CA1214109A - Fluid flow augmentor - Google Patents
Fluid flow augmentorInfo
- Publication number
- CA1214109A CA1214109A CA000435965A CA435965A CA1214109A CA 1214109 A CA1214109 A CA 1214109A CA 000435965 A CA000435965 A CA 000435965A CA 435965 A CA435965 A CA 435965A CA 1214109 A CA1214109 A CA 1214109A
- Authority
- CA
- Canada
- Prior art keywords
- vanes
- hollow body
- diffuser
- fluid flow
- vortex
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
ABSTRACT
There is described a fluid flow concentrating device suitable, for example, for concentrating the flow of tidal waters or of wind, which comprises a hollow body closed at one end and open at the other. The body has a fixed circumferential wall composed of a plurality of fixed spaced vanes and a diffuser channel located at the open end of the wall. Fluid moving from outside the device through the vanes to the inside of the body creates a vortex within the body and a fluid flow axially of the body through the diffuser channel. In certain preferred embodi-ments a turbine is located for rotation in a direction opposite to the direction of rotation of the vortex about a vertical axis, centrally within the diffuser downstream of the fluid flow. The turbine can be used to drive a generator or a motor to, for example, propel a marine craft, or, the augmentor can be used on a aircraft to assist the lift of a wing, or, in another application, can be used with a jet turbine engine to improve both the intake to and the thrust from the engine.
There is described a fluid flow concentrating device suitable, for example, for concentrating the flow of tidal waters or of wind, which comprises a hollow body closed at one end and open at the other. The body has a fixed circumferential wall composed of a plurality of fixed spaced vanes and a diffuser channel located at the open end of the wall. Fluid moving from outside the device through the vanes to the inside of the body creates a vortex within the body and a fluid flow axially of the body through the diffuser channel. In certain preferred embodi-ments a turbine is located for rotation in a direction opposite to the direction of rotation of the vortex about a vertical axis, centrally within the diffuser downstream of the fluid flow. The turbine can be used to drive a generator or a motor to, for example, propel a marine craft, or, the augmentor can be used on a aircraft to assist the lift of a wing, or, in another application, can be used with a jet turbine engine to improve both the intake to and the thrust from the engine.
Description
The presen-t invention is concerned with fluid flow concentrating devices and in one of its aspects with a ~1ind corlcen-trating device in the form of a vortex generator of the -tornado-type.
It is knownfrom United States patent No. ~,070,131 -to provide a device in which atmospheric wind is admitted into a vertically extending open ended structure which is spaced lrom the ground or connected to a subterranean ram-air tunnel. The admitted wind is directed against the interior curved surface of the s-truc-ture and provides a vortex flow and khis flow provides a corres-ponding low pressure core which draws the air into the bottom of the structure to drive a horizontal turbine. Other fluid flow devices of the prior art are to be seen in United States pa-tents Nos. 4,236,866; 4,142,822; 4,269,563; 4,~60,325 and 1,519,447.
Other wind augmentation types of devices are also in experimental use, these fall broadly into the categories of "duct augmentor tubines" and "tip vane turbines". The devices of the prior art have been useful for particular applications but are limited in their scope of application.
The present invention seeks to provide a fluid flow concentrator which will have a wide versatility of application.
According to the present invention there is provided a ~luid ~low concentrating device comprising a substantially hollow body substantially closed at one end and open a~ the other, an axially ex-tending vortex stabilizing column arranged substantially centrally of the hollow body, the body having a fixed circumferen-tial wall means co~lposed of a plurality of fixed spaced vanes and a di~fuser channel located at the open end oE the wall means, whereby fluid moving from the outside -the device subs-tantially radially through the vanes -to the inslde of the body, creates a vortex within the hollow body and a fluid 10w axially of -the body throuyh the diffuser channel.
In a preferred form of the device the vanes are substan-tially equally spaced circumferentially and maybe of aerofoil cross-section.
In one preferred embodiment of the invention the vor-te~
stabili2ing column may extend -through -the diffuser channel. If desired, the column may be provided with a plurality of brace members extending radially outwardly of the column within the substantially hollow body.
The vanes may conveniently be provided with trailing edge fluid flow modifiers which may be flap-like elements.
