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EP1738112A1 - Damping of vibration of a combustion chamber by resonators - Google Patents

Damping of vibration of a combustion chamber by resonators

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Publication number
EP1738112A1
EP1738112A1 EP05732027A EP05732027A EP1738112A1 EP 1738112 A1 EP1738112 A1 EP 1738112A1 EP 05732027 A EP05732027 A EP 05732027A EP 05732027 A EP05732027 A EP 05732027A EP 1738112 A1 EP1738112 A1 EP 1738112A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
resonators
prechamber
injection
damping
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.)
Granted
Application number
EP05732027A
Other languages
German (de)
French (fr)
Other versions
EP1738112B1 (en
Inventor
Chris MÄDING
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ArianeGroup GmbH
Original Assignee
Astrium GmbH
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 Astrium GmbH filed Critical Astrium GmbH
Publication of EP1738112A1 publication Critical patent/EP1738112A1/en
Application granted granted Critical
Publication of EP1738112B1 publication Critical patent/EP1738112B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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 device for damping vibrations of a combustion chamber, at least one resonator being connected to the combustion chamber in terms of vibration technology.
  • damping chambers are arranged in the area of the injection head in a fuel distribution chamber and are connected to the combustion chamber in terms of vibrations via passage channels.
  • the arrangement in the fuel distribution chamber which is used, for example, to distribute hydrogen, ensures that the damping chambers are actively cooled.
  • relatively complex design measures are necessary for this. Nevertheless, it cannot be ruled out that hot combustion chamber combustion gases will penetrate directly into the damping chambers via the passage channels and lead to impairment or even destruction of the damping chambers.
  • 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, at least one resonator being connected to the combustion chamber in terms of vibration technology.
  • the at least one resonator is connected to a prechamber in terms of vibration technology and the prechamber is connected to the combustion chamber in terms of vibration technology via at least one passage channel. It is thereby achieved that the resonator or resonators that are used for damping the vibrations are no longer directly connected to the combustion chamber or to the interior of the combustion chamber. Rather, there is only an indirect connection via the intermediate prechamber.
  • the resonators can thus be arranged in areas which are subject to less temperature stress or less temperature changes. Nevertheless, the vibrations of the combustion chamber can reach the resonators via the passage channel and the prechamber and thus the vibrations of the combustion chamber can be effectively damped.
  • a first further development of the invention provides 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 prechamber is arranged upstream of the at least one injection element.
  • a single fuel flow can be provided, which is fed to the combustion chamber.
  • Two or more fuel flows can also be provided, which are supplied to the combustion chamber by the injection elements and, if appropriate, are already mixed in or immediately after the injection elements.
  • the prechamber is arranged in an area through which at least one of the fuel flows passes before it flows through the injection element or elements.
  • the injection elements are located between the combustion chamber or the interior of the combustion chamber and the prechamber.
  • the combustion chamber adjoins an injection head with at least one injection element, which is designed for introducing a fuel flow into the combustion chamber, and the prechamber is arranged in terms of flow technology in the region of the at least one injection element.
  • the prechamber thus lies in an area through which at least one of the fuel flows passes while it flows through the injection element or elements.
  • the injection elements and the prechamber are arranged next to each other in terms of flow in front of the combustion chamber or the interior of the combustion chamber.
  • the prechamber can, in particular, be connected in terms of flow to a fuel flow before it reaches the interior of the combustion chamber.
  • the fuel flow is not only directed around a resonator as in the case of DE 34 32 607 A1, for example, but it reaches the interior of the resonator, so that the resonance volume of the resonator itself can be kept largely constant at the temperature of the fuel flow.
  • the resonator as well as the prechamber are connected to a gaseous fuel flow, since a particularly good vibration connection between the resonator and the combustion chamber can then be guaranteed via the fuel flow.
  • the passage channel is designed as part of an injection element. In principle, however, separate passage channels can also be provided, which guarantee a vibration 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 generally well known from the prior art.
  • FIGS. 1 to 4 A special exemplary embodiment of the present invention is explained below with reference to FIGS. 1 to 4 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 ⁇ / 4 resonators in an injection head cover plate
  • Fig. 3 Rocket engine with double-row ⁇ / 4 resonators in front of the injection head
  • Fig. 4 Rocket engine with ⁇ / 4 resonators in the injection head
  • acoustic resonators known from the prior art cited at the beginning.
  • Helmoltz resonators Both types of resonators consist of small volumes which are connected directly to the chamber in the devices according to the prior art. Vibration energy is dissipated in these resonators when the excited frequency of the chamber matches the natural frequency of the resonator.
  • Resonators are narrow-band absorbers and therefore have to be tuned to the frequency to be damped.
  • Helmoltz resonators are used for damping in a wider frequency range compared to the ⁇ / 4 resonators, which have to be tuned to a discrete frequency.
  • Resonators arranged axially upward from the combustion chamber, ie counter to the direction of flow, in the area of the injection head form undesirable backflow zones in this area, as a result of which an additional heat flow occurs in the direction of the injection head, which can influence the stability of the injection head.
  • the present invention offers a resonator arrangement 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 main flow engines as well as other gaseous injection engines of one of two or more fuel components.
  • main flow engines gaseous exhaust gases from a fuel turbine are fed back into a fuel flow (main flow) and are passed together with the fuel flow into the combustion chamber.
  • main flow gaseous exhaust gases from a fuel turbine are fed back into a fuel flow (main flow) and are passed together with the fuel flow into the combustion chamber.
  • a gaseous fuel such as hydrogen.
  • the fuel is passed in liquid form through cooling channels of the rocket engine and converted into a gaseous state due to the heat absorption.
  • 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 delimited 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 stream of a gaseous fuel and turbine exhaust gases (gas) enter a prechamber 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 a prechamber 17 and from there via annular gaps 8 between a pipe 28 and a sleeve of a coaxial injection element 4 into the interior 9 reaches the combustion chamber.
  • a gaseous fuel stream such as hydrogen (gH2)
  • GSH2 hydrogen
  • a further, for example liquid, fuel flow such as liquid oxygen enters the interior 9 of the combustion chamber 1 via a further chamber 27 and the pipe 28.
  • the vibrations of the combustion chamber 1 according to the invention can also be damped by arranging resonators 5, 5a, 5b in the region of the prechambers 7, 17 so that they communicate with the prechamber 7, 17 in terms of flow.
  • the Helmholtz resonator 5 can be designed as a circumferential ring Chamber be formed in the wall of the prechamber 7, which is connected to the prechamber 7 via an annular passage gap, as shown in FIG. 1.
  • Fig. 2 shows an alternative embodiment, wherein ⁇ / 4 resonators 5 are arranged in the form of cylinders open on one side in the cover plate 6 of the injection head 3. As shown in FIG. 2, several ⁇ / 4 resonators 5 can be arranged uniformly distributed. In the case of FIG. 2, the ⁇ / 4 resonators 5 are arranged in a ring around the central axis of the cover plate 6.
  • FIG. 3 shows an arrangement of ⁇ / 4 resonators 5a, 5b in the wall of the prechamber 7.
  • the ⁇ / 4 resonators 5a, 5b are designed as bores in the wall of the prechamber 7.
  • These ⁇ / 4 resonators 5a, 5b can also be arranged in a uniformly distributed manner.
  • the ⁇ / 4 resonators 5a, 5b are arranged in two rings lying one above the other in the wall of the prechamber 7.
  • all the ⁇ / 4 resonators 5, 5a, 5b can in principle be of identical design in order to damp exactly one defined oscillation frequency.
  • the ⁇ / 4 resonators 5, 5a, 5b can preferably be designed differently, so that in each case one group of ⁇ / 4 resonators 5, 5a, 5b is adapted to a specific oscillation frequency.
  • the lower ⁇ / 4 resonators 5a are designed as shorter bores and are therefore adapted to higher oscillation frequencies than the upper ⁇ / 4 resonators 5b, which are designed as longer bores.
  • ⁇ / 4 resonators 5 are provided as bores in the wall of the injection head 3 in the region of a prechamber 7, which encloses the injection elements 4.
  • the ⁇ / 4 resonators 5 can be distributed uniformly, for example in a ring, in the wall of the injection head 3, and here too there can be several groups of ⁇ / 4 resonators 5 with different adaptation to different vibration frequencies.
  • gaseous fuel such as gH2 enters the pre-chamber 7 and is introduced into the interior 9 of the combustion chamber 1 via annular gaps 8.
  • This flow path of the gaseous fuel represents a vibration connection between the interior 9 of the combustion chamber 1 and the prechamber 7, analogous to the above explanations for FIGS. 1 to 3.
  • These vibrations thus reach the ⁇ / 4 resonators 5 in the wall the prechamber 7 and can be effectively damped there by the resonator effect of the ⁇ / 4 resonators 5.
  • the main advantage of the invention is the largely constant temperature of the gas in the resonators 5, 5a, 5b during the entire duration of 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, no further arrangements such as resonators need to be provided in addition to the usual cooling. In addition, the design according to the present invention enables a significantly higher number of resonator examples to be accommodated, since the individual exemplary embodiments according to 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.

