WO2009073406A2 - Rotary mechanically reciprocated sliding metal vane air pump and boundary layer gas turbines integrated with a pulse gas turbine engine system - Google Patents
Rotary mechanically reciprocated sliding metal vane air pump and boundary layer gas turbines integrated with a pulse gas turbine engine system Download PDFInfo
- Publication number
- WO2009073406A2 WO2009073406A2 PCT/US2008/084328 US2008084328W WO2009073406A2 WO 2009073406 A2 WO2009073406 A2 WO 2009073406A2 US 2008084328 W US2008084328 W US 2008084328W WO 2009073406 A2 WO2009073406 A2 WO 2009073406A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- air
- turbine
- air pump
- shaft
- boundary layer
- Prior art date
Links
Classifications
-
- 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
Definitions
- This invention is directed to the field of rotary mechanically reciprocated sliding metal vane air pumps and boundary layer turbines integrated into an pulse explosion driven gas turbine engine system.
- Lobe blowers have two shafts that drives two lobes which are synchronized via a gear box, and therefore cannot be integrated mechanically with the main shaft of pulse driven gas turbine engines.
- Sliding vane blowers in commercial use utilize graphite vanes, typically four per rotor, that are positioned in angle slots in the rotor that permit the vanes to extend into the pump cavity by centrifugal force during rotation.
- the vanes do not extend across the diameter of the pump housing via a slot in the pump shaft and rotor and do not mechanically reciprocate. Moreover, they are subject to breaking or shattering by explosive back pressure.
- Boundary layer phenomenon and technology has been in use for various applications for over a century beginning with Nikola Tesla vortex turbines patented in 1906 and 1913. Boundary layer turbines are utilized with all types of working fluids that maintain a constant pressure and flow the same as centrifugal and axial flow turbines.
- This patent utilizes a hybrid boundary layer turbine with high pressure pulsing working fluid.
- a rotary reciprocating sliding vane air pump and boundary layer turbines are integrated with the shaft of an explosion-driven gas turbine engine system.
- the air pumps have a cavitated block housing with two end plates that house a slotted rotor and a rotating reciprocating sliding vane.
- the rotor is mounted on and at the center of a slotted turbine shaft that permits the reciprocating sliding vane to move back and forth in the cavity as the rotor and shaft turn in the cavitated housing.
- the cavity in the housing is offset from the centerline of the shaft, creating a space between the rotor and the housing wall.
- the dimensions of the rotor and cavity determine displacement per revolution.
- Air is positively displaced at the inlet of the cavitated housing and positively displaced at the outlet. Air inlet and outlet ports enter and exit the cavitated housing wall at 90 degrees and 270 degrees respectively as the rotor and vane rotate clockwise.
- This invention utilizes an air compressor or blower having a single rotary mechanically reciprocated sliding metal vane.
- the vane is slidably contained in a slotted rotor and a slotted shaft.
- Contact with the housing wall mechanically forces the vane to move back and forth in a reciprocal motion within the slot across the diameter of the cavitated housing inducing and exhausting two pulses of air per revolution.
- This invention utilizes pulsed charges of air to produce explosions when mixed with fuel and ignited in combustion chambers with arcing ignitions, producing explosive forces that are exhausted from the combustion chambers via nozzles at high velocity.
- This invention also utilizes hybrid boundary layer gas turbine wheels as a means of converting high temperature, high pressure, and high velocity working fluid to shaft horsepower.
- Conventional boundary layer turbines consist of a series of hybrid disks bolted together with spacers between the disks.
- the hybrid boundary layer turbine of the present invention uses a solid wheel with grooves machined in its outer surface
- Fig. 1 is a cross sectional view of a rotary reciprocating sliding vane air pump, cavitated housing, slotted rotor, slotted shaft and sliding vane;
- Fig. 2 is an end view of a boundary layer gas turbine wheels, showing vanes formed by grooves in the perimeter of the wheel;
- Fig. 3 is a cross sectional view of an explosion driven boundary layer gas turbine engine system utilizing pulsed combustion air produced by the rotary reciprocating sliding vane air pump and manifolds conveying combustion air to the engines combustion chambers;
- Fig. 4 is a side view of the components of Figs. 1 - 3 assembled.
- the rotary reciprocating sliding vane air pump shown in Fig.1 and two boundary layer gas turbines - one of which is shown in Fig. 2 - are integrated to form an explosion driven gas turbine engine system shown in Figs. 3 - 4.
- the rotary reciprocating sliding vane air pump includes a housing 11 with a slotted rotor 12 mounted on a slotted shaft 13.
- the housing 11 has a cavity whose center is offset from the center line of the shaft 13, thus forming an eccentric annular space between the rotor 12 and cavity wall.
- a single mechanically reciprocated sliding metal vane 14 is positioned in the slotted rotor 12 so as to extend across the diameter of the housing 11 cavity 15.
- the vane is sized so that both its ends contact the wall of the cavity as the rotor turns.
- the cavity wall is approximately cylindrical; however, it may be made slightly non- cylindrical if desired to maintain uniform blade contact at all points.
- An inlet air channel 16 extends from the top of the housing 11 through the cavity 15 wall at 90 degrees.
- An outlet air channel 17 extends from the top of the housing 11 through the cavity wall 15 at 270 degrees.
- each of the boundary layer gas turbine assemblies includes a circular disk 23 disposed within a closely fitting housing. Central portions on either side of a center plane of the disk are milled out to form a flywheel.
- the disk has a bore at its center and is mounted on the slotted shaft 13.
- the periphery of the disk 23 has a series of deep circumferential grooves which form circumferential vanes 24 whose surfaces lie in radial planes. The depth and number of the grooves, and the circumference of the disk 23 determine the total surface area of the vanes.
- the boundary layer gas turbine 23 is situated within the turbine housing 30.
- the turbine 23 is mounted on the main shaft 13.
- Combustion chambers 20 and 21 are mounted on the housing 30, and arc electrodes 31 and 32 are positioned in the combustion chambers 20 and 21.
- the outlet from the mechanically reciprocated sliding metal vane air pump supplies combustion air to the center manifold 22, which directs the combustion air to the combustion chambers 20 and 21.
- Fuel injectors 18 and 19 mix fuel with the combustion air as it flows through the Venturis entering the combustion chambers 20 and 21.
- Arcing electrodes 31 and 32 then detonate the fuel-air mixtures, producing high pressure and velocity working fluid.
- Gas nozzles 25 and 28 are bored in the housing 30 at an angle that directs combusted high pressure and velocity gases from the combustion chambers 20 and 21 toward the vanes 24 of the boundary layer gas turbine. The gases flow between the vanes 24, creating frictional drag on the vane surfaces. Exhaust gas ports 26 and 27 in the housing 30 are positioned 90 degrees downstream from the nozzles 25 and 28 exhaust manifolds 33 and 33' exhaust the spent gases from the turbines 24 into the atmosphere.
- the components are assembled with the air pump housing 11 at the center, between two boundary layer gas turbine housings 30 and 30A.
- Those components and the end bearing plates 37 and 38 are all positioned on a common main shaft 13, separated by spacers 36 and held together with four tie bolts 35 positioned in all corners of the housings 11, 30, 30A, and the end bearing plates 37 and 38.
- the entire assembly is mounted on a common structure such as a base plate 34 to maintain rigidity.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Rotary Pumps (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2010536080A JP2011517741A (en) | 2007-11-30 | 2008-11-21 | Boundary layer gas turbine combined with rotary and mechanical reciprocating sliding metal vane air pump and pulse gas turbine engine system |
CN2008800115578A 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 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US94834807A | 2007-11-30 | 2007-11-30 | |
US11/948,348 | 2007-11-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2009073406A2 true WO2009073406A2 (en) | 2009-06-11 |
WO2009073406A3 WO2009073406A3 (en) | 2009-08-13 |
Family
ID=40718435
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
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 |
Country Status (4)
Country | Link |
---|---|
JP (1) | JP2011517741A (en) |
KR (1) | KR20100096116A (en) |
CN (1) | CN101652546B (en) |
WO (1) | WO2009073406A2 (en) |
Cited By (4)
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 |
WO2015164261A1 (en) * | 2014-04-21 | 2015-10-29 | Amorphic Tech Ltd | Unitary pump and turbine energy exchanger |
US9551292B2 (en) | 2011-06-28 | 2017-01-24 | Bright Energy Storage Technologies, Llp | Semi-isothermal compression engines with separate combustors and expanders, and associated systems and methods |
IT202000021277A1 (en) * | 2020-09-09 | 2022-03-09 | Antonino Pietro Zoratto | ROTARY ENGINE ARCHITECTURE |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2536214B (en) * | 2015-03-05 | 2020-05-27 | Elogab O | Engine system and method of generating electricity from an internal combustion engine |
CN109931182B (en) * | 2019-04-25 | 2024-02-20 | 西安航空学院 | Eccentric sliding vane type gas turbine |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5470197A (en) * | 1994-10-28 | 1995-11-28 | Cafarelli; Robert S. | Turbine pump with boundary layer blade inserts |
JP2000120579A (en) * | 1998-10-13 | 2000-04-25 | Ntn Corp | Turbo molecular pump |
US20050276681A1 (en) * | 2004-06-14 | 2005-12-15 | Avina David C | Combined cycle boundary layer turbine |
Family Cites Families (2)
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 |
JPH08296575A (en) * | 1995-04-25 | 1996-11-12 | Smc Corp | Rotary vane type compressor and vacuum pump |
-
2008
- 2008-11-21 WO PCT/US2008/084328 patent/WO2009073406A2/en active Application Filing
- 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
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5470197A (en) * | 1994-10-28 | 1995-11-28 | Cafarelli; Robert S. | Turbine pump with boundary layer blade inserts |
JP2000120579A (en) * | 1998-10-13 | 2000-04-25 | Ntn Corp | Turbo molecular pump |
US20050276681A1 (en) * | 2004-06-14 | 2005-12-15 | Avina David C | Combined cycle boundary layer turbine |
Cited By (7)
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 |
US9062548B2 (en) | 2010-03-01 | 2015-06-23 | Bright Energy Storage Technologies, Llp | Rotary compressor-expander systems and associated methods of use and manufacture, including integral heat exchanger systems |
US9551292B2 (en) | 2011-06-28 | 2017-01-24 | Bright Energy Storage Technologies, Llp | Semi-isothermal compression engines with separate combustors and expanders, and associated systems and methods |
WO2015164261A1 (en) * | 2014-04-21 | 2015-10-29 | Amorphic Tech Ltd | Unitary pump and turbine energy exchanger |
US9759066B2 (en) | 2014-04-21 | 2017-09-12 | Amorphic Tech Ltd | Unitary pump and turbine energy exchanger |
IT202000021277A1 (en) * | 2020-09-09 | 2022-03-09 | Antonino Pietro Zoratto | ROTARY ENGINE ARCHITECTURE |
EP3967844A1 (en) * | 2020-09-09 | 2022-03-16 | Antonino Pietro Zoratto | Rotary engine architecture |
Also Published As
Publication number | Publication date |
---|---|
CN101652546B (en) | 2011-09-07 |
CN101652546A (en) | 2010-02-17 |
JP2011517741A (en) | 2011-06-16 |
WO2009073406A3 (en) | 2009-08-13 |
KR20100096116A (en) | 2010-09-01 |
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