EP1571650B1 - Device for producing acoustic fields with a defined modal composition - Google Patents

Device for producing acoustic fields with a defined modal composition Download PDF

Info

Publication number
EP1571650B1
EP1571650B1 EP04090083A EP04090083A EP1571650B1 EP 1571650 B1 EP1571650 B1 EP 1571650B1 EP 04090083 A EP04090083 A EP 04090083A EP 04090083 A EP04090083 A EP 04090083A EP 1571650 B1 EP1571650 B1 EP 1571650B1
Authority
EP
European Patent Office
Prior art keywords
flow
arrangement
accordance
obstacles
shedding
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.)
Expired - Fee Related
Application number
EP04090083A
Other languages
German (de)
French (fr)
Other versions
EP1571650A1 (en
Inventor
Marco Dr. Rose
Fredi Dr. Holste
Frank Dr. Arnold
Alastair David Moore
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.)
Rolls Royce Deutschland Ltd and Co KG
Rolls Royce PLC
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Rolls Royce PLC
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 Rolls Royce Deutschland Ltd and Co KG, Rolls Royce PLC filed Critical Rolls Royce Deutschland Ltd and Co KG
Priority to EP04090083A priority Critical patent/EP1571650B1/en
Priority to DE502004009480T priority patent/DE502004009480D1/en
Priority to US11/068,980 priority patent/US7516815B2/en
Publication of EP1571650A1 publication Critical patent/EP1571650A1/en
Application granted granted Critical
Publication of EP1571650B1 publication Critical patent/EP1571650B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K15/00—Acoustics not otherwise provided for
    • G10K15/04—Sound-producing devices
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/175—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using interference effects; Masking sound
    • G10K11/178—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using interference effects; Masking sound by electro-acoustically regenerating the original acoustic waves in anti-phase
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K2210/00—Details of active noise control [ANC] covered by G10K11/178 but not provided for in any of its subgroups
    • G10K2210/30—Means
    • G10K2210/321—Physical
    • G10K2210/3212—Actuator details, e.g. composition or microstructure

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft eine Anordnung zur Erzeugung von Schallfeldern bestimmter modaler Zusammensetzung als simulierte Schallquelle für akustische Untersuchungen, insbesondere zur Simulation des von Rotor-Stator-Anordnungen von Turbomaschinen erzeugten Schalls oder als Gegenschallfeld zur aktiven Schallminderung.The invention relates to an arrangement for generating sound fields of certain modal composition as a simulated sound source for acoustic examinations, in particular for simulating the sound generated by rotor-stator arrangements of turbomachinery or as a counter-sound field for active noise reduction.

In vielen technischen Bereichen ist die Anwendung und der Betrieb bestimmter Vorrichtungen, wie beispielsweise Flugzeugantriebe, Fahrzeugantriebe, Verdichter, Gasturbinen, Lüftungsanlagen, Ventilatoren und dgl., mit einem unerwünschten, aero-akustisch bedingten Geräuschpegel verbunden. In solchen Anlagen, beispielsweise bei den Rotor-Stator-Systemen von Verdichtern und Gasturbinen, ist die Untersuchung der Ursachen für die Entstehung und Ausbreitung des Luftschalls oder von zur Geräuschdämpfung getroffenen Maßnahmen mit einer realitätsnahen Versuchsanlage mit einem erheblichen technischen Aufwand verbunden. Bei Turbomaschinen sind derartige Untersuchungen mit Rotor-Stator -Anordnungen möglich, die wegen der erforderlichen Antriebseinheiten, der beweglichen Teile, des hohen Gewichts und der notwendigen Steuermechanismen aufwendig und teuer sind. Außerdem ist auch die Erzeugung eines simulierten Schallfeldes zu Testzwecken oder als Gegenschallfeld zur aktiven Schallminderung, wie beispielsweise in der US 5 702 230 oder der US 5 590 849 beschrieben, mit einem beträchtlichen apparativen, steuerungstechnischen und energetischen Aufwand für die Anordnung und den Betrieb von aktiven Elementen, wie beispielsweise Lautsprecher oder piezo-elektrische Geräuschquellen, verbunden. Zusätzliche Schwierigkeiten bereiten insbesondere die Bereitstellung leistungsfähiger Aktuatoren, deren hohes Gewicht, deren Energiebedarf und deren Betrieb bei hohen Temperaturen, Drücken und Strömungsgeschwindigkeiten.In many technical fields, the application and operation of certain devices, such as aircraft engines, vehicle drives, compressors, gas turbines, ventilation systems, fans, and the like, is associated with undesirable aero-acoustic noise levels. In such systems, for example in the rotor-stator systems of compressors and gas turbines, the investigation of the causes of the formation and propagation of airborne sound or measures taken for noise reduction with a realistic test facility is associated with considerable technical effort. In turbomachinery such investigations are possible with rotor-stator arrangements, which are complicated and expensive because of the required drive units, the moving parts, the high weight and the necessary control mechanisms. In addition, the generation of a simulated sound field for test purposes or as a counter-field for active noise reduction, such as in the US 5,702,230 or the US 5,590,849 described, associated with a considerable apparatus, control technology and energy costs for the arrangement and operation of active elements, such as speakers or piezoelectric noise sources. In particular, the provision of powerful actuators, their high weight, their energy requirements and their operation at high temperatures, pressures and flow velocities pose additional difficulties.