In a preferred construction a turbine is mounted for rotation, ln the direction opposite to the direction of rotation of the vortex, centrally within the diffuser, about a vertical axis. The blades of the turbine may conveniently b~ located within the diffuser~
In one application of the device according to the present invention the hollow body may be located on an airborne craft with the open end of the body being normally directed in the direction of the ground, in this application the fluid may be, at least in part, a hot gas, a toroidal duct conveniently maybe arranged in the craft adjacent to the diffuser channe~ so as to blow the hot gas into the hollow body through the vanes which in this instance would be hollow.
In another application of -the device, the hollow body may be mounte~ externally a-t -the in-take of a je-t engine, the circum-feren-tial wall means providing a pointed cone shape struc-ture extending forwardly of -the engine in-take, point forward. In this construction the vanes, may be -twis-ted and/or -tapered.
According to another application of the present inven-tion the hollow body may be moun-ted on a marine vessel wi-th the open end of the body being normally directed upwardly; convenien-tly a turbine shaft may be provided within the body centrally and axially thereof and may carry radially extending turbine blades within the diffuser for rotation in a direction opposite to -the direc-tion of rotation of the generated vortex, the end of the -turbine shaft remote from the blades may be connected for, say, propulsion of the vessel, for example by mechanical or electrical means.
The following is a description by way of example of certain embodiments of the present invention reference being had to the accompanying drawings in which:
Figure 1 is a schematic representation partly in section of a fluid flow concentrating device;
Figure 2 is a plan view of the device of Figure l;
Figure 2a, i5 a detail of various vane cross-section configurations;
Figure 2b is a schematic representation similar to Figure 1 but including a ~urbine.
Figure 3 is a schematic representation, partially in section of an application to augment the lift of an aircraft wing;
Figure 4 is a plan view in part sec-tion of -the device of Figure 3;
Figure 5 i.s a schematic representation of a marine application, Figure 6 is a schematic representation of an ~ppli-cation as an intake augmentor and a -thrust augmentor for a je-t engine; and Figure 7 is a schematic representation of the application of the device in accordance with Figures 3 and 6 to an aircraft.
Referring now to drawings in which like parts have been given like numbers. A fluid flow concentrating device 10 comprises a substantially hollow body 11 closed at one end 12 and open a-t the other 13. The body has a fixed circumferential wall 14 com-posed of a plurality of fixed substantially equally spaced vanes 1~ and a diffuser channel 18 located at the open end 13 of the wall 14. As shown the vertical axis is normal to the direction of fluid flow F and wherever practical, the portion of the device 10 will be selected so that its axis is normal to the fluid flow.
Fluid moving from outside the wall 14 through -the vanes 16 to the inside of the body creates a vortex V within the hollow body 11 and a fluid flow axially of the body 11, outwardly through the diffuser channel 180 A vortex stabili2ing column 20 may be provided axially of the hollow body and centrally thereofO In order to get highly efficient use of the vortex~ the vane angle should preferably be about ~5 with the radius, further the ratio of the overall height of the device to the minimum diame-ter of -the diffuser should preferably be near uni-ty, as can be seen in Figure 1.
. O
The vanes 16 may be of aerofoil cross-section as in E~igure 2a or may be of other suitable shapes for example, as al 50 shown in Figure 2a. The vanes 16 may be provided with fluid flow modifiers, as seen in Figure 2 as Elaps 22 hinged -to -the trailiny edge of the vanes 16.
As seen in Figure 2 -the stabilizing column 20 may be pro~ided wi-th a plurality of brace members 24 extending radially outwardly from the column 20 within the hollow body and connected at -the outer edges to -the diffuser 18.
In one preferred application, see Figure 2b, the augmen-tor of Figure 1 is modified to incorporate a turbine 29 mounted on a centrally located, axially extending, turbine shaft 30. Turbine blades 31 are housed within the diffuser 18 and provide a particu-larly safe and compact configuration. By placing the tubine 29 downstream of the vor-tex V the advantage is achieved that the energy in the axial exhaust flow, ra-ther than in the vortex itself, is used. The design of the turbine blades is selected in accor-dance with accep~ed engineering proceedures, such that the turbine blades 31 are driven in a direction opposite -to the direction of rotation of the vortex V and thus the turbine does not diminish the vortex V. The turbine shaft 30~ is supported inside the diffuser 18 by bearing in hub 25 with brace members 24. The opposite end of the shaft, is connected to a device for power utilization say an electric generator located outside the closed end 12.
The fluid flow concen-trating device 10 as described with respect to Figures 1, 2, 2a, and 2b is suitable for use in a wide variety of applications. It can be used as a device to augment wind veloci-tes, which may in turn be used to drive an air turbine or it may be used hydraulically, say, in a tidal si-tua-tion, or low-head hydro power generation. In a tidal si-tua-tion -the incominy tide F would act to enter the vanes 16 in the same fashion as a wind and create a whirlpool which could be used in an~ sui-table fashion, for example to drive a hydraulic turbine in opposi-te direc-tion to the whirlpool.
Turning now to Figure 3 which shows, together wi-th Figure 4, the arrangement of the device in an airborne craft as a lift augmentor for the wing of an aircraft. Here the concentrating device 10 is mounted on top o~ the aircraft wing 35 with the closed end 12 o~ the body spaced from the upper sur~ace 36 of the wing by the vanes 16. In this preferred configuration, the vanes 16 form a substantially frusto-concical structure, narrower at the top then at the base. The vanes may be twisted and/or tapered.
The diffuser channel ]8 is arranged within the wing itself and communicates with the underside 37 o~ the wing.
As the aircraft moves through the air, a wind ~ is created and this passes through the vanes 16 and produces a vortex V2 which provides a downwardly directed airflow to augment the lift of the wing: The air entering the device 10 can be controlled by means o~ trailing edge flaps in the vanes 16 as in Figure 2 0 If required, for say, a VTOL application, a toroidal shaped duct 38 is located around the diffuser channel 18 and is provided with hot gases from the aircraft propulsion engines through a duct 39.
The hot gases entering the duct 38 from the duct 39, pass around the duct 38 into the vanes 16, which in this configuratiOn are hollow, and are blown through nozzles at the tralling edge of -the vanes 16 (see arrows 40 in Figure 4) to produce the vortex in the device 10. The resultant thrust from the hollo~ bod~ 11 through the diffuser 18 may be controlled by a but-terfly va:lve 42, suitably mounted in the difEuser 18 on the stabilizer column 20.
Figure 7 shows the arrangement of the lift augmentor as seen in Figures 3 and 4, in an aircraft at 45, that is to say, near the wing tips and generating trailing vortices which rotate in the same sense as the wing tip trailing vortices.
Figure 5 shows the application of the device 10 as a wind augmentor to drive a turbine 31, the shaft 30 of which is connected to some suitable power takeoff, for example, an elec-trical generator, which in turn can drive an electric motor to propel the watercraftO
Figure 6 shows the application of the device 10 in two fashions to a jet engine. The intake augmentor 50 is mounted externally at the intake 51 of a jet engine and the circumferen-tial wall 14 extends forwardly of the engine intake, the vanes 16 providing a conical configuration, closed at one end by the point 54. In this instance, since the wall 14 is not cylindrical, the vanes 16 advantageously may be twisted and/or tapered. The air taken in through the vanes 16 creates a vortex V3 and improves the efficiency of the engine intake, by increasing the velocity of the intake air. The diffuser 1~ is shaped so as to provide a smooth flow into the intake of the engine. The cone shape of the augmentor 50 additionally ~, .
Sr~
inhibits bird ingestion.
At the exhaust end o the jet engine the engine bod~
itself provides the closed end 12 -to the device 10 arranged as a thrust augmentor 60, vanes 16 conveniently being, as in the case of the intake augmentor, twisted and/or tapered and once again the diffuser 18 at the open end o~ the concentrator lO
provides Eor the escape of exhaust gases from the jet engine.
External air passing through the vanes 16 crea-tes a vortex V4 which improves the performance of the engine and this vortex is stabili~ed by the jet flow itself. That is to say the convergent mixing flow induced by the free jet on passing through the augmentor 60 causes a reduction in pressure around the jet thereby increasing the jet velocit~ and the jet thrust~
The subsequent increase of the mixing flow, strengthens the axial vortex and produces a ring vortex 61 which further augments the thrust. Yet a urther augmentation of the thrust results from ~he increased entropy of the mixing flow by the hot jet gases through convection and radiation.
