CN101652546A - The rotary machine that combines with the gas-burning pulse turbine system reciprocatingly slide metal blade air pump and boundary layer gas turbine - Google Patents
The rotary machine that combines with the gas-burning pulse turbine system reciprocatingly slide metal blade air pump and boundary layer gas turbine Download PDFInfo
- Publication number
- CN101652546A CN101652546A CN200880011557A CN200880011557A CN101652546A CN 101652546 A CN101652546 A CN 101652546A CN 200880011557 A CN200880011557 A CN 200880011557A CN 200880011557 A CN200880011557 A CN 200880011557A CN 101652546 A CN101652546 A CN 101652546A
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- CN
- China
- Prior art keywords
- air
- blade
- air pump
- turbine
- cavity
- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C18/00—Rotary-piston pumps specially adapted for elastic fluids
- F04C18/30—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
- F04C18/34—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members
- F04C18/344—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
- F04C18/3441—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member the inner and outer member being in contact along one line or continuous surface substantially parallel to the axis of rotation
- F04C18/3442—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member the inner and outer member being in contact along one line or continuous surface substantially parallel to the axis of rotation the surfaces of the inner and outer member, forming the inlet and outlet opening
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C23/00—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids
- F04C23/005—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids of dissimilar working principle
- F04C23/006—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids of dissimilar working principle having complementary function
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C23/00—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids
- F04C23/02—Pumps characterised by combination with or adaptation to specific driving engines or motors
Abstract
The rotary machine blade air pump that reciprocatingly slides combines with pulsed driven boundary layer combustion gas turbine on being positioned at single axle.Described axle has groove, and aligns with slotted rotor that Mechanical Driven the metal blade that reciprocatingly slides.Cavity on the housing departs from the center line of axle, thereby forms cavity between rotor and cavity wall.Air is forced to import in the inlet of cavity housing, and is forced to discharge in the outlet port.Suction port and air outlet enter and draw with spending angles the hollow shell body wall with an angle of 90 degrees and 270 respectively.Pressurized air imports via manifold in the firing chamber on the sidewall be installed in turbine shroud.The arc electrode fuel-air mixture that ignited is drained into high temperature and high pressure pulsed operation fluid in the blade of boundary layer gas turbine thereby produce via nozzle.
Description
Technical field
The present invention relates to such technical field, wherein reciprocatingly slide metal blade air pump and boundary layer turbines of rotary machine is combined into the gas turbine system that deflagration pulse drives.
Background technique
In the combustion gas turbine field that deflagration pulse (explosion-pulse) drives, for example at U. S. Patent 6,000, the combustion gas turbine that proposes in 214, turbo machine is modified model Pei Erdun (Pelton) water wheels that detonation drives, its have kinetic energy impact and the expanding gas effect under pass the blade seat ring and force the blade that moves.Utilization is installed in Roots type blade (Roots-type lobe) blower or the sliding blade blower on main turbine and the shaft assembly from the outside, produce pressurized air.
Therefore the blade blower has two axles, and its driving obtains two synchronous blades by gearbox, can not carry out mechanical bond with the main shaft of the combustion gas turbine of pulsed drive.The sliding blade blower that uses in commerce adopts graphite vanes, and each rotor is four blades usually, and they are positioned in the epitrochanterian chamfered groove, and blade can be extended in the pump chamber by centrifugal force in rotary course.Blade can not extend through the diameter portion of pump case via pump shaft and epitrochanterian groove, and can not be back and forth mechanical.And they are easy to fracture take place under the back-pressure effect of detonation or shatter.
The Nikola Tesla vortex turbo machine that patented and authorize since 1906 and 1913, boundary layer phenomenon and technology were used to various application occasions more than 100 year.Boundary layer turbines is applied to all types of working fluids, and it is with centrifugal identical with axial flow turbine, and working fluid keep-ups pressure and flow constant.
Summary of the invention
The present invention adopts a kind of hybrid boundary layer turbines with high pressure pulsed operation fluid.
According to the present invention, rotary reciprocatingly slide blade air pump and boundary layer turbines are that the axle of the gas turbine system that drives with detonation combines.Air pump has the cylinder body that has cavity, and it has reciprocatingly slide two end plates of blade of ccontaining slotted rotor and rotation.Rotor be installed in the trough of belt turbine shaft in the heart, described axle make reciprocatingly slide blade can along with rotor and axle in the cavity housing rotation and move forward and backward.Cavity on the housing departs from the center line of axle, thereby forms the space between rotor and shell body wall.The size of rotor and cavity has determined each rotating amount of movement.Air is forced to import in the import of cavity housing, and is forced to discharge in outlet.Along with rotor and blade turn clockwise, suction port and air outlet enter and draw with spending angles the hollow shell body wall with 90 degree and 270 respectively.
When the suction port on the reciprocal metal blade rotation of the rotary machine process hollow shell body wall, vacuum makes from the inflation of inlet hole and forces to move, and makes the force air in the cavity move to air outlet hole.During each the revolution, import and discharge twice of inflation.The air of discharging enters manifold via safety check.Manifold is directly introduced the valveless type firing chamber that is installed on the turbine shroud with air.Fuel sprays in the venturi hole of firing chamber, and fuel and air mixture is lighted by the arc mode.Detonation gas produces back-pressure in Venturi tube, and has reduced the air flows that flows to the firing chamber; Air in the manifold temporarily is reintroduced to opposite firing chamber thus.Main deflagration pulse is discharged the firing chamber via nozzle, and described nozzle is guided the expanding gas of the high speed/lightweight of heat the blade of boundary layer combustion gas turbine into, thereby forces turbine, axle and sliding-vane rotor rotation, produces and charges into combustion air continuously.
The present invention adopts has single rotary machine the reciprocatingly slide air compressor or the blower of metal blade.Blade is slidably received within on slotted rotor and the spline shaft.With contacting that shell body wall carries out, the diameter portion that forces blade to pass the cavity housing in the to-and-fro motion mode in groove mechanically moves forward and backward, thereby each revolution imports and discharge twice pulse of air.
The present invention adopts the pulse inflation, with generation detonation when obtaining lighting in the firing chamber with fuel mix and in the arc mode, thereby produces the detonation power to discharge via nozzle at a high speed from the firing chamber.
The present invention also adopts hybrid boundary layer combustion gas turbine runner, as the device that high temperature, high pressure and high speed operation fluid is changed into air horsepower.Conventional boundary layer turbines comprises the spacer between the utilization dish and a series of mixing pans that bolt links together.Compound boundary layer turbo machine of the present invention adopts solid wheel, and its further groove forms on its outer surface by machining.
With reference to the accompanying drawing that preferred implementation is shown, will further discuss principle of the present invention.The detailed protocol of representing among the figure is used to example, rather than limits All aspects of of the present invention.
Description of drawings
In the accompanying drawings:
Fig. 1 is the cross-sectional view of rotary reciprocatingly slide blade air pump, empty capsid, slotted rotor, spline shaft and sliding blade;
Fig. 2 is the end elevation of boundary layer combustion gas turbine runner, has shown by the formed blade of the groove in the periphery of runner;
Fig. 3 is the cross-sectional view of the boundary layer gas turbine system that drives of detonation, and described turbine system utilization is by the rotary blade air pump and combustion air is transported to the pulse-combustion air that manifold produced of engine chamber of reciprocatingly sliding; And
Fig. 4 is the side view after the parts shown in Fig. 1-3 obtain assembling.
Embodiment
In preferred implementation of the present invention, rotary blade air pump and two the boundary layer combustion gas turbines (Fig. 2 has shown one of them) of reciprocatingly sliding shown in Figure 1 combine, to form the gas turbine system that the detonation shown in Fig. 3-4 drives.
With reference to Fig. 1, the rotary blade air pump that reciprocatingly slides comprises housing 11, and this housing 11 has the slotted rotor 12 that is installed on the spline shaft 13.Housing 11 has cavity, and its misalignment is opened the center line of axle 13, has formed eccentric annular space thus between rotor 12 and cavity wall.The single machinery metal blade 14 that reciprocatingly slides is positioned in the slotted rotor 12, with the diameter portion of the cavity 15 that extends through housing 11.The size of blade is designed such that when rotor rotation, two ends of blade all contact cavity wall.Cavity wall is a general cylindrical shape; Yet, also can make non-cylindrical slightly if desired, to remain on the even blade contact of all points.
Gas-entered passageway 16 extends through cavity wall 15 from the top of housing 11 with becoming an angle of 90 degrees.Outlet passageway 17 extends through cavity wall 15 from the top of housing 11 with 270 with spending angles.When spline shaft 13 and slotted rotor 12 turned clockwise, air was sucked eccentric space by the machinery metal blade 14 that reciprocatingly slides via gas-entered passageway Final 16 system, and was forced to move in the gas-entered passageway 17 by the machinery metal blade 14 that reciprocatingly slides subsequently.Thus, the each revolution of the rotary blade that reciprocatingly slides will produce twice inflation (twocharges of air).
With reference to Fig. 2, each in the gas turbine assembly of boundary layer all comprises the disk 23 in the housing that is arranged in close fit.Core on any side of central plane of dish by milling to form flywheel.Coil therein that the heart has the hole, and be installed on the spline shaft 13.Dish 23 periphery has a series of dark circumferential grooves, and they have constituted its surface and have been positioned at circumferential vanes 24 on the radial plane.The degree of depth of groove and quantity and coil the total surface area that 23 periphery has determined blade.
When high-velocity combustion gas entered groove, the friction drag force on the blade wall drove and makes the turbine disk 23 to quicken.When the peripheral velocity of turbine reached the speed of high-speed gas, the boundary layer was formed on the blade surface, thereby kept the speed of the turbine disk 23.
As shown in Figure 3, boundary layer gas turbine 23 is positioned at turbine shroud 30.Turbine 23 is installed on the main shaft 13. Firing chamber 20 and 21 is installed on the housing 30, and arc electrode 31 and 32 is arranged in firing chamber 20 and 21.Supply with combustion airs from the machinery outlet that the metal blade air pump draws that reciprocatingly slides to center manifold 22, described center manifold 22 is guided combustion air into firing chamber 20 and 21.When combustion air flow through the Venturi tube that enters in firing chamber 20 and 21, fuel injector 18 and 19 mixed fuel with combustion air.Arc electrode 31 and 32 is pilot fuel-AIR MIXTURES subsequently, thereby produces high pressure and working fluid at a high speed.Gas nozzle 25 and 28 is at a certain angle in housing 30 perforates, thus the blade 24 that high pressure that the burning of the chamber of spontaneous combustion in the future 20 and 21 obtains and high-speed gas are guided the boundary layer gas turbine into.Gas flows between blade 24, thereby forms the friction drag force on blade surface.Waste gas outlet 26 on the housing 30 positions with 28 downstreams at nozzle 25 with 27 with becoming an angle of 90 degrees, and exhaust manifold 33 and 33 ' enters atmosphere with waste gas from turbine 24.
As shown in Figure 4, center and the air pump housing 11 of described each parts between two boundary layer gas turbine casings 30 and 30A assembled.Those parts and overhang bracket plate 37 and 38 all are positioned on the shared main shaft 13, are separated by liner 36, and utilize four tie bolts 35 at all places, bights of being positioned at housing 11,30,30A and overhang bracket plate 37 and 38 and keep together.Whole assembly is installed on the sharing structure (for example base plate 34), to keep rigidity.
Because the present invention can carry out modification and change, so foregoing description and accompanying drawing be construed as merely example, and the present invention is limited by accessory claim.
Claims (6)
1. internal-combustion engine comprises:
Supporting the housing of running shaft,
Air pump with air intlet and air outlet slit; Described air pump is driven by described running shaft, producing twice pulse of compressed air when each revolution, and
At least one turbine assembly, wherein each turbine assembly comprises:
A pair of valveless type firing chamber, they link to each other with described air outlet slit by manifold separately; Wherein, each firing chamber has fuel is imported to device in the pressurized air, and described pressurized air enters in the firing chamber, and each firing chamber also has the device of lighting the fuel-air mixture in the firing chamber, and
The turbo machine that combustion air drove of origin spontaneous combustion chamber; Described turbo machine is installed to a side of described air pump on described running shaft.
2. internal-combustion engine as claimed in claim 1 is characterized in that, described air pump comprises:
Housing, its shell body wall defines cavity, wherein passes described shell body wall and has formed air intlet and air outlet slit; The misalignment of described cavity is opened the center line of described axle,
Thereby be fixed on axle and go up the rotor that in cavity, rotates; Wherein, described rotor and described shell body wall between form eccentric annular space; Described rotor and axle have the alignment slot that extends on diametric(al),
Be arranged in the single metal blade in the described alignment slot slidably, the size of described blade is designed such that two end in contact of blade shell body wall, and then make: when rotor rotates in described cavity, blade pass is crossed described air intlet air is drawn in the eccentric annular space, and by described air outlet slit air is discharged eccentric annular space.
3. internal-combustion engine as claimed in claim 3 is characterized in that described turbo machine is a boundary layer turbines, and its periphery defines a plurality of circumferential grooves, and described circumferential groove defines a plurality of circumferential vanes therein; Described circumferential vanes has enough surface areas, so that form the boundary layer when combustion gas are drawn towards turbo machine.
4. internal-combustion engine as claimed in claim 3 is characterized in that, described turbine assembly comprises two turbine assemblies, wherein, comprises a turbine assembly separately in the both sides of described air pump.
5. internal-combustion engine as claimed in claim 2 is characterized in that, described turbine assembly comprises two turbine assemblies, wherein, comprises a turbine assembly separately in the both sides of described air pump.
6. internal-combustion engine as claimed in claim 1 is characterized in that, described turbine assembly comprises two turbine assemblies, wherein, comprises a turbine assembly separately in the both sides of described air pump.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US94834807A | 2007-11-30 | 2007-11-30 | |
| US11/948,348 | 2007-11-30 | ||
| PCT/US2008/084328 WO2009073406A2 (en) | 2007-11-30 | 2008-11-21 | Rotary mechanically reciprocated sliding metal vane air pump and boundary layer gas turbines integrated with a pulse gas turbine engine system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101652546A true CN101652546A (en) | 2010-02-17 |
| CN101652546B CN101652546B (en) | 2011-09-07 |
Family
ID=40718435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008800115578A Expired - Fee Related CN101652546B (en) | 2007-11-30 | 2008-11-21 | Rotary mechanically reciprocated sliding metal vane air pump and boundary layer gas turbines integrated with a pulse gas turbine engine system |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JP2011517741A (en) |
| KR (1) | KR20100096116A (en) |
| CN (1) | CN101652546B (en) |
| WO (1) | WO2009073406A2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111267974A (en) * | 2015-03-05 | 2020-06-12 | 奥萨马·伊劳格布 | Method and system for reducing drag in a vehicle |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9057265B2 (en) | 2010-03-01 | 2015-06-16 | Bright Energy Storage Technologies LLP. | Rotary compressor-expander systems and associated methods of use and manufacture |
| JP2014522938A (en) | 2011-06-28 | 2014-09-08 | ブライト エナジー ストレージ テクノロジーズ，エルエルピー． | Quasi-isothermal compression engine with separate combustor and expander and corresponding system and method |
| ES2822988T3 (en) | 2014-04-21 | 2021-05-05 | Amorphic Tech Ltd | Unit Pump and Turbine Power Exchanger |
| CN109931182B (en) * | 2019-04-25 | 2024-02-20 | 西安航空学院 | Eccentric sliding vane type gas turbine |
| IT202000021277A1 (en) * | 2020-09-09 | 2022-03-09 | Antonino Pietro Zoratto | ROTARY ENGINE ARCHITECTURE |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3022909C2 (en) * | 1980-06-19 | 1985-09-05 | Schottel-Werft Josef Becker Gmbh & Co Kg, 5401 Spay | Centrifugal pump, in particular for driving watercraft |
| US5470197A (en) * | 1994-10-28 | 1995-11-28 | Cafarelli; Robert S. | Turbine pump with boundary layer blade inserts |
| JPH08296575A (en) * | 1995-04-25 | 1996-11-12 | Smc Corp | Rotary vane type compressor and vacuum pump |
| JP2000120579A (en) * | 1998-10-13 | 2000-04-25 | Ntn Corp | Turbo molecular pump |
| US7241106B2 (en) * | 2004-06-14 | 2007-07-10 | Avina David Christopher | Combined cycle boundary layer turbine |
-
2008
- 2008-11-21 CN CN2008800115578A patent/CN101652546B/en not_active Expired - Fee Related
- 2008-11-21 KR KR1020107011786A patent/KR20100096116A/en not_active Application Discontinuation
- 2008-11-21 JP JP2010536080A patent/JP2011517741A/en not_active Withdrawn
- 2008-11-21 WO PCT/US2008/084328 patent/WO2009073406A2/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111267974A (en) * | 2015-03-05 | 2020-06-12 | 奥萨马·伊劳格布 | Method and system for reducing drag in a vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20100096116A (en) | 2010-09-01 |
| WO2009073406A3 (en) | 2009-08-13 |
| WO2009073406A2 (en) | 2009-06-11 |
| JP2011517741A (en) | 2011-06-16 |
| CN101652546B (en) | 2011-09-07 |
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| ASS | Succession or assignment of patent right |
Owner name: ALPHA POWER SYSTEM CO., LTD. Free format text: FORMER OWNER: R. SCRAGG Effective date: 20100330 |
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| C41 | Transfer of patent application or patent right or utility model | ||
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Effective date of registration: 20100330 Address after: Florida, USA Applicant after: Scragg Robert Address before: Florida, USA Applicant before: R.Skrague |
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| CF01 | Termination of patent right due to non-payment of annual fee |