DE102016009629A1 - "Arrangement of a valve of a detonation combustion chamber" - Google Patents
"Arrangement of a valve of a detonation combustion chamber" Download PDFInfo
- Publication number
- DE102016009629A1 DE102016009629A1 DE102016009629.2A DE102016009629A DE102016009629A1 DE 102016009629 A1 DE102016009629 A1 DE 102016009629A1 DE 102016009629 A DE102016009629 A DE 102016009629A DE 102016009629 A1 DE102016009629 A1 DE 102016009629A1
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- DE
- Germany
- Prior art keywords
- combustion chamber
- detonation
- ignition
- detonation combustion
- chambers
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F02K7/02—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 jet being intermittent, i.e. pulse-jet
- F02K7/04—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 jet being intermittent, i.e. pulse-jet with resonant combustion chambers
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/10—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
- F02C5/11—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect using valveless combustion chambers
-
- 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
- F23R7/00—Intermittent or explosive combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
Pulsdetonationsbrennkammer, dadurch gekennzeichnet, dass das Detonationsbrennkammer Gehäuse (7) der Detonationsbrennkammer (1) wenigstens zwei koaxial oder radial dazu angeordnete Ringzündkammern (3n) mit wenigstens drei um jeweils 120° zueinander versetzten Oxydationsmittelzufuhren (2n) und Brennstoffzufuhren (5n) aufweist, wobei wenigstens jeweils drei um 120° versetzte Zündelemente (4n) am Außenrand der Ringzündkammern (3n) platziert sind und die Ringzündkammern (3n) dieselben mechanischen Dimensionen und Abstände zueinander aufweisen oder auch davon abweichende Dimensionen und dass das Detonationsbrennkammer Gehäuse (7) die Reaktandenzufuhr (9) und wenigstens ein Zündelement (10n) aufweist.Pulse detonation combustion chamber, characterized in that the detonation combustion chamber housing (7) of the detonation combustion chamber (1) at least two coaxial or radial annular ignition chambers (3n) with at least three mutually offset by 120 ° Oxydationsmittelzufuhren (2n) and fuel supply (5n), wherein at least in each case three ignition elements (4n) offset by 120 ° are placed on the outer edge of the annular ignition chambers (3n) and the annular ignition chambers (3n) have the same mechanical dimensions and distances from one another or also deviating dimensions, and that the detonation combustion chamber housing (7) supplies the reactant (9) and at least one ignition element (10n).
Description
Die vorliegende Erfindung betrifft eine Pulsdetonationsbrennkammer zum Betreiben eines Flugtriebwerks. Detonationstriebwerke „Pulse Detonation Engines” – kurz auch PDE – sind wegen ihres geringeren Treibstoffverbrauchs gegenüber Turbojets oder Turbofans Gegenstand theoretischer und experimenteller Forschung. Man unterscheidet insbesondere zwischen „Impuls Detonations Engine (IDT)” und „Spin Detonations Engine (SPE)”, wobei bei den IDT impulsartige Detonationen und bei den SPE kontinuierliche Detonationswellen provoziert werden. Eine Variante sind „Pulsed Detonation Rocket Engine (PDRE)” die wie bei herkömmlichen Flüssigtreibstoffraketen Oxidator und Brennstoff mischen und diese pulsweise zur Detonation bringen. Ein Problem stellt hierbei die Länge des Detonationsrohres, die sogenannte Hochlauflänge, dar. Um Gemisch bedingte effektive Detonationen in diesem Rohr zu provozieren, liegt das optimale Verhältnis Rohrlänge zum Durchmesser des Detonationsrohres (L/D) bei ca. 1/100. Aus Bauraum- und Gewichtsgründen wir aber ein wesentlich kleineres LID Verhältnis bis herab von 1/30 und kleiner gewünscht, wobei die Zündgeschwindigkeit und Gemischbildung möglichst gesteigert werden sollen. Teilweise wird versucht, dies durch mechanische Hindernisse innerhalb des Detonationsrohres zu erreichen. Aufgabe der vorliegenden Erfindung ist es, eine Zündkammer für eine Pulsdetonationsbrennkammer nach den Merkmalen des Anspruchs 1 zur Verfügung zu stellen.The present invention relates to a pulse detonation combustion chamber for operating an aircraft engine. Detonation Engines "Pulse Detonation Engines" - PDEs for short - are the subject of theoretical and experimental research because of their lower fuel consumption compared to turbojets or turbofans. In particular, a distinction is made between "Impulse Detonation Engine (IDT)" and "Spin Detonation Engine (SPE)", in which IDT generates pulse-like detonations and, in the case of SPE, continuous detonation waves. A variant are "Pulsed Detonation Rocket Engine (PDRE)" which mix like conventional liquid fuel rockets oxidizer and fuel and bring them pulsating detonation. One problem here is the length of the detonation tube, the so-called run-up length. In order to provoke mixture-related effective detonations in this tube, the optimum tube length to diameter of the detonation tube (L / D) is approximately 1/100. For space and weight reasons, but we wanted a much smaller LID ratio down to 1/30 and smaller, with the ignition speed and mixture formation should be increased as possible. Partial attempts are made to achieve this by mechanical obstacles within the detonation tube. The object of the present invention is to provide an ignition chamber for a pulse detonation combustion chamber according to the features of claim 1.
Erfindungsgemäß wird diese Aufgabe dadurch gelöst, dass die Wandung des Detonationsbrennkammer Gehäuses mit mehreren zueinander beabstandeten koaxialen Ringzündkammern umgeben ist denen ein Oxydationsmittel und Brennstoff zugeführt werden, wobei in den Ringzündkammern das zündfähige Gemisch mittels mehrerer Zündelemente gezündet wird und so in einem ersten Verfahren die über die Reaktanden Zufuhr des Detonationsrohres zugeführten Reaktanden zündet oder auch selbst Detonationswellen im Detonationsraum auslösen können.According to the invention, this object is achieved in that the wall of the detonation combustion chamber housing is surrounded with a plurality of coaxial annular ignition chambers spaced apart which an oxidant and fuel are supplied, wherein in the annular ignition chambers the ignitable mixture is ignited by means of several ignition elements and in a first method over the Reactants supply the detonation tube supplied reactants ignites or even trigger detonation waves in the detonation space.
In folgendem wird die Erfindung anhand eines bevorzugten Ausführungsbeispiels in Verbindung einer Zeichnung beschrieben.In the following the invention will be described with reference to a preferred embodiment in conjunction with a drawing.
Dabei zeigt:Showing:
Erfindungsgemäß weist die Wandung des Detonationsbrennkammer Gehäuses (
- 1. Die Ringzündkammern (
3n ) wirken über die darin zugeführten Reaktanden als Zündmittel für die über die Reaktandenzufuhr (9 ) in den Detonationsraum (8 ) zugeführten Reaktanden und werden gleichzeitig oder auch nicht gleichzeitig gezündet. - 2. Die Ringzündkammern (
3n ) sind so ausgelegt und werden zeitlich so gezündet, dass sie selbst im Detonationsraum (8 ) Detonationswellen erzeugen, wobei die Reaktandenzufuhr (9 ) dann ersatzlos entfallen kann oder auch nicht. - 3. Die Erzeugung von Detonationswellen im Detonationsraum (
8 ) kann auch alternierend als Zündmittel der über die Reaktandenzufuhr (9 ) im Detonationsraum (8 ) zugeführten Reaktanden als auch selbst Detonationswellen in den Detonationsraum (8 ) einbringend wirken. - 4. Die Ringzündkammern (
3n ) können jeweils H2 und/oder O2 liefern und die Brennstoffzufuhr (9 ) entsprechend O2 und/oder H2, wobei die Zündung dann über das Zündelement (10 ) erfolgt. - 5. Zur physikalischen Trennung nach jeweils erfolgter Detonation bzw. Detonationswellen kann eine der Ringzündkammern (
3n ) oder auch mehrere davon ein inertes Gas in den Detonationsraum (8 ) liefern. - 6. Zur Strömungsbeeinflussung der Flammenfront können die Ringzündkammern (
3n ) ganz oder teilweise als Blenden (11n ) mit gleichgroßen oder unterschiedlich großen Durchmessern ausgebildet sein.
