular portion 47 below. After the sealing ring 49 is installed by fastening the opposite ends of the tightly enclosed sealing ring 49 to the corresponding part 46 with the pivot pin 50, the circular part 47 is firmly fixed in place with the press-fit pin 48. . Seal ring 49 is similar to piston rings, but is preferably made of spring steel. The ends of the two pairs of such rings are rotatably connected to each other by a resilient strip 51 (Fig. 14), usually of spring steel, which rotates about a pivot center 52.

The blade thus produced is fixedly mounted on a stub shaft 53 . A bevel gear is mounted on the stub shaft for meshing with a corresponding bevel gear of a transmission 54 which in turn is interconnected with the aforementioned power output shaft 55 for the air compressor power input shaft 20 .

Compression of the fuel mixture (or air in diesel mode) occurs on one side of the machine (the other handles exhaust) as in the compression stroke of the aforementioned air compressor. The compressed load is delivered to the combustion chamber 37 near the end of the compression stroke through a port 56 and passage 57 in Figures 11 and 12, the exhaust port 58 being closed by the inner surface of the rotor. As a result, the compressed fuel mixture in the combustion chamber is ignited and at the same time the exhaust port 58 is opened allowing the combusted gases to expand into the rotor cavity 44 from the other side. The machine is then driven and a compression cycle begins in this rotor cavity on the opposite side of the vane. Simultaneously, on the other side of the cylindrical blade strut, the removal of combusted gases begins, as the respective ends 46 of the blades 43 on that side of the blade strut 38 advance in the respective rotor cavities 44, such that The combusted gases are pushed out of the inner gas outlet 59 ( FIGS. 11 and 13 ), through the passage 60 and the outer gas outlet 61 at the exposed end of the vane strut 38 . Behind this forward vane end 46 , a quantity of fuel mixture (or air in diesel mode) flows through port 40 , channel 41 and port 42 .

Longitudinal seals S (Figs. 12 and 13) are installed along and cover compressor ports 56 and 58, 42 and 59, and 19 and 29 (Fig. 9).

This mechanism acts as a pump as shown in Figures 1-9 except that the air inlet 29 (Figure 9) becomes the liquid inlet and the discharge port must be elongated and relocated so that its center coincides with port 29 so that, The two sets of ports are always communicated with their corresponding rotor cavities in the corresponding working cycle. This does not mean that the discharge port has to be the same size as the inlet, since the volume discharged is equal to the volume entered by adjusting the amount of power input. This is ideal because it provides the advantages of a positive displacement pump over a rotary mechanism.

In the embodiment of Figures 9 and 10, the drain ports 19, channels 32 and drain ports 33 need only be replaced by ports and passages at opposite ends of the rotor cavity.

However, in both embodiments, separate pipes (similar to pipe 33 in Figure 1) connecting these inlet and discharge ports should be installed so that the pump will have only one inlet and one outlet.

Hydraulic motors and air motors are similar in construction and function to pumps.

In all embodiments, with the exception of the internal combustion engine, by providing a rimless multi-spoke wheel and corresponding multiple cavities according to the aforementioned commercial "single propeller" air compressors instead of the gear transmission as the rotational synchronization means is possible. By installing the teeth protruding from the middle of the length of the blade and the corresponding auxiliary rotor cavity from the opposite sides in the length direction of the blade, the continuous rotation of the blade similar to that obtained by the aforementioned multi-spoke rimless wheel is obtained and the same effect is achieved , is also possible. Like this, as shown in Figure 16, several sets of teeth 62 can be adorned on opposite sides of the lengthwise direction of the blade 63, and as shown in the schematic diagram of Figure 17, in the rotor garden between the small chamber 65 that accommodates the blade Several sets of auxiliary cavities 64 may be provided on the surface to receive the teeth.

For internal combustion engines, adding turbine blades directly to or around the rotor and supplying the air thus compressed to a carburetor or fuel injector in a conventional manner provides a turbocompressor of a conventional type. Such air can also be used to cool the rotor and seal oil as will be apparent to those skilled in the art.

The embodiment of Figures 18 and 19 is a simplified version of the air compressor of Figures 1-9 and is now recommended as the best mode currently contemplated for making such an air compressor as well as other forms of the invention such as pumps and motors .

In the simplified embodiment, a cylindrical blade support 66 is fixedly mounted by means of a wall bracket 67 as a fixed part of the device and carries a rotatable rotor 68 . The rotor 68 shown here has a body 68a of generally spherical configuration effectively providing two cavities 69 . These two cavities open respectively to the inner cylindrical surface of the rotor which interfaces with the cylindrical surface of the blade strut 66 . The ring 68b at the mounting end of the blade strut 66 and the plate 68c at its opposite end and the shaft corresponding to 20 secure the rotor to the blade strut 66 in much the same way as in the embodiment of FIGS. 1 and 2 .

A shaft 70 in the center of the blade strut 66 extends from the rigid mount to the rotor plate 68c and is journalled with bearings 72 and 73 . The shaft has a fixed gear 74 which meshes with a corresponding gear 75 ( FIG. 19 ) fixedly mounted on a corresponding stub shaft 76 of a corresponding blade 77 . Thus, the rotational motion of the rotor 68 is transmitted to each blade by a single shaft. In addition, this configuration most effectively provides air inflow passages 78 on opposite sides of shaft 70 extending from each inlet at the exposed end of fixed cylinder 66 almost to the opposite end and each corresponding compression Air flows out of channel 79 .

In cases where the machine constitutes a motor and it is necessary to install rotor seals, the system shown in Figure 20 can be used. Longitudinal sealing strips 80 and 81 shown in the figure extend from one end to the other along one side of the rotor on the peripheral contour of the cylindrical blade strut, and each has a set of seals from opposite ends of the strut. Inwardly extending arms 80a and 81a. The two sealing strips are hinged together at 82 and 83 respectively. Between the two arms at the opposite ends, the springs 84 of the sealing strips respectively push the sealing strips towards each other so that they are pressed against the respective vanes 77 . Springs 85 at the hinged ends of the arms force the seals 80 and 81 against the inner cylindrical surface of the rotor 68 as the rotor rotates. A set of similar sealing strips 86 and 87 are similarly mounted on the opposite side of the vane strut 66 and are also pressed against the corresponding inner cylindrical surfaces of the vanes 77 and rotor 68 by corresponding springs 88 and 89, respectively. . Fluid to be compressed enters a compression chamber in rotor 68 through opening 78a, from which compressed air exits through opening 79a. As a motor, gas enters the expansion chamber in the rotor 68 through opening 78a, and exhaust gas exits through opening 79a.

The embodiment of Figures 21 and 22 is also presently preferred. A best mode is presented here which is currently expected to be the largest for the working volume of the fluid concerned. Different from the elongated blade 77 among Fig. 18 and 19, the blade in the garden cylindrical blade strut 91 here is to have the garden-shaped structure of the radial oblong hole 92 that direction is opposite respectively, and the spiral wall 93 of rotor 94 is respectively Cooperate with these elongated holes, and the cavity 95 of this rotor is separated. The driving means of the rotor 94 and the air inlet and outlet are basically the same as in the embodiment of Figs. 18 and 19 .

The embodiment of FIG. 23 is an internal combustion engine similar to that of FIG. 11, which is used here as an aircraft engine to drive propeller 96. The impeller 96 is housed in a nose 97a of the rotor 97 . Air is drawn in through a front opening 99a of a casing 99 for attachment to the aircraft frame and is precompressed by compressor blades 97b mounted on the rotor 97 and movable between fixed blades 99b mounted on the casing 99 . Precompressed air flows through passage 100 to a conventional fuel mixing system (not shown) in housing rear portion 99c. Exhaust gases exit through openings 101 in housing portion 99c. A lubricating oil cooling and circulation system (not shown) may include transmission gear 102 and radiator coil 103 functioning as a pump. In this internal combustion engine, a seal ring system similar to that of Fig. 20 can be used, which is shown in Fig. 27 and will be described later.

Figure 24 shows an internal combustion engine substantially the same as that shown in Figure 23, coupled to an air compressor having circular blades similar to those of Figures 21 and 22. In this embodiment, the respective rotors 104a and 104b of the engine 105 and the compressor 106 are connected together to form a unit driven by the engine. Air enters the engine via an opening (not shown) in the front wall 107 a of the engine casing 107 , flows through a pre-compressor 108 and passage 109 to the compressor 106 . The cylindrical blade struts 110 and 111 are fixed rigidly to the casing 112, for example by means of bolts (not shown). When used as an industrial air compressor, its casing is fastened to any fixed frame. Engine exhaust may be directed through passage 113 for compression with intake air. The compressed air exits via corresponding channels 114 .

Fig. 25 shows an air compressor substantially equivalent to Fig. 24 but incorporated in a squirrel-cage induction motor serving as a drive. The rotor 115 of the compressor unit has a squirrel-cage secondary winding and also serves as the rotor of the electric motor. The primary winding 117 is mounted to and supported by a fixed housing constituting the stator of the motor. The housing 118 also supports the cylindrical blade support 19 . Electrical connection of the primary winding 117 to an alternate power source (current power source) is conventional.

Figure 26 shows an internal combustion engine substantially equivalent to the air compression machine of Figure 24, but mounted on a generator similar in construction to the squirrel-cage motor of Figure 25. As the generator rotor 120 rotates, the brushless DC exciter 121 feeds current to the rotor poles 122 , thereby inducing a voltage across the stator winding 123 . Electrical connections (not shown) are also conventional. This embodiment is particularly effective for electric traction wheels of vehicles and power supply units for ship propulsion.

In the engines of the foregoing embodiments, sealing is achieved in a manner similar to that shown in FIG. 20 . As shown in Figure 27, on the side of the cylindrical blade strut, a set of longitudinal sealing strips 124 and 125 with arms 124a and 125a respectively, are hinged at 126 and 127 respectively. The spring 128 corresponds to the spring 84 . On the opposite side of this blade strut, a set of auxiliary longitudinal sealing strips 129 and 130 with arms 129a and 130a are likewise hinged at 131 and 132 respectively, spring 133 corresponding to spring 88 . Here, however, the sets of arms 124a and 125a and 129a and 130a are pushed apart by respective springs 134 acting on arm extensions 135 and 136, respectively, rather than by separate sets of springs. Air for the fuel mixture enters the corresponding engine rotor compression cavity through inlet 137 , compressed fuel mixture enters the corresponding rotor cavity through port 139 , and exhaust gas exits through outlet 140 .

Fig. 28 shows the pump device 142 of the present invention as an artificial heart similar in structure to the unit shown in Figs. The rotor 144 of the pump unit 142 is generally spherical like the rotors of Figures 18 and 19 and fits within a suitable heart-shaped housing 145 for proper anchoring within a receptive human or animal body. Cylindrical blade struts 164 are mounted on housing 145 and have rotatable circular blades 147, respectively, which are interconnected by gears as in FIGS. 18 and 19 and are driven synchronously with rotor 144. Blood is pumped through inflow channels 148, 149 corresponding to the connected systemic and pulmonary veins, respectively, and through outlets 150 and 151, respectively, corresponding to the connected systemic and pulmonary arteries. The blades 147 are designed to reproduce the natural pumping cycle of the replaced heart, reminiscent of the pumping cycle of a human heart, where a pause occurs once per cycle. A cable 152 connected to a battery carried outside the body supplies power to two motors each driving the rotor 144 through a corresponding pinion 153 meshing with the ring gear of the rotor 144 . Each motor 143 itself can drive the rotor 144 . The two motors are mounted so that there is always a backup should one fail. Shaft 155 drives the synchronous gear.

As shown, the actual size of the artificial heart is basically the motor pumping 5 liters of blood per minute at a speed of about 35 revolutions per minute. If used as an assist device for the natural heart, the size and pumping capacity will be reduced accordingly.

Whereas the invention has been illustrated and described herein with specific reference to the embodiment which is the best mode presently contemplated for carrying out the invention, it should be understood that the invention may be adapted to various embodiments without departing from what is herein disclosed and which is defined by the following claims. The summarized main inventive ideas can produce multiple transformations.

Claims (59)

1, a kind of rotating machinery of fluid control, it includes

One is cylindrical and the rotor of power transmission is housed,

One and the close-fitting fixed cylinder of described rotor,

Be used to make described cylinder to be installed in device on the described cylinder with respect to the hard-wired device of described rotor with described rotor,

At least one pair of position in rotor is relative, be carved with spiral lamination and on the rotor barrel surface to the cavity of described fixed cylinder surface opening,

At least one pair of is contained in diametical side of direction on the described fixed cylinder and independently rotary blade separately, this vanes fixed on rectangular of the spin axis of described cylinder and described rotor,

Make described blade and the described rotor device of rotation synchronously,

Make the fluid in the described machinery flow into the device in the proal approach of described blade in the above-mentioned cavity,

The device that fluid is discharged from this machinery under described blade effect,

The invention is characterized in,

Described rotor one end has the cylindrical hole of indent,

Be contained in the indent cylindrical hole of described rotor described fixed cylinder coaxial line,

Described blade be slim-lined construction and be one on another configuration be rotatably installed in the corresponding chambers in the face of the fixed cylinder surface opening.

According to the machinery of claim 1, it is characterized in that 2, the device that supplies the device of fluid inflow and supply fluid to discharge comprises the inlet/outlet device of the periphery that leads to described fixed cylinder; The Stamping Steel Ribbon that upwards extends to another at described cylinder axis from an end is housed in the relative side of each described mouthful device.

3, according to the machinery of claim 1, it is characterized in that, blade is leptosomatic, and synchronizer comprises from the middle extended several groups of teeth of each opposing longitudinal edges of length of blade, and the auxiliary cavity of several groups of correspondences is arranged in the relative side of the cylindrical form interior surface of rotor, be used for when machine operation, admitting corresponding tooth.

4, according to the machinery of claim 2, it is characterized in that, Stamping Steel Ribbon comprise fixed cylinder with a few group leader's bars, respectively be assembled with Stamping Steel Ribbon be pressed against the opposite corresponding blade surface elastic device and Stamping Steel Ribbon is pressed against the elastic device of the rotor surface on opposite.

According to the machinery of claim 1, it is characterized in that 5, blade is the round structure that diametical radially elongated slot is arranged, and the spirality wall that the cavity of rotor is adapted to described elongated slot separately.

6, according to the machinery of claim 1, it is characterized in that, be used to make fixed cylinder to comprise a shell that is anchored on described cylinder rigidly and surrounds rotor basically with respect to the hard-wired device of rotor.

According to the machinery of claim 6, it is characterized in that 7, rotor has the secondary winding of an electricapparatus and shell has the secondary windings of described machinery.

According to the machinery of claim 6, it is characterized in that 8, fixed cylinder, blade and rotor are suitable for use as the pump-unit of an artificial heart, a brshless DC motor is housed in the shell, this motor drives described pump-unit by being connected with a power supply; The device that flows into for fluid comprises vena systemica and the pulmonary venous inlet that is used for connecting respectively a life entity, and the device of discharging fluid comprises and is used for connecting body artery and Pulmonic outlet respectively.

9, a kind of rotating machinery with fluid control of Structure of Internal-Combustion Engine, it includes

One is cylindrical and the rotor of power transmission is housed,

One with the close-fitting fixed cylinder of described rotor, be used to make described cylinder to be installed in device on the described cylinder with respect to the hard-wired device of described rotor and described rotor,

At least one pair of position in rotor is relative, be carved with spiral lamination and on the rotor periphery to the cavity of described fixed cylinder surface opening,

At least one pair of is contained in diametical side of direction and independently rotary blade on the described fixed cylinder separately, and this vanes fixed makes described blade and the described rotor device of rotation synchronously on the rectangular axle of the spin axis of described cylinder and described rotor,

Make the fluid in the described machinery flow into the device in the proal approach of described blade in the described cavity,

The device that fluid is discharged from this machinery under described blade effect,

A firing chamber,

Around the seal arrangement of each blade edge configuration of keeping in touch with the rotor cavity surface,

The device that igniting gaseous fuel mixture is used is housed in described firing chamber,

The device that fluid flows into include an outside inlet and one from this mouthful lead to of the vertical side of fixed cylinder inner enter the mouth go into circulation road, when a rotor cavity during via described inlet, this passage imports the place ahead that blade is advanced in this rotor cavity with a gaseous fuel mixture or air

A less mouth that is positioned at described fixed cylinder vertical opposite one side and leads to described firing chamber, the gaseous fuel mixture or the air that will compress when rotor cavity passes through less mouth are imported this firing chamber from this rotor cavity,

Outlet in the described firing chamber of described vertical offside of described fixed cylinder, the gaseous fuel mixture or the air that will compress when rotor cavity passes through less mouth are imported this firing chamber from this rotor cavity,

Outlet in the described firing chamber of described vertical offside of described fixed cylinder, the fuel mixture in will expanding when this outlet of rotor cavity process is transported to this rotor cavity from described firing chamber,

The device of discharging fluid comprise the interior outfall of a described vertical side in fixed cylinder and one lead to by this mouthful outside the passage of outfall, the rotor cavity of pressure expansion gas drain boles in a process is entered the atmosphere,

The invention is characterized in,

Described rotor one end has the cylindrical hole of indent;

Be contained in the cylindrical hole of indent of described rotor described fixed cylinder coaxial line;

Described blade is slim-lined construction and is one and disposes on another, is rotatably installed in the corresponding chambers in the face of the fixed cylinder surface opening,

Described firing chamber is in described fixed cylinder.

10, according to the machinery of claim 9, it is characterized in that, each blade is formed with the rounded portions that the plane contacts, the edge tightens together facing to the edge, with one the 3rd intermediate portion by two, seal ring is the elastic ring that cracks, one group end is anchored on described circular portion rotationally, and another group end is connected to each other with the same slender member of pivot pin that is contained in this end, and a pivot that this slender member is rotated is arranged in the middle of this slender member.

According to the machinery of claim 9, it is characterized in that 11, the fluid of inflow is a kind of gaseous fuel mixture, and ignition mechanism is a spark plug that links with the firing chamber.

According to the machinery of claim 9, it is characterized in that 12, the fluid of inflow is an air, and ignition mechanism is the fuel injector that is used for the firing chamber.

According to the machinery of claim 9, it is characterized in that 13, internal-combustion engine is contained on the shell that fixed cylinder is housed; Transmission device is connected with the rotor of described motor.

According to the machinery of claim 13, it is characterized in that 14, transmission device comprises the outstanding nose of an engine rotor and be contained in the propulsion device and the blade of this nose that shell is suitable for being contained in the launch vehicle resemble the aircraft.

According to the machinery of claim 13, it is characterized in that 15, transmission device comprises an air compressor that the compression rotor that cooperates with engine rotor is arranged, this compressor has a compressed air outlet, is used to provide Driving force.

16, a kind of rotating machinery of fluid control, it includes

The rotor that power transmission is housed,

One with the close-fitting fixed cylinder of described rotor, be used to make described cylinder to be installed in device on the described post with respect to the hard-wired device of described rotor with described rotor,

At least one pair of in rotor position relatively, be carved with screw thread and on the rotor barrel surface to the cavity of described fixed cylinder surface opening,

At least one pair of is contained in diametical side of direction and independently rotary blade on the described cylinder separately, and this vanes fixed makes described blade and the described rotor device of rotation synchronously on the rectangular axle of the spin axis of described cylinder and described rotor,

Make the fluid in the described machinery flow into the device in the proal approach of described blade in the described cavity,

The device that fluid is discharged from this machinery under described blade effect,

The invention is characterized in,

Described rotor is general spherical, and described rotor one end has the cylindrical hole of indent;

Be contained in the indent cylindrical hole of described rotor described fixed cylinder coaxial line,

Described blade is slim-lined construction and is one and disposes on another, is rotatably installed in the corresponding chambers in the face of the fixed cylinder surface opening,

Synchronizer comprises and axially being installed on the rotor and the axially extended axle of fixed cylinder, in described fixed cylinder, be contained in described axle the neck place thrust device and be connected described gear drive with rotatable blade,

The inner device that flows into for fluid of machinery comprises the antipodal passage that is positioned at described axle and described synchronizer both sides and almost extends to this cylinder opposite one end from the inlet that is positioned at fixed cylinder one end.

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