Classifications

• • 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
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
  • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
• • 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
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
• • 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
  • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
  • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
  • F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
  • F28D7/0058—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for only one medium being tubes having different orientations to each other or crossing the conduit for the other heat exchange medium
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
  • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
  • F28D7/10—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
  • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
  • F28F13/12—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by creating turbulence, e.g. by stirring, by increasing the force of circulation
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F28—HEAT EXCHANGE IN GENERAL
  • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
  • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
  • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
  • F28F3/022—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being wires or pins
• • 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
  • F05D2250/80—Size or power range of the machines
  • F05D2250/82—Micromachines

Definitions

• the invention relates to a micro gas turbine plant with an annular recuperator for heat transfer from an exhaust gas stream to an air stream.
• Micro gas turbine plants usually comprise the following components:
• Micro gas turbine plants are often only two to three meters long, one to two meters wide and one to two meters high.
• Micro-gas turbine plants are used for a decentralized power supply, with the generated electrical power being less than 250 kW.
• the waste heat is often used for heating purposes, such as buildings.
• Micro-gas turbine plants are usually single-shaft machines in which the generator, compressor and turbine are arranged on a shaft.
• micro-gas turbine plants air is sucked in from the compressor and compressed.
• the air is preheated in the annular recuperator and fed to the combustion chamber.
• burners are arranged, which burn a fuel gas with the preheated air.
• the turbine of the micro gas turbine system is driven by the hot exhaust gases from the combustion chamber.
• annular recuperator is usually formed as a hollow cylinder and encloses a portion of the components.
• Recuperators are heat exchangers in which heat is transferred from a warmer fluid stream to a colder fluid stream spatially separate therefrom, the two fluids not being mixed together.
• recuperators of micro-gas turbine plants the combustion air is preheated by the hot exhaust gases of the turbine.
• WO 02/39045 A2 describes a micro gas turbine plant with an annular recuperator.
• the hot exhaust gas flow of the turbine flows through axial inlets into the recuperator and on the opposite side via axial inlets from the recuperator.
• This has a negative effect on the efficiency of the micro gas turbine plant.
• the management of the exhaust gas flow important structural features of the micro gas turbine plant.
• WO 02/39045 A2 a micro-gas turbine plant is described in which the recuperator is permanently installed in a housing and can not be replaced without much effort.
• the object of the invention is to provide a micro-gas turbine plant with an annular recuperator, in which the heat transfer between the exhaust stream and the air stream is optimized. This should contribute to an increase in efficiency.
• the individual components should be easily accessible for maintenance work.
• the micro-gas turbine plant should be easy to install and inexpensive to manufacture. Also a reliable operation should be guaranteed.
• This object is achieved in that the exhaust gas flow flows through radial inlets into the recuperator and / or flows through radial outlets from the recuperator.
• the terms axial and radial are directions that refer to a rotation axis as a reference system. This axis of rotation is formed by the shaft in micro gas turbine plants.
• the exhaust gas flow via radial inlets into the recuperator and via radial outlets from the recuperator.
• the supply and removal of the exhaust gas flow is thus not via axial but via radial inlets and outlets.
• the newly designed micro gas turbine plant is easy to assemble and thus inexpensive to manufacture. By this exhaust gas duct good heat transfer and a higher efficiency of the micro gas turbine plant can be achieved.
• the annular recuperator preferably has a hollow cylindrical geometry. It extends in the axial direction and encloses other components of the micro gas turbine plant. In particular, it proves to be advantageous if the recuperator at least partially surrounds the combustion chamber, preferably completely surrounds it. In particular, this is an annular combustion chamber.
