WO1995035469A1 - Perfectionnements se rapportant a des dispositifs alimentes par de l'energie solaire - Google Patents

Perfectionnements se rapportant a des dispositifs alimentes par de l'energie solaire Download PDF

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Publication number
WO1995035469A1
WO1995035469A1 PCT/GB1995/001401 GB9501401W WO9535469A1 WO 1995035469 A1 WO1995035469 A1 WO 1995035469A1 GB 9501401 W GB9501401 W GB 9501401W WO 9535469 A1 WO9535469 A1 WO 9535469A1
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WO
WIPO (PCT)
Prior art keywords
heat exchanger
turbine
heat
heat exchange
air
Prior art date
Application number
PCT/GB1995/001401
Other languages
English (en)
Inventor
Paris Misak Herouni
Original Assignee
Solargen Energy Corporation B.V.I.
Gaye, Adrian, Lawrence
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
Family has litigation
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Application filed by Solargen Energy Corporation B.V.I., Gaye, Adrian, Lawrence filed Critical Solargen Energy Corporation B.V.I.
Priority to AU26796/95A priority Critical patent/AU2679695A/en
Publication of WO1995035469A1 publication Critical patent/WO1995035469A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G6/00—Devices for producing mechanical power from solar energy
    • F03G6/06—Devices for producing mechanical power from solar energy with solar energy concentrating means
    • F03G6/064—Devices for producing mechanical power from solar energy with solar energy concentrating means having a gas turbine cycle, i.e. compressor and gas turbine combination
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S20/00—Solar heat collectors specially adapted for particular uses or environments
    • F24S20/20—Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S23/00—Arrangements for concentrating solar-rays for solar heat collectors
    • F24S23/70—Arrangements for concentrating solar-rays for solar heat collectors with reflectors
    • F24S23/72—Arrangements for concentrating solar-rays for solar heat collectors with reflectors with hemispherical reflective surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S30/00—Arrangements for moving or orienting solar heat collector modules
    • F24S30/40—Arrangements for moving or orienting solar heat collector modules for rotary movement
    • F24S30/42—Arrangements for moving or orienting solar heat collector modules for rotary movement with only one rotation axis
    • F24S30/425—Horizontal axis
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/40—Solar thermal energy, e.g. solar towers
    • Y02E10/46—Conversion of thermal power into mechanical power, e.g. Rankine, Stirling or solar thermal engines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/40—Solar thermal energy, e.g. solar towers
    • Y02E10/47—Mountings or tracking

