WO1988002062A1 - Dispositif pour traiter l'air de combustion de moteurs a reaction - Google Patents

Dispositif pour traiter l'air de combustion de moteurs a reaction Download PDF

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Publication number
WO1988002062A1
WO1988002062A1 PCT/DE1987/000422 DE8700422W WO8802062A1 WO 1988002062 A1 WO1988002062 A1 WO 1988002062A1 DE 8700422 W DE8700422 W DE 8700422W WO 8802062 A1 WO8802062 A1 WO 8802062A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustion chamber
nitrogen
turbine
combustion
oxygen
Prior art date
Application number
PCT/DE1987/000422
Other languages
German (de)
English (en)
Inventor
Eugen Plaksin
Original Assignee
Eugen Plaksin
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 Eugen Plaksin filed Critical Eugen Plaksin
Publication of WO1988002062A1 publication Critical patent/WO1988002062A1/fr

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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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
    • B01D53/24—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols by centrifugal force

Definitions

  • the invention relates to a device for treating the combustion air of engines with at least one combustion chamber.
  • engines are designed as a propeller-turbine air jet engine, single-flow air jet engine or dual-flow jet engine and contain axial compressors or radial compressors.
  • radial compressors the intake air flow is deflected by 90 ° to the drive axis, compressed and fed to the combustion chambers.
  • axial compressors however, the air flow is compressed parallel to the drive axis, with the air flow being supplied with smaller cross sections within several compressor stages. The air compressed in this way reaches the combustion chambers after the last compressor stage.
  • around 70% of the air volume supplied serves to center the combustion chamber flame and cool the combustion chamber walls.
  • the invention has for its object to provide a device for aircraft jet engines with which the nitrogen content of the combustion air entering the combustion chambers is reduced and an increased oxygen content reaches the combustion chambers.
  • the oxygen should only be used for combustion and the nitrogen should at least partially be supplied for cooling the high-thermal turbines.
  • the greater proportion of nitrogen should be used to sheath the exhaust gas jet.
  • the efficiency is to be increased and the fuel requirement is to be reduced, the proportions of the toxic exhaust gases, such as carbon monoxide, carbon dioxide and nitrogen oxide, being reduced.
  • guide means are provided to give the combustion air a rotational movement about the longitudinal axis of the engine in addition to an axial movement before entering the combustion chamber, and in that a separating element is provided with which the heavy oxygen and / or Ozone molecules are separated from the lighter nitrogen molecules and passed into the combustion chamber, with the nitrogen being guided past the combustion chamber.
  • the device according to the invention makes it possible to pass a considerably larger proportion of oxygen into the combustion chambers, as a result of which the fuel requirement is reduced and the efficiency is increased.
  • An improved ver Burning with optimal use of the fuel used is achieved and the exhaust gas values are improved.
  • the combustion air is separated mechanically into nitrogen and oxygen or ozone using the separating element.
  • centrifugal forces acting on the individual molecules arise in the flow of the combustion air which drive the comparatively heavier oxygen and ozone molecules to the outside.
  • the combustion air is passed through a spiral-shaped tube, an enrichment of oxygen and ozone molecules taking place in the area of the outer wall of this circulation tube, while an enrichment of nitrogen takes place on the inside.
  • the heavy oxygen or ozone molecules being collected with a channel and passed into the respective combustion chamber.
  • the stator blades of the compressor can also be enriched radially on the outside with oxygen or ozone and the fractionation can be carried out at the outlet of the compressor.
  • the nitrogen separated in this way is guided past the combustion chambers and, shortly before the turbine of the steel engine, a predeterminable part, in the order of 20% according to the invention, is diverted and directed to the turbines in order to cool them.
  • Nitrogen alone is comparatively inert chemically and large energies are required to separate the nitrogen, namely about 942 KJ / MOL; about 494 KJ / MOL is required for oxygen and 435 KJ / MOL for hydrogen.
  • the turbine is cooled by a chemically largely passive gas, similar to nitrogen, and protected from oxygen. The problems encountered in the design of turbines so far are solved in a surprisingly simple manner.
  • means for increasing the pressure are provided after the separating elements in order to supply the oxygen and / or the ozone, taking into account the pressure in the combustion chamber.
  • the pressure-increasing means are on Provided end of the guide tube.
  • corresponding pressure-influencing means are assigned to a branch in order to direct a predeterminable portion of the nitrogen flowing past the combustion chamber to the turbine with increased pressure.
  • the speed of the air in the circulation tube can be predetermined in that the opening of the pipe leading into the exhaust gas jet is increased or decreased in accordance with the speed requirement.
  • the remaining, relatively large proportion of nitrogen is fanned out behind the turbine or behind an afterburner and is laid as a jacket around the hot exhaust gas jet (800 to 900 ° C.).
  • the cold nitrogen jacket also acts as a silencer because it can absorb large amounts of heat and energy.
  • the enrichment of nitrogen or oxygen and ozone brought about by the guide means according to the invention can be increased by exposing the combustion air to UV radiation.
  • the guide means contain the above-mentioned tubes, openings are expediently provided on their outer sides in order to install UV lamps, preferably with UV-C rays.
  • the combustion air can be enriched with ozone. It should be noted that the specific gravity of nitrogen remains unchanged at 1.25 g / dm 3 the oxygen increases from 1.43 g / dm 3 to 2.41 g / dm 3 for ozone.
  • UV-C rays with wavelengths between 250 to 280 nanometers are preferably used. With such short-wave radiation, particularly effective ozonation is achieved.
  • other rays in particular UV-A rays, whose wavelength is between 315 to 400 nanometers and / or UV-B rays with wavelengths between 280 and 315 nanometers, can also be used. Due to such UV steel, wherein several UV radiation sources are expediently arranged along the guide means, an enrichment of 60% and above in ozone can be brought about. On the other hand, since ozone quickly decomposes back into oxygen, the oxygen is largely available again in the combustion chambers.
  • Fig. 5 shows an attachment scheme for a order! tube with separator
  • FIGS. 1 to 4 enlarges detail I according to FIGS. 1 to 4, Fig. 7 unwound a view of a
  • FIG. 8 is a view of the half-shell according to FIG. 7 in viewing direction VI,
  • FIG. 9 shows a view of three segments of the separating elements in viewing direction VII according to FIG. 7,
  • Fig. 10 is a section along section line VIII according to
  • 11 is a section developed in the plane of the drawing according to section line IX of FIG. 10.
  • Fig. 1 shows schematically a longitudinal section through an inflow jet engine with an air inlet 1 of a compressor 3 and an air inlet 2 of a circulation pipe 20.
  • the axial compressor compresses the intake air and conveys it into a number of combustion chambers 4, which the turbine 5 with the Outlet 6 is downstream for the exhaust gas flow.
  • Aufriller 20 provided, which is arranged in the context of the invention spirally and / or over an angular range of 360 ° around the circumference of the compressor 3.
  • the circulating tube 20, which is indicated in a triangle-like manner only for the sake of the simplified illustration, consequently has a part located in front of and behind the plane of the drawing.
  • the combustion air flowing in at the air inlet 2 is forced through the circulation pipe 20 into an orbit with respect to the longitudinal axis 22, with an enrichment of the oxygen molecules, which are more scarce compared to nitrogen, taking place in the area of the outer wall 24.
  • the circulation tube 20 are also Radiation sources 16, in particular UV-C. Rays, assigned.
  • the circulation tube 20 has openings on the outside in order to install suitable UV-C radiation sources or lamps and to illuminate the tube section by section on the inside.
  • the inner surfaces of the tube are at least partially mirrored in a suitable manner in order to obtain a high reflection and consequently to achieve an improved ozone enrichment. This reflection can be achieved in particular by chromating.
  • a separating wedge is arranged at the end of the circulation pipe 20, specifically in the area of the outer surface 24, in order to introduce the heavier oxygen and ozone molecules through a guide pipe 26 into the combustion chamber 4.
  • the guide tube 26 is designed in such a way that a change in pressure takes place with regard to the pressure present in the combustion chamber.
  • the mouth 28 of the guide tube is expediently designed as a Laval nozzle.
  • the guide tube 26 projects with its mouth 28 sufficiently far into the combustion chamber 4 so that the oxygen or ozone can flow in reliably.
  • the guide tube 26 is formed at the end as a Laval nozzle, whereby a pressure ratio to the external pressure, in the order of magnitude of in particular 1: 7, is achieved without difficulty.
  • by enlarging or reducing the pipe end on the exhaust gas jet from Um! Aufrschreib allows the control or specification of the speed of the air in the circulation pipe.
  • the relatively light nitrogen flows through the appropriately axial pipe section 30 past the combustion chamber 4 and a branch 8 becomes a Predeterminable proportion of the nitrogen flowing past is directed to the turbine 5 for the purpose of cooling the same. Since the chemical reactivity of nitrogen alone is relatively low, not only is there cooling, but effective protection against oxygen is also achieved.
  • the remaining approximately 80% of the nitrogen are fed in at the inlet 9 behind the turbine 5 and form a jacket around the hot exhaust gas jet at the outlet 6 of the turbine 5.
  • corresponding means are also assigned to the pipe branch in the context of this invention.
  • the pressure of the nitrogen directed to the turbine can be supplied to the turbine in a correspondingly increased manner.
  • the circulation pipes 20 are designed as circumferential, flattened pipes that extend over the length of the compressor stages, with each of the combustion chambers 4 being assigned such a pipe.
  • Fig. 2 shows a turbopro engine with a propeller 10 in front of the air inlet 1 of the compressor 3 and the air inlet 2 of the circulation tube 20.
  • a larger suction turbine by means of which air not only in the compressor 3 but when it starts up is also pumped into the separation device according to the invention.
  • FIG. 3 A further embodiment is shown in FIG. 3, namely a fan engine with a turbine 11, which is surrounded by a partial jacket 12. Air is also pumped from this fan turbine immediately into the circulation tube 22 of the separating device according to the invention.
  • Fig. 4 shows an embodiment of a two-circuit turbofan engine with a casing flow compressor turbines 13 in a casing 14.
  • the casing 14 extends over the entire length and that of Air supplied to the separator is taken from this outer jacket stream.
  • FIG. 5 shows the attachment diagram with a circulation tube 20, which has a number of UVC radiation sources 16 on its outside.
  • the circulation pipe 20 extends over a predetermined angular range around the longitudinal axis 22 of the engine. An angular range of 360 ° is specified within the scope of the invention. It should be noted that a corresponding number of circulation pipes 20 is arranged distributed over the circumference in accordance with the number of combustion chambers. By means of the respective separating wedge 7, the oxygen or ozone enriched on the outer surface is separated from the nitrogen and conveyed through the guide tube 26 into the assigned combustion chamber.
  • the separating wedge 7 is arranged at a distance from the outer surface 24 so that the oxygen or ozone which is predominantly present due to centrifugal forces in the region of the outer surface 24 is separated and through the guide tube 26 can be directed radially inward into the combustion chamber.
  • FIG. 7 and 8 show an engine half-shell, namely in a development in the drawing plane or in an axial view.
  • the stators 18 of the individual compressor stages are not arranged in the half-shell 17 parallel to the longitudinal axis but offset in the circumferential direction.
  • the air entering through the air inlet 1 is consequently forced into a movement rotating around the longitudinal axis 22 of the engine.
  • This circumferential movement when flowing through the compressor stages in turn leads to an enrichment of oxygen or ozone radially on the outside. It is essential here that practically the entire amount of air compressed by the compressor can be separated into nitrogen and oxygen.
  • Separating elements are arranged behind the compressor stages and are designed here as segments 32. Such a segment 32 is provided for each of the combustion chambers.
  • FIG. 9 shows a view in the axial direction of three such segments 32. It is spaced radially inward from the outer wall 24 the separating wedge 7 arranged.
  • the separating wedge 7 is the front edge of a trapezoid-like bottom part 34 which forms a funnel-like channel with side walls 36, which ends in the mouth 29.
  • a guide tube can be connected to the mouth 29 in order to supply the oxygen or ozone to the combustion chamber.
  • the nitrogen present below the separating wedges 7 is guided along the radially inner inner surfaces of the base parts 34 and flows out through openings 38 in order to be fed through branches of the turbine via branches of the turbine in accordance with the pipe sections explained at the outset, and to a greater extent behind the turbine than Sheath to be placed around the exhaust jet. It is also important for this embodiment to design the mouth 29 or a guide tube connected thereto as a lava nozzle for the purpose of increasing the pressure.
  • FIG. 10 shows a section along section line X according to FIG. 9.
  • the trapezoid-like base part 34 which is curved in accordance with the radius, as well as the correspondingly designed ceiling 35 of the guide tube 26 can be clearly seen.
  • 11 shows a section along the section line XI in a development in the plane of the drawing, the side walls 36 tapering from the separating wedge 7 in the axial direction toward the rear to the mouth 29 being shown here.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Supercharger (AREA)

Abstract

Dispositif pour traiter l'air de combustion de moteurs à réaction comportant au moins une chambre de combustion (4). L'invention a pour objet de réduire le pourcentage d'azote contenu dans l'air de combustion et parvenant dans la chambre de combustion, et d'augmenter le pourcentage d'oxygène. En outre, l'azote doit servir, au moins partiellement, à refroidir la turbine fortement sollicitée thermiquement. Des moyens de guidage (20) sont prévus pour communiquer à l'air de combustion, avant son entrée dans la chambre de combustion (4), outre un mouvement axial, un mouvement rotatif autour de l'axe longitudinal (22) du réacteur. D'autre part, au moins un élément séparateur (7) sépare les molécules relativement lourdes d'oxygène et/ou d'ozone des molécules comparativement légères d'azote et achemine les premières dans la chambre de combustion (4), faisant passer l'azote devant ladite chambre.
PCT/DE1987/000422 1986-09-20 1987-09-17 Dispositif pour traiter l'air de combustion de moteurs a reaction WO1988002062A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DEP3632055.2 1986-09-20
DE19863632055 DE3632055A1 (de) 1986-09-20 1986-09-20 Vorrichtung fuer die aufbereitung der verbrennungsluft

Publications (1)

Publication Number Publication Date
WO1988002062A1 true WO1988002062A1 (fr) 1988-03-24

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Application Number Title Priority Date Filing Date
PCT/DE1987/000422 WO1988002062A1 (fr) 1986-09-20 1987-09-17 Dispositif pour traiter l'air de combustion de moteurs a reaction

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EP (1) EP0284618A1 (fr)
DE (1) DE3632055A1 (fr)
WO (1) WO1988002062A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006045946B4 (de) * 2006-09-28 2008-11-06 Wjatscheslaw Boguslajew Verbrennungskammer, die ein äußeres Gehäuse, ein Flammrohr, Kraftstoffdüsen, eine Zündkerze und Ionisierungskammer mit darin aufgestellten Elektroden enthält und sich dadurch kennzeichnet, daß ihre Ionisierungskammer mit Drehbarkeit ausgeführt ist
US11462666B2 (en) 2020-05-15 2022-10-04 Lumileds Llc Light-emitting device with configurable spatial distribution of emission intensity

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR854001A (fr) * 1938-12-01 1940-04-03 Perfectionnements aux moteurs et turbines à combustion
FR2211590A1 (fr) * 1972-12-20 1974-07-19 Brown Robert
DE3049389A1 (de) * 1980-06-24 1983-01-20 Gottfried 6486 Brachttal Bähr Verfahren und vorrichtung zur sauerstoffanreicherung von verbrennungsluft
WO1983000100A1 (fr) * 1981-06-29 1983-01-20 Richard Chalupa Cyclone d'enrichissement d'un melange gazeux
DE3100312A1 (de) * 1980-12-29 1983-02-10 Gottfried 6486 Brachttal Bähr Verfahren, vorrichtung und anwendung einer rotations-gasgemischtrennung nach dem prinzip der rotations-sauerstoff-anreicherung, jedoch ohne magnetischen energieinhalt, zum zweck der trennung von im molekulargewicht unterschiedlicher gase, mit aufbereitung der abgase und kreislaufeinsatz fuer die zweite komponente
EP0082600A1 (fr) * 1981-12-18 1983-06-29 The Garrett Corporation Système enrichi en oxygène
US4434613A (en) * 1981-09-02 1984-03-06 General Electric Company Closed cycle gas turbine for gaseous production

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR854001A (fr) * 1938-12-01 1940-04-03 Perfectionnements aux moteurs et turbines à combustion
FR2211590A1 (fr) * 1972-12-20 1974-07-19 Brown Robert
DE3049389A1 (de) * 1980-06-24 1983-01-20 Gottfried 6486 Brachttal Bähr Verfahren und vorrichtung zur sauerstoffanreicherung von verbrennungsluft
DE3100312A1 (de) * 1980-12-29 1983-02-10 Gottfried 6486 Brachttal Bähr Verfahren, vorrichtung und anwendung einer rotations-gasgemischtrennung nach dem prinzip der rotations-sauerstoff-anreicherung, jedoch ohne magnetischen energieinhalt, zum zweck der trennung von im molekulargewicht unterschiedlicher gase, mit aufbereitung der abgase und kreislaufeinsatz fuer die zweite komponente
WO1983000100A1 (fr) * 1981-06-29 1983-01-20 Richard Chalupa Cyclone d'enrichissement d'un melange gazeux
US4434613A (en) * 1981-09-02 1984-03-06 General Electric Company Closed cycle gas turbine for gaseous production
EP0082600A1 (fr) * 1981-12-18 1983-06-29 The Garrett Corporation Système enrichi en oxygène

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Publication number Publication date
DE3632055A1 (de) 1988-03-24
EP0284618A1 (fr) 1988-10-05

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