- 1. The ring ignition chambers (
3n ) act via the reactants supplied therein as ignition means for the via the Reaktandenzufuhr (9 ) into the detonation room (8th ) and are ignited simultaneously or not at the same time. - 2. The ring ignition chambers (
3n ) are designed and ignited in time so that they themselves in the detonation space (8th ) Generate detonation waves, whereby the Reaktandenzufuhr (9 ) can then be omitted without replacement or not. - 3. The generation of detonation waves in the detonation space (
8th ) can also be used alternately as ignition means of the Reaktandenzufuhr (9 ) in the detonation room (8th ) Reactants and even detonation waves in the detonation space (8th ) contribute. - 4. The ring ignition chambers (
3n ) can each supply H2 and / or O2 and the fuel supply (9 ) corresponding to O2 and / or H2, the ignition then being ignited via the ignition element (10 ) he follows. - 5. For the physical separation after each successful detonation or detonation waves, one of the ring ignition chambers (
3n ) or several of them an inert gas in the detonation space (8th ) deliver. - 6. For influencing the flow of the flame front, the ring ignition chambers (
3n ) in whole or in part as diaphragms (11n ) be formed with the same size or different diameters.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
- 11
- PulsdetonationsbrennkammerPulse detonation combustor
- 22
- OxydationsmittelzufuhrOxydationsmittelzufuhr
- 33
- RingzündkammerRingzündkammer
- 44
- Zündelementigniter
- 55
- Brennstoffzufuhrfuel supply
- 66
- OxydationsmittelzufuhrOxydationsmittelzufuhr
- 77
- Pulsdetonationsbrennkammer GehäusePulse detonation combustion chamber housing
- 88th
- Detonationsraumdetonation chamber
- 99
- Reaktandenzufuhrreactant
- 1010
- Zündelementigniter
- 1111
- Blendecover
Claims (6)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016009629.2A DE102016009629A1 (en) | 2016-08-06 | 2016-08-06 | "Arrangement of a valve of a detonation combustion chamber" |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016009629.2A DE102016009629A1 (en) | 2016-08-06 | 2016-08-06 | "Arrangement of a valve of a detonation combustion chamber" |
Publications (1)
Publication Number | Publication Date |
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DE102016009629A1 true DE102016009629A1 (en) | 2018-02-08 |
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ID=60996243
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Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102016009629.2A Withdrawn DE102016009629A1 (en) | 2016-08-06 | 2016-08-06 | "Arrangement of a valve of a detonation combustion chamber" |
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DE (1) | DE102016009629A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111520767A (en) * | 2020-06-03 | 2020-08-11 | 西安热工研究院有限公司 | Pulse detonation combustion chamber capable of adjusting energy distribution of outlet gas |
-
2016
- 2016-08-06 DE DE102016009629.2A patent/DE102016009629A1/en not_active Withdrawn
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111520767A (en) * | 2020-06-03 | 2020-08-11 | 西安热工研究院有限公司 | Pulse detonation combustion chamber capable of adjusting energy distribution of outlet gas |
CN111520767B (en) * | 2020-06-03 | 2023-07-25 | 西安热工研究院有限公司 | Pulse detonation combustor capable of adjusting outlet gas energy distribution |
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R086 | Non-binding declaration of licensing interest | ||
R119 | Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee |