WO2005091272A1 - Anordnung zur lärmreduzierung in turbofantriebwerken - Google Patents
Anordnung zur lärmreduzierung in turbofantriebwerken Download PDFInfo
- Publication number
- WO2005091272A1 WO2005091272A1 PCT/DE2005/000073 DE2005000073W WO2005091272A1 WO 2005091272 A1 WO2005091272 A1 WO 2005091272A1 DE 2005000073 W DE2005000073 W DE 2005000073W WO 2005091272 A1 WO2005091272 A1 WO 2005091272A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- horns
- hot gas
- cover plate
- assembly
- flow channel
- Prior art date
Links
- 230000002745 absorbent Effects 0.000 abstract description 6
- 239000002250 absorbent Substances 0.000 abstract description 6
- 238000010438 heat treatment Methods 0.000 abstract 3
- 238000005253 cladding Methods 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 9
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000006096 absorbing agent Substances 0.000 description 1
- 239000006098 acoustic absorber Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- 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
- G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- 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 invention relates to an arrangement for reducing the noise generated by turbofan engines, especially in the hot gas area.
- Active methods are known for reducing the noise generated by turbofan engines in the hot gas range, e.g. US 5,386,689.
- sound sources for generating counter-sound in the hot gas area of the engine are provided.
- An acoustic absorber is known from DE 196 07 290 A1. It consists of a pot-like lower part, in which a single horn extends.
- the object of the invention is to provide an arrangement with which an effective reduction of the noise generated by turbofan engines in the hot gas range can be achieved, the arrangement being intended to have only a low weight in accordance with the aeronautical requirements.
- energy is withdrawn from the sound waves generated there by means of an absorbent lining of the hot gas region of a turbofan engine, which energy is then no longer emitted. Dissipation occurs due to viscous losses in the lining, which is structured as follows: a plurality of adjacent cavities, four horns extending into each cavity,
- the horns are attached with their Hommund to a perforated cover plate and the cover plate forms a wall of the hot gas flow channel.
- FIG. 1 shows the cross-sectional sketch of a turbofan engine with an acoustically absorbing lining according to the invention in the hot gas region;
- Figure 2 is a top and cross-sectional view of the absorbent liner
- Fig. 3 is a sketch of the home geometry of the absorbent lining.
- FIG. 1 shows the cross-sectional sketch of a turbofan engine.
- the fresh air drawn in is divided into two partial flows.
- a first portion is led around the combustion chamber BK to the nozzle, where it is mixed with the hot exhaust gases from the combustion chamber BK (so-called bypass).
- the other partial flow is fed via several compressor stages VS into the combustion chamber BK (annular cross section) and from there to the nozzle.
- the flow channel SK downstream of the combustion chamber BK with an annular cross section is the hot gas area of the engine in the sense of the present invention.
- This is provided with the sound-absorbing lining A according to the invention, in such a way that the sound-absorbing lining A forms the outer wall of the so-called “infernal plug” IP of the engine.
- the absorbent lining A comprises a plurality of essentially rectangular cavities HR with an approximately square base area GF, into each of which four horns H are introduced (FIG. 2).
- the horns have a first opening with a larger diameter HM, the so-called Hommund, and a second opening with a smaller diameter, the so-called Hornhals HH.
- the horns H are attached to their horn mouth HM by spot welding on a cover plate AB.
- the cover plate AB is perforated in the area of the horn mouth HM (area of the perforation P), with a porosity of at least 20%, in a preferred embodiment 30%, the diameter of the holes being 1 mm.
- the horns H preferably have a circular cross section. The horns do not reach the base GF of a cavity, so that there is a space between the horn neck HH and the base GF.
- a cavity HR is delimited by cover plate AB and base area GF by four side areas SF.
- the cavities are arranged directly next to one another without a space and are each separated from one another by a common side wall SF. A very weight-saving design is thus achieved.
- Length of the horns (measured in the axial direction): 23 mm diameter of the horn mouth: 23 mm diameter of the home neck: 7 mm
- the depth of the cavities - measured in the hom direction - is 34 mm.
- the tapering of the homewall from horn mouth to horn neck does not necessarily have to be linear.
- Other shapes, e.g. hyperbolic or in the manner of a segment of a circle are possible.
- the absorbent structure is based on the principle of a Helmholtz resonator.
- the air mass entering the horns through the perforation couples to the giving cavity volume and thus represents a damped spring-mass system.
- the use of these absorbers allows the absorption of acoustic energy with a low overall height.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Multimedia (AREA)
- Exhaust Silencers (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2007503184A JP4659021B2 (ja) | 2004-03-17 | 2005-01-20 | ターボファンエンジン内の騒音低減構造 |
US10/592,932 US7819224B2 (en) | 2004-03-17 | 2005-01-20 | Assembly for reducing noise in turbofan engines |
EP05714879A EP1726004A1 (de) | 2004-03-17 | 2005-01-20 | Anordnung zur lärmreduzierung in turbofantriebwerken |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004012929.0 | 2004-03-17 | ||
DE102004012929A DE102004012929B3 (de) | 2004-03-17 | 2004-03-17 | Anordnung zur Lärmreduzierung in Turbofantriebwerken |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005091272A1 true WO2005091272A1 (de) | 2005-09-29 |
Family
ID=34353596
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2005/000073 WO2005091272A1 (de) | 2004-03-17 | 2005-01-20 | Anordnung zur lärmreduzierung in turbofantriebwerken |
Country Status (5)
Country | Link |
---|---|
US (1) | US7819224B2 (de) |
EP (1) | EP1726004A1 (de) |
JP (1) | JP4659021B2 (de) |
DE (1) | DE102004012929B3 (de) |
WO (1) | WO2005091272A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007292064A (ja) * | 2006-03-24 | 2007-11-08 | Snecma | ターボジェットノズルの中心体 |
DE102011008920A1 (de) * | 2011-01-19 | 2012-07-19 | Rolls-Royce Deutschland Ltd & Co Kg | Schallabsorber, insbesondere für einen Gasturbinenabgaskonus und Verfahren zu dessen Herstellung |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8826669B2 (en) | 2011-11-09 | 2014-09-09 | Pratt & Whitney Canada Corp. | Gas turbine exhaust case |
US9200537B2 (en) | 2011-11-09 | 2015-12-01 | Pratt & Whitney Canada Corp. | Gas turbine exhaust case with acoustic panels |
US8944753B2 (en) | 2011-11-09 | 2015-02-03 | Pratt & Whitney Canada Corp. | Strut mounting arrangement for gas turbine exhaust case |
DE102011120979A1 (de) * | 2011-12-13 | 2013-06-13 | Rolls-Royce Deutschland Ltd & Co Kg | Akustischer Absorber |
GB201301702D0 (en) | 2013-01-31 | 2013-03-20 | Rolls Royce Plc | Exhaust cone |
US8997923B2 (en) * | 2013-08-12 | 2015-04-07 | Hexcel Corporation | Sound wave guide for use in acoustic structures |
US10344711B2 (en) * | 2016-01-11 | 2019-07-09 | Rolls-Royce Corporation | System and method of alleviating blade flutter |
US10465539B2 (en) * | 2017-08-04 | 2019-11-05 | Pratt & Whitney Canada Corp. | Rotor casing |
FR3074223A1 (fr) * | 2017-11-28 | 2019-05-31 | Airbus Operations | Panneau d’attenuation acoustique pour aeronef. |
US11059559B2 (en) * | 2018-03-05 | 2021-07-13 | General Electric Company | Acoustic liners with oblique cellular structures |
FR3088905A1 (fr) * | 2018-11-28 | 2020-05-29 | Airbus Operations (S.A.S.) | Structure d’absorption acoustique comprenant un système de drainage de liquide et ensemble propulsif comportant une telