EP1738112B1 - Rocket engine with damping of vibration of the combustion chamber by resonators - Google Patents

Rocket engine with damping of vibration of the combustion chamber by resonators Download PDF

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Publication number
EP1738112B1
EP1738112B1 EP05732027.7A EP05732027A EP1738112B1 EP 1738112 B1 EP1738112 B1 EP 1738112B1 EP 05732027 A EP05732027 A EP 05732027A EP 1738112 B1 EP1738112 B1 EP 1738112B1
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EP
European Patent Office
Prior art keywords
combustion chamber
chamber
resonators
injection
resonator
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EP05732027.7A
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German (de)
French (fr)
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EP1738112A1 (en
Inventor
Chris MÄDING
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ArianeGroup GmbH
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ArianeGroup GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a rocket engine with a device for damping vibrations of a combustion chamber, wherein at least one resonator is vibrationally connected to the combustion chamber.
  • Damping chambers are arranged in the region of the injection head in a fuel distribution space and connected via passage channels with the combustion chamber vibration technology.
  • the fuel distribution space which serves for example for the distribution of hydrogen, although an active cooling of the damping chambers is ensured.
  • this relatively complex design measures are necessary. Nevertheless, it can not be ruled out that hot combustion chamber combustion gases penetrate directly into the damping chambers via the passage channels and lead to impairment or even destruction of the damping chambers.
  • the apparatus includes a resonator positioned between a diffuser outlet and fuel-air mixers disposed within the combustor.
  • the resonator is formed by a plurality of resonator tubes disposed around the combustor and each having an end open toward the interior of the combustor.
  • DE 101 63 561 A1 discloses a rocket engine comprising a combustion chamber, means for damping vibrations of the combustion chamber and an antechamber, the vibration damping means comprising at least one resonator vibrationally connected to the combustion chamber, the combustion chamber being upstream of an injection head; wherein in the injection head at least one injection element for introducing a fuel flow is provided in the combustion chamber, and wherein the prechamber is connected via at least one passage passage with the combustion chamber vibration technology.
  • the object of the present invention is therefore to provide an improved possibility for damping vibrations of a combustion chamber with the aid of resonators.
  • the invention relates to a device for damping vibrations of a combustion chamber, wherein at least one resonator is vibrationally connected to the combustion chamber.
  • the at least one resonator is vibrationally connected to an antechamber and the prechamber is connected in terms of vibration technology via at least one passage channel to the combustion chamber.
  • This ensures that the one or more resonators that are used to dampen the vibrations, no longer directly with the combustion chamber, or with the interior of the combustion chamber in communication. Rather, there is only an indirect connection via the intermediate antechamber.
  • the resonators can be arranged in areas that are subjected to a lower temperature load or lower temperature changes. Nevertheless, the vibrations of the combustion chamber via the passage channel and the antechamber can reach up to the resonators and thus the vibrations of the combustion chamber can be effectively damped.
  • a first embodiment of the invention provides that the combustion chamber adjoins an injection head with at least one injection element, which is designed to introduce a gaseous fuel flow into the combustion chamber, and the pre-chamber is arranged in terms of flow before the at least one injection element. It can be provided a single fuel stream, which is supplied to the combustion chamber. It is also possible to provide two or more fuel streams which are supplied to the combustion chamber through the injection elements and, if appropriate, are already mixed in or immediately after the injection elements.
  • the pre-chamber is arranged in this alternative in an area that passes at least one of the fuel streams before it flows through the injector or the injection elements. So that are the injection elements between the combustion chamber or the interior of the combustion chamber and the antechamber.
  • the combustion chamber adjoins an injection head with at least one injection element, which is designed to introduce a fuel flow into the combustion chamber, and the pre-chamber is arranged in terms of flow in the region of the at least one injection element.
  • the pre-chamber is in an area that passes at least one of the fuel streams, while it flows through the injection element or elements.
  • the injection elements and the pre-chamber are fluidly arranged side by side in front of the combustion chamber or the interior of the combustion chamber.
  • At least one of the fuel streams can serve to keep the temperature of the resonators largely constant by actively cooling the resonators.
  • the prechamber fluidly communicate with a fuel flow before it reaches the interior of the combustion chamber.
  • the fuel flow is thereby not only diverted around a resonator as in the case of DE 34 32 607 A1 but it reaches the interior of the resonator, so that the resonance volume of the resonator itself can be kept substantially constant at the temperature of the fuel flow.
  • the resonator as well as the antechamber with a gaseous fuel flow in conjunction since then on the fuel flow, a particularly good vibration control connection between the resonator and the combustion chamber can be ensured.
  • the passage channel is formed as part of an injection element. In principle, however, it is also possible to provide separate passageways which guarantee a vibration-technical connection between the interior of the combustion chamber and the prechamber.
  • the resonators can be designed, for example, as Helmholtz resonators or as ⁇ / 4 resonators. Such resonators are basically well known from the prior art.
  • acoustic resonators known from the cited prior art.
  • Helmoltz resonators Both resonator types consist of small volumes, which are directly connected to the chamber in the prior art devices. In these resonators, a dissipation of the vibration energy takes place when the excited frequency of the chamber coincides with the natural frequency of the resonator.
  • Resonators are narrow-band absorbers and must therefore be tuned to the frequency to be damped.
  • Helmholtz resonators are used for attenuation in a wider frequency range compared to the ⁇ / 4 resonators, which must be tuned to a discrete frequency.
  • arranged resonators in the region of the injection head form undesirable sudströmzonen in this area, whereby an additional heat flow in the direction of the injection head is formed, which may affect the stability of the injection head.
  • the present invention provides a resonator assembly which is independent of the hot combustion gases and thus the temperature in the combustion chamber. At the same time a negative influence on the arrangement of the injection elements and the combustion chamber cooling is avoided.
  • the invention is particularly applicable to mainstream engines and other gaseous injection engines of one or two or more fuel components.
  • mainstream propulsion systems gaseous exhaust gases from a fuel turbine are returned to a fuel stream (main stream) and sent into the combustion chamber along with the fuel stream.
  • a gaseous fuel such as hydrogen.
  • the fuel is passed in liquid form through cooling channels of the rocket engine and converted into gaseous state due to the heat absorption.
  • gaseous fuel streams which are passed through injection elements in the interior of a combustion chamber and burned there.
  • Fig. 1 to 3 show examples of a mainstream rocket engine.
  • the engine each has a combustion chamber 1, which is bounded upstream by an injection plate 2 of an injection head 3.
  • injection elements 4 are arranged, which serve to direct one or more fuel flows into the interior 9 of the combustion chamber 1.
  • the injection head 3 is bounded upstream by a cover plate 6.
  • the injection elements 4 are either tubular, but they can also be formed by a combination of tubes and one or more coaxial sleeves.
  • the injection elements 4 or the tubes or sleeves are connected to the injection plate 2 and / or the cover plate 6.
  • the main flow of a gaseous fuel and turbine exhaust gases (gas) reach an antechamber 7 in front of the injection head and are then passed through the injection elements 4 into the interior 9 of the combustion chamber 1.
  • Fig. 4 shows an expander-cycle engine, in which a gaseous fuel stream such as hydrogen (gH2) is passed into an antechamber 17 and from there via annular gaps 8 between a pipe 28 and a sleeve of a coaxial injection element 4 in the interior 9 of the combustion chamber passes , Via another chamber 27 and the tube 28, another, for example, liquid fuel stream such as liquid oxygen enters the interior 9 of the combustion chamber first
  • a gaseous fuel stream such as hydrogen (gH2)
  • Fig. 1 shows an arrangement of a Helmholtz resonator 5 in the wall of the antechamber 7.
  • the Helmholtz resonator 5 as a circular circumferential Chamber may be formed in the wall of the prechamber 7, which is connected via an annular passage gap with the prechamber 7, as in Fig. 1 shown.
  • Fig. 2 shows an alternative embodiment, wherein ⁇ / 4 resonators 5 are arranged in the form of unilaterally open cylinders in the cover plate 6 of the injection head 3. As in Fig. 2 shown, a plurality of ⁇ / 4 resonators 5 may be arranged uniformly distributed. In the case of Fig. 2 the ⁇ / 4 resonators 5 are arranged annularly around the central axis of the cover plate 6.
  • ⁇ / 4 resonators 5a, 5b in the wall of the prechamber 7 is provided.
  • the ⁇ / 4 resonators 5a, 5b are formed as holes in the wall of the prechamber 7. These ⁇ / 4 resonators 5a, 5b can also be distributed uniformly.
  • the ⁇ / 4 resonators 5a, 5b are arranged in two superimposed rings in the wall of the prechamber 7.
  • ⁇ / 4 resonators 5, 5a, 5b are basically identical in design, in order to damp exactly one defined oscillation frequency.
  • the ⁇ / 4 resonators 5, 5a, 5b may be formed differently, so that in each case a group of ⁇ / 4 resonators 5, 5a, 5b is adapted to a specific oscillation frequency.
  • the lower ⁇ / 4 resonators 5a are formed as shorter holes and thus adapted to higher vibration frequencies than the upper ⁇ / 4 resonators 5b, which are formed as longer holes.
  • the determination of the geometrical dimensions has to take into account the respective temperature conditions of the gas in the region of the resonators, since this has a direct influence on the speed of sound and thus also on the frequency.
  • ⁇ / 4 resonators 5 are provided as holes in the wall of the injection head 3 in the region of an antechamber 17, which encloses the injection elements 4.
  • the ⁇ / 4 resonators 5 can be uniformly distributed, for example, annularly, be arranged in the wall of the injection head 3 and there may also be several groups of ⁇ / 4 resonators 5 with different adaptation to different vibration frequencies.
  • gaseous fuel such as gH2 enters the pre-chamber 17 and is introduced via annular gaps 8 into the interior 9 of the combustion chamber 1.
  • This flow path of the gaseous fuel is a vibration connection between the interior 9 of the combustion chamber 1 and the antechamber 17, analogous to the above statements to the FIGS. 1 to 3 ,
  • these vibrations reach the ⁇ / 4 resonators 5 in the wall of the antechamber 17 and can be effectively attenuated there by the resonator effect of the ⁇ / 4 resonators 5.
  • the essential advantage of the invention is the largely constant temperature of the gas in the resonators 5, 5a, 5b during the entire duration of the operation of the engine. Furthermore, there is a simplification of the construction in the high-temperature region of the combustion chamber 1, since in the region of the wall of the combustion chamber 1 and in the injection plate in addition to the usual cooling no further arrangements such as resonators more must be provided. In addition, the construction according to the present invention enables a much higher number of resonator examples to be accommodated, since the individual embodiments according to FIGS FIGS.
  • Helmholtz resonators 5 and / or ⁇ / 4 resonators 5a, 5b in the wall of the prechamber 7 and / or ⁇ / 4 resonators 5 can be provided in the cover plate 6.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Description

Die vorliegende Erfindung betrifft ein Raketentriebwerk mit einer Einrichtung zum Dämpfen von Schwingungen einer Brennkammer, wobei mindestens ein Resonator schwingungstechnisch mit der Brennkammer verbunden ist.The present invention relates to a rocket engine with a device for damping vibrations of a combustion chamber, wherein at least one resonator is vibrationally connected to the combustion chamber.

Solche Einrichtungen sind grundsätzlich aus dem Stand der Technik bekannt. Sowohl DE 34 32 607 A1 als auch US 5,353,598 A beschreiben Einrichtungen zum Dämpfen von Schwingungen einer Brennkammer, wobei mindestens ein Resonator bzw. eine Dämpfungskammer unmittelbar oder über Durchtrittskanäle mit der Brennkammer eines Raketentriebwerkes verbunden ist.Such devices are basically known from the prior art. Either DE 34 32 607 A1 as well as US 5,353,598 A describe means for damping vibrations of a combustion chamber, wherein at least one resonator or a damping chamber is connected directly or via passageways with the combustion chamber of a rocket engine.

Nachteilig an den Einrichtungen nach US 5,353,598 A ist jedoch, dass die Resonatoren direkt mit der Brennkammer des Raketentriebwerkes verbunden sind. Damit kann es zu einer Überhitzung der Resonatoren aufgrund von eintretenden heißen Verbrennungsgasen aus dem Brennkammerraum kommen. Die Folge ist, dass die Resonatoren ihre Resonanzwirkung verlieren und entsprechend nicht mehr zur Dämpfung von Schwingungen der Brennkammer beitragen können.Disadvantageous to the facilities US 5,353,598 A is, however, that the resonators are connected directly to the combustion chamber of the rocket engine. This can lead to overheating of the resonators due to incoming hot combustion gases from the combustion chamber space. The consequence is that the resonators lose their resonance effect and accordingly can no longer contribute to the damping of vibrations of the combustion chamber.

Bei der DE 34 32 607 A1 sind Dämpfungskammern im Bereich des Einspritzkopfes in einem Treibstoffverteilerraum angeordnet und über Durchtrittskanäle mit der Brennkammer schwingungstechnisch verbunden. Durch die Anordnung im Treibstoffverteilerraum, der beispielsweise zur Verteilung von Wasserstoff dient, wird zwar eine Aktivkühlung der Dämpfungskammern gewährleistet. Hierzu sind aber relativ aufwändige konstruktive Maßnahmen notwendig. Es kann trotzdem nicht ausgeschlossen werden, dass heiße Brennkammer-Verbrennungsgase über die Durchtrittskanäle unmittelbar in die Dämpfungskammern eindringen und zu einer Beeinträchtigung oder gar Zerstörung der Dämpfungskammern führen.In the DE 34 32 607 A1 Damping chambers are arranged in the region of the injection head in a fuel distribution space and connected via passage channels with the combustion chamber vibration technology. By the arrangement in the fuel distribution space, which serves for example for the distribution of hydrogen, although an active cooling of the damping chambers is ensured. But this relatively complex design measures are necessary. Nevertheless, it can not be ruled out that hot combustion chamber combustion gases penetrate directly into the damping chambers via the passage channels and lead to impairment or even destruction of the damping chambers.

Aus der US 5,685,157 B ist eine Vorrichtung zur Schwingungsdämpfung von Druckstößen in einem Verbrenner einer Gasturbine gezeigt. Die Vorrichtung umfasst einen Resonator, der zwischen einem Diffusorauslass und im Innern des Verbrenners angeordneten Treibstoff-Luftmischern positioniert ist. Der Resonator ist durch eine Vielzahl von Resonatorröhren gebildet, die um den Verbrenner herum angeordnet sind und jeweils ein zum Innern des Verbrenners hin offenes Ende aufweisen.From the US 5,685,157 B is shown a device for vibration damping of pressure surges in a gas turbine engine. The apparatus includes a resonator positioned between a diffuser outlet and fuel-air mixers disposed within the combustor. The resonator is formed by a plurality of resonator tubes disposed around the combustor and each having an end open toward the interior of the combustor.

DE 101 63 561 A1 offenbart ein Raketentriebwerk, das eine Brennkammer, eine Einrichtung zum Dämpfen von Schwingungen der Brennkammer und eine Vorkammer umfasst, wobei die Einrichtung zum Dämpfen von Schwingungen mindestens einen Resonator aufweist, der schwingungstechnisch mit der Brennkammer verbunden ist, wobei die Brennkammer stromaufwärts an einen Einspritzkopf angrenzt, wobei in dem Einspritzkopf mindestens ein Einspritzelement zum Einleiten einer Treibstoffströmung in die Brennkammer vorgesehen ist, und wobei die Vorkammer über mindestens einen Durchtrittskanal mit der Brennkammer schwingungstechnisch verbunden ist. Aufgabe der vorliegenden Erfindung ist daher die Bereitstellung einer verbesserten Möglichkeit zum Dämpfen von Schwingungen einer Brennkammer mit Hilfe von Resonatoren. DE 101 63 561 A1 discloses a rocket engine comprising a combustion chamber, means for damping vibrations of the combustion chamber and an antechamber, the vibration damping means comprising at least one resonator vibrationally connected to the combustion chamber, the combustion chamber being upstream of an injection head; wherein in the injection head at least one injection element for introducing a fuel flow is provided in the combustion chamber, and wherein the prechamber is connected via at least one passage passage with the combustion chamber vibration technology. The object of the present invention is therefore to provide an improved possibility for damping vibrations of a combustion chamber with the aid of resonators.

Diese Aufgabe wird mit den Merkmalen von Anspruch 1 und von Anspruch 2 gelöst.This object is achieved with the features of claim 1 and of claim 2.

Gegenstand der Erfindung ist eine Einrichtung zum Dämpfen von Schwingungen einer Brennkammer, wobei mindestens ein Resonator schwingungstechnisch mit der Brennkammer verbunden ist. Gemäß der Erfindung ist vorgesehen, dass der mindestens eine Resonator mit einer Vorkammer schwingungstechnisch verbunden ist und die Vorkammer über mindestens einen Durchtrittskanal mit der Brennkammer schwingungstechnisch verbunden ist. Damit wird erreicht, dass der oder die Resonatoren, die zur Dämpfung der Schwingungen verwendet werden, nicht mehr unmittelbar mit der Brennkammer, bzw. mit dem Innenraum der Brennkammer, in Verbindung stehen. Vielmehr besteht nur eine mittelbare Verbindung über die zwischengeschaltete Vorkammer. Damit können die Resonatoren in Bereichen angeordnet werden, die einer geringeren Temperaturbelastung bzw. geringeren Temperaturänderungen unterworfen sind. Trotzdem können die Schwingungen der Brennkammer über den Durchtrittskanal und die Vorkammer bis zu den Resonatoren gelangen und damit die Schwingungen der Brennkammer effektiv gedämpft werden.The invention relates to a device for damping vibrations of a combustion chamber, wherein at least one resonator is vibrationally connected to the combustion chamber. According to the invention, it is provided that the at least one resonator is vibrationally connected to an antechamber and the prechamber is connected in terms of vibration technology via at least one passage channel to the combustion chamber. This ensures that the one or more resonators that are used to dampen the vibrations, no longer directly with the combustion chamber, or with the interior of the combustion chamber in communication. Rather, there is only an indirect connection via the intermediate antechamber. Thus, the resonators can be arranged in areas that are subjected to a lower temperature load or lower temperature changes. Nevertheless, the vibrations of the combustion chamber via the passage channel and the antechamber can reach up to the resonators and thus the vibrations of the combustion chamber can be effectively damped.

Ein erstes Ausführungsbeispiel der Erfindung sieht vor, dass die Brennkammer an einen Einspritzkopf mit mindestens einem Einspritzelement angrenzt, der zum Einleiten einer gasförmigen Treibstoffströmung in die Brennkammer ausgebildet ist, und die Vorkammer strömungstechnisch vor dem mindestens einen Einspritzelement angeordnet ist. Es kann dabei ein einziger Treibstoffstrom vorgesehen sein, der der Brennkammer zugeführt wird. Es können auch zwei oder mehrere Treibstoffströme vorgesehen sein, die durch die Einspritzelemente der Brennkammer zugeführt werden und ggf. bereits in oder unmittelbar nach den Einspritzelementen vermischt werden. Die Vorkammer ist bei dieser Alternative in einem Bereich angeordnet, den mindestens einer der Treibstoffströme passiert, bevor er das oder die Einspritzelemente durchströmt. Damit liegen also die Einspritzelemente zwischen der Brennkammer bzw. dem Innenraum der Brennkammer und der Vorkammer.A first embodiment of the invention provides that the combustion chamber adjoins an injection head with at least one injection element, which is designed to introduce a gaseous fuel flow into the combustion chamber, and the pre-chamber is arranged in terms of flow before the at least one injection element. It can be provided a single fuel stream, which is supplied to the combustion chamber. It is also possible to provide two or more fuel streams which are supplied to the combustion chamber through the injection elements and, if appropriate, are already mixed in or immediately after the injection elements. The pre-chamber is arranged in this alternative in an area that passes at least one of the fuel streams before it flows through the injector or the injection elements. So that are the injection elements between the combustion chamber or the interior of the combustion chamber and the antechamber.

Alternativ dazu kann aber auch vorgesehen werden, dass die Brennkammer an einen Einspritzkopf mit mindestens einem Einspritzelement angrenzt, der zum Einleiten einer Treibstoffströmung in die Brennkammer ausgebildet ist, und die Vorkammer strömungstechnisch im Bereich des mindestens einen Einspritzelements angeordnet ist. Damit liegt die Vorkammer in einem Bereich, den mindestens einer der Treibstoffströme passiert, während er das oder die Einspritzelemente durchströmt. Damit sind also die Einspritzelemente und die Vorkammer strömungstechnisch nebeneinander vor der Brennkammer bzw. dem Innenraum der Brennkammer angeordnet.Alternatively, however, it can also be provided that the combustion chamber adjoins an injection head with at least one injection element, which is designed to introduce a fuel flow into the combustion chamber, and the pre-chamber is arranged in terms of flow in the region of the at least one injection element. Thus, the pre-chamber is in an area that passes at least one of the fuel streams, while it flows through the injection element or elements. Thus, therefore, the injection elements and the pre-chamber are fluidly arranged side by side in front of the combustion chamber or the interior of the combustion chamber.

In beiden Fällen kann mindestens einer der Treibstoffströme dazu dienen, durch eine Aktivkühlung der Resonatoren die Temperatur der Resonatoren weitgehend konstant zu halten. Hierfür kann insbesondere die Vorkammer strömungstechnisch mit einer Treibstoffströmung in Verbindung stehen, bevor diese den Innenraum der Brennkammer erreicht. Die Treibstoffströmung wird dabei nicht lediglich um einen Resonator herumgeleitet wie beispielsweise im Fall der DE 34 32 607 A1 , sondern sie erreicht den Innenraum des Resonators, so dass das Resonanzvolumen des Resonators selbst weitgehend konstant auf der Temperatur der Treibstoffströmung gehalten werden kann. Idealerweise steht der Resonator wie auch die Vorkammer mit einer gasförmigen Treibstoffströmung in Verbindung, da dann über die Treibstoffströmung eine besonders gute schwingungstechnische Verbindung zwischen Resonator und Brennkammer gewährleistet werden kann.In both cases, at least one of the fuel streams can serve to keep the temperature of the resonators largely constant by actively cooling the resonators. For this purpose, in particular, the prechamber fluidly communicate with a fuel flow before it reaches the interior of the combustion chamber. The fuel flow is thereby not only diverted around a resonator as in the case of DE 34 32 607 A1 but it reaches the interior of the resonator, so that the resonance volume of the resonator itself can be kept substantially constant at the temperature of the fuel flow. Ideally, the resonator as well as the antechamber with a gaseous fuel flow in conjunction, since then on the fuel flow, a particularly good vibration control connection between the resonator and the combustion chamber can be ensured.

Bevorzugt wird vorgesehen, dass der Durchtrittskanal als Teil eines Einspritzelements ausgebildet ist. Es können grundsätzlich aber auch separate Durchtrittskanäle vorgesehen sein, die eine schwingungstechnische Verbindung zwischen dem Innenraum der Brennkammer und der Vorkammer garantieren.It is preferably provided that the passage channel is formed as part of an injection element. In principle, however, it is also possible to provide separate passageways which guarantee a vibration-technical connection between the interior of the combustion chamber and the prechamber.

Die Resonatoren können beispielsweise als Helmholtz-Resonatoren oder als λ/4-Resonatoren ausgebildet sein. Solche Resonatoren sind grundsätzlich aus dem Stand der Technik hinreichend bekannt.The resonators can be designed, for example, as Helmholtz resonators or as λ / 4 resonators. Such resonators are basically well known from the prior art.

Ein spezielles Ausführungsbeispiel der vorliegenden Erfindung wird nachfolgend anhand der Figuren 1 bis 4 am Beispiel eines Raketentriebwerkes erläutert. Es zeigen:

Fig. 1:
Raketentriebwerk mit Helmholtz-Resonator vor dem Einspritzkopf
Fig. 2:
Raketentriebwerk mit λ/4-Resonatoren in einer Einspritzkopf-Deckplatte
Fig. 3:
Raketentriebwerk mit zweireihigen λ/4-Resonatoren vor dem Einspritzkopf
Fig. 4:
Raketentriebwerk mit λ/4-Resonatoren im Einspritzkopf
A specific embodiment of the present invention will be described below with reference to FIGS FIGS. 1 to 4 explained using the example of a rocket engine. Show it:
Fig. 1:
Rocket engine with Helmholtz resonator in front of the injection head
Fig. 2:
Rocket engine with λ / 4 resonators in an injection head cover plate
3:
Rocket engine with double-row λ / 4 resonators in front of the injection head
4:
Rocket engine with λ / 4 resonators in the injection head

Bei der Verbrennung von Treibstoffen in Raketenbrennkammern kommt es häufig während des Betriebes zur Ausbildung von unterschiedlichen hochfrequenten Schwingungen. Aufgrund der hohen thermischen und mechanischen Belastung führen derartige Schwingungen zu Schäden oder sogar zur Zerstörung der Raketentriebwerkes, wenn diese nicht rechtzeitig gedämpft werden.During the combustion of fuels in rocket combustion chambers, it often comes during operation to form different high-frequency vibrations. Due to the high thermal and mechanical load such vibrations lead to damage or even the destruction of the rocket engine, if they are not damped in time.

Eine Methode zur Dämpfung solcher Schwingungen ist die aus dem eingangs zitierten Stand der Technik bekannte Verwendung von akustischen Resonatoren. Hierbei unterschiedet man zwischen Helmoltz - Resonatoren und λ/4-Resonatoren. Beide Resonatoren-Typen bestehen aus kleinen Volumen, welche bei den Einrichtungen nach dem Stand der Technik direkt mit der Kammer verbunden sind. In diesen Resonatoren findet eine Dissipation der Schwingungsenergie statt, wenn die angeregte Frequenz der Kammer mit der Eigenfrequenz des Resonators übereinstimmt. Resonatoren sind schmalbandige Absorber und müssen aus diesem Grunde auf die zu dämpfende Frequenz abgestimmt werden. Helmoltz-Resonatoren dienen der Dämpfung in einem weiteren Frequenzbereich im Vergleich zu den λ/4-Resonatoren, welche auf eine diskrete Frequenz abgestimmt werden müssen. In beiden Fällen liegt neben der Abhängigkeit von den geometrischen Abmessungen eine starke Abhängigkeit von der Schallgeschwindigkeit und somit von der Temperatur vor. Somit besteht die Gefahr einer Verschiebung der Dämpfungsfrequenz durch die Aufheizung des Gases in den Resonatoren. Außerdem ist die genaue Abstimmung besonders der effektiveren λ/4-Resonatoren aufwendiger, da die Temperaturverhältnisse in den Resonatoren nur experimentell bestimmt werden können und somit eine Neuabstimmung in den meisten Fällen erforderlich ist. Außerdem sind derartige Systeme mit zusätzlichem konstruktivem Aufwand verbunden, aufgrund der ohnehin vorhandenen Kühlproblematik der Brennkammer in diesem Bereich. Axial von der Brennkammer nach oben, d.h. entgegen der Strömungsrichtung, angeordnete Resonatoren im Bereich des Einspritzkopfes bilden unerwünschte Rückströmzonen in diesem Bereich, wodurch ein zusätzlicher Wärmefluss in Richtung des Einspritzkopfes entsteht, was die Stabilität des Einspritzkopfes beeinflussen kann.One method for damping such vibrations is the use of acoustic resonators known from the cited prior art. A distinction is made between Helmoltz resonators and λ / 4 resonators. Both resonator types consist of small volumes, which are directly connected to the chamber in the prior art devices. In these resonators, a dissipation of the vibration energy takes place when the excited frequency of the chamber coincides with the natural frequency of the resonator. Resonators are narrow-band absorbers and must therefore be tuned to the frequency to be damped. Helmholtz resonators are used for attenuation in a wider frequency range compared to the λ / 4 resonators, which must be tuned to a discrete frequency. In both cases lies next to the Depending on the geometric dimensions of a strong dependence on the speed of sound and thus of the temperature before. Thus, there is a danger of a shift of the damping frequency by the heating of the gas in the resonators. In addition, the exact tuning of more effective λ / 4 resonators is more expensive, since the temperature conditions in the resonators can only be determined experimentally and thus a re-adjustment is required in most cases. In addition, such systems are associated with additional design effort, due to the already existing cooling problem of the combustion chamber in this area. Axially from the combustion chamber upwards, ie opposite the flow direction, arranged resonators in the region of the injection head form undesirable Rückströmzonen in this area, whereby an additional heat flow in the direction of the injection head is formed, which may affect the stability of the injection head.

Die vorliegende Erfindung bietet eine Resonatorenanordnung welche von den heißen Verbrennungsgasen und damit der Temperatur in der Brennkammer unabhängig ist. Gleichzeitig wird eine negative Beeinflussung der Anordnung der Einspritzelemente und der Brennkammerkühlung vermieden. Die Erfindung ist insbesondere bei Hauptstrom-Triebwerken sowie anderen Triebwerken mit gasförmiger Einspritzung einer von zwei oder mehreren Treibstoffkomponenten anwendbar. Bei Hauptstrom-Treibwerken werden gasförmige Abgase einer Treibstoffturbine wieder einem Treibstoffstrom (Hauptstrom) zugeführt und zusammen mit dem Treibstoffstrom in die Brennkammer geleitet. Eine weitere Anwendungsmöglichkeit stellen Expander-Cycle-Triebwerke dar, in denen der Antrieb der Treibstoffturbine mit einem gasförmigen Treibstoff wie Wasserstoff erfolgt. Zuvor wird der Treibstoff in flüssiger Form durch Kühlkanäle des Raketentriebwerkes geleitet und aufgrund der Wärmeaufnahme in gasförmigen Zustand überführt. Bei beiden Arten von Triebwerken liegen also gasförmige Treibstoffströme vor, die über Einspritzelemente in den Innenraum einer Brennkammer geleitet und dort verbrannt werden.The present invention provides a resonator assembly which is independent of the hot combustion gases and thus the temperature in the combustion chamber. At the same time a negative influence on the arrangement of the injection elements and the combustion chamber cooling is avoided. The invention is particularly applicable to mainstream engines and other gaseous injection engines of one or two or more fuel components. In mainstream propulsion systems, gaseous exhaust gases from a fuel turbine are returned to a fuel stream (main stream) and sent into the combustion chamber along with the fuel stream. Another application is expander cycle engines, in which the drive of the fuel turbine is carried out with a gaseous fuel such as hydrogen. Previously, the fuel is passed in liquid form through cooling channels of the rocket engine and converted into gaseous state due to the heat absorption. In both types of engines so there are gaseous fuel streams, which are passed through injection elements in the interior of a combustion chamber and burned there.

Fig. 1 bis 3 zeigen Beispiele eines Hauptstrom-Raketentriebwerkes. Das Triebwerk weist jeweils eine Brennkammer 1 auf, die stromaufwärts durch eine Einspritzplatte 2 eines Einspritzkopfes 3 begrenzt wird. In diesem Einspritzkopf 3 sind Einspritzelemente 4 angeordnet, die dazu dienen, eine oder mehrere Treibstoffströmungen in den Innenraum 9 der Brennkammer 1 zu leiten. Der Einspritzkopf 3 wird stromaufwärts durch eine Deckplatte 6 begrenzt. Die Einspritzelemente 4 sind entweder rohrförmig ausgebildet, sie können aber auch durch eine Kombination von Rohren und einer oder mehreren koaxialen Hülsen gebildet werden. Die Einspritzelemente 4 bzw. die Rohre oder Hülsen sind mit der Einspritzplatte 2 und/oder der Deckplatte 6 verbunden. Der Hauptstrom eines gasförmigen Treibstoffes sowie Turbinenabgase (Gas) gelangen in eine Vorkammer 7 vor dem Einspritzkopf und werden dann durch die Einspritzelemente 4 in den Innenraum 9 der Brennkammer 1 geleitet. Fig. 1 to 3 show examples of a mainstream rocket engine. The engine each has a combustion chamber 1, which is bounded upstream by an injection plate 2 of an injection head 3. In this injection head 3 injection elements 4 are arranged, which serve to direct one or more fuel flows into the interior 9 of the combustion chamber 1. The injection head 3 is bounded upstream by a cover plate 6. The injection elements 4 are either tubular, but they can also be formed by a combination of tubes and one or more coaxial sleeves. The injection elements 4 or the tubes or sleeves are connected to the injection plate 2 and / or the cover plate 6. The main flow of a gaseous fuel and turbine exhaust gases (gas) reach an antechamber 7 in front of the injection head and are then passed through the injection elements 4 into the interior 9 of the combustion chamber 1.

Fig. 4 zeigt dagegen ein Expander-Cycle-Triebwerk, bei dem ein gasförmiger Treibstoffstrom wie Wasserstoff (gH2) in eine Vorkammer 17 geleitet wird und von dort über ringförmige Spalte 8 zwischen einem Rohr 28 und einer Hülse eines koaxialen Einspritzelements 4 in den Innenraum 9 der Brennkammer gelangt. Über eine weitere Kammer 27 und das Rohr 28 gelangt ein weiterer, beispielsweise flüssiger Treibstoffstrom wie flüssiger Sauerstoff in den Innenraum 9 der Brennkammer 1. Fig. 4 on the other hand shows an expander-cycle engine, in which a gaseous fuel stream such as hydrogen (gH2) is passed into an antechamber 17 and from there via annular gaps 8 between a pipe 28 and a sleeve of a coaxial injection element 4 in the interior 9 of the combustion chamber passes , Via another chamber 27 and the tube 28, another, for example, liquid fuel stream such as liquid oxygen enters the interior 9 of the combustion chamber first

Hochfrequente Schwingungen, die in der Brennkammer 1 bei der Verbrennung des oder der Treibstoffe entstehen, pflanzen sich über Treibstoff-Gasströme, die durch die Einspritzelemente 4 strömen, stromaufwärts bis in eine Vorkammer 7, 17 fort. Daher kann eine Dämpfung der Schwingungen der Brennkammer 1 gemäß der Erfindung auch dadurch erfolgen, dass Resonatoren 5, 5a, 5b im Bereich der Vorkammern 7, 17 angeordnet werden, so dass sie strömungstechnisch mit der Vorkammer 7, 17 kommunizieren.High-frequency vibrations, which arise in the combustion chamber 1 during the combustion of the fuel or fuels themselves, via fuel gas streams flowing through the injection elements 4, upstream into an antechamber 7, 17 on. Therefore, an attenuation of the vibrations of the combustion chamber 1 according to the invention can also take place in that resonators 5, 5a, 5b are arranged in the region of the prechambers 7, 17, so that they communicate fluidically with the antechamber 7, 17.

Fig. 1 zeigt eine Anordnung eines Helmholtz-Resonators 5 in der Wand der Vorkammer 7. Dabei kann der Helmholtz-Resonator 5 als ringförmig umlaufende Kammer in der Wand der Vorkammer 7 ausgebildet sein, die über einen ringförmigen Durchtrittsspalt mit der Vorkammer 7 verbunden ist, wie in Fig. 1 dargestellt. Fig. 1 shows an arrangement of a Helmholtz resonator 5 in the wall of the antechamber 7. Here, the Helmholtz resonator 5 as a circular circumferential Chamber may be formed in the wall of the prechamber 7, which is connected via an annular passage gap with the prechamber 7, as in Fig. 1 shown.

Fig. 2 zeigt eine alternative Ausführungsform, wobei λ/4-Resonatoren 5 in Form von einseitig offenen Zylindern in der Deckplatte 6 des Einspritzkopfes 3 angeordnet sind. Wie in Fig. 2 dargestellt, können mehrere λ/4-Resonatoren 5 gleichförmig verteilt angeordnet sein. Im Fall der Fig. 2 sind die λ/4-Resonatoren 5 ringförmig um die Mittelachse der Deckplatte 6 angeordnet. Fig. 2 shows an alternative embodiment, wherein λ / 4 resonators 5 are arranged in the form of unilaterally open cylinders in the cover plate 6 of the injection head 3. As in Fig. 2 shown, a plurality of λ / 4 resonators 5 may be arranged uniformly distributed. In the case of Fig. 2 the λ / 4 resonators 5 are arranged annularly around the central axis of the cover plate 6.

In Fig. 3 ist eine Anordnung von λ/4-Resonatoren 5a, 5b in der Wand der Vorkammer 7 vorgesehen. Die λ/4-Resonatoren 5a, 5b sind dabei als Bohrungen in der Wand der Vorkammer 7 ausgebildet. Auch diese λ/4-Resonatoren 5a, 5b können gleichförmig verteilt angeordnet sein. Im Fall der Fig. 3 sind die λ/4-Resonatoren 5a, 5b in zwei übereinander liegenden Ringen in der Wand der Vorkammer 7 angeordnet.In Fig. 3 an arrangement of λ / 4 resonators 5a, 5b in the wall of the prechamber 7 is provided. The λ / 4 resonators 5a, 5b are formed as holes in the wall of the prechamber 7. These λ / 4 resonators 5a, 5b can also be distributed uniformly. In the case of Fig. 3 the λ / 4 resonators 5a, 5b are arranged in two superimposed rings in the wall of the prechamber 7.

Es können im Fall der Figuren 2 und 3 alle λ/4-Resonatoren 5, 5a, 5b grundsätzlich identisch ausgebildet sein, um genau eine definierte Schwingungsfrequenz zu dämpfen. Bevorzugt können aber die λ/4-Resonatoren 5, 5a, 5b unterschiedlich ausgebildet sein, so dass jeweils eine Gruppe von λ/4-Resonatoren 5, 5a, 5b an eine bestimmte Schwingungsfrequenz angepasst wird. Im Fall der Fig. 3 sind die unteren λ/4-Resonatoren 5a als kürzere Bohrungen ausgebildet und damit an höhere Schwingungsfrequenzen angepasst als die oberen λ/4-Resonatoren 5b, die als längere Bohrungen ausgebildet sind.It can in the case of Figures 2 and 3 all λ / 4 resonators 5, 5a, 5b are basically identical in design, in order to damp exactly one defined oscillation frequency. Preferably, however, the λ / 4 resonators 5, 5a, 5b may be formed differently, so that in each case a group of λ / 4 resonators 5, 5a, 5b is adapted to a specific oscillation frequency. In the case of Fig. 3 the lower λ / 4 resonators 5a are formed as shorter holes and thus adapted to higher vibration frequencies than the upper λ / 4 resonators 5b, which are formed as longer holes.

Bei der Verwendung einer derartigen Resonatoren-Anordnung erfolgt die Abstimmung auf die jeweilig zu dämpfende Frequenz, d.h. f(Kammer)=f(Resonator). Die Bestimmung der geometrischen Abmessungen hat unter Berücksichtigung der jeweiligen Temperaturverhältnisse des Gases im Bereich der Resonatoren zu erfolgen, da dieses einen direkten Einfluss auf die Schallgeschwindigkeit und somit auch auf die Frequenz hat.When using such a resonator arrangement, the tuning to the particular frequency to be attenuated, ie f (chamber) = f (resonator) . The determination of the geometrical dimensions has to take into account the respective temperature conditions of the gas in the region of the resonators, since this has a direct influence on the speed of sound and thus also on the frequency.

Gleiches gilt grundsätzlich für das Ausführungsbeispiel nach Fig. 4. Hier sind λ/4-Resonatoren 5 als Bohrungen in der Wand des Einspritzkopfes 3 in dem Bereich einer Vorkammer 17 vorgesehen, welche die Einspritzelemente 4 umschließt. Auch hier können also die λ/4-Resonatoren 5 gleichförmig verteilt, beispielsweise ringförmig, in der Wand des Einspritzkopfes 3 angeordnet sein und es können auch hier mehrere Gruppen von λ/4-Resonatoren 5 mit unterschiedlicher Anpassung an unterschiedliche Schwingungsfrequenzen vorliegen. Wie bereits beschrieben tritt gasförmiger Treibstoff wie gH2 in die Vorkammer 17 ein und wird über Ringspalte 8 in den Innenraum 9 der Brennkammer 1 eingeleitet. Dieser Strömungsweg des gasförmigen Treibstoffes stellt eine schwingungstechnische Verbindung zwischen dem Innenraum 9 der Brennkammer 1 und der Vorkammer 17 dar, analog zu den obigen Ausführungen zu den Figuren 1 bis 3. Damit gelangen diese Schwingungen bis zu den λ/4-Resonatoren 5 in der Wand der Vorkammer 17 und können dort durch die Resonatorwirkung der λ/4-Resonatoren 5 effektiv gedämpft werden.The same applies in principle for the embodiment according to Fig. 4 , Here λ / 4 resonators 5 are provided as holes in the wall of the injection head 3 in the region of an antechamber 17, which encloses the injection elements 4. Again, therefore, the λ / 4 resonators 5 can be uniformly distributed, for example, annularly, be arranged in the wall of the injection head 3 and there may also be several groups of λ / 4 resonators 5 with different adaptation to different vibration frequencies. As already described, gaseous fuel such as gH2 enters the pre-chamber 17 and is introduced via annular gaps 8 into the interior 9 of the combustion chamber 1. This flow path of the gaseous fuel is a vibration connection between the interior 9 of the combustion chamber 1 and the antechamber 17, analogous to the above statements to the FIGS. 1 to 3 , Thus, these vibrations reach the λ / 4 resonators 5 in the wall of the antechamber 17 and can be effectively attenuated there by the resonator effect of the λ / 4 resonators 5.

Der wesentliche Vorteil der Erfindung besteht in der weitgehend konstanten Temperatur des Gases in den Resonatoren 5, 5a, 5b während der gesamten Dauer des Betriebes des Triebwerkes. Weiterhin ergibt sich eine Vereinfachung der Konstruktion in dem Hochtemperaturbereich der Brennkammer 1, da im Bereich der Wand der Brennkammer 1 sowie in der Einspritzplatte außer der üblichen Kühlung keine weiteren Anordnungen wie Resonatoren mehr vorgesehen werden müssen. Außerdem ermöglicht die Bauweise nach der vorliegenden Erfindung die Unterbringung einer wesentlich höheren Anzahl von Resonatorebeispielsweisen, da die einzelnen Ausführungsbeispiele nach den Figuren 1 bis 3 auch kombiniert werden können, so dass Helmholtz-Resonatoren 5 und/oder λ/4-Resonatoren 5a, 5b in der Wand der Vorkammer 7 und/oder λ/4-Resonatoren 5 in der Deckplatte 6 vorgesehen werden können. The essential advantage of the invention is the largely constant temperature of the gas in the resonators 5, 5a, 5b during the entire duration of the operation of the engine. Furthermore, there is a simplification of the construction in the high-temperature region of the combustion chamber 1, since in the region of the wall of the combustion chamber 1 and in the injection plate in addition to the usual cooling no further arrangements such as resonators more must be provided. In addition, the construction according to the present invention enables a much higher number of resonator examples to be accommodated, since the individual embodiments according to FIGS FIGS. 1 to 3 can also be combined so that Helmholtz resonators 5 and / or λ / 4 resonators 5a, 5b in the wall of the prechamber 7 and / or λ / 4 resonators 5 can be provided in the cover plate 6.

Claims (3)

  1. Rocket engine, comprising a combustion chamber (1), a device for damping oscillations of the combustion chamber (1) and a pre-chamber (7),
    wherein the device for damping oscillations comprises at least one resonator (5, 5a, 5b) which is vibrationally connected to the combustion chamber (1),
    wherein the combustion chamber (1) is arranged upstream and adjacent to an injection plate (2) of an injection head (3), wherein at least one injection element (4) for introducing a gaseous fuel stream into the combustion chamber (1) is provided in the injection head (3),
    wherein the at least one resonator (5, 5a, 5b) is in fluid connection with the pre-chamber (7) and is vibrationally connected to the pre-chamber (7),
    and wherein the pre-chamber (7) is vibrationally connected to the combustion via at least one through channel (8),
    wherein the pre-chamber (7), which is fluidically connected to the gaseous fuel stream and from which the gaseous fluid stream is directed into the combustion chamber (1), in the direction of flow, is provided in front of the at least one injection element (4).
  2. Rocket engine, comprising a combustion chamber (1), a pre-chamber (17), a further chamber (27) and a device for damping oscillations of the combustion chamber (1),
    wherein the device for damping oscillations comprises at least one resonator (5) which is vibrationally connected to the combustion chamber (1),
    wherein the combustion chamber (1) is arranged upstream and adjacent to an injection head (3) which comprises at least one injection element (4) for introducing a first fuel stream into the combustion chamber (1),
    wherein the further chamber (27) is connected to the combustion chamber (1) via the injection element (4) so as to direct the first fuel stream into the combustion chamber,
    wherein the at least one resonator (5) is in fluid connection with the pre-chamber (17) and is vibrationally connected to the pre-chamber (17),
    and wherein the pre-chamber (17) is vibrationally connected to the combustion via at least one through channel (8),
    wherein the at least one injection element (4) and the pre-chamber (17) are fluidically arranged in parallel in front of the combustion chamber (1) and a second gaseous fluid stream is directed from the pre-chamber (17) into the combustion chamber (1).
  3. Rocket engine according to claim 1 or 2,
    characterized in that
    through channel (8, 18) is formed as a part of an injection element (4). an opening communicating with an open area of the injection head.
EP05732027.7A 2004-04-17 2005-04-07 Rocket engine with damping of vibration of the combustion chamber by resonators Expired - Lifetime EP1738112B1 (en)

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DE102004018725.8A DE102004018725B4 (en) 2004-04-17 2004-04-17 Damping of vibrations of a combustion chamber by resonators
PCT/DE2005/000622 WO2005100858A1 (en) 2004-04-17 2005-04-07 Damping of vibration of a combustion chamber by resonators

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US8033111B2 (en) 2011-10-11
US20080245072A1 (en) 2008-10-09
DE102004018725A1 (en) 2005-11-10
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EP1738112A1 (en) 2007-01-03
WO2005100858A1 (en) 2005-10-27

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