Definitions

  • This invention concerns solar powered devices by which a fluid can be heated by concentrating the energy from the sun incident on the earth's surface so as to produce an intense local heating effect.
  • the rays of energy from the sun can be considered to be substantially parallel at the surface of the earth and with rotation of the earth relative to the sun the angle of incidence of the "parallel" rays will vary for any point on the surface of the earth during the daylight hours.
  • French Patent Specification No. 635283 describes an arrangement in which a generally hemispherical reflecting surface is fixed relative to the surface of the earth and a heat exchanger is located above the hemispherical surface, drive means being provided to move the heat exchanger as the angle at which energy from the sun varies during the daylight hours and during the year.
  • the hemispherical reflecting surface is itself inclined depending on the latitude at which the reflector is located on the surface of the earth.
  • the radiation incident on the heat exchanger heats either water or oil which is pumped through the heat exchanger so as to provide a mechanism for transferring heat from the exchanger to heating coil so as to heat air to drive a turbine H which itself can then rotate another machine such as an alternativeator.
  • the heat exchanger shown in the French Patent Specification No. 635283 suffers from a significant disadvantage in that much of the reflected energy from the sun impinges on the surface of the heat exchanger with only grazing incidence.
  • the heat exchange system described in French Patent Specification No. 635283 suffers from the disadvantge that the air supply to the turbine H cannot be raised to a temperature greater than the temperature of the fluid medium circulating in the heat exchanger.
  • the fluids described are liquids such as water or oil.
  • the temperature of the air supplied to the driven turbine H should be considerably higher than is achievable using water or oil as the heat transfer medium if useful turbine efficiency is to be achieved.
  • a system for use with a solar energy collecting device adapted to concentrate solar energy to heat gases in a heat exchange means comprises a gas turbine having an air inlet, a compressor, an expansion chamber, and at least one turbine rotatable by expanding gases leaving the expansion chamber, wherein the expansion chamber is replaced at least in part by the heat exchange means, so that the compressed air from the compressor is supplied to the heat exchange means and the heated air from the heat exchanger means is supplied to the inlet to the turbine.
  • the heat exchange means preferably raises the temperature of the compressed air to in excess of 800°C.
  • the heat exchange means may comprise first and second heat exchangers, one heated by solar energy and a second heat exchanger beyond the turbine to recover latent heat in the air leaving the turbine.
  • the second heat exchanger may serve to heat air from the compressor before it is supplied to the inlet of the solar energy heated exchanger.
  • the second heat exchanger therefore comprises a pre-heater for the air.
  • the turbine and generating set are conveniently mounted at the upper end of an arm which is movable in altitude and rotation at the upper end of a fixed column, and at least part of the heat exchange means is arranged at the lower end of the arm.
  • a method of driving an electrical machine such as a generating set comprises:
  • the heat exchange means preferably comprises an upright stem and an upper member having a concavely curved downwardly facing underside arranged symmetrically above the stem, each of said stem and said upper member having fluid passage means associated therewith through which fluid can pass, the outer surface of the stem and the underside of the upper member serving as heat energy collecting surfaces which are thermally coupled to the fluid passage means so as to comprise heat exchange means, in which the heat exchange means of the upper member forms the main heat energy collecting part of the device, and the collecting device focusses solar energy onto the stem and/or the concavely curved downwardly facing underside.
  • the downwardly facing upper member is typically supported by two or more generally radially directed spokes having minimal thickness so as to cast minimal shadow on the underside of the said upper member.
  • the upright stem may extend upwardly to the centre of the concavely curved surface, but in a preferred arrangement, the stem only extends up to the point where the spokes radiate outwardly, so that there is minimal obstruction to cast a shadow.
  • Fluid flow is typically via a first passage to the upper end of the central strut, a co-axial downfeed from the top of the strut to the bottom thereof internally of the strut, an annular return passage between the co-axial downfeed and the wall of the strut through which fluid can rise, one or more passages through the spokes between the upper end of the strut and the lower outer edge of the downwardly facing upper member through which fluid can pass to the outermost and lowermost regions of the concavely curved surface thereof, and one or more fluid paths within the said member thermally coupled to the said surface to enable the fluid to flow to one or more upper outlets from which heated fluid can pass.
  • the mixture of gases is preferably air.
  • the fluid passage through the downwardly facing member follows a generally tortuous path so as to increase the dwell time of the fluid therewithin, so as to increase the time that the fluid is exposed to solar energy reflected from the reflector onto the concavely curved surface.