• the radial inlets and the radial outlets are arranged on mutually axially opposite sides of the recuperator. In this way, the exhaust gas flow first flows through the entire recuperator in the axial direction before it leaves again. Due to the higher residence time, the heat exchange between the two fluid streams is improved.
• the recuperator has an inner and / or outer lateral surface.
• they are self-contained cylindrical lateral surfaces. It proves to be advantageous if these consist of a metal or an alloy.
• the inner circumferential surface is preferably arranged axially centered in the outer circumferential surface.
• the inner lateral surface and / or the outer lateral surface have openings which form radial inlets and / or radial outlets for the exhaust gas flow.
• openings which form radial inlets and / or radial outlets for the exhaust gas flow.
• slot-shaped and / or circular openings are introduced into the otherwise closed cylindrical lateral surfaces, for example by punching, drilling or milling.
• the inner lateral surface and / or the outer lateral surface are formed in a preferred variant of the invention from a bent metal strip, preferably a sheet metal strip.
• the cylindrical lateral surfaces form an inner or outer band.
• the metal strip is bent to form a cylindrical surface that surrounds a cylindrical space. At the edges, where the curved metal strip meets, this is preferably welded together.
• Radial inlet openings and / or radial outlet openings for the exhaust gas flow can be introduced into the metal strips. Preferably, the openings are punched.
• the production of such an inner and outer lateral surface is particularly cost-effective.
• Such formed from metallic strips lateral surfaces are characterized by a low weight.
• annular combustion chamber is arranged in the cylindrical space, which encloses the inner circumferential surface. Axially in this space preferably runs a flow space for the exhaust gases leaving the turbine.
• the inner circumferential surface extends over the entire length of the recuperator.
• openings are introduced, which form radial inlets for the exhaust gas flow of the turbine.
• the openings can be milled, for example.
• the openings can be stamped, this method is particularly suitable for a production of the lateral surface of a metal strip.
• the outer lateral surface extends in the axial direction only to an exhaust gas collector. As a result, no outlet openings for the exhaust gas flow must be introduced, but the exhaust gas, after flowing through the recuperator, enters the annular exhaust gas collector which surrounds the recuperator.
• the inner lateral surface and / or the outer lateral surface can also be formed from a tube with a slightly greater wall thickness, wherein the inner tube is preferably arranged axially centered in the outer tube.
• openings are provided in the inner tube which form the radial inlets for the exhaust gas flow.
• the openings may be formed in particular as slots.
• openings can be introduced, which form the radial outlets for the exhaust gas flow. These openings are preferably also formed as slots.
• the two fluid streams flow in the recuperator at least partially in countercurrent to each other.
• the average temperature difference between the two fluid streams is greater, so that the transmitted heat output increases in comparison to cross or DC flow.
• the air flow flows in via axial inlets and / or out via axial outlets.
• the air flow enters an end face of the hollow cylindrical recuperator and leaves the recuperator on the opposite end face.
• the combustion air stream is preheated in the recuperator before it is fed to the combustion chamber.
• the combustion air is previously compressed by the compressor and thus is under pressure when flowing through the recuperator.
• passages for the hot exhaust gas flow and passages for the air flow are arranged adjacent to each other. In each case, a passage for the exhaust gas flow and a passage for the air flow alternates.
• Adjacent passages are separated by at least one wall.
• the wall may be, for example, a thin metallic sheet.
• the passages are divided into channels which extend in the axial direction and are arranged along the circumference of the annular recuperator.
• a channel for the exhaust gas flow and a channel for the air flow alternate along the circumference.
• the channels extend over the entire axial length of the recuperator.
• the walls extend between an inner lateral surface and an outer lateral surface of the recuperator.
• the walls Preferably, the walls have a curved course, so that evolvent shaped channels form.
• the walls are aligned parallel to one another and arranged along the circumference of the annular recuperator.
• FIG. 2 is a perspective view of the lateral surfaces of the recuperator from the perspective of the air inlet side
