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WO2003010433A1 - Turbine a action radiale pour statoreacteur rotatif - Google Patents

Turbine a action radiale pour statoreacteur rotatif Download PDF

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Publication number
WO2003010433A1
WO2003010433A1 PCT/US2002/023319 US0223319W WO03010433A1 WO 2003010433 A1 WO2003010433 A1 WO 2003010433A1 US 0223319 W US0223319 W US 0223319W WO 03010433 A1 WO03010433 A1 WO 03010433A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
set forth
ramjet
rotary
inlet
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.)
Ceased
Application number
PCT/US2002/023319
Other languages
English (en)
Inventor
Shawn P. Lawlor
Donald Kendrick
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ramgen Power Systems LLC
Original Assignee
Ramgen Power Systems LLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Ramgen Power Systems LLC filed Critical Ramgen Power Systems LLC
Publication of WO2003010433A1 publication Critical patent/WO2003010433A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/005—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2210/00—Working fluids
    • F05D2210/30—Flow characteristics
    • F05D2210/31—Flow characteristics with Mach-number kept constant along the flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/10—Application in ram-jet engines or ram-jet driven vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/12—Purpose of the control system to maintain desired vehicle trajectory parameters
    • F05D2270/122—Speed or Mach number
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention is related to rotary ramjet engines and their components and particularly to the use of turbines for extraction of additional energy from exhaust gases leaving such engines.
  • Such rotary ramjet engines are particularly useful for generation of electrical and mechanical power at efficiencies substantially improved over power plants currently in widespread commercial use.
  • a variety of small to medium size electrical and/or mechanical power plant applications could substantially benefit from a prime mover that provides a significant improvement from the currently known net efficiencies. Specifically, improved efficiency is increasingly important as fuel costs continue to rise.
  • Such small to medium size mechanical or electrical power plants typically but not exclusively from about 1 megawatt up to as much as about 100 megawatts — are required in a wide range of industrial applications, including stationary electric power generating units, in rail locomotives, and in marine power systems. Power plants in this general size range are well suited to use in industrial and utility electrical generation and cogeneration facilities.
  • Such equipment is often employed to provide prime movers for electrical power needs while simultaneously supplying thermal energy to an industrial facility. Increasingly, such equipment is used to provide stand-alone merchant electric power production facilities.
  • Power plant designs which are now commonly utilized in such applications include (a) gas turbines, driven by the combustion of natural gas, fuel oil, or other fuels, and which capture the kinetic energy from the exiting combustion gases, (b) steam turbines, driven by the expansion of steam that is generated by heat recovery steam generators at gas turbine facilities, or by the expansion of steam generated in stand alone facilities from boilers via the combustion of coal, fuel oil, natural gas, solid waste, or other fuels, and (c), from large scale reciprocating engines, usually diesel cycle and typically fired with fuel oils.
  • a power plant design involving the use of a ramjet engine as the prime mover, has higher overall cycle efficiencies when compared to those heretofore-used power plants of which we are aware. Compared to many power plants commonly in use today, such a power plant design is simple, more compact, relatively inexpensive, easier to install and to service, and/or otherwise superior to currently operating plants of which we are aware. To even further enhance the efficiency of such power plants, a unique radial turbine design has been developed in which the turbine is affixed on a common shaft (or on complementary shaft portions acting along a common rotating axis) with a rotary ramjet engine, and turns as the same rotary speed as the ramjet engine rotor.
  • the energy of the exhaust gas from the ramjet engine is efficiently captured by the radial turbine.
  • the radial turbine eliminates the need to capture turbine power output via a separate, external gear and/or a separate electrical generation device.
  • the common shaft mounted radial turbine is beneficial commercially because it enables a power plant to avoid additional separate power output or generation equipment, yet captures otherwise discarded energy from the exhaust gases, thus increasing overall efficiency.
  • an impulse turbine in one embodiment, includes an impeller which is affixed to an extended output shaft portion of the ramjet rotor shaft. Energetic exhaust gases leaving the ramjet combustion chamber are exhausted outward into a slightly pressurized turbine inlet duct. The exhaust gases exit the turbine inlet duct through an outlet nozzle block, which creates a jet of exhaust substantially tangentially to the turbine impeller.
  • a turbine blade configuration may be preselected, so that the turbine has its rotational energy, as captured from the exhaust gases, transferred to the output shaft at the output shaft rate of rotation.
  • a combustion exhaust gas duct may be used to collect and discharge the hot exhaust gas stream to a conduit for transport to a heat exchanger, where the hot exhaust gases are cooled by way of heating up a heat transfer fluid, such as water, in which case the production of hot water or steam results.
  • the heat transfer fluid may be utilized for thermal purposes, or for mechanical purposes, such as driving a steam turbine. In any event, ultimately, the cooled combustion gases are exhausted to the ambient air.
  • one aspect of the present invention resides in the provision of a rotary ramjet engine to generate mechanical and/or electrical power.
  • one of the many objectives achievable by the developments taught herein may be advanced by providing a ramjet driven power generation plant that is capable of reliably and efficiently recovering kinetic energy from exiting combustion gases
  • FIG. 1 provides a partial cross-sectional view of the rotating assembly of an exemplary power plant apparatus, showing rotating output shaft affixed to a rotor and rotatably secured therewith, and with a radial turbine mounted for rotary motion in response to exiting combustion gas, and showing the turbine affixed to a common shaft with the high speed rotor, and the exhaust heat recuperation equipment for cogeneration applications, as well as an electrical generator, gearbox, and shaft coupling.
  • FIG. 2 is a side elevation view of a fully assembled power plant apparatus of the type first illustrated in FIG. 1 above, showing, from right to left, a starter motor, an electrical generator, a gear box, a shaft coupling, the output shaft, an inlet air plenum, the basic rotary ramjet engine, and the impulse turbine casing.
  • FIG. 3 is a partially sectioned perspective view of a portion of the impulse turbine, illustrating the flow path for the hot exhaust gases from the exit of the ramjet into an exhaust gas plenum, and then to the radial impulse turbine.
  • FIG. 4 is a partially sectioned perspective view of the impulse turbine assembly, seen as if assembled external to the rotary ramjet engine, wherein the impulse turbine is illustrated as if mounted on an unseen output shaft, and showing the hub, and illustrating substantially radial impeller blades with a final expansion/deflection nozzle portion on the distal end portion thereof.
  • FIG. 5 is a perspective view of a radial turbine impeller, showing the substantially radial turbine blades extending above a curved substantially conical impeller base.
  • FIG. 6 is a simplified flow diagram depicting capture of thermal energy from an exhaust gas stream to produce steam or hot water, after capture of kinetic energy in an impulse turbine.
  • FIG. 7 is a perspective view of a nozzle blade for use in a block of nozzles surrounding the periphery of the inlet to the radial turbine, showing how each nozzle blade is affixed utilizing a bolt, as well as graphically illustrating the redirection of exhaust gases by the nozzle blade by an angle alpha.
  • FIG. 1 A perspective overview of an exemplary compact electrical generator set 20 is provided in FIG. 1.
  • Components shown include the rail frame skid 22 with integral lubrication oil reservoir and adjacent lube oil pumps 24, the compact rotary ramjet engine 26 with output shaft 28, a gearbox 30, an electrical generator 32, and a starter motor 34.
  • Inlet air as indicated by reference letter A is supplied via inlet duct 36 to a circumferential inlet air supply plenum 38 and thence through a substantially radial air inlet 40 for supply to a pre-swirl compressor inlet 42.
  • a pre-swirl compressor 44 provides compression of the inlet air A.
  • about 1.0 psig of pressure, more or less, is developed.
  • FIG. 1 A perspective overview of an exemplary compact electrical generator set 20 is provided in FIG. 1.
  • Components shown include the rail frame skid 22 with integral lubrication oil reservoir and adjacent lube oil pumps 24, the compact rotary ramjet engine 26 with output shaft 28, a gearbox 30, an electrical generator 32
  • the compressed inlet air is allowed to decelerate in a diffuser portion 46 of pre-swirl compressor outlet duct 48, to build a reservoir of low velocity pressurized inlet air.
  • converging portion 50 of outlet duct 48 convects inlet air to the primary fuel injectors 51.
  • the resultant fuel air mixture is deflected by inlet guide vanes 52 (of which only one guide vane 52 in the guide-vane row is shown in FIGS. 1 and 3) to provide both axial and tangential ramjet inlet velocities as required to produce, at design conditions, a negligible inflow angle of attack at the leading edge 54 of the ramjet inlet centerbody 56.
  • the supersonic ramjet inlet utilizes the kinetic energy inherent in the air mass or fuel/air premix due to the relative velocity between the ramjet inlet and the supplied air or fuel/air premix stream, to compress the inlet air (or, alternately, the inlet fuel/air mixture), preferably via an oblique shock wave structure.
  • the inlet stream is compressed utilizing a shock wave flow pattern operating with compression primarily laterally with respect to the plane of rotation of the rotor 70, to compress the inlet fuel/air mix between the inlet centerbody 56 and adjacent inlet 60 and outlet 62 strake structures.
  • compression and combustion is preferably achieved utilizing a small number of ramjets, (normally expected to be in the range from 2 to 5 total, with accompanying inlet and outlet strakes), and within an aerodynamic duct formed by the spirally disposed, or more specifically, helically disposed inlet 60 and outlet 62 strakes, as opposed to a traditional gas turbine or other axial flow compressor which utilizes many rotor and stator blades.
  • the fuel and combustion air are preferably premixed prior to feed to the ramjet inlet.
  • fuel injectors 51 add necessary amounts of fuel to an inlet fluid entering through diffuser 48.
  • the inlet fluid may be either a fuel free oxidant containing stream, or may contain some high value fuel such as hydrogen, or some low value fuel, such as coal bed methane, coal mine purge gas, landfill methane, biomass produced fuel gas, sub-quality natural gas, or other low grade fuels.
  • the velocity of the compressed inlet fuel/air mixture must be high at the intermixing point between the combustion chamber and the delivery point of the combustible fuel/air mixture, so that flashback of the flame front from the combustor toward the inlet is avoided.
  • the residence time in the diffuser is too short, and the total pressure too low, to initiate an auto-ignition process.
  • the premix is compressed and heated, the in-flowing fluid has substantially entered the combustion chamber, and thus ignition or detonation is substantially avoided in this engine design, unlike, for example the situation in a conventional gas turbine compressor when ingesting an air stream having fuel therein.
  • the velocity through the combustion chamber 72 is substantially reduced by providing a combustion chamber 72 having larger flow area than provided by the inlet ducts thereto, i.e., the passageways between the inlet centerbody 56 and the inlet 60 and outlet 62 strakes.
  • High-speed exhaust gas exiting the combustion chamber 72 propels the rotor 70 at the desired rim speed under design load conditions. Accordingly, in the ramjet configuration illustrated, the acceleration and deceleration of the inlet fluid, and the acceleration and deceleration of the outlet combustion gases, is accomplished efficiently. As illustrated in FIGS.
  • the hot gas products of combustion as indicated by reference arrow 100, after discharge from the combustion chamber 72 flow through a ramjet outlet nozzle, and thence along the outlet strake 62, and are directed rearward to turbine inlet duct 106.
  • pressure is established, up to as much as 40 psig or so.
  • the hot exhaust gases exiting the ramjet combustor are accumulated in a pressure accumulator 121 to capture energy therein.
  • the pressure accumulator 121 has an inlet 123 and an exit 125. At the exit 125 of the pressure accumulator 121 , a block of outlet nozzles 107 is provided. As seen in FIGS.
  • the exhaust gases GS in the turbine inlet duct 106 escape radially inward in the direction of reference arrow EG1 then is redirected by an angle alpha ( ⁇ ) to a direction that is substantially tangential to turbine impeller 108 via redirection between adjacent outlet nozzles 107 in a circular patterned block of outlet nozzles 107.
  • the angle alpha ( ⁇ ) is at or slightly larger than about ninety degrees. In this way, exhaust gas pressure is converted to exhaust gas jets J acting substantially tangentially to the periphery of the inlet edge 109 of the turbine impeller 108. Note, as better illustrated in FIG.
  • the impeller blades 111 have proximal ends 105 that form the start of inlet portions 111 1 of the impeller blades 111.
  • the proximal ends 105 extend outward in a starfish arm fashion from the inlet edge 109 at the base 103 of impeller 108.
  • the energetic exhaust gas products thence race radially inwardly along impeller blades 111 and thence escape rearwardly, with additional expansion and deflection against exit portion 111 2 of blades 111 , and thence outward from the outlet 113 of casing 104 of the turbine impeller 108.
  • energy is extracted and work is applied to the exit or hot section output shaft portion 28'.
  • exit output shaft portion 28' may be a single common shaft, or cooperative shaft portions acting along a common rotational centerline axis, depending upon the design of the output shaft 28 (and possibly 28') in conjunction with rotor 70. In this manner, the rotor 70 and the turbine impeller 108 can rotate in a common direction.
  • the hot exhaust gases 100 may be further utilized by capturing thermal energy therein by being directed, after outlet 113, to an exhaust heat exchanger 110 in duct 115, to heat condensate 112 and produce hot water or high pressure steam 114, before discharge via stack S.
  • the high pressure steam 114 may be utilized in any applicable process host as is typical in a cogeneration system, or utilized in high pressure steam turbine blades yet additional to the ramjet engine design disclosed herein.
  • the net system efficiency at rated power output is preferably at least 38%. More preferably, the net system efficiency at rated power output of such a system configuration is at least 45%, where the quality of generated steam permits.
  • the exhaust flow typically has a high degree of recoverable energy.
  • the radially inward exhaust gas flow noted as exhaust gas EGi in FIGS. 4 and 7, provides a high velocity gas, which is changed in direction by deflection through adjacent outlet nozzles 107 of the type noted in FIG. 7.
  • Any suitable shape may be chosen for nozzles 107, as necessary for maximizing efficiency at the selected gas properties and velocities, but as shown in FIG. 7, an airfoil shape nozzle 107 is suitable in some embodiments.
  • an aperture 209 defined by interior edge walls 211 in a leading edge lobe portion 213 provides space for fitting therethrough of bolt 252,for the nozzle 107 to be secured in a block pattern in the casing 104.
  • the radially inward flow path of the exhaust gas EGi is changed in direction by an angle alpha ( ⁇ ) via redirection between adjacent nozzles 107 in the nozzle block arranged in a circular pattern as denoted by bolts 252 (see FIG. 4).
  • the kinetic energy in exhaust gas jets (identified by reference numeral J in FIG. 7) is thus captured in the impulse turbine. This is because most or substantially all of the remaining pressure in the exhaust gas flow is expanded, and leaves the outlet nozzle block 107 at near atmospheric pressure.
  • a preferred turbine stage for extracting the remaining energy is designed to capture and convert the jet velocity into useable mechanical power, and preferably avoids additional complexity of appreciable pressure decrease or expansion of the exhaust gas flow stream.
  • the impulse turbine 108 is important because of the additional energy recovery and overall system efficiency improvement provided.
  • the ramjet flowpath would develop approximately 303 horsepower (gross, before system losses) of mechanical shaft power per pound mass flow of exiting the ramjet.
  • the impulse turbine assuming an efficiency of 80 percent, the impulse turbine could extract as much as 100 horsepower or more, and even up to as much as 118 horsepower, per pound mass from the ramjet exhaust flow.
  • these numbers may vary for any specific design.
  • the design taught herein may be applicable for operation of rotor 70 rim 250 at a Mach number of at least 1.5, and more generally, in the range from 1.5 to about 3.0. In some embodiments, an optimum range for Mach number of the rotor 70 of the rim 250 would range at 2.5 or more. Attention is now directed to FIGS. 4 and 5.
  • a plurality of outlet nozzles 107 are located circumferentially about the inlet to the impulse turbine 108, with their location being foreshadowed by way of the location of fasteners 252.
  • impeller 108 is mounted at its hub 260 (having interior sidewall 262) on shaft portion 28', indicated only in hidden lines.
  • impeller 111 has been described as having an inlet portion 111 ⁇ and outlet portion 111 2 , the impeller 111 may also have a distinct transition zone 111 3 therebetween, with the exact shape being selected for a particularly service, velocity, and pressure profile.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un ensemble générateur à statoréacteur rotatif (20) doté d'une turbine d'échappement radiale (108). Cette turbine d'échappement radiale (108) comprend un moyeu conique sensiblement incurvé possédant une surface extérieure d'où partent des aubes de turbine, ainsi qu'un boîtier d'accumulation de pression (106) reliant la sortie du statoréacteur (72, 74, 56, 60, 62) à l'entrée de la turbine d'échappement.
PCT/US2002/023319 2001-07-23 2002-07-23 Turbine a action radiale pour statoreacteur rotatif Ceased WO2003010433A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US91223901A 2001-07-23 2001-07-23
US09/912,239 2001-07-23