In Figure 7 the fashion of mounting the devices of Figure 6 on an aircraft is illustrated.
It will be understood that the thrust augmentor 60 could also be used to augment the thrust from a rocket engine when operatin~ in the atmosphere in a manner similar to its use with a jet engine.
It is knownfrom United States patent No. ~,070,131 -to provide a device in which atmospheric wind is admitted into a vertically extending open ended structure which is spaced lrom the ground or connected to a subterranean ram-air tunnel. The admitted wind is directed against the interior curved surface of the s-truc-ture and provides a vortex flow and khis flow provides a corres-ponding low pressure core which draws the air into the bottom of the structure to drive a horizontal turbine. Other fluid flow devices of the prior art are to be seen in United States pa-tents Nos. 4,236,866; 4,142,822; 4,269,563; 4,~60,325 and 1,519,447.
Other wind augmentation types of devices are also in experimental use, these fall broadly into the categories of "duct augmentor tubines" and "tip vane turbines". The devices of the prior art have been useful for particular applications but are limited in their scope of application.
The present invention seeks to provide a fluid flow concentrator which will have a wide versatility of application.
According to the present invention there is provided a ~luid ~low concentrating device comprising a substantially hollow body substantially closed at one end and open a~ the other, an axially ex-tending vortex stabilizing column arranged substantially centrally of the hollow body, the body having a fixed circumferen-tial wall means co~lposed of a plurality of fixed spaced vanes and a di~fuser channel located at the open end oE the wall means, whereby fluid moving from the outside -the device subs-tantially radially through the vanes -to the inslde of the body, creates a vortex within the hollow body and a fluid 10w axially of -the body throuyh the diffuser channel.
In a preferred form of the device the vanes are substan-tially equally spaced circumferentially and maybe of aerofoil cross-section.
In one preferred embodiment of the invention the vor-te~
stabili2ing column may extend -through -the diffuser channel. If desired, the column may be provided with a plurality of brace members extending radially outwardly of the column within the substantially hollow body.
The vanes may conveniently be provided with trailing edge fluid flow modifiers which may be flap-like elements.
In a preferred construction a turbine is mounted for rotation, ln the direction opposite to the direction of rotation of the vortex, centrally within the diffuser, about a vertical axis. The blades of the turbine may conveniently b~ located within the diffuser~
In one application of the device according to the present invention the hollow body may be located on an airborne craft with the open end of the body being normally directed in the direction of the ground, in this application the fluid may be, at least in part, a hot gas, a toroidal duct conveniently maybe arranged in the craft adjacent to the diffuser channe~ so as to blow the hot gas into the hollow body through the vanes which in this instance would be hollow.
In another application of -the device, the hollow body may be mounte~ externally a-t -the in-take of a je-t engine, the circum-feren-tial wall means providing a pointed cone shape struc-ture extending forwardly of -the engine in-take, point forward. In this construction the vanes, may be -twis-ted and/or -tapered.
According to another application of the present inven-tion the hollow body may be moun-ted on a marine vessel wi-th the open end of the body being normally directed upwardly; convenien-tly a turbine shaft may be provided within the body centrally and axially thereof and may carry radially extending turbine blades within the diffuser for rotation in a direction opposite to -the direc-tion of rotation of the generated vortex, the end of the -turbine shaft remote from the blades may be connected for, say, propulsion of the vessel, for example by mechanical or electrical means.
The following is a description by way of example of certain embodiments of the present invention reference being had to the accompanying drawings in which:
Figure 1 is a schematic representation partly in section of a fluid flow concentrating device;
Figure 2 is a plan view of the device of Figure l;
Figure 2a, i5 a detail of various vane cross-section configurations;
Figure 2b is a schematic representation similar to Figure 1 but including a ~urbine.
Figure 3 is a schematic representation, partially in section of an application to augment the lift of an aircraft wing;
Figure 4 is a plan view in part sec-tion of -the device of Figure 3;
Figure 5 i.s a schematic representation of a marine application, Figure 6 is a schematic representation of an ~ppli-cation as an intake augmentor and a -thrust augmentor for a je-t engine; and Figure 7 is a schematic representation of the application of the device in accordance with Figures 3 and 6 to an aircraft.
Referring now to drawings in which like parts have been given like numbers. A fluid flow concentrating device 10 comprises a substantially hollow body 11 closed at one end 12 and open a-t the other 13. The body has a fixed circumferential wall 14 com-posed of a plurality of fixed substantially equally spaced vanes 1~ and a diffuser channel 18 located at the open end 13 of the wall 14. As shown the vertical axis is normal to the direction of fluid flow F and wherever practical, the portion of the device 10 will be selected so that its axis is normal to the fluid flow.
Fluid moving from outside the wall 14 through -the vanes 16 to the inside of the body creates a vortex V within the hollow body 11 and a fluid flow axially of the body 11, outwardly through the diffuser channel 180 A vortex stabili2ing column 20 may be provided axially of the hollow body and centrally thereofO In order to get highly efficient use of the vortex~ the vane angle should preferably be about ~5 with the radius, further the ratio of the overall height of the device to the minimum diame-ter of -the diffuser should preferably be near uni-ty, as can be seen in Figure 1.
. O
The vanes 16 may be of aerofoil cross-section as in E~igure 2a or may be of other suitable shapes for example, as al 50 shown in Figure 2a. The vanes 16 may be provided with fluid flow modifiers, as seen in Figure 2 as Elaps 22 hinged -to -the trailiny edge of the vanes 16.
As seen in Figure 2 -the stabilizing column 20 may be pro~ided wi-th a plurality of brace members 24 extending radially outwardly from the column 20 within the hollow body and connected at -the outer edges to -the diffuser 18.
In one preferred application, see Figure 2b, the augmen-tor of Figure 1 is modified to incorporate a turbine 29 mounted on a centrally located, axially extending, turbine shaft 30. Turbine blades 31 are housed within the diffuser 18 and provide a particu-larly safe and compact configuration. By placing the tubine 29 downstream of the vor-tex V the advantage is achieved that the energy in the axial exhaust flow, ra-ther than in the vortex itself, is used. The design of the turbine blades is selected in accor-dance with accep~ed engineering proceedures, such that the turbine blades 31 are driven in a direction opposite -to the direction of rotation of the vortex V and thus the turbine does not diminish the vortex V. The turbine shaft 30~ is supported inside the diffuser 18 by bearing in hub 25 with brace members 24. The opposite end of the shaft, is connected to a device for power utilization say an electric generator located outside the closed end 12.
The fluid flow concen-trating device 10 as described with respect to Figures 1, 2, 2a, and 2b is suitable for use in a wide variety of applications. It can be used as a device to augment wind veloci-tes, which may in turn be used to drive an air turbine or it may be used hydraulically, say, in a tidal si-tua-tion, or low-head hydro power generation. In a tidal si-tua-tion -the incominy tide F would act to enter the vanes 16 in the same fashion as a wind and create a whirlpool which could be used in an~ sui-table fashion, for example to drive a hydraulic turbine in opposi-te direc-tion to the whirlpool.
Turning now to Figure 3 which shows, together wi-th Figure 4, the arrangement of the device in an airborne craft as a lift augmentor for the wing of an aircraft. Here the concentrating device 10 is mounted on top o~ the aircraft wing 35 with the closed end 12 o~ the body spaced from the upper sur~ace 36 of the wing by the vanes 16. In this preferred configuration, the vanes 16 form a substantially frusto-concical structure, narrower at the top then at the base. The vanes may be twisted and/or tapered.
The diffuser channel ]8 is arranged within the wing itself and communicates with the underside 37 o~ the wing.
As the aircraft moves through the air, a wind ~ is created and this passes through the vanes 16 and produces a vortex V2 which provides a downwardly directed airflow to augment the lift of the wing: The air entering the device 10 can be controlled by means o~ trailing edge flaps in the vanes 16 as in Figure 2 0 If required, for say, a VTOL application, a toroidal shaped duct 38 is located around the diffuser channel 18 and is provided with hot gases from the aircraft propulsion engines through a duct 39.
The hot gases entering the duct 38 from the duct 39, pass around the duct 38 into the vanes 16, which in this configuratiOn are hollow, and are blown through nozzles at the tralling edge of -the vanes 16 (see arrows 40 in Figure 4) to produce the vortex in the device 10. The resultant thrust from the hollo~ bod~ 11 through the diffuser 18 may be controlled by a but-terfly va:lve 42, suitably mounted in the difEuser 18 on the stabilizer column 20.
Figure 7 shows the arrangement of the lift augmentor as seen in Figures 3 and 4, in an aircraft at 45, that is to say, near the wing tips and generating trailing vortices which rotate in the same sense as the wing tip trailing vortices.
Figure 5 shows the application of the device 10 as a wind augmentor to drive a turbine 31, the shaft 30 of which is connected to some suitable power takeoff, for example, an elec-trical generator, which in turn can drive an electric motor to propel the watercraftO
Figure 6 shows the application of the device 10 in two fashions to a jet engine. The intake augmentor 50 is mounted externally at the intake 51 of a jet engine and the circumferen-tial wall 14 extends forwardly of the engine intake, the vanes 16 providing a conical configuration, closed at one end by the point 54. In this instance, since the wall 14 is not cylindrical, the vanes 16 advantageously may be twisted and/or tapered. The air taken in through the vanes 16 creates a vortex V3 and improves the efficiency of the engine intake, by increasing the velocity of the intake air. The diffuser 1~ is shaped so as to provide a smooth flow into the intake of the engine. The cone shape of the augmentor 50 additionally ~, .
Sr~
inhibits bird ingestion.
At the exhaust end o the jet engine the engine bod~
itself provides the closed end 12 -to the device 10 arranged as a thrust augmentor 60, vanes 16 conveniently being, as in the case of the intake augmentor, twisted and/or tapered and once again the diffuser 18 at the open end o~ the concentrator lO
provides Eor the escape of exhaust gases from the jet engine.
External air passing through the vanes 16 crea-tes a vortex V4 which improves the performance of the engine and this vortex is stabili~ed by the jet flow itself. That is to say the convergent mixing flow induced by the free jet on passing through the augmentor 60 causes a reduction in pressure around the jet thereby increasing the jet velocit~ and the jet thrust~
The subsequent increase of the mixing flow, strengthens the axial vortex and produces a ring vortex 61 which further augments the thrust. Yet a urther augmentation of the thrust results from ~he increased entropy of the mixing flow by the hot jet gases through convection and radiation.
In Figure 7 the fashion of mounting the devices of Figure 6 on an aircraft is illustrated.
It will be understood that the thrust augmentor 60 could also be used to augment the thrust from a rocket engine when operatin~ in the atmosphere in a manner similar to its use with a jet engine.
Claims (25)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A fluid flow concentrating device comprising a substan-tially hollow body substantially closed at one end and open at the other, an axially extending vortex stabilizing column arranged substantially centrally of the hollow body, the body having a fixed circumferential wall means composed of a plurality of fixed spaced vanes and a diffuser channel located at the open end of said wall means, whereby fluid moving from outside the device substantially radially through said vanes to the inside of said body, creates a vortex within said hollow body and a fluid flow axially of said body through said diffuser channel.
2. A device as claimed in claim 1 in which said vanes are substantially equally spaced circumferentially.
3. A device as claimed in claim 1 in which said vanes are of aerofoil cross-section.
4. A device as claimed in claim 1 in which the stabilizing column extends through the diffuser channel.
5. A device as claimed in claim 1 or claim 4 in which said column is provided with a plurality of brace members extending radially outwardly of the column within the substantially hollow body.
6. A device as claimed in claim 1 or claim 2 or claim 3 in which the vanes are provided with fluid flow modifiers extending along the trailing edges of said vanes.
7. A device according to claim 1 or claim 2 or claim 3 further comprising a turbine located for rotation, in a direction opposite to the direction of rotation of said vortex, about a vertical axis, centrally within the diffuser downstream of the fluid flow.
8. A device as claimed in claim 1 in which the column is a turbine shaft and carries, adjacent an outer end, radially exten-ding turbine blades mounted for rotation, downstream of the fluid flow, centrally of the device about a vertical axis within the diffuser in a direction opposite to the direction of rotation of the vortex.
9. A device as claimed in claim 1 in which hollow body is located on an airborne craft with said open end being normally directed in the direction of the ground.