US 2 987 033 beschreibt auch eine Anordnung zur Erzeugung simulierter Schallquellen für akustische Untersuchungen. US 2,987,033 also describes an arrangement for generating simulated sound sources for acoustic examinations.

Der Erfindung liegt die Aufgabe zugrunde, eine Anordnung zur Erzeugung von Schallfeldern bestimmten modalen Inhalts, im folgenden auch als Modengenerator bezeichnet, zur Anwendung als simulierte Schallquelle für wissenschaftlich-technische Untersuchungen oder als Gegenschallfeld zur aktiven Schallminderung anzugeben, die einfach ausgebildet ist und mit geringem Kostenaufwand hergestellt und betrieben werden kann.The invention has for its object to provide an arrangement for generating sound fields specific modal content, hereinafter referred to as a mode generator for use as a simulated sound source for scientific-technical studies or as a counter-field for active noise reduction, which is simple and low cost can be manufactured and operated.

Erfindungsgemäß wird die Aufgabe mit einer gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Vorrichtung gelöst. Weitere Merkmale und vorteilhafte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen.According to the invention, the object is achieved with a device designed according to the features of patent claim 1. Further features and advantageous developments of the invention will become apparent from the dependent claims.

Der Grundgedanke der Erfindung besteht mit anderen Worten in der Bereitstellung eines Modengenerators, der einen von einem fließfähigen Medium, insbesondere einem Gas, durchströmten Strömungskanal mit in diesem ausgebildeten Strömungshindernissen umfasst. Die Strömungshindernisse sind so geformt, dass von diesen Wirbel aus dem strömenden Medium abgelöst werden. Die Form und Größe der Strömungshindernisse und die Strömungsgeschwindigkeit in dem Strömungskanal sind so gewählt, dass eine bestimmte Ablösefrequenz der Wirbel nicht unterschritten wird. Die Anzahl und räumliche Anordnung der Strömungshindernisse ist so eingestellt, dass ein durch die Gesamtheit der abgelösten Wirbel bedingtes, sich periodisch zeitlich und räumlich veränderndes Druckfeld erzeugt wird. Dieses Druckfeld regt ein Schallfeld von bestimmter modaler Zusammensetzung an, das auf die Wirbelablösung synchronisierend zurückwirkt. Der so durch Rückkopplung gebildete Resonanzkreis, bei dem die Wirbelablösefrequenz im Bereich der Resonanzfrequenz des anzuregenden Schallfeldes ist, stellt eine Schallwelle dar. Mit einfachsten Mitteln kann damit eine Schallquelle für bestimmte akustische Untersuchungen, zum Beispiel unter Fortfall der Stator-Rotor-Anordnung bei Triebwerksuntersuchungen, simuliert werden. Gleichermaßen können mit einer derart einfachen und kostengünstigen Anordnung Gegenschallfelder zur aktiven Schallminderung erzeugt werden. Der Apparate-, Gewichts- und Kostenaufwand kann erheblich reduziert werden.In other words, the basic idea of the invention consists in the provision of a mode generator which comprises a flow channel through which a flowable medium, in particular a gas, flows with flow obstacles formed therein. The flow obstacles are shaped so that these swirls are released from the flowing medium. The shape and size of the flow obstacles and the flow velocity in the flow channel are chosen so that a certain frequency of removal of the vortex is not exceeded. The number and spatial arrangement of the flow obstacles is set so that one through the entirety of the detached Whirl conditional, periodically and spatially changing pressure field is generated. This pressure field stimulates a sound field of a certain modal composition, which reacts synchronously to the vortex shedding. The resonant circuit thus formed by feedback, in which the vortex shedding frequency is in the range of the resonance frequency of the sound field to be excited, represents a sound wave. With the simplest means can thus a sound source for certain acoustic examinations, for example, with elimination of the stator-rotor arrangement in engine examinations, be simulated. Similarly, with such a simple and inexpensive arrangement counter-noise fields for active noise reduction can be generated. The apparatus, weight and cost can be significantly reduced.

Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:

Fig. 1
eine Seitenansicht einer erfindungsgemäßen Vorrichtung zur Erzeugung modaler Schallfelder (aero-akustischer Modengenerator);
Fig. 2
die Vorrichtung nach Fig. 1 in einem Längsschnitt;
Fig. 3
eine perspektivische Darstellung der Vorrichtung nach Fig. 1;
Fig. 4
eine Seitenansicht einer anderen Ausführungsform einer Vorrichtung zur Erzeugung modaler Schallfelder;
Fig. 5
die Vorrichtung nach Fig. 4 in einem Längsschnitt;
Fig. 6
eine perspektivische Darstellung eines Strömungshindernisses gemäß der Ausführungsform nach Fig. 4;
Fig. 7
eine Schnittansicht der Stützstange des Strömungshindernisses nach Fig. 6;
Fig. 8
eine Schnittansicht des eine Wirbelablösung bewirkenden Strömungshindernisses nach Fig. 6; und
Fig. 9
eine Darstellung des Wirkprinzips der Vorrichtung zur Erzeugung modaler Schallfelder.
An embodiment of the invention will be explained in more detail with reference to the drawing. Show it:
Fig. 1
a side view of a device according to the invention for generating modal sound fields (aero-acoustic mode generator);
Fig. 2
the device after Fig. 1 in a longitudinal section;
Fig. 3
a perspective view of the device according to Fig. 1 ;
Fig. 4
a side view of another embodiment of a device for generating modal sound fields;
Fig. 5
the device after Fig. 4 in a longitudinal section;
Fig. 6
a perspective view of a flow obstacle according to the embodiment according to Fig. 4 ;
Fig. 7
a sectional view of the support rod of the flow obstacle after Fig. 6 ;
Fig. 8
a sectional view of the vortex shedding causing flow obstacle after Fig. 6 ; and
Fig. 9
a representation of the active principle of the device for generating modal sound fields.