Publications (1)

Publication Number Publication Date
WO2003010433A1 true WO2003010433A1 (fr) 2003-02-06

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Application Number Title Priority Date Filing Date
PCT/US2002/023319 Ceased WO2003010433A1 (fr) 2001-07-23 2002-07-23 Turbine a action radiale pour statoreacteur rotatif

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011055575A1 (fr) * 2009-11-05 2011-05-12 三菱重工業株式会社 Roue de turbine
CN104234755A (zh) * 2014-09-18 2014-12-24 北京航空航天大学 一种抑制间隙泄露的向心涡轮叶片背部小翼结构
US11596783B2 (en) 2018-03-06 2023-03-07 Indiana University Research & Technology Corporation Blood pressure powered auxiliary pump

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
US4066381A (en) * 1976-07-19 1978-01-03 Hydragon Corporation Turbine stator nozzles
WO1998027330A1 (fr) * 1996-12-16 1998-06-25 Ramgen Power Systems, Inc. Statoreacteur pour la production d'energie

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
US4066381A (en) * 1976-07-19 1978-01-03 Hydragon Corporation Turbine stator nozzles
WO1998027330A1 (fr) * 1996-12-16 1998-06-25 Ramgen Power Systems, Inc. Statoreacteur pour la production d'energie

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011055575A1 (fr) * 2009-11-05 2011-05-12 三菱重工業株式会社 Roue de turbine
JP2011099366A (ja) * 2009-11-05 2011-05-19 Mitsubishi Heavy Ind Ltd タービンホイール
CN102378849A (zh) * 2009-11-05 2012-03-14 三菱重工业株式会社 涡轮机叶轮
US9011097B2 (en) 2009-11-05 2015-04-21 Mitsubishi Heavy Industries, Ltd. Turbine wheel
CN104234755A (zh) * 2014-09-18 2014-12-24 北京航空航天大学 一种抑制间隙泄露的向心涡轮叶片背部小翼结构
US11596783B2 (en) 2018-03-06 2023-03-07 Indiana University Research & Technology Corporation Blood pressure powered auxiliary pump

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