  • the tortuous path may for example comprise one or more spiral passages .
  • a separate spiral path may be started from the outermost end of each of the said spokes and the different spiral paths may be intertwined in the form of a multistart thread.
  • a device as aforesaid is preferably used with a part- spherical reflector for heating air to drive a turbine.
  • the curved surface on the underside of the upper member is preferably positioned so as to be post focal to the reflector surface.
  • the curved surface must have sufficient depth and its profile or shape can be predicted using equations which use as their starting point the condition of perpendicularity of all rays reflected off the reflector surface to the heat exchanger at any point.
  • equation (1) The above will be referred to as equation (1).
  • equation (1) if 1 is greater than 0.5, the surface is preefocal.
  • the geometrical surface containing all the possible local focal points is sometimes referred to as the caustic surface.
  • the caustic curve must not be crossed by the heat exchanger because the edge of the heat exchanger will then create a shadow on part of the surface of revolution of the caustic curve.
  • the heat exchange means within the stem and the heat exchange means within the upper member may be connected in series so as to heat the same fluid or they may operate quite independently, the one heating one fluid and the other heating another fluid.
  • the effective aperture of the part-spherical reflecting surface is increased if the first elongate heat exchanger in the stem is used to preheat the fluid before it passes to the upper member.
  • the surface of the elongate unit may be profiled so as to provide trunkated conical surfaces having different inclined angles at different positions along the length of the stem so that energy reflected by the reflector towards the stem will be incident more or less normally on the various regions of the surface thereof. This is of distinct advantage since the reflectivity from a surface is usually least when the angle of incidence is near normal to the surface.
  • heat exchange means requires reinforcing ribs to increase rigidity or fins to increase the surface area, these ribs and/or fins should be inside the unit.
  • the gases preferably may pass first through the elongate unit and then through the second unit.
  • Figure 1 illustrates how parallel rays of energy incident on a part spherical surface will be reflected
  • Figure 2 illustrates the coordinates of the point of crossing of the main heat exchanger with caustic curves
  • Figure 3 further illustrates the reflection of energy from a spherical surface
  • Figure 4 shows a basic form of construction of a composite heat exchanger to collect more energy than would be collected by a single heat exchanger
  • Figure 5 illustrates the parameters associated with the design of Figure 4.
  • Figure 6 illustrates a preferred form of construction for the outside surface of the lower linear heat exchange element of Figure 4.
  • Figure 7 shows the fluid flow through the elongate supplementary heat exchanger
  • Figure 8 shows how the exit pipe can leave the upper end of the heat exchanger of Figure 7;
  • Figure 9 is a diagrammatic representation of a composite heat exchanger for use with a spherical surface mirror
  • Figure 10 is a plan view from below of the exchanger unit of Figure 9;
  • Figure 11 shows an alternative form of construction of the tortuous path through the main heat exchanger between the inner and outer surfaces
  • Figure 12 shows how the outside diameter of the main unit of Figure 9 can be reduced
  • FIGS 13, 14 and 15 illustrate the theory behind the development of the main exchanger
  • Figures 16 and 17 illustrate the theory behind the development of the supplementary or additional heat exchanger
  • Figure 18 is a theoretical illustration of a part spherical reflector surface set to receive radiation from the sun for heating a heat exchanger (not shown) in accordance with the invention
  • Figure 19 is a diagrammatic constructional drawing showing one embodiment of reflector and heat exchanger and mounting assembly.
  • Figure 20 illustrates alternative detail of the upper end of the tower and illustrates how the swinging heat exchanger and rotating machine assembly can be mounted for movement about two axes.
  • Figure 21 is a flow diagram showing how compressed air can be passed to the auxiliary and main heat exchangers before being applied to the entry side of a turbine for driving an electric generating set, in accordance with the invention.
  • the solar energy station shown in the drawings has a fixed spherical concentrator (mirror) 10 using air as the agent of energy transfer.
  • the unit is intended to have low capital and operating costs for the widest usage. Production of models producing electricity of a few kW to multiples of 10MW is envisaged.
  • the Main Heat Exchanger 12 heat exchanger selected is of the post-focal type, concave to the mirror.
  • the profile (shape) of the working-surface of the heat exchanger (12) is dictated by equations, worked out using the condition of perpendicularity of all rays reflected off the spherical mirror surface to the heat exchanger (12) at any point.
  • Gases heated by the two heat exchangers 12 and 14 can be used to drive a high temperature air turbine with integral preliminary compressor, gas turbine engine used in helicopters and aircraft. In fact, it is only necessary to remove the combustion chamber and introduce air ducts, in order to modify such an engine.