Gemäß der Zeichnung sind in einem Strömungskanal 1 an dessen Innenumfang in regelmäßigem Abstand verteilt angeordnete Strömungshindernisse, gemäß den Figuren 1 bis 3 in Form von nur in einer Querschnittsebene angeordneten, senkrecht von der Kanalinnenwand abstrebenden, durchgehend rechteckigen Stegen 10 von gleicher Länge mit abgerundeten Kanten, vorgesehen. Das heißt, die Strömungshindernisse 2 können zur Erzeugung unterschiedlicher modaler Schallfelder auch andere Querschnittsformen aufweisen, weiter in den Kanalinnenraum hineinreichen oder näher an der Kanalwand liegen oder, wie in den Figuren 4 bis 8 dargestellt, auf Stützen im Kanal angeordnet sein oder auch als in die Kanalwand eingeformte Vertiefungen (nicht dargestellt) ausgebildet sein. Insbesondere ist die Querschnittsform der Strömungshindernisse 2 für die Ausbildung des Schallfeldes in dem Strömungskanal 1 von Bedeutung. Des Weiteren können die Strömungshindernisse 2 in ein und demselben Strömungskanal 1 auch unterschiedlich ausgebildet sein. Schließlich ist die Anordnung und Anzahl der Strömungshindernisse 2 variabel. Das heißt, die Strömungshindernisse können einzeln oder in einer größeren Anzahl auch in zwei oder mehreren Querschnittsebenen des Strömungskanals 1, und zwar auch versetzt zueinander angeordnet sein (jeweils nicht dargestellt). Der Strömungskanal 1 wird in Richtung des Pfeils 3 von einem fließfähigen Medium, hier einem Gas, durchströmt. In dem vorliegenden Fall der Simulation des Schallfeldes einer Rotor-Stator-Anordnung für eine Gasturbine, Verdichter oder dgl. handelt es sich um ein Heißgas oder ein Kaltgas. Die Ausbreitung des Schalls erfolgt gemäß dem Pfeil 4 in Strömungsrichtung 3 und entgegen der Strömungsrichtung 3. Bei der in den Figuren 4 bis 8 gezeigten Ausführungsvariante sind zur Ausbildung der Strömungshindernisse 2 Stege 11 vorgesehen, bei denen auf einer Stützstange 11a im Abstand von der Kanalinnenwand jeweils zwei Wirbelablöseabschnitte 11b im Abstand voneinander angeformt sind. Das Profil der Stützstange 11a ist, wie Fig. 7 zeigt, so geformt, das von diesem im Wesentlichen keine Wirbel abgelöst werden können.According to the drawing are distributed in a flow channel 1 at its inner circumference at regular intervals arranged flow obstacles, according to the FIGS. 1 to 3 arranged in the form of only in a cross-sectional plane, perpendicular from the channel inner wall abstrebenden, continuous rectangular webs 10 of equal length with rounded edges, provided. This means that the flow obstacles 2 can also have other cross-sectional shapes for generating different modal sound fields, extend further into the channel interior or lie closer to the channel wall or, as in FIGS FIGS. 4 to 8 represented, be arranged on supports in the channel or as formed in the channel wall recesses (not shown). In particular, the cross-sectional shape of the flow obstacles 2 for the formation of the sound field in the flow channel 1 of importance. Furthermore, the flow obstacles 2 can also be designed differently in one and the same flow channel 1. Finally, the arrangement and number of flow obstacles 2 is variable. That is, the flow obstacles may individually or in a larger number in two or more cross-sectional planes the flow channel 1, and that also be offset from each other (each not shown). The flow channel 1 is flowed through in the direction of the arrow 3 by a flowable medium, in this case a gas. In the present case, the simulation of the sound field of a rotor-stator assembly for a gas turbine, compressor or the like is a hot gas or a cold gas. The propagation of the sound is carried out according to the arrow 4 in the flow direction 3 and counter to the flow direction 3. When in the FIGS. 4 to 8 2, webs 11 are provided for forming the flow obstacles, in which two vortex separating sections 11b are formed at a distance from each other on a support rod 11a at a distance from the channel inner wall. The profile of the support rod 11a is how Fig. 7 shows, shaped, can be detached from this substantially no vortex.

Der Wirkungsmechanismus des oben beschriebenen Schallfeldgenerators (aero-akustischer Modengenerator) zur Umwandlung der Strömungsenergie des Mediums in akustische Energie eines sich in Strömungsrichtung und entgegen der Strömungsrichtung fortpflanzenden Schallfeldes wird anhand der Fig. 9 wie folgt beschrieben: Aufgrund der Strömung lösen sich am Strömungshindernis 2 periodisch Wirbel 5 und 6 ab, die in Strömungsrichtung hinter dem Strömungshindernis 2 eine Wirbelstraße 7 bilden. Die Ablösefrequenz der Wirbel 5, 6 hängt von der Strömungsgeschwindigkeit und der Form und Größe des jeweiligen Strömungshindernisses 2 ab. Infolge der durch die periodische Wirbelablösung erzeugten Wechseldrücke entstehen Töne, die sich bei und oberhalb einer bestimmten Frequenz (cut-on-Frequenz, Resonanzfrequenz) im Strömungskanal 1 ausbreiten können. Diese Frequenz hängt von der Kanalgeometrie (Querschnittsform, Abmessungen), von der Strömungsgeschwindigkeit und der Gastemperatur ab. Die durch die periodische Wirbelablösung erzeugten Töne bilden in dem Strömungskanal 1 ein akustisches Druckfeld 8, das heißt, ein modales Schallfeld oder mindestens eine akustische Mode mit in Umfangsrichtung und/oder radialer Richtung, variabler Amplitude, die synchron auf das Strömungshindernis 2 und die von diesem ausgehende periodische Ablösung der Wirbel zurückwirkt (feedback loop gemäß Pfeil 9). Es entsteht ein geschlossener Resonanzkreis zwischen der Wirbelablösung und der akustischen Mode 8 sowie der akustischen Mode 8 und der Wirbelablösung, das heißt, die akustische Mode prägt der Wirbelablösung ihre Frequenz und Phase auf und durch die synchrone Rückkopplung der Moden auf die Wirbelbildung bildet sich ein hoher Schalldruckpegel aus, der in der Lage ist, bestimmte Lärmverhältnisse in technischen Anlagen, zum Beispiel in einer Rotor-Stator-Anordnung, zu simulieren oder auch - phasenverschoben - zur aktiven Schallminderung eines vorhandenen Schalldruckpegels benutzt werden kann. Die für die Schallerzeugung erforderliche Energie wird der Energie des strömenden Mediums entzogen, jedoch ist der Energieentzug vernachlässigbar klein und ohne Einfluss auf die Wirkung der zu untersuchenden technischen Vorrichtung, z.B. einer Rotor-Stator-Anordnung einer Turbomaschine.The mechanism of action of the above-described sound field generator (aero-acoustic mode generator) for converting the flow energy of the medium into acoustic energy of a propagating in the flow direction and against the flow direction of the sound field is based on Fig. 9 As a result of the flow, vortexes 5 and 6, which form a vortex street 7 behind the flow obstacle 2 in the flow direction, detach periodically at the flow obstacle 2. The separation frequency of the vortices 5, 6 depends on the flow velocity and the shape and size of the respective flow obstacle 2. As a result of the alternating pressures generated by the periodic vortex shedding tones that can propagate at and above a certain frequency (cut-on frequency, resonance frequency) in the flow channel 1. This frequency depends on the channel geometry (cross-sectional shape, dimensions), flow rate and gas temperature. The by the periodic Vortex shedding generated tones form in the flow channel 1, an acoustic pressure field 8, that is, a modal sound field or at least one acoustic mode with circumferentially and / or radial direction, variable amplitude, the synchronous to the flow obstacle 2 and emanating from this periodic detachment of the Vortex reacts (feedback loop according to arrow 9). The result is a closed resonant circuit between the vortex shedding and the acoustic mode 8 and the acoustic mode 8 and the vortex shedding, that is, the acoustic mode imposes its frequency and phase on the vortex shedding and by the synchronous feedback of the modes to the vortex formation forms a high Sound pressure level, which is able to simulate certain noise conditions in technical systems, for example in a rotor-stator arrangement, or - phase-shifted - can be used for active noise reduction of an existing sound pressure level. The energy required for the generation of sound is removed from the energy of the flowing medium, but the energy withdrawal is negligibly small and without influence on the effect of the technical device under investigation, eg a rotor-stator arrangement of a turbomachine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Strömungskanalflow channel
22
Strömungshindernisflow obstruction
33
Strömungsrichtung, StrömungsenergieflusssFlow direction, flow energy flow
44
Schallausbreitungsrichtung, akustischer EnergieflussSound propagation direction, acoustic energy flow
55
abgelöste Wirbeldetached vertebrae
66
abgelöste Wirbeldetached vertebrae
77
Wirbelstraße, aerodynamische SchallquelleVortex street, aerodynamic sound source
88th
Akust. Mode, modales Schallfeld, DruckfeldAudible. Fashion, modal sound field, pressure field
99
Feedback Loop, Rückkopplung zw. 8 und 2Feedback loop, feedback between 8 and 2
1010
Stege mit gleichbleibendem ProfilWebs with constant profile
1111
Stege mit mehreren AblöseabschnittenBars with several detachment sections
11a11a
StützstangeStabilizer
11b11b
WirbelablöseabschnittVortex shedding section

Claims (8)

  1. Arrangement for the generation of sonic fields of a specific modal composition as simulated sound source for acoustic investigations, in particular for the simulation of the sound produced by rotor-stator arrangements of turbomachines, or as opposing sonic field for active sound reduction, characterized by a flow duct (1) flown by a fluid with at least one flow obstacle (2) provided in this flow duct (1) for the periodic shedding of vortexes (5, 6) at a certain shedding frequency depending on the shape and size of the at least one flow obstacle (2) and the velocity of flow, with the number and spatial arrangement of the flow obstacles (2) being selected such that a periodically spatially and temporally changing pressure field for the excitation of a sonic field (8) of a certain modal composition is produced by the entirety of the shed vortexes which reacts synchronizingly on the vortex shedding, with a resultant resonant circuit, whose vortex shedding frequency is in the range of the resonant frequency of the sonic field to be excited, being the sound source.
  2. Arrangement in accordance with Claim 1, characterized in that several flow obstacles (2) are arranged at regular or irregular intervals in one or several cross-sectional plane(s) of the flow duct (1) both circumferentially and in the direction of flow.
  3. Arrangement in accordance with Claim 2, characterized in that the flow obstacles (2) are projections (10, 11) sticking out from the inner wall of the flow duct which are profiled such that periodic shedding of vortexes (5 and 6) for creating a vortex path (7) and sounds as well as the respective acoustic modes (8) is ensured.
  4. Arrangement in accordance with Claim 3, characterized in that the projections (11) include a stay (11 a) with one or several vortex shedding portion(s) (11 b) which are remote of the inner wall of the flow duct (1) and/or spaced from each other, with the stay being profiled such that it produces no, or only negligible, vortex shedding.
  5. Arrangement in accordance with Claim 2, characterized in that the flow obstacles (2) are cavities formed into the inner wall of the flow duct (1).
  6. Arrangement in accordance with Claim 1, characterized in that the fluid is a cold gas or a hot gas.
  7. Arrangement in accordance with Claim 1, characterized in that means for vibration excitation are provided to control the phase relation of vortex shedding at the flow obstacles.
  8. Arrangement in accordance with one of the Claims 1 to 4 and 7, characterized in that the flow obstacles (2) are adjustable in several axes.
EP04090083A 2004-03-03 2004-03-03 Device for producing acoustic fields with a defined modal composition Expired - Fee Related EP1571650B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP04090083A EP1571650B1 (en) 2004-03-03 2004-03-03 Device for producing acoustic fields with a defined modal composition
DE502004009480T DE502004009480D1 (en) 2004-03-03 2004-03-03 Arrangement for generating sound fields with a specific modal composition
US11/068,980 US7516815B2 (en) 2004-03-03 2005-03-02 Arrangement for the generation of sonic fields of a specific modal composition

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04090083A EP1571650B1 (en) 2004-03-03 2004-03-03 Device for producing acoustic fields with a defined modal composition

Publications (2)

Publication Number Publication Date
EP1571650A1 EP1571650A1 (en) 2005-09-07
EP1571650B1 true EP1571650B1 (en) 2009-05-13

Family

ID=34746054

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04090083A Expired - Fee Related EP1571650B1 (en) 2004-03-03 2004-03-03 Device for producing acoustic fields with a defined modal composition

Country Status (3)

Country Link
US (1) US7516815B2 (en)
EP (1) EP1571650B1 (en)
DE (1) DE502004009480D1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1675085A4 (en) * 2003-07-25 2012-04-18 Nikolai Alekseevich Baranov Flight simulator
US7717229B2 (en) * 2008-05-09 2010-05-18 Siemens Energy, Inc. Gas turbine exhaust sound suppressor and associated methods
WO2010056984A2 (en) * 2008-11-14 2010-05-20 The Regents Of The University Of Michigan Acoustical fluid control mechanism
US20140212265A1 (en) * 2013-01-30 2014-07-31 Robert A. Putnam Gas turbine inlet silencer
US10722990B2 (en) 2016-09-15 2020-07-28 General Electric Company Method for installing and removing modularized silencer baffles
CN108278158B (en) * 2017-01-06 2022-05-13 通用电气公司 System and method for improved inlet muffling baffle
CN108278157B (en) 2017-01-06 2022-08-02 通用电气公司 System and method for improved inlet silencer baffle
US11227575B2 (en) * 2018-08-10 2022-01-18 Dell Products, L.P. Aerodynamic acoustic resonator to dissipate energy from air movers
CN113179465B (en) * 2021-04-15 2022-08-19 上海交通大学 Pipeline high-order acoustic modal generating device and control method

Family Cites Families (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2514129A (en) * 1947-10-08 1950-07-04 Ultrasonic Corp Apparatus for generating sound waves
US2704504A (en) * 1950-02-02 1955-03-22 Arthur O Wilkening Sound trap and air transfer device
US2708006A (en) * 1953-11-05 1955-05-10 Backman Hans Fredrik Muffler assembly for internal combustion engines
US2987033A (en) * 1959-04-01 1961-06-06 Coceano Domenico Acoustical generator
US3292727A (en) * 1963-05-06 1966-12-20 Messerschmitt Ag High power sound generator for sonic fatique testing
FR1376576A (en) * 1963-08-02 1964-10-31 Snecma Silencers for reactors
US3378100A (en) * 1965-10-18 1968-04-16 Air Filter Corp Sound attenuator
US3533486A (en) * 1968-11-08 1970-10-13 Gen Electric Jet engine silencer with retractable sound absorbing body
US3612446A (en) * 1969-10-10 1971-10-12 Herbert A Lebert Means and method for preventing the formation of audible frequencies in fluids passing over an airfoil section
US3575259A (en) * 1970-04-10 1971-04-20 Boeing Co Retractable noise suppression system
US4298089A (en) * 1976-12-23 1981-11-03 The Boeing Company Vortex generators for internal mixing in a turbofan engine
US4346781A (en) * 1978-11-16 1982-08-31 Massachusetts Institute Of Technology Lined-duct acoustic filter
US4241805A (en) * 1979-04-02 1980-12-30 Vibration And Noise Engineering Corporation High pressure gas vent noise control apparatus and method
GB2049887B (en) * 1979-05-23 1982-12-01 Coal Industry Patents Ltd Acoustic liner for attenuating noise
US4300656A (en) * 1980-09-11 1981-11-17 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Multiple pure tone elimination strut assembly
US4464108A (en) * 1980-11-21 1984-08-07 Donald Korenyi Combustion apparatus
JPS6217675Y2 (en) * 1980-12-05 1987-05-07
US4439104A (en) * 1981-06-15 1984-03-27 The Garrett Corporation Compressor inlet guide vane and vortex-disturbing member assembly
DE3233654C2 (en) * 1982-09-10 1986-01-16 Ewald Dörken AG, 5804 Herdecke Sound-absorbing component
CH671848B (en) * 1986-05-16 1989-09-29
US4718393A (en) * 1986-11-20 1988-01-12 Bakish Richard J Air-fuel homogenizer
US4909346A (en) * 1989-06-27 1990-03-20 Nordam Jet engine noise suppression system
JPH0577794A (en) * 1991-09-20 1993-03-30 Mitsubishi Heavy Ind Ltd Noise reducing device for high-speed flow noise
CA2104991C (en) * 1993-08-27 1996-09-10 Nestor Ewanek Sound reduction unit for compressors
US5590849A (en) * 1994-12-19 1997-01-07 General Electric Company Active noise control using an array of plate radiators and acoustic resonators
US5702230A (en) * 1996-01-29 1997-12-30 General Electric Company Actively controlled acoustic treatment panel
US5904318A (en) * 1996-12-18 1999-05-18 Towfiq; Foad Passive reduction of aircraft fuselage noise
DE69805883T2 (en) * 1997-03-04 2003-02-13 Nippon Soken Device for preventing flow noise in throttle valves
CA2206885C (en) * 1997-06-03 2013-01-08 Nester Ewanek Acoustic chamber
US5947081A (en) * 1997-08-12 1999-09-07 Kim; Sei Y. Air flow system for internal combustion engine
US6471157B1 (en) * 1999-03-22 2002-10-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Device and method for reducing aircraft noise
US6092621A (en) * 1999-06-29 2000-07-25 General Electric Company Methods and apparatus for suppressing engine test cell howl
US6309176B1 (en) * 1999-11-12 2001-10-30 Siemens Automotive Inc. Noise attenuating sound resonator for automotive cooling module shroud
GB0016149D0 (en) * 2000-06-30 2000-08-23 Short Brothers Plc A noise attenuation panel
DE10103942C1 (en) * 2001-01-30 2002-05-23 Oskar Bschorr Flow-operated sound generator e.g. for providing active noise damping or acoustic warning signal, has flow boundary layer altered by controlled actuators within aerodynamic structure inserted in flow
CN1539058A (en) * 2001-06-29 2004-10-20 赫罗・普拉桑塔・维贾亚 Air-stirring blade for internal combustion engine
US7234297B2 (en) * 2002-06-06 2007-06-26 Maybeck James C Motorcycle exhaust enhancers
US7131514B2 (en) * 2003-08-25 2006-11-07 Ford Global Technologies, Llc Noise attenuation device for a vehicle exhaust system
US8166775B2 (en) * 2003-10-09 2012-05-01 Ford Global Technologies, Llc Noise attenuating device for a heating-ventilation-cooling system of a motor vehicle

Also Published As

Publication number Publication date
DE502004009480D1 (en) 2009-06-25
US7516815B2 (en) 2009-04-14
EP1571650A1 (en) 2005-09-07
US20050194206A1 (en) 2005-09-08

Similar Documents

Publication Publication Date Title
EP1571650B1 (en) Device for producing acoustic fields with a defined modal composition
EP1367311B1 (en) Sound damper for a flow duct, in particular for use in a turbine inlet casing
EP2582921B1 (en) Noise-reduced turbomachine
EP1978337B1 (en) Ultrasound meter for determining the flow rate of a flowing medium
DE3320481A1 (en) Method and device for influencing the flow on aerodynamic profiles
Atkins et al. Nonreflective boundary conditions for high-order methods
DE102014206820A1 (en) A method of removing hydrocarbonaceous deposits formed on a surface of a device
Nonomura et al. POD of aeroacoustic fields of a jet impinging on an inclined plate
DE19538178C1 (en) Damper plate inside pipe has perforated sectors separated from each
DE19822148C2 (en) Method and device for reducing noise in media carrying pipes
DE102012104684A1 (en) Wind tunnel nozzle and wind tunnel
DE102010060929A1 (en) Aero-acoustic wind tunnel has fan that is arranged in closed current return tube in which free cross-sectional area is suddenly changed according to specific amount of change in outer periphery of free cross-sectional area
Fabian et al. Rearward forcing of an unsteady compressible cascade
EP1785589A1 (en) Turbine blade, in particular for a turbine of a thermal power plant
Grace Unsteady blade pressure-The BVI model vs. the gust model
Siegenthaler et al. A preliminary study in regularizing the coherent structures in a planar, weakly-compressible, free shear layer
DE102020115734A1 (en) Device, system and method for investigating the flow around turbine blades with supersonic flow
DE102012010509B4 (en) Device for generating a flow
DE19500450A1 (en) Resonance reduction system in gas pipes
EP2540992A2 (en) Dispositif et procédé de génération d'un choc formant des remous en anneau ainsi que la turbomachine dotée d'un tel dispositif
DE399620C (en) Process for separating gaseous mixtures into their components by centrifugal force
DE10103942C1 (en) Flow-operated sound generator e.g. for providing active noise damping or acoustic warning signal, has flow boundary layer altered by controlled actuators within aerodynamic structure inserted in flow
Hamed et al. Numerical simulations of transonic flow acoustic resonance in cavity
DE102021209284A1 (en) Device and method for influencing a main fluid flow and nozzle
DE102016005086A1 (en) Apparatus for climate qualification of vibration generators

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20041203

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIN1 Information on inventor provided before grant (corrected)

Inventor name: ARNOLD, FRANK DR.

Inventor name: ROSE, MARCO DR.

Inventor name: HOLSTE, FREDI DR.

Inventor name: MOORE, ALASTAIR DAVID

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 502004009480

Country of ref document: DE

Date of ref document: 20090625

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20100216

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20120406

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20120326

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004009480

Country of ref document: DE

Representative=s name: ,

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20120328

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004009480

Country of ref document: DE

Owner name: ROLLS-ROYCE PLC, GB

Free format text: FORMER OWNER: ROLLS-ROYCE PLC, ROLLS-ROYCE DEUTSCHLAND LTD & C, , GB

Effective date: 20130402

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004009480

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNER: ROLLS-ROYCE PLC, ROLLS-ROYCE DEUTSCHLAND LTD & C, , GB

Effective date: 20130402

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004009480

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNERS: ROLLS-ROYCE PLC, LONDON, GB; ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20130402

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004009480

Country of ref document: DE

Owner name: ROLLS-ROYCE PLC, GB

Free format text: FORMER OWNERS: ROLLS-ROYCE PLC, LONDON, GB; ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20130402

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20130303

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20131129

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004009480

Country of ref document: DE

Effective date: 20131001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130402

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20131001

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130303