10. A device as claimed in claim 1 in which hollow body is located on an airborne craft with open end being normally directed in the direction of the ground and said fluid is at least in part a hot gas, a toroidal duct being provided in said craft adjacent said diffuser channel and arranged to blow said hot gas into said hollow body through said vanes.
11. A device as claimed in claim 1 in which said hollow body is mounted on top of an aircraft wing with said closed end of the body spaced from the upper surface of said wing by said vanes and forming a substantially frusto-concical structure narrower at the top than at the base and in which said fluid is at least in part of a hot gas, said diffuser channel being arranged within the wing and communicating with the underside thereof, a toroidal shaped duct being provided in said aircraft wing surrounding said diffuser channel and being arranged to blow said hot gas through said vanes into said hollow body, whereby to provide an axial flow of gas substantially vertically downwardly of the underside of said wing.
12. A device as claimed in claim 1 in which said hollow body is mounted on a marine vessel with said open end being normally directed upwardly, a turbine shaft being provided within said body centrally and axially thereof, and carrying radially extending turbine blades within said diffuser for rotation in a direction opposite to the direction of the rotation of the generated vortex, the end of said turbine shaft remote from said blades being connected for power utilization.
13. A device as claimed in claim 1 in which said vanes are provided, at their trailing edges with a flow modifying means.
14. A device as claimed in claim 13 in which said flow modifying means are flap elements.
15. A device as claimed in claim 13 in which said flow modi-fying means are straight nozzles along said trailing edges of the vanes.
16. A fluid flow concentrating device comprising a substan-tially hollow body of conical configuration, closed at one end at a point and open at the other, the body having a fixed circum-ferential wall means composed of a plurality of fixed spaced vanes and a diffuser channel located at the open end of the wall means, whereby fluid moving from outside the device through said vanes to the inside of said body creates a vortex within said hollow body and a fluid flow axially of said body through said diffuser channel.
17. A fluid flow concentrating device comprising a substan-tially hollow body of conical configuration mounted externally at the intake of a jet engine, said body being closed at one end at a point and open at the other, the body having a fixed circumferen-tial wall means extending forwardly of the engine intake, point forward, and being composed of a plurality of fixed space vanes and a diffuser channel located at the open end of the wall means, whereby fluid moving from outside the device through said vanes to the inside of said body creates a vortex within said hollow body and a fluid flow axially of said body through said diffuser chan-nel.
18. A device as claimed in claim 17 in which the vanes are twisted.
19. A device as claimed in claim 16 or claim 18 in which said vanes are tapered.
20. A device as claimed in claim 1 in which said hollow body is mounted on top of an aircraft wing with said closed end of said body spaced from the upper surface of said wing by said vanes, said diffuser channel being arranged within the wing and communicating with the underside thereof, and an axially extending column arranged centrally of the hollow body and mounting, adjacent its outer end, within said diffuser channel, a butterfly control valve means for throttling the diffuser channel.
21. A device as claimed in claim 20 in which said vanes form a substantially frusto-conical structure narrower at the top than at the base.
22. A device as claimed in claim 1 in which said hollow body is mounted at the trailing end of one of a jet and rocket engine with the diffuser downstream of the jet and the body being closed at one end by the engine, said vanes being twisted.
23. A device as claimed in claim 22 in which the vanes are tapered.
24. A device as claimed in claim 1 in which said hollow body is mounted at the trailing end of one of a jet and a rocket engine with the diffuser downstream of the jet and the body being closed at one end by the engine, said vanes being tapered having a larger chord dimension at one end than at the other end.
25. A fluid flow concentrating device as claimed in claim 1 in which the overall height to diameter ratio of the diffuser is near unity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000435965A CA1214109A (en) | 1983-09-02 | 1983-09-02 | Fluid flow augmentor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000435965A CA1214109A (en) | 1983-09-02 | 1983-09-02 | Fluid flow augmentor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1214109A true CA1214109A (en) | 1986-11-18 |
Family
ID=4126002
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000435965A Expired CA1214109A (en) | 1983-09-02 | 1983-09-02 | Fluid flow augmentor |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1214109A (en) |
-
1983
- 1983-09-02 CA CA000435965A patent/CA1214109A/en not_active Expired
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |