EP1738112B1 - Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs - Google Patents

Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs 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
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.)
Active
Application number
EP05732027.7A
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German (de)
English (en)
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EP1738112A1 (fr
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
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ArianeGroup GmbH
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Publication of EP1738112A1 publication Critical patent/EP1738112A1/fr
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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 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.

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)

Claims (3)

  1. Moteur de fusée, comprenant une chambre de combustion (1), un moyen pour amortir les vibrations de la chambre de combustion (1) et une préchambre (7),
    dans lequel le moyen pour amortir les vibrations comprend au moins un résonateur (5, 5a, 5b) relié de manière vibratoire à la chambre de combustion (1),
    dans lequel la chambre de combustion (1) est contiguë, du côté amont, à une plaque d'injection (2) d'une tête d'injection (3), au moins un élément d'injection (4) étant prévu dans la tête d'injection (3) pour introduire un flux de combustible gazeux dans la chambre de combustion (1),
    dans lequel ledit au moins un résonateur (5, 5a, 5b) est disposé en liaison fluidique avec la préchambre (7) et relié de manière vibratoire à la préchambre (7),
    et dans lequel la préchambre (7) est reliée de manière vibratoire à la chambre de combustion (1) par au moins un canal de passage (8),
    dans lequel la préchambre (7) qui est reliée fluidiquement au flux de combustible gazeux et à partir de laquelle le flux de combustible gazeux est conduit dans la chambre de combustion (1), est prévue en amont dudit au moins un élément d'injection (4) dans la direction du flux.
  2. Moteur de fusée, comprenant une chambre de combustion (1), une préchambre (17), une autre chambre (27) et un moyen pour amortir les vibrations de la chambre de combustion (1),
    dans lequel le moyen pour amortir les vibrations comprend au moins un résonateur (5) relié de manière vibratoire à la chambre de combustion (1),
    dans lequel la chambre de combustion (1) est contiguë, du côté amont, à une tête d'injection (3) qui comprend au moins un élément d'injection (4) pour introduire un premier flux de combustible dans la chambre de combustion (1),
    dans lequel l'autre chambre (27) est reliée à la chambre de combustion (1) par l'élément d'injection (4) pour conduire le premier flux de combustible dans la chambre de combustion,
    dans lequel ledit au moins un résonateur (5) est disposé en liaison fluidique avec la préchambre (17) et relié de manière vibratoire à la préchambre (17),
    et dans lequel la préchambre (17) est reliée de manière vibratoire à la chambre de combustion (1) par au moins un canal de passage (18),
    dans lequel ledit au moins un élément d'injection (4) et la préchambre (17) sont disposés fluidiquement l'un à côté de l'autre en amont de la chambre de combustion (1), et un second flux de combustible gazeux est conduit à partir de la préchambre (17) dans la chambre de combustion (1).
  3. Moteur de fusée selon la revendication 1 ou 2,
    caractérisé en ce que
    le canal de passage (8, 18) est conçu comme une partie d'un élément d'injection (4).
EP05732027.7A 2004-04-17 2005-04-07 Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs Active EP1738112B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004018725.8A DE102004018725B4 (de) 2004-04-17 2004-04-17 Dämpfung von Schwingungen einer Brennkammer durch Resonatoren
PCT/DE2005/000622 WO2005100858A1 (fr) 2004-04-17 2005-04-07 Amortissement de vibrations d'une chambre de combustion au moyen de resonateurs

Publications (2)

Publication Number Publication Date
EP1738112A1 EP1738112A1 (fr) 2007-01-03
EP1738112B1 true EP1738112B1 (fr) 2019-07-03

Family

ID=34964533

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05732027.7A Active EP1738112B1 (fr) 2004-04-17 2005-04-07 Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs

Country Status (4)

Country Link
US (1) US8033111B2 (fr)
EP (1) EP1738112B1 (fr)
DE (1) DE102004018725B4 (fr)
WO (1) WO2005100858A1 (fr)

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EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
US8733106B2 (en) * 2011-05-03 2014-05-27 General Electric Company Fuel injector and support plate
WO2013043078A1 (fr) * 2011-09-22 2013-03-28 General Electric Company Capuchon de chambre de combustion pour amortissement de dynamiques à basse fréquence
US8532847B1 (en) * 2012-09-28 2013-09-10 Fukashi Andoh Vibration suppressing device for spacecraft
DE102013213860A1 (de) * 2013-07-16 2015-01-22 Siemens Aktiengesellschaft Brennerdüsenträger mit Resonatoren
CN106461222B (zh) 2014-05-19 2019-03-15 西门子公司 具有共振器的燃烧器装置
DE102015218687A1 (de) * 2015-09-29 2017-04-13 Siemens Aktiengesellschaft Brenneranordnung für eine Ringbrennkammer mit Resonatoren
DE102016209650B4 (de) 2016-06-02 2019-03-14 Arianegroup Gmbh Einspritzvorrichtung für ein raketentriebwerk
DE102017127831A1 (de) 2017-11-24 2019-05-29 Arianegroup Gmbh Einspritzkopf für ein triebwerk, triebwerk und rakete
DE102019110258A1 (de) 2019-04-15 2020-10-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Injektorvorrichtung für eine Triebwerksvorrichtung, Triebwerksvorrichtung und Luft- und/oder Raumfahrzeug
RU2738391C2 (ru) * 2019-04-30 2020-12-11 Акционерное общество "Государственный космический научно-производственный центр имени М.В. Хруничева" Камера сгорания
EP3916212B1 (fr) 2020-05-28 2022-09-28 ArianeGroup GmbH Élément d'injection pour moteur, plaque avant pour une tête d'injecteur et procédé de fabrication d'un élément d'injection
CN112746910A (zh) * 2020-10-29 2021-05-04 北京航天动力研究所 一种抑制高频不稳定燃烧的喷注器
US11988113B2 (en) * 2020-12-18 2024-05-21 The Boeing Company Ducted inlet for reducing flow oscillations

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Also Published As

Publication number Publication date
WO2005100858A1 (fr) 2005-10-27
DE102004018725B4 (de) 2015-02-12
EP1738112A1 (fr) 2007-01-03
US8033111B2 (en) 2011-10-11
US20080245072A1 (en) 2008-10-09
DE102004018725A1 (de) 2005-11-10

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