CN1070993C

CN1070993C - Rotary jet engine

Info

Publication number: CN1070993C
Application number: CN93109859A
Authority: CN
Inventors: 约瑟夫·沃尔特·施通
Original assignee: Individual
Current assignee: Individual
Priority date: 1993-07-12
Filing date: 1993-07-12
Publication date: 2001-09-12
Anticipated expiration: 2013-07-12
Also published as: CN1097485A

Abstract

A rotary jet engine comprises a casing having an intake zone and an exhaust zone separated from each other, a rotor installed to rotate in the casing, and at least one injection device, wherein the injection device has an intake port and an exhaust port, and the injection device is installed on the rotor, wherein the intake port separates the rotation axis of the rotor and faces the intake zone so that air from the intake zone impacts into the injection device for combustion, thereby causing the thrust to rotate the rotor, and the jet engine also has a device to prevent fluid from flowing from the intake zone into the exhaust zone.

Description

Rotary jet engine

The present invention relates to a kind of rotary engine that utilizes fluid jet to produce power (below be called " rotary jet engine ").

Utilize the motor of expansion fluid driving output shaft, the working room that has a volume to change usually along with the expansion of fluid.Usually, the working room is limited between the surface of two walls, and at least one wall surface can move relative to another wall surface, so that the power that expansion fluid produces is sent on the output shaft.But the structure that two wall surfaces of this needs move is mutually brought two problems: one is two sealing problems between the surface, and another then is the frictional loss problem.

CN-1037192 discloses a kind of rotary jet engine, but it fails to address the above problem well.

The purpose of this invention is to provide a kind of rotary engine, this motor does not use the working room of variable volume.Thus, the present invention tries hard to solve traditional rotary engine and common sealing problem and the frictional loss problem that exists of internal-combustion engine.

According to a kind of rotary jet engine of the present invention, it comprises a housing with air-breathing district spaced apart from each other and exhaust area, one be mounted to can be in housing rotor rotated, at least one produces the injection apparatus of propulsive fluid from the burning of fuel and air, described injection apparatus has an intakeport, be used to suck from the air in described air-breathing district with described air and deliver to a firing chamber, be admitted to air mixing and by ignition at this place's fuel, described injection apparatus also has a relief opening and is used for propulsive fluid is sprayed into described exhaust area, described injection apparatus is installed on the described rotor, its intakeport separates the running shaft of described rotor and enters described injection apparatus and burn to realize that air impacts from described air-breathing district towards described air-breathing district, thereby its thrust makes described rotor rotation, described air breathing engine also has the prevention fluid flows into described exhaust area from described air-breathing district device, it is characterized in that, at least another injection apparatus also is installed on the static part of motor, it is positioned to from the propulsive fluid of its ejection is impacting rotor, thereby makes the rotor rotation.

Described air-breathing and exhaust area to small part in the best described housing is separated by described rotor.

The device that described prevention fluid flows can comprise a seal arrangement that is located between described housing and the described rotor.As an alternative or the device that flows of additional described prevention fluid can comprise that one produces the device than the high pressure of the pressure of exhaust area in air-breathing district.The device that should produce malleation in air-breathing district can comprise an air feeder that air is infeeded air-breathing district.

In a kind of structure, be provided with the rotor of two counterrotatings, has an injection apparatus on one of them rotor at least, this injection apparatus is arranged to, the thrust that it is produced can drive the rotor at this injection apparatus place, and makes the impact force of the propulsive fluid that this injection apparatus produces can drive the rotor of counterrotating.In another structure, the rotor of two counterrotatings is arranged, an injection apparatus is installed on each rotor at least.The thrust that each injection apparatus is arranged to dependence itself drives the rotor at this injection apparatus place, and the impact force of the propulsive fluid that dependence itself is produced drives the rotor of counterrotating.

Be that propulsive fluid is the atmosphere through heating, and can adopt any proper device to heat especially easily.

In this structure, injection apparatus preferably includes a burner, and burner can adopt traditional form.In this case, in burner, utilize the aerial burning of fuel to come heated air.Fuel can be liquid hydrocarbon fuel, for example, and power kerosene.

Yet, be appreciated that any other suitable device all can be used to heated air, for example, can adopt the nuclear heating process of some form.

Preferably rotor is installed on the output shaft.

Rotor can comprise a rotor disk, and the intakeport of injection apparatus can be opened in a side of rotor disk, and its relief opening then is opened in the opposite side of rotor disk.

Also one or more rotors can be arranged.Having under the situation with upper rotor part, these rotors can rotate in the same way, also can counterrotating.Under latter event, be connected with driving between the output shaft along output shaft opposite direction rotor rotated and can adopt any suitable Placement, for example gear Placement.

This rotary jet engine preferably comprises a reaction device again, and the propulsive fluid of discharging from injection apparatus is towards this reaction device, to strengthen the thrust of injection apparatus.Reaction device can comprise the reaction surface that many circle spacings are provided with, for example blade.

Housing preferably has the basic columniform sidewall that is, cylindrical side wall is coaxial with the spin axis of rotor basically.This housing can comprise air-breathing district and exhaust area, and the intakeport of injection apparatus communicates with air-breathing district, and its relief opening then communicates with exhaust area.

Also many burners can be set.These burners can be installed in couples, and each is installed in the radially relative both sides of rotor spin axis to burner.

The present invention will be by obtaining clearer understanding below in conjunction with accompanying drawing to the description of several specific embodiments.Wherein:

Fig. 1 is the schematic end view of first embodiment's rotary jet engine;

Fig. 2 is the diagrammatic side view of motor shown in Figure 1;

Fig. 3 is the burner schematic representation that is used for first embodiment's rotary jet engine;

Fig. 4 is the schematic representation of second embodiment's rotary jet engine;

Fig. 5 is the diagrammatic side view of the 3rd embodiment's rotary jet engine;

Fig. 6 is the schematic end view of the 4th embodiment's rotary jet engine;

Fig. 7 is the schematic end view of the 5th embodiment's rotary jet engine;

Fig. 8 is the schematic representation of engine rotor shown in Figure 7 from unilateral observation;

Fig. 9 is the schematic representation that engine rotor shown in Figure 8 is observed from opposite side;

Figure 10 is a kind of supporting way schematic representation of rotary jet engine output shaft.In order to hold fuel delivery system.

Shown in Fig. 1,2 and 3, the rotary jet engine of first embodiment of the invention comprises rotor 11, and rotor 11 is fixedly mounted on the output shaft 13 by bearing 14 swivel bearings.Rotor 11 is installed within the housing 15, and housing 15 has a cylindrical side wall 17, and sidewall 17 is coaxial with the spin axis of output shaft 13, and forms an inner region 19.Cylindrical side wall 17 combines with header pipe 21, and header pipe 21 forms annular outer region 23, annular outer region 23 and rotating shaft coaxle, and communicate with inner region 19 by annular space 25.Tangential outlet pipe 27 communicates with header pipe 21.

Can clearly be seen that from Fig. 2 output shaft 13 stretches out from the two ends of housing 15.

Rotor 11 comprises a dish 31, and the radial inner end of dish 31 is fixedly mounted on the output shaft 13, and has a pair of burner 33.Two burners 33 are arranged on the radially relative both sides of output shaft, and this can be clear that from Fig. 1.Dish 31 extends the annular space 25 on the sidewall 17 of housing 15 and has rigid seal 32 in its outer end.Rigid seal is arranged on very and is spaced from each other near sidewall 17 parts that form gap 25 and with this part, flows through the gap to stop fluid.

Rotor 11 also comprises a cylindrical rotor wall 34, and cylindrical rotor wall 34 is fixedly mounted on coaxially have been failed on the axle 13, with rotation together thereupon.More particularly, cylindrical rotor wall 34 is installed in rotor disk 31 and is installed on two supporting elements 36 on the output shaft 13, and each supporting element 36 is positioned at a side of rotor disk 31.

Cylindrical rotor wall 34 inwardly separates with the cylindrical side wall 17 of housing 15.Two walls 17,34 are worked in coordination and are formed the air chamber 38 that is positioned between the two, and air chamber 38 receives atmosphere, and this will narrate hereinafter.

Can clearly be seen that from Fig. 3 each burner 33 all has structural type commonly used, comprise an intakeport 35, a firing chamber 37 and an exhaust nozzle 39.Intakeport 35 is connected with air-breathing loudspeaker 40, and exhaust nozzle 39 is furnished with elongated catheter 42.Each burner is arranged on the dish 31 like this, and intakeport 35 is communicated with the air chamber 38 that forms air-breathing district, and like this, elongated catheter 42 stretches out annular space 25, and its exhaust port side is communicated with the perimeter 32 in the header pipe 21 interior exhaust territories that form.

Burner sucks atmosphere in the air chambers 38 through intakeport 35, and by the burning heated air of hydrocarbon fuels.To produce propulsive fluid.Fuel is by in the fuel injector 43 spirt burners, and ignited by ignition mechanism 45.Along with the carrying out of combustion process, the air expanded by heating, air is with the zone in the spray pattern process exhaust nozzle 39 spirt header pipes 21 as a result.From the air of burner ejection, produce thrust and make the rotor rotation, moment of torsion is passed to output shaft 13.

Reaction device 50 comprises with a plurality of reaction surface of the blade 51 forms formation of circle spacing, is arranged in the header pipe 21.Impact on blade 51 from the propulsive fluid of each nozzle 39 ejection, strengthened the propelling force that propulsive fluid produces.Blade 51 also plays even guiding propulsive fluid, along the effect of flowing away from the direction of rotor, thereby produces the mobile graphic that leads to tangential outlet pipe.

As mentioned above, each burner 33 connects the suction air from the air chamber 38 in the housing 15.Propulsive efficiency that each burner produces and/or thrust can improve by increasing the mass flow rate that enters the air of burner by its intakeport 35.And the MAF that enters burner can increase by the air pressure in the rising air chamber 38.In this embodiment, this can be by being provided with two impeller assemblys 52 on rotor 11, and the side that each impeller assembly 52 is located at rotor disk 31 realizes.Impeller assembly 52 rotates in company with the rotation of output shaft, and air is blasted air chamber 38, thereby improves the air pressure in the air chamber 38.A series of fixed guide vanes 53 are arranged between each impeller assembly 52 and the burner, with the axial centre zone of rotor that even air is led, and enter in the air-breathing loudspeaker door of intakeport 35 of burner.

Be transported in the air chamber 38 and the air that arrives the rotor axial center region can be directed to atmosphere by two impeller assemblys 52, perhaps supply with by an air conveying system that combines with filtrating equipment.

Separation within air chamber 38 and the header pipe 21 between the formed zone helps avoid or limits at least the propulsive fluid of burner discharge to sucking the pollution of air.Like this, also help in the engine operation process in the raising of the positive air pressure of generation in air chamber 38 under the effect of impeller assembly 52.

Second embodiment as shown in Figure 4, it and first embodiment are similar in many aspects, but each burner 33 is installed on the independent rotor disk 31.In addition, burner is to be orientated like this, makes its intakeport 35 be arranged on a side of dish separately, and its exhaust nozzle 39 is arranged on the opposite side of dish separately.This structure arrangement is particularly useful for keeping the separation between air-breathing and the propulsive fluid, thereby, avoid or reduced propulsive fluid at least air-breathing pollution.Two rotor disks 31 are divided into core 61 and pair of end portions 63 3 parts with inner region 19.The exhaust nozzle 39 of burner communicates with core 61, and the intakeport 35 of each nozzle communicates with an end 63 respectively.Rotor disk 31 complements each other to form sealing with housing, or the fluid that limits at least between adjacent portion 62 and 63 flows.

In this embodiment, each impeller assembly 52 is transported to air respectively a respective end portions 63 of housing under pressure.Although only provide an a kind of side structure of motor shown in Figure 4, each impeller assembly also can be accepted air from air conveying system 65.

Embodiment shown in Figure 5, the structural type of motor is compared with above-mentioned several embodiments, and is fairly simple.Burner 33 is installed on the spider 31, and the direct admission of air from atmosphere of each burner.There are not impeller assembly or other to deliver air to air transport device in the zone that holds rotor under pressure.Embodiment as shown in Figure 4 is such, and its burner tilts to install, and makes intakeport 35 and exhaust nozzle 39 be arranged on the relative both sides of dish.

Example structure shown in Figure 6 and aforementioned several embodiment are similar a bit, and difference is that burner 33 is arranged on the position of close relatively output shaft 13.This helps reducing the rotary inertia of rotor, and is easy to the balance of rotor.Each intakeport 35 has the air-breathing loudspeaker 40 of a prolongation, and air-breathing loudspeaker 40 extend on the circumference of rotor, and each exhaust nozzle also has an extension conduit 42, and this conduit 42 extends to the outside of dish, with reactance blade 51 that propulsive fluid is led.

Another embodiment of rotary jet engine is shown in Fig. 7,8 and 9, and the radial dimension of motor severally has the embodiment of annular row slip ring to compare with aforementioned, and is compact.Because its compactedness, this motor is suitable for being used in automotive field.This motor comprises rotor 111, and rotor 111 is fixedly mounted on the output shaft 113 by bearing 114 swivel bearings.Rotor 111 is installed in the housing 115, and housing 115 has a cylindrical side wall 117, and cylindrical side wall 117 is coaxial with the spin axis of output shaft 113, and forms inner region 119.Housing 115 has first end wall 120 and second end wall 122 that is positioned at inner area 119 two ends.First end wall 120 is provided with the suction port (not shown), second end wall 122 and the cylindrical side wall 117 common vent port conduit 124 that form, and vent port conduit 124 stops at annular exit 126 places.

Output shaft 113 stretches out the two ends of housing 115, can clearly be seen that this structure from Fig. 7.

Rotor 111 comprises a dish 131, coils 131 radial inner end and is fixedly mounted on the output shaft 113, and have a pair of burner 133.Two burners 113 are arranged on the radially relative both sides of output shaft.

Rotor disk is divided into two districts with inner region 119, i.e. air-breathing district 119a who communicates with intakeport on the end wall 120, an exhaust area 119b who communicates with vent port conduit 124.

Lip ring 130 is housed on the cylindrical side wall 117, and it is very near the radially outer of rotor disk 131, but separates with it.Rotor 131 and Sealing 130 are worked in coordination, and make mobile being restricted of fluid between two zones of 119a and 119b.

Rotor 111 also comprises cylindrical rotor wall 134, and cylindrical rotor wall 134 is positioned at air-breathing district 119a, and coaxial and be fixedly mounted on the output shaft 113, rotates therewith.More particularly, cylindrical rotor wall 134 is installed on rotor disk 131 and the supporting element 136, and supporting element 136 is arranged on the output shaft 113, and is positioned at the side of rotor disk 131, and rotor disk 131 is facing to end wall 120.

Cylindrical rotor wall 134 inwardly separates with the cylindrical side wall 117 of housing 115.Two walls 117,134 are worked in coordination and are formed the air chamber 138 that is positioned between the two, the atmosphere that air chamber 138 receives by the intakeport (not shown) on the end wall 120.

Each burner 133 adopts traditional form, comprises an intakeport 135, a firing chamber 137 and an exhaust nozzle 139.Intakeport 135 comprises air-breathing oviduct 140, and exhaust nozzle 139 is furnished with the conduit 142 of extension.Each burner is installed on the dish 131, intakeport 135 is communicated with air chamber 138 among the air-breathing district 119a, and extension conduit 142 communicates with exhaust area 119b.

Reaction device 150 comprises a plurality of reaction surface that constitute with the form of isolated blade on the circumference, is arranged among the exhaust area 119b.The propulsive fluid that ejects from each nozzle 139 impacts on blade 151, thereby has strengthened the propelling force that propulsive fluid produces.Blade 151 also plays even guiding propulsive fluid and flows along the direction away from rotor, thereby forms the mobile graphic that leads to vent port conduit 124.

Blade 151 is installed on the cylindrical side wall 117, and the footpath extends towards cylindrical baffle 154 in backward, and cylindrical baffle 154 helps to hold propulsive fluid and with its guiding vent port conduit 124.Baffle plate 154 is fixedly mounted on second end wall 122 of housing 115, and crosses exhaust area 119b to rotor disk 131 extensions.Another Sealing 155 that is installed on the rotor disk 131 is worked in coordination with baffle plate 154, and the fluid between restrict rotor dish and baffle plate flows.

Each burner 133 sucks air from the air chamber 138 in the housing 115.Enter the air of air chamber through the intakeport on the end wall 120, by impeller assembly 152 and with it the stator 153 of cooperating send burner to.Impeller assembly 152 comprises two-stage, i.e. first group 156 and the second level 158.Air is sent in the process of gas burner through air chamber 138, and the two-stage impeller assembly increases air pressure step by step.Stator 153 is installed on the housing 115, and two-stage is also arranged, and comprises the first order 160 between the two-stage impeller assembly, and the second level 162 between second level impeller assembly and rotor disk 131.

(not shown) in another embodiment, rotary jet engine has the rotor of counterrotating, and each rotor driven is connected on the public output shaft.The benefit of this structure is: counterrotating is eliminated or is reduced 3 gyroscopic effects at least.Each rotor has a burner and an auxiliary reaction device at least, as blade.Adopt this structure, each epitrochanterian burner can promote two rotors.Carry the rotor of each burner, the thrust that is produced by burner promotes.Burner is also arranged to such an extent that the propulsive fluid of therefrom ejection directly is sprayed onto on the reaction device of another rotor.Propulsive fluid is flushed to another epitrochanterian this effect and makes this rotor rotation.

In another embodiment, (do not show among the figure) yet, burner is installed on the static part of motor, and arrange to such an extent that the propulsive fluid that sprays from burner is impacted on rotor, thereby make the rotor rotation.Rotor is equipped with reaction surface, and as blade, propulsive fluid directly impacts facing to blade, rotatablely moves thereby produce.

Although among the aforementioned various embodiment, what utilize during rotary jet engine work is liquid hydrocarbon fuel, is appreciated that any suitable fuel all can be used to heated air, to produce propulsive fluid.

Yet liquid carbon hydrogen fuel is a kind of form of fuel easily, and this fuel can be delivered to burner by transfer line 70 (see figure 10)s, and transfer line 70 extends along the output shaft 13 of motor.Be bearing in the position of bearing 14 rotatably at output shaft, be provided with passage sleeve 71, transfer line 70 can pass through from passage sleeve 71.Each passage sleeve 71 comprises a ferrule element 73, and ferrule element 73 has one or more axial bores 75, and transfer line can extend by these axial bores 75.

Can find out obviously that from above-mentioned the rotary jet engine that various embodiment provided is compared with many traditional engine structures, its structure is simpler.

Though, several specific embodiments of the present invention are described in detail,, clearly, the present invention is not limited to this, can make various replacements and modification, but can not exceed scope of the present invention.

Claims

1. A rotary jet engine comprising a casing having spaced-apart intake and exhaust regions, a rotor mounted for rotation within the casing, at least one propellant fluid produced from the combustion of fuel and air injection means having a suction port for taking in air from said suction zone and sending said air to a combustion chamber where fuel is fed to mix with air and ignited for combustion, The injection device also has an exhaust port for injecting propellant fluid into the exhaust area, the injection device is installed on the rotor, and its suction port is separated from the rotation axis of the rotor and faces the suction zone to realize air impingement from the suction zone into the injection device for combustion, so that its thrust rotates the rotor, and the jet engine also has the function of preventing fluid from flowing from the suction zone into the exhaust zone installation,

It is characterized in that at least one further injection device is mounted on the stationary part of the engine, arranged so that the propelling fluid injected therefrom impinges on the rotor, thereby causing the rotor to rotate.

2. The rotary jet engine of claim 1 wherein said intake and exhaust regions within said housing are at least partially separated by said rotor.

3. 2. The rotary jet engine of claim 1 wherein said means for preventing fluid flow includes a seal disposed between said casing and said rotor.

4. 2. The rotary jet engine of claim 1 wherein said means for preventing fluid flow includes a means for creating a pressure in the suction region that is higher than the pressure in the discharge region.

5. 2. The rotary jet engine of claim 1, further comprising means for generating a positive pressure in the suction region, the means including an air supply means for supplying air into the suction region.

6. 5. The rotary jet engine of claim 5 wherein said air supply means includes a vane assembly operatively connected to said rotor.

7. 2. The rotary jet engine of claim 1 wherein said rotor comprises a rotor disc on which at least one injection device is mounted.

8. The rotary jet engine according to claim 7, wherein the air intake region and the exhaust region are located on axially opposite sides of the rotor disk.

9. 2. The rotary jet engine of claim 1, wherein the exhaust region is located radially outward of the suction region relative to the rotor.

10. 2. The rotary jet engine of claim 1, further comprising a reaction means, the propelling fluid discharged from the injection means being directed to said reaction means.

11. 2. The rotary jet engine of claim 1 wherein said reaction means includes a plurality of circumferentially spaced reaction surfaces.

12. The rotary jet engine of claim 11 wherein said casing has an exhaust port in communication with the exhaust region, said reaction means being positioned to direct propelling fluid in the exhaust region to the exhaust port .

13. 2. The rotary jet engine of claim 1 wherein said injection means comprises an injection burner.