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WO2003010431A1 - Ensemble de generateur de statoreacteur rotatif et compact - Google Patents

Ensemble de generateur de statoreacteur rotatif et compact Download PDF

Info

Publication number
WO2003010431A1
WO2003010431A1 PCT/US2002/023186 US0223186W WO03010431A1 WO 2003010431 A1 WO2003010431 A1 WO 2003010431A1 US 0223186 W US0223186 W US 0223186W WO 03010431 A1 WO03010431 A1 WO 03010431A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
set forth
inlet
ramjet
steam
Prior art date
Application number
PCT/US2002/023186
Other languages
English (en)
Inventor
Shawn P. Lawlor
Robert C. Steele
Original Assignee
Ramgen Power Systems, Inc.
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, Inc. filed Critical Ramgen Power Systems, Inc.
Publication of WO2003010431A1 publication Critical patent/WO2003010431A1/fr

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
    • F02K7/10—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
    • 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
    • F02K7/005—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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/56—Combustion chambers having rotary flame tubes

Definitions

  • This invention relates to the field of power generation. More particularly, the invention relates to compact stationary power generation units utilizing ramjets for creating shaft power, and using such power for electrical generation.
  • a compact rotary ramjet engine based generator set and, more particularly, a rotary ramjet engine having an inlet air compressor (i.e., supercharger) for increasing power produced from a supersonic ramjet inlet and suitable combustion chamber structure. It would also be desirable that such an engine be provided with an optional impulse turbine stage for additional energy recovery, in order to enable the engine to maintain high efficiency power output even when provided in relatively small sizes, such as from less than 1000 kW up to about 10,000 kW of electrical power generation capability.
  • One embodiment of a newly developed novel rotary ramjet engine based generator set design disclosed herein has, in series gas flow combination, rotating components including an inlet air compressor (supercharger) for increasing pressure to the inlet air supply (which pressure is subsequently converted to kinetic energy, i.e., swirl velocity, by inlet guide vanes) a rotary ramjet with a rotor having a rotating combustion chamber portion including a ramjet compression inlet, a flame holder, and an outlet nozzle.
  • an impulse turbine is provided for recovering kinetic energy from hot escaping combustion gases.
  • the rotor has an output shaft operably connected, normally via a speed-adjusting gearbox, to an electrical generator.
  • Adjacent static housing for the rotating components is provided to define an inlet air compressor discharge duct, a substantially cylindrical engine casing wall circumferentially confining the rotary combustion chamber portion, and optionally, an impulse turbine casing for confining, receiving, and containing hot combustion gases before and after passage through the impulse turbine.
  • An exhaust gas collection duct is provided to receive the hot exhaust gas flow.
  • a heat recuperator is preferably (but optionally) supplied in the exhaust gas collection duct to recover thermal energy from the exhaust gas collection duct and generate pressurized steam therefrom.
  • pressurized steam can be used directly in a steam section of the impulse turbine, or can be utilized elsewhere in a cogeneration heat recovery system.
  • the rotary ramjet design preferably utilizes an inlet centerbody in which ramjet compression is achieved at supersonic inlet inflow velocities, by exploiting an oblique shock extending from a leading edge structure laterally outwardly to, at the design velocity, confining inlet and outlet strakes.
  • the combustor and accompanying strakes are affixed to the rotor in a preselected, substantially matched helical angle orientation, so as to smoothly and continuously acquire clean inlet air and discharge the resulting products of combustion.
  • the combustion chamber is simplified in that a rear wall of the inlet centerbody serves as a forward wall of a combustion chamber, providing for flame holding.
  • a combustor cavity is defined to provide for through mixing of fuel and air, and to provide sufficient residence time for reaction of fuel with oxidant in order to minimize the escape of incomplete combustion products from the combustor.
  • the foregoing combustion chamber configuration provides for improved flame holding, better flame front development, and for improved mixing of fuel and air at supersonic inlet velocities.
  • the combustor flameholder extends outward from the rim of the rotor toward the stationary, substantially cylindrical tubular interior peripheral wall (less running clearance).
  • Yet another aspect may include matching the axial arid tangential flows at the inlet centerbody and at the exhaust outlet nozzle of the ramjet, providing a primarily tangential flow type engine is provided with reduced energy loss due to unmatched flow rates, or due to excess or unnecessary axial flow.
  • FIG. 1 shows a partially sectioned perspective view of a compact rotary ramjet engine, rail mounted and coupled with an electrical generator and starting motor.
  • FIG. 2 shows a side elevation view of a 800 kW size compact rotary ramjet engine, further illustrating the components set forth in FIG. 1 above.
  • FIG. 3 shows a rear end view of the 800 kW size compact rotary ramjet engine just set forth in FIG. 2 above.
  • FIG. 4 shows a front-end view of the 800 kW size compact rotary ramjet engine just set forth in FIG. 3 above.
  • FIG. 5 shows a partially broken away perspective view a compact rotary ramjet engine, showing a pre-swirl compressor to act on the air inlet, fuel injection nozzles, the use of inlet air guide vanes, a rotary ramjet with inlet and outlet strakes and an inlet centerbody accompanying one ramjet combustor, an impulse turbine to receive hot exhaust gases exiting the ramjet combustor, and the related planetary gear set for coupling output power from the impulse turbine to the output shaft.
  • FIG. 6 is a partially broken away perspective view of the steam turbine portion of
  • the impulse turbine illustrating the steam turbine blading, inlet nozzles, a low pressure
  • FIG. 7 is a vertical cross-sectional view of the compact rotary ramjet engine
  • FIG. 8 illustrates the recovery of heat from hot exhaust gas to create pressurized steam for use in the steam turbine, to provide additional shaft power in the compact
  • FIG. 9 illustrates the recovery of heat from the exhaust gas for use by in an
  • FIG. 10 is a graphical representation of the net system efficiency of the compact
  • FIG. 1 1 is a graphical representation of the net system efficiency of the compact
  • FIG. 12 illustrates the use of a compound impulse turbine blade, where a portion
  • the blade includes steam buckets, and a portion of the blade is configured to react to
  • FIG. 1 A perspective overview of an exemplary embodiment of a compact electrical generator set 20 is provided in FIG. 1.
  • Basic components include the rail frame skid 22 with integral lubrication oil reservoir and adjacent lube oil pumps, 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 radial air inlet 40 for supply to a pre-swirl compressor inlet 42. From compressor inlet 42 a pre-swirl compressor 44 provides compression of the inlet air A.
  • 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 accelerates inlet air, and directs the air over the primary fuel injectors 51.
  • the resultant fuel air mixture is deflected and accelerated by inlet guide vanes 52 (of which only one guide vane 52 in the guide-vane row is shown in FIG. 1 ) 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.
  • Inlet and exhaust strakes 60 and 62 are preferably spiral or helical in shape, and are offset at a helical angle from the plane of rotation R of the rotor 70 at the same matching angle, as noted in FIG 7.
  • the exemplary technique of providing lean pre-mixed fuel at negligible angle of attack enables the inlet fluid to be supplied with minimal pressure loss, viscous fluid flow complications, or parasitic power losses.
  • 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, by compressing the inlet air (or, alternately, the inlet fuel/air mixture), preferably via an oblique Shock wave structure.
  • the inlet stream is compressed utilizing a 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.
  • the compressed inlet fuel/air mix is also contained by the substantially cylindrical tubular interior sidewall portion 80 of the engine casing 82.
  • the compression and combustion is achieved utilizing only a small number of ramjets, (normally expected to be in the range from 2 to 5 total, with accompanying inlet and outlet strakes for each ramjet), 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 using many rotor and stator blades.
  • fuel injectors 51 add the fuel to an inlet fluid (which may be either be a fuel free oxidant containing stream, or which 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) provided through diffuser portion 46 of compressor outlet duct 48.
  • inlet fluid which may be either be a fuel free oxidant containing stream, or which 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 should preferably 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 reduced or avoided.
  • the residence time in the diffuser is too short, and the total pressure too low, to initiate an auto-ignition process. Further, by the time the premix is compressed and heated, the in-flowing fluid has entered the combustion chamber, and thus ignition or detonation is entirely avoided in this engine design, unlike, for example the situation in the usual gas turbine compressor section design.
  • downstream of the rear wall 104 of inlet centerbody 56 may be stabilized by substantially reducing the velocity through the combustion chamber 72 by providing a combustion chamber 72 having larger flow area than provided by the inlet ducts thereto. Localized recirculation zones may also be provided in order to have an adequate residence time to substantially eliminate creation of carbon monoxide in the combustor.
  • a combustion chamber 72 with a constant duct height and a predetermined overall length Lc is provided.
  • this overall length Lc is determined by providing a combustor residence time of about 5 ms to about 10 ms, more or less, as based on equilibrium flame temperature predictions sufficient for CO oxidation to CO 2 to leave only a environmentally acceptable CO quantity in the high energy hot exhaust gases.
  • the hot exhaust gases (products of combustion) 156 directly after discharge from the combustion chamber 72 flow through the ramjet outlet nozzle 124, and thence along the outlet strake 62, and are directed, preferably at low pressure but still containing axial and tangential swirl kinetic energy to exhaust gas blade portions 157 in an impulse turbine 158, for extraction of the kinetic energy based on the overall swirl energy inherent in such hot exhaust gases 156.
  • the hot exhaust gases 156 may be further utilized by being directed to an exhaust heat exchanger 160 to heat condensate 161 and produce steam 162.
  • FIGS. 7 the hot exhaust gases (products of combustion) 156
  • the steam 162 may be directed through high-pressure steam supply ports 164 and thence through inlet vanes (nozzles) 166, preferably fixed in orientation, and thence into the steam blade 168 portions of compound impulse turbine blades 158'.
  • the compound impulse turbine blades 158' have two distinct flow regions, an outer blade 168 for receiving steam, and an inner blade 165 for receiving exhaust gas.
  • the outer blade portion 168 is of smaller length, longitudinally in the flow direction, than the inner blade portion 165.
  • the low pressure steam 170 is exhausted from the impulse turbine steam blade portion 168 through low pressure steam chamber 171 via low pressure steam discharge ports 172 and is directed to a condenser 173 (see FIG. 8) and sent via pump 174 to the heat exchanger 160 for replenishment of the supply of high pressure steam 162 to be sent to the high pressure steam supply nozzles 164 mentioned above, for acting on the compound turbine blades 158'.
  • the compound turbine blade 158' has an annular arc platform segment 175 between the steam bucket portion 168 and the hot gas portion 165. The annular arc platform segments 175 on adjacent compound turbine blades 158' cooperate to provide a substantially continuous annular ring, so as to effectively maintain separation of steam and hot gas.
  • a planetary gear system 200 is used for transmission of power from the impulse turbine 158 to a geared spline 202 on shaft portion 204.
  • the impulse turbine 158 is not directly affixed to, and turns at a different speed than, rotor 70. Additionally, it should be noted that in order to minimize aerodynamic drag and efficiently operate the outer portions of the rotor 70 at supersonic tangential velocities, means could be provided to reduce drag of the rotor 70.
  • This can take the form of a fixed housing 208 with a small interior gap G between the rotor surface 210 and an interior 212 of housing 208, or, alternately, take the form of a vacuum means to remove air from adjacent the rotor 70.
  • rotor drag minimizing techniques are taught in U.S. Patent No. 5,372,005, issued December 14, 1994 to Lawlor, the disclosure of which is incorporated herein by this reference. As noted in FIGS.
  • the just described exemplary ramjet engine generator set at the described exemplary operating conditions has a net system efficiency at rated power of at least 32%, and more preferably, of at least 35%, and most preferably, from about 37% to about 39%, when operating using an impulse turbine for recovery of kinetic energy from hot exhaust gases, but without a steam turbine.
  • the net system efficiency at rated power output is preferably at least 35%. More preferably, the net system efficiency at rated power output of such a system configuration is at least 38%, and most preferably, from about 45% to about 46%.

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

Abstract

L'invention concerne un statoréacteur rotatif conçu pour fonctionner avec un composant à très faible flux axial. Le moteur comprend un rotor (70), un arbre (28), une pluralité de brûleurs de statoréacteur montés sur la périphérie du rotor (70). Un ensemble d'onglets hélicoïdaux espacés les uns des autres s'étend à partir de la surface externe du rotor en direction de la paroi intérieure du carter moteur, ménageant un jeu fonctionnel à partir de celui-ci. Un corps central est prévu pour chaque statoréacteur possédant une chambre de combustion (72). Le corps central est disposé de manière parallèle par rapport aux onglets et comprend une structure de bord d'attaque, des parois latérales opposées, une cavité façonnée et une paroi terminale arrière.
PCT/US2002/023186 2001-07-23 2002-07-23 Ensemble de generateur de statoreacteur rotatif et compact WO2003010431A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US91222601A 2001-07-23 2001-07-23
US09/912,226 2001-07-23

Publications (1)

Publication Number Publication Date
WO2003010431A1 true WO2003010431A1 (fr) 2003-02-06

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Application Number Title Priority Date Filing Date
PCT/US2002/023186 WO2003010431A1 (fr) 2001-07-23 2002-07-23 Ensemble de generateur de statoreacteur rotatif et compact

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2833064A3 (fr) * 2013-07-31 2015-07-15 Siemens Aktiengesellschaft Centrale thermique au charbon

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2680950A (en) * 1946-12-18 1954-06-15 Lewis D Burch Direct reaction rotary translation engine
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US3727409A (en) * 1961-03-30 1973-04-17 Garrett Corp Hypersonic aircraft engine and fuel injection system therefor
US3729930A (en) * 1970-06-23 1973-05-01 Rolls Royce Gas turbine engine
US3971209A (en) * 1972-02-09 1976-07-27 Chair Rory Somerset De Gas generators
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
WO1998027330A1 (fr) * 1996-12-16 1998-06-25 Ramgen Power Systems, Inc. Statoreacteur pour la production d'energie

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2680950A (en) * 1946-12-18 1954-06-15 Lewis D Burch Direct reaction rotary translation engine
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US3727409A (en) * 1961-03-30 1973-04-17 Garrett Corp Hypersonic aircraft engine and fuel injection system therefor
US3729930A (en) * 1970-06-23 1973-05-01 Rolls Royce Gas turbine engine
US3971209A (en) * 1972-02-09 1976-07-27 Chair Rory Somerset De Gas generators
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
WO1998027330A1 (fr) * 1996-12-16 1998-06-25 Ramgen Power Systems, Inc. Statoreacteur pour la production d'energie

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2833064A3 (fr) * 2013-07-31 2015-07-15 Siemens Aktiengesellschaft Centrale thermique au charbon

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