Landscapes

  • 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)

Abstract

The invention relates to a device for damping the vibration of a combustion chamber (1), at least one resonator (5, 5a, 5b) being connected to the combustion chamber (1) in a vibration-damping manner. The resonator (5, 5a, 5b) is connected to a pre-combustion chamber (7, 17) in a vibration-damping manner, and the pre-combustion chamber (7) is connected to the combustion chamber (1) in a vibration-damping manner by means of a channel (8, 18).

Description

Dämpfung von Schwingungen einer Brennkammer durch Resonatoren Damping of vibrations in a combustion chamber by resonators

Die vorliegende Erfindung betrifft eine Einrichtung zum Dämpfen von Schwingungen einer Brennkammer, wobei mindestens ein Resonator schwingungstechnisch mit der Brennkammer verbunden ist.The present invention relates to a device for damping vibrations of a combustion chamber, at least one resonator being connected to the combustion chamber in terms of vibration technology.

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. Both DE 34 32 607 A1 and US Pat. No. 5,353,598 A describe devices for damping vibrations of a combustion chamber, at least one resonator or a damping chamber being connected directly or via passage channels to 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.A disadvantage of the devices according to US 5,353,598 A, however, is that the resonators are connected directly to the combustion chamber of the rocket engine. This can lead to overheating of the resonators due to hot combustion gases entering from the combustion chamber space. The result is that the resonators lose their resonance effect and accordingly can no longer contribute to damping 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. Aufgabe der vorliegenden Erfindung ist daher die Bereitstellung einer verbesserten Möglichkeit zum Dämpfen von Schwingungen einer Brennkammer mit Hilfe von Resonatoren.In DE 34 32 607 A1, damping chambers are arranged in the area of the injection head in a fuel distribution chamber and are connected to the combustion chamber in terms of vibrations via passage channels. The arrangement in the fuel distribution chamber, which is used, for example, to distribute hydrogen, ensures that the damping chambers are actively cooled. However, relatively complex design measures are necessary for this. Nevertheless, it cannot be ruled out that hot combustion chamber combustion gases will penetrate directly into the damping chambers via the passage channels and lead to impairment or even destruction of the damping chambers. 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.

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, at least one resonator being connected to the combustion chamber in terms of vibration technology. According to the invention, it is provided that the at least one resonator is connected to a prechamber in terms of vibration technology and the prechamber is connected to the combustion chamber in terms of vibration technology via at least one passage channel. It is thereby achieved that the resonator or resonators that are used for damping the vibrations are no longer directly connected to the combustion chamber or to the interior of the combustion chamber. Rather, there is only an indirect connection via the intermediate prechamber. The resonators can thus be arranged in areas which are subject to less temperature stress or less temperature changes. Nevertheless, the vibrations of the combustion chamber can reach the resonators via the passage channel and the prechamber and thus the vibrations of the combustion chamber can be effectively damped.

Eine erste Weiterbildung der Erfindung sieht vor, 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 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. 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.A first further development of the invention provides 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 prechamber is arranged upstream of the at least one injection element. A single fuel flow can be provided, which is fed to the combustion chamber. Two or more fuel flows can also be provided, which are supplied to the combustion chamber by the injection elements and, if appropriate, are already mixed in or immediately after the injection elements. In this alternative, the prechamber is arranged in an area through which at least one of the fuel flows passes before it flows through the injection element or elements. Thus, the injection elements are located between the combustion chamber or the interior of the combustion chamber and the prechamber. Alternatively, however, it can also be provided that the combustion chamber adjoins an injection head with at least one injection element, which is designed for introducing a fuel flow into the combustion chamber, and the prechamber is arranged in terms of flow technology in the region of the at least one injection element. The prechamber thus lies in an area through which at least one of the fuel flows passes while it flows through the injection element or elements. Thus, the injection elements and the prechamber are arranged next to each other in terms of flow in front of the combustion chamber or the interior of the combustion chamber.

In beiden Fällen kann mindestens einer der Treibstoff ströme 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 be used to keep the temperature of the resonators largely constant by actively cooling the resonators. For this purpose, the prechamber can, in particular, be connected in terms of flow to a fuel flow before it reaches the interior of the combustion chamber. The fuel flow is not only directed around a resonator as in the case of DE 34 32 607 A1, for example, but it reaches the interior of the resonator, so that the resonance volume of the resonator itself can be kept largely constant at the temperature of the fuel flow. Ideally, the resonator as well as the prechamber are connected to a gaseous fuel flow, since a particularly good vibration connection between the resonator and the combustion chamber can then be guaranteed via the fuel flow.

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. 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.It is preferably provided that the passage channel is designed as part of an injection element. In principle, however, separate passage channels can also be provided, which guarantee a vibration connection between the interior of the combustion chamber and the prechamber. The resonators can be designed, for example, as Helmholtz resonators or as λ / 4 resonators. Such resonators are generally 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:A special exemplary embodiment of the present invention is explained below with reference to FIGS. 1 to 4 using the example of a rocket engine. Show it:

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 EinspritzkopfFig. 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 Fig. 3: Rocket engine with double-row λ / 4 resonators in front of the injection head Fig. 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.When fuels are burned in rocket combustion chambers, different high-frequency vibrations often occur during operation. Due to the high thermal and mechanical stress, such vibrations lead to damage or even destruction of the rocket engine if it is not dampened 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 prior art cited at the beginning. A distinction is made between Helmoltz resonators and λ / 4 resonators. Both types of resonators consist of small volumes which are connected directly to the chamber in the devices according to the prior art. Vibration energy is dissipated in these resonators when the excited frequency of the chamber matches the natural frequency of the resonator. Resonators are narrow-band absorbers and therefore have to be tuned to the frequency to be damped. Helmoltz resonators are used for damping in a wider frequency range compared to the λ / 4 resonators, which have to be tuned to a discrete frequency. In both cases lies next to the Dependence on the geometric dimensions a strong dependence on the speed of sound and thus on the temperature before. There is therefore a risk of a shift in the damping frequency due to the heating of the gas in the resonators. In addition, the exact tuning, especially of the more effective λ / 4 resonators, is more complex, since the temperature conditions in the resonators can only be determined experimentally and a re-tuning is therefore necessary in most cases. In addition, systems of this type are associated with additional design outlay because of the cooling problems of the combustion chamber in this area, which are already present. Resonators arranged axially upward from the combustion chamber, ie counter to the direction of flow, in the area of the injection head form undesirable backflow zones in this area, as a result of which an additional heat flow occurs in the direction of the injection head, which can influence 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 Treibstoff ström 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. 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.The present invention offers a resonator arrangement 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 main flow engines as well as other gaseous injection engines of one of two or more fuel components. In main flow engines, gaseous exhaust gases from a fuel turbine are fed back into a fuel flow (main flow) and are passed together with the fuel flow into the combustion chamber. Another application is the expander cycle engine, in which the fuel turbine is driven with a gaseous fuel such as hydrogen. Before this, the fuel is passed in liquid form through cooling channels of the rocket engine and converted into a gaseous state due to the heat absorption. In both types of engines, there are gaseous fuel flows which are directed into the interior of a combustion chamber via injection elements and burned there. 1 through 3 show examples of a mainstream rocket engine. The engine each has a combustion chamber 1 which is delimited 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 delimited 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 stream of a gaseous fuel and turbine exhaust gases (gas) enter a prechamber 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 Treibstoff ström 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 a prechamber 17 and from there via annular gaps 8 between a pipe 28 and a sleeve of a coaxial injection element 4 into the interior 9 reaches the combustion chamber. A further, for example liquid, fuel flow such as liquid oxygen enters the interior 9 of the combustion chamber 1 via a further chamber 27 and the pipe 28.

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 that occur in the combustion chamber 1 during the combustion of the fuel or fuels propagate upstream into a prechamber 7, 17 via fuel gas flows that flow through the injection elements 4. Therefore, the vibrations of the combustion chamber 1 according to the invention can also be damped by arranging resonators 5, 5a, 5b in the region of the prechambers 7, 17 so that they communicate with the prechamber 7, 17 in terms of flow.

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.1 shows an arrangement of a Helmholtz resonator 5 in the wall of the prechamber 7. The Helmholtz resonator 5 can be designed as a circumferential ring Chamber be formed in the wall of the prechamber 7, which is connected to the prechamber 7 via an annular passage gap, as shown in FIG. 1.

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 cylinders open on one side in the cover plate 6 of the injection head 3. As shown in FIG. 2, several λ / 4 resonators 5 can be arranged uniformly distributed. In the case of FIG. 2, the λ / 4 resonators 5 are arranged in a ring 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.3 shows an arrangement of λ / 4 resonators 5a, 5b in the wall of the prechamber 7. The λ / 4 resonators 5a, 5b are designed as bores in the wall of the prechamber 7. These λ / 4 resonators 5a, 5b can also be arranged in a uniformly distributed manner. In the case of FIG. 3, the λ / 4 resonators 5a, 5b are arranged in two rings lying one above the other 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.In the case of FIGS. 2 and 3, all the λ / 4 resonators 5, 5a, 5b can in principle be of identical design in order to damp exactly one defined oscillation frequency. However, the λ / 4 resonators 5, 5a, 5b can preferably be designed differently, so that in each case one 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 designed as shorter bores and are therefore adapted to higher oscillation frequencies than the upper λ / 4 resonators 5b, which are designed as longer bores.

Bei der Verwendung einer derartigen Resonatoren-Anordnung erfolgt die Abstimmung auf die jeweilig zu dämpfende Frequenz, d.h. f(κammer)=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. 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 7 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 7 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 7 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 7 und können dort durch die Resonatorwirkung der λ/4-Resonatoren 5 effektiv gedämpft werden.When using such a resonator arrangement, the tuning is carried out to the respective frequency to be damped, ie f (κammer) = f (resonator) - the geometric dimensions must be determined taking 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. The same applies in principle to the exemplary embodiment according to FIG. 4. Here, λ / 4 resonators 5 are provided as bores in the wall of the injection head 3 in the region of a prechamber 7, which encloses the injection elements 4. Here, too, the λ / 4 resonators 5 can be distributed uniformly, for example in a ring, in the wall of the injection head 3, and here too there can 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 7 and is introduced into the interior 9 of the combustion chamber 1 via annular gaps 8. This flow path of the gaseous fuel represents a vibration connection between the interior 9 of the combustion chamber 1 and the prechamber 7, analogous to the above explanations for FIGS. 1 to 3. These vibrations thus reach the λ / 4 resonators 5 in the wall the prechamber 7 and can be effectively damped 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 main advantage of the invention is the largely constant temperature of the gas in the resonators 5, 5a, 5b during the entire duration of 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, no further arrangements such as resonators need to be provided in addition to the usual cooling. In addition, the design according to the present invention enables a significantly higher number of resonator examples to be accommodated, since the individual exemplary embodiments according to 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

Patentansprüche claims 1. Einrichtung zum Dämpfen von Schwingungen einer Brennkammer (1), wobei mindestens ein Resonator (5, 5a, 5b) schwingungstechnisch mit der Brennkammer (1 ) verbunden ist, dadurch gekennzeichnet, dass der mindestens eine Resonator (5, 5a, 5b) mit einer Vorkammer (7, 17) schwingungstechnisch verbunden ist und die Vorkammer (7) über mindestens einen Durchtrittskanal (8, 18) mit der Brennkammer (1 ) schwingungstechnisch verbunden ist.1. Device for damping vibrations of a combustion chamber (1), at least one resonator (5, 5a, 5b) being connected to the combustion chamber (1) in terms of vibration technology, characterized in that the at least one resonator (5, 5a, 5b) is connected to a prechamber (7, 17) is connected in terms of vibration technology and the prechamber (7) is linked with the combustion chamber (1) in terms of vibration technology via at least one passage channel (8, 18). 2. Einrichtung nach Anspruch 1 , dadurch gekennzeichnet, dass die Brennkammer (1) an einen Einspritzkopf (3) mit mindestens einem Einspritzelement (4) angrenzt, der zum Einleiten einer Treibstoffströmung in die Brennkammer (1 ) ausgebildet ist, und die Vorkammer (7, 17) strömungstechnisch vor dem mindestens einen Einspritzelement (4) angeordnet ist.2. Device according to claim 1, characterized in that the combustion chamber (1) adjoins an injection head (3) with at least one injection element (4) which is designed to introduce a fuel flow into the combustion chamber (1), and the prechamber (7 , 17) is arranged upstream of the at least one injection element (4). 3. Einrichtung nach Anspruch 1 , dadurch gekennzeichnet, dass die Brennkammer (1 ) an einen Einspritzkopf (3) mit mindestens einem Einspritzelement (4) angrenzt, der zum Einleiten einer Treibstoffströmung in die Brennkammer (1 ) ausgebildet ist, und die Vorkammer (7, 17) strömungstechnisch im Bereich des mindestens einen Einspritzelements (4) angeordnet ist. 3. Device according to claim 1, characterized in that the combustion chamber (1) adjoins an injection head (3) with at least one injection element (4), which is designed to introduce a fuel flow into the combustion chamber (1), and the prechamber (7 , 17) is arranged fluidically in the area of the at least one injection element (4). 4. Einrichtung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Vorkammer (7, 17) strömungstechnisch mit einer Treibstoffströmung in Verbindung steht.4. Device according to one of claims 1 to 3, characterized in that the prechamber (7, 17) is fluidically connected to a fuel flow. 5. Einrichtung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass der Durchtrittskanal (8, 18) als Teil eines Einspritzelements (4) ausgebildet ist. 5. Device according to one of claims 1 to 4, characterized in that the passage channel (8, 18) is designed as part of an injection element (4).
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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