• 3 is a perspective view of the lateral surfaces of the recuperator from the perspective of the air outlet side
• 4 is an enlarged view of alternately arranged exhaust gas and air passages
• FIG. 5 shows a shingle with an alternative variant of the closure of the passages, a as an axial front view
• Fig. 1 shows a micro gas turbine plant 1.
• the micro gas turbine plant is in the embodiment 1, 6 m long, 1, 7 m wide, has a diameter of 0.7 m and an electrical power of 100 kW.
• the micro gas turbine plant 1 comprises a turbine 2, which drives a shaft 3.
• a compressor 4 and a rotor 5 are arranged on the shaft 3.
• the compressor 4 is a single-stage centrifugal compressor.
• As turbine 2 a single-stage radial turbine is used.
• the rotor 5 is surrounded by a stator 6.
• Rotor 5 and stator 6 are components of a generator 7, which is used to generate electricity.
• the combustion chamber 10 includes burner 1 1 in which a fuel gas is burned with the preheated air to an exhaust gas. The fuel gas is passed via feeders 12 to the burners 1 1.
• the exhaust gas flows over the turbine 2 and drives it.
• the expanded exhaust gas stream 13 flows radially into the recuperator 9, flows through the recuperator 9 in the axial direction and flows radially out of the recuperator 9.
• the exhaust gas stream 13 releases heat to the air stream 8.
• the cooled exhaust gas stream 13 flows into an annular exhaust gas collector 14 and leaves the micro gas turbine system 1 through an exhaust gas shaft 15.
• the recuperator 9 encloses the combustion chamber 10.
• Fig. 2 shows a perspective view of the lateral surfaces 16, 17 of a recuperator 9 from the viewpoint of the air inlet side.
• the lateral surfaces 16, 17 are formed by two tubes.
• the inner circumferential surface 16 has openings at one end.
• the openings are designed as longitudinal slots extending in the axial direction.
• the openings form radial inner inlets 18 for the exhaust gas flow 13.
• the outer circumferential surface 17 also has openings.
• the openings are designed as longitudinal slots extending in the axial direction.
• the openings form radial outer outlets 19 for the exhaust gas stream 13.
• the recuperator 9 has passages 20 for the exhaust gas flow 13 and passages 21 for the air flow 8.
• the passages 20, 21 are arranged alternately to one another along the circumference of the annular recuperator 9. Passages 20, 21 fill the entire space between inner circumferential surface 16 and outer circumferential surface 17 of recuperator 9. In FIGS. 2 and 3, only three of these passages 20, 21 are shown by way of example.
• the passages 20, 21 extend in an axial direction over the entire length of the lateral surfaces 16.
• the passages 20, 21 are spatially from each other through Walls 22 separated, so that no mixing between the air stream 8 and the exhaust gas stream 13 occurs.
• the walls 22 have a curved course and form involutes which extend between the inner lateral surface 16 and the outer lateral surface 17.
• the walls 22 are arranged parallel to each other.
• All walls 15 are metallic foils.
• the foils consist of a steel, preferably X6CrNiTi 18-10. They have a thickness of 0.125 mm.
• the passages 20 for the exhaust gas stream 13 are closed at the end faces of the recuperator 9 of cover 23.
• the cover elements 23 are sheets which also have a curved course.
• the passages 21 for the air flow 8 are open at the end faces of the recuperator 9. 2, the air flow 8 enters the recuperator 9 through axial inlets 24, flows through the passages 21 in the axial direction and leaves the recuperator 9 through axial outlets 25 (shown in FIG. 3) the opposite end face of the recuperator. 9
• the hot exhaust gas stream 13 passes through the radial inner inlets 18 into the passages 20, flows through them in the axial direction and leaves the passages 20 through the radial outer outlets 19.
• the exhaust gas stream 13 emerging from the radial outer outlets 19 flows into the annular exhaust gas collector 14 (FIGS. 1) and leaves the micro gas turbine plant 1 through the exhaust shaft 15th
• FIG. 3 shows a perspective view of the lateral surfaces 16, 17 of the recuperator 9 from the perspective of the air outlet side.
• the air flow 8 leaves the passages 21 via the axial outlets 25.
• the air flow 8 and the exhaust gas flow 13 at least partially flow in countercurrent to one another.
• the radial inner inlets 18 and the radial outer outlets 19 are arranged on mutually axially opposite sides of the recuperator 9.
• FIG. 4 shows a section of the annular recuperator with passages 20 for the exhaust gas stream 13 and passages 21 for the air stream 8. In FIG. 4, for the sake of clarity, only four passages 20, 21 are shown by way of example.
• the passages are arranged alternately to each other. They fill the entire space of the recuperator between the inner circumferential surface 16 and the outer lateral surface 17.
• the inner jacket surface 16 is formed by an inner tube and the outer jacket surface 17 by an outer tube.
• fillings 26 are arranged in each passage 20 for the hot exhaust gas flow 13 and in each passage for the air flow.
• the fillings 26 for the hot exhaust gas stream are covered by covers 27 and are thus not visible in the illustration of FIG. 4.
• the covers 27 close the passages 20 of the exhaust gas stream 13 at the front and rear end faces of the recuperator.
• the covers 27 also have a curved course and are welded to the walls 22.
• the fillings 26 consist of a wire arrangement.
• This wire arrangement is designed as a wire mesh, in which wires 28, which extend in the radial direction, are alternately guided over and under wires 29, which extend in the axial direction.
• the outer tube has grooves 30 which extend on its inner side in the axial direction.
• the inner tube has grooves 31 which extend on its outer side in the axial direction.
• FIGS 5 a and 5 b show a shingle of the recuperator 9.
• a shingle is a structural unit of the recuperator 9.
• the recuperator 9 is preferably constructed from a plurality of shingles, preferably more than one hundred and twenty, in particular more than one hundred and fifty shingles. In the exemplary embodiment, the recuperator 9 is constructed from one hundred and eighty five shingles.
• Figures 5 a and 5 b show an alternative structure of such a shingle.
• walls 22 covers 27 are welded.
• first covers 27 are welded axially forward and axially behind the exhaust side of walls 22.
• a strip 32 is inserted radially in each case between two walls 22 radially on the outside and a strip 33 on the inside.
• covers 27 also strips can be used, which preferably have a rectangular or square profile, so that the covers 27 are formed as elongated cuboid metallic body, which are preferably placed on a longitudinal side on a wall 22 and welded thereto.
• FIGS. 6 a and 6 b show a cassette.
• the illustration shows only an exemplary number of shingles.
• the figures show shingles without a curved course.
• a cassette is a module of the recuperator 9. These cassettes are compact units from which the recuperator 9 can be composed.
• the recuperator 9 consists of more than five such modules and less than ten such modules.
• Each module preferably comprises more than ten and fewer than forty shingles, more preferably more than fifteen and fewer than thirty-five shingles.
• a comb 34 serves for fixing and / or connection of the individual elements.
• the metallic comb 34 is welded to adjacent elements.
• a plurality of covers 27 can be used, the connected to each other.
• adjacent covers are welded together.
• recuperator 9 For the manufacture of the recuperator 9, it proves to be advantageous if initially welded to two walls 22 covers 27. Then the two walls 22 are aligned with their covers 27 to each other. At the point where adjacent covers 27 meet, they are welded together. In this case, a weld 36, which extends between the two covers 27 forms. The weld seam 36 between the adjacent covers 27 extends in the radial direction on the front sides of the recuperator 9. In this case, two covers 27 welded together always seal a passage 20 of the exhaust gas flow 13. The passages 21 for the compressed air flow 8 are at the end faces of the recuperator 9 open.
• Figures 7 a, 7 b and 7 c show a variant with clamping plates as covers 27.
• the figures show Schingeln for clarity reasons without curved course.
• a mirror plate 35 serves for fixing and / or connection of the individual elements.
• the metallic mirror plate 35 is welded to the adjacent elements.
• Figures 8 a, 8 b and 8 c show a variant without clamping plates, wherein the metal foils formed as walls 22 are crimped.
• the figures show shingles without a curved course.
• a cover 27 is first welded.
• a wall 22 of the neighboring shingles is crimped to the cover 27.
• laser welding is suitable as the welding method.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Physics & Mathematics (AREA)
• Thermal Sciences (AREA)
• Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Applications Claiming Priority (3)

Publications (1)

Family

ID=47845897

Family Applications (2)

Family Applications After (1)

Country Status (5)

Cited By (1)

Families Citing this family (9)

Family Cites Families (24)

• 2013
  • 2013-02-19 EP EP13708673.2A patent/EP2839135A1/de not_active Withdrawn
  • 2013-02-19 US US14/380,166 patent/US20150023778A1/en not_active Abandoned
  • 2013-02-19 US US14/380,159 patent/US20150020500A1/en not_active Abandoned
  • 2013-02-19 EP EP13708674.0A patent/EP2839136A1/de not_active Withdrawn
  • 2013-02-19 WO PCT/EP2013/000481 patent/WO2013124053A1/de active Application Filing
  • 2013-02-19 CN CN201380010341.0A patent/CN104246177A/zh active Pending
  • 2013-02-19 CN CN201380010344.4A patent/CN104246178A/zh active Pending
  • 2013-02-19 WO PCT/EP2013/000482 patent/WO2013124054A1/de active Application Filing
• 2015
  • 2015-04-22 HK HK15103876.6A patent/HK1203589A1/zh unknown
  • 2015-04-22 HK HK15103879.3A patent/HK1203590A1/zh unknown

Non-Patent Citations (1)

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