  • a preferred gas turbine engine this project comprises the type GTE-350 as used in the M12 helicopter. Such an engine will work at half-power in the present system, which will extend its life and result in considerable noise reduction. Unfortunately it also decreases the turbine's efficiency. All low-power GTEs have low efficiency (approx 10%). It is, however, possibe to double the efficiency by use of a 'regenerative' heat exchanger. Powerful GTEs (1 to 20 MW) have an efficiency of up to 40%.
  • GTE-350 The main parameters of GTE-350 to be taken into account in this instance are:
  • R 0.777 is selected to ensure the optimal length of the additional heat exchanger. Its length can extend to the mirror surface (in which case the entire hemisphere will be used). But this is not optimal either in regard to construction or cost. Having such a length, there would be problems of movement, requirement for major construction and rotation mechanisms - resulting in high costs and creating large shadows on the mirror. At the same time, in order to make use of the edges of the hemisphere, it would be necessary to construct a mirror having almost ten times the surface area.
  • the selected value of R 0.777 ensures reception of the required power and relatively reduced length of the additional heat exchanger.
  • the main parameters of the additional heat exchanger are shown in Table I.
  • the degree of solar energy concentration on the surface and the surface temperature of the additional heat exchanger depends greatly on its diameter 2r.
  • the additional heat exchanger does not cast a shadow on the mirror (because it is positioned in the shadow of the main heat exchanger), nor on the main heat exchanger. It is important that the latter is achieved.
  • the additional heat exchanger does not cast a shadow with its upper edge for ray 0.1 directed to the top of the main heat exchanger (See Figure 5).
  • the cylindrical heat exchanger requires in fact the highest degree of accuracy in design of the mirror surface.
  • the heat exchangers have to ensure the heating of the 1.5kg/sec air flow up to the required temperature required for at the input to the selected turbine. Typically this temperature should be not less than 810°C. At the same time, there must not be any substantial loss of pressure due to friction within the heat exchangers. The required pressure at the turbine input is approximately 3 atmospheres.
  • Equation (1) describes the profile of the main heat exchanger.
  • Version 1 K is the ratio between the surface o of the elementary ring in the aperture plane of the mirror and the surface m of the corresponding elementary ring on the surface of the main Heat exchanger. m ra
  • Figure 10 also shows the theoretical curve of temperature distribution along the shape of the main heat exchanger, supposing that there is no flow of air and that it achieves a heat balance between absorption and transmission of energy (ie that the material of the heat exchanger surface is absolute black body) .
  • the temperature of heating ( t m ° C) can be calculated by the formula :
  • K V (here K ms ) is the ratio between the surface of mirror aperture (less the shadow surface from the main heat exchanger) and the corresponding surface of cross section of the main heat exchanger.
  • K ms K ms
  • the broken curve indicates the distribution of K along the shape of the main heat exchanger .
  • Figure 10 also shows the (broken) curve t ms °C of temperature distribution along the hypothetical discs in the cross sections of the main heat exchanger which are in heat balance (absorption- transmission) without flow of air.
  • This curve is only theoretical, just giving an impression of the physics of the main heat exchanger.
  • the curve has the same character as the curve K ms , P ms . It is calculated by formula (8).
  • the total used surface is therefore equal to 673m 2 .
  • the additional heat exchanger receives energy from about 56% of additional surface to the surface used by the main heat exchanger and 36% of the total used surface of the mirror aperture. This is a major increase.
  • the coefficient of concentration K a on the surface of the additional heat exchanger is the ratio between the surface of the elementary ring in the plane of the mirror aperture ( - and the surface of the corresponding elementary cylinder on the surface of the additional heat exchanger
  • Figure 13 shows the graph of distribution of K a (and P a ) dependant on the distance 2 a along the axis of the additional heat exchanger for two different diameters (2r) of the cylinder.
  • Figure 13 also shows the curves of distribution of temperatures (t a °C) along the length of the additional heat exchanger, which is calculated by formula (8) on the supposition that there is no air flow in the heat exchanger and, on its surface (considered to be absolute black body), there is a balance between absorbed and transmitted energy.
  • the main axis of the mirror has to decline from the vertical by 40° to the South, so as to lie in the equator plane.
  • the sun changes position from this direction by ⁇ 23°30'.
  • Figure 14 illustrates the mirror in the local meridian plane.
  • Figure 15 illustrates the cross section of the mirror in the equator plane. If, in this plane, we make the same reduction based on the Sin 16° factor, then with the full aperture angle
  • the mirror will work for ⁇ 24°, ie 11 ⁇ 2 hours each side of midday .
  • the used surface decreases by approximately a further 10% since some of the rays beyond ⁇ 51° will be screened by the edge of the mirror.
  • the full surface of the built mirror area (curved) is equal to:
  • Figure 18 illustrates the geodesic map of the chosen site.
  • the average coefficient of concentration for the main heat exchanger K aa is given by:
  • the average coefficient of concentration for the additional heat exchanger K aa is:
  • the mirror may be constructed from a large number of separate pieces with dimensions of 0.3m x 0.3m. Nine or twelve such pieces can be considered to make up one standard panel .
  • the panels are set on the supporting structure with provision to adjust their inclination.
  • the reflecting pieces are made from polished metal (aluminium) or glass (typically of 5mm thickness) with the reverse side made reflective by a film of aluminium or silver together with a protective coating.
  • the coeficient of reflection should be close to 0.9.
  • the supporting structure, tower and swinging arm are made from welded steel frames. Typicaly the control equipment is housed within this structure.
  • Figure 17 illustrates the arm in two extreme positions.
  • the down position permits direct access from the tower to the heat exchangers, turbine and other equipment housed inside the arm.
  • the mounting system is of "azimuth - elevation” type (see Figure 17).
  • An automatic control system is included to target and track the sun. (Tracking is also achieved by photo-guide).
  • the control equipment is preferably be programmed to rapidly remove the heat exchanger from the focal point of the mirror in the event that the incoming flow of air to the heat exchanger fails.
  • the control system desks may be housed in one area and electrical transformers and high voltage equipment may be housed in a separate area.
  • a pipework system conveys water around the upper perimeter of the mirror. Using warm water, it is also possible to clean away snow. Snow- removal is not a major problem because, during winter, it tends to be the more vertical parts of the mirror which are used to reflect the solar energy onto the heat exchangers.
  • Figure 21 shows how compressed air from a compressor (100) is fed via a preheater regenerative heat exchanger (102) to the central downfeed (104) the lower (additional) heat exchanger (106) of a composite heat exchanger such as is described with reference to Figures 1 to 16.
  • the heated air returns via the outer passage (108) in the lower exchanger (106) to the lower end of a tortuous (typically spiral) passage through the main heat exchanger (110). At the upper end of the latter the air temperature is at its maximum.
  • Typical temperatures achieved throughout the heating phase are shown in Figure 21.
  • the temperature of the air entering the compressor is shown at ambient (ie 15°C).
  • the temperature is typically 133°C.
  • the regenertive heat exchanger will only come into play after the system has been operating for a short time, but in the steady state conduction a temperature rise of approximately 300°C can be expected so that when the air enters exchanger (104), it is at 430°C.
  • a typical transfer temperature of 560°C will be obtained between (104) and (110) giving a final temperature of 810°C at (112).
  • the pressure of the air entering the turbine is typically at 3 atmospheres.
  • the temperature drop across the turbine (112) is of the order of 300°C so that a typical exhaust temperature (pre (102)) will be 533°C, and the cooling effect of the heat exchanger (102) will reduce the final exhaust temperature to approximately 200°C.
  • An electrical generator (typically an alternator) (114) is mounted on a common shaft (116) on which the compressor (100) and turbine (112) are also mounted.
  • a starter motor (119) is also attachable to or mounted on the same shaft (116).
  • a power supply (not shown) for the motor (118) may take the form of a battery and charging circuit which operates from the generator output.
  • a chamber between the compressor (100) and the turbine (112) is supplied with combustible fuel (either liquid fuel in aerosol form or gas) which is burnt in the chamber to heat the compressed air from the compressor (100) to temperatures of the order of 800°C or above, so as to drive the turbine (112) and rotate the shaft (116).
  • combustible fuel either liquid fuel in aerosol form or gas
  • a supplementary gas burner (not shown) may be employed at such times to heat the airstream entering (112) to the required temperature, so as to keep the shaft running at the design speed.
  • a gas control valve and temperature and load/speed detectors can be used to control gas to the burner (s).
  • liquid fuel such as petroleum based fuels, or even solid fuel, may be used in an appropriate burner.
  • a preferred turbine for the prototype system shown in the drawings is a helicopter gas turbine type 350 as developed for use in the type MI2 helicopter. In the prototype system this turbine will in fact be operating at half power which will not only extend its useful life but also result in considerable reduction in noise.
  • Low powered gas turbine engines typically have an efficiency of 10% but by using the regenerative heat exchanger to recover exhaust gas heat, this can be doubled to approximately 20%
  • More powerful gas turbine engines can have such high latent efficiencies of the order of 40%.
  • An ex aircraft (helicopter) gas turbine engine can be readily modified to enable its use in the system described, by removing the combustion chamber and introducing air ducts to and from the heat exchangers.
  • the shaft (116) is preferably in line and coaxial with the axis of the heat exchanger limits (104/110), and is mounted within the pivoting arm of the unit shown in Figure 19, with the heat exchangers (104/110) at the lower end thereof.
  • the turbine/generating set may be mounted at the upper end of the arm or midway. This only entails flexible electrical power leads to the arm.

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  • Life Sciences & Earth Sciences (AREA)
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  • Combustion & Propulsion (AREA)
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Abstract

Système de conversion d'énergie destiné à convertir de l'énergie solaire en énergie rotationnelle, comprenant un dispositif collecteur d'énergie solaire conçu pour concentrer cette énergie afin de chauffer des gaz dans des moyens (102-110) échangeurs de chaleur, une turbine à gaz comportant une entrée (116) d'air, un compresseur (100), une chambre d'expansion, ainsi qu'au moins une turbine (112) entraînée par les gaz d'expansion quittant la chambre d'expansion, laquelle est formée au moins en partie par les moyens (110) échangeurs de chaleur, l'air comprimé provenant du compresseur (100) étant fourni aux moyens (102-110) échangeurs de chaleur et l'air chauffé provenant de ces moyens étant fourni à l'orifice d'entrée de la turbine (112). Les moyens échangeurs de chaleur élèvent la température de l'air comprimé à plus de 800 °C, et ils peuvent comprendre un premier (104-108) ainsi qu'un second (102) échangeur de chaleur, le premier (104-108) étant chauffé par l'énergie solaire, et le second (102), situé au-delà de la turbine, étant destiné à récupérer la chaleur latente de l'air quittant la turbine (112). Le second échangeur (102) de chaleur sert à chauffer l'air provenant du compresseur (100) avant que cet air ne soit introduit dans l'orifice d'entrée de l'échangeur (104) chauffé à l'énergie solaire, le second échangeur (102) comprenant, par conséquent, un dispositif de préchauffage de l'air. On peut monter la turbine sur l'extrémité supérieure d'un bras lui-même fixé sur l'extrémité supérieure d'une colonne fixe, aux fins de rotation et de réglage de l'inclinaison de l'un par rapport à l'autre. La turbine peut être conçue pour entraîner une machine génératrice d'électricité.
PCT/GB1995/001401 1994-06-18 1995-06-15 Perfectionnements se rapportant a des dispositifs alimentes par de l'energie solaire WO1995035469A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU26796/95A AU2679695A (en) 1994-06-18 1995-06-15 Improvements in and relating to solar energy powered devices

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Application Number Priority Date Filing Date Title
GB9412260A GB9412260D0 (en) 1994-06-18 1994-06-18 Improvements in and relating to solar energy powered devices
GB9412260.3 1994-06-18

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100467974C (zh) * 2006-08-31 2009-03-11 张耀红 太阳能集热发电装置
US9726155B2 (en) 2010-09-16 2017-08-08 Wilson Solarpower Corporation Concentrated solar power generation using solar receivers
US10876521B2 (en) 2012-03-21 2020-12-29 247Solar Inc. Multi-thermal storage unit systems, fluid flow control devices, and low pressure solar receivers for solar power systems, and related components and uses thereof
FR3098573A1 (fr) * 2019-07-13 2021-01-15 Roland Garré Propulseur pour aéronef utilisant l‘énergie solaire.

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR635283A (fr) * 1927-03-31 1928-03-12 Machine solaire à air atmosphérique
FR2365085A1 (fr) * 1976-09-20 1978-04-14 Anvar Capteur d'energie solaire a miroir spherique fixe
US4173968A (en) * 1976-05-17 1979-11-13 Steward Willis G Receiver for solar energy
FR2436946A2 (fr) * 1978-09-22 1980-04-18 Anvar Capteur d'energie solaire a miroir spherique fixe
US4217147A (en) * 1976-06-02 1980-08-12 Georg Ziemba Facility for generating technically useable energy by conversion of solar energy
GB2060860A (en) * 1979-09-17 1981-05-07 Kraftwerk Union Ag Solar power installation
US4280327A (en) * 1979-04-30 1981-07-28 The Garrett Corporation Solar powered turbine system
US4403601A (en) * 1979-07-26 1983-09-13 Hunt Arlon J Radiation receiver
US4509333A (en) * 1983-04-15 1985-04-09 Sanders Associates, Inc. Brayton engine burner
CH654627A5 (en) * 1981-06-23 1986-02-28 Bertrand Reymont Solar power plant

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR635283A (fr) * 1927-03-31 1928-03-12 Machine solaire à air atmosphérique
US4173968A (en) * 1976-05-17 1979-11-13 Steward Willis G Receiver for solar energy
US4217147A (en) * 1976-06-02 1980-08-12 Georg Ziemba Facility for generating technically useable energy by conversion of solar energy
FR2365085A1 (fr) * 1976-09-20 1978-04-14 Anvar Capteur d'energie solaire a miroir spherique fixe
FR2436946A2 (fr) * 1978-09-22 1980-04-18 Anvar Capteur d'energie solaire a miroir spherique fixe
US4280327A (en) * 1979-04-30 1981-07-28 The Garrett Corporation Solar powered turbine system
US4403601A (en) * 1979-07-26 1983-09-13 Hunt Arlon J Radiation receiver
GB2060860A (en) * 1979-09-17 1981-05-07 Kraftwerk Union Ag Solar power installation
CH654627A5 (en) * 1981-06-23 1986-02-28 Bertrand Reymont Solar power plant
US4509333A (en) * 1983-04-15 1985-04-09 Sanders Associates, Inc. Brayton engine burner

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100467974C (zh) * 2006-08-31 2009-03-11 张耀红 太阳能集热发电装置
US9726155B2 (en) 2010-09-16 2017-08-08 Wilson Solarpower Corporation Concentrated solar power generation using solar receivers
US10280903B2 (en) 2010-09-16 2019-05-07 Wilson 247Solar, Inc. Concentrated solar power generation using solar receivers
US11242843B2 (en) 2010-09-16 2022-02-08 247Solar Inc. Concentrated solar power generation using solar receivers
US10876521B2 (en) 2012-03-21 2020-12-29 247Solar Inc. Multi-thermal storage unit systems, fluid flow control devices, and low pressure solar receivers for solar power systems, and related components and uses thereof
FR3098573A1 (fr) * 2019-07-13 2021-01-15 Roland Garré Propulseur pour aéronef utilisant l‘énergie solaire.

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AU2679695A (en) 1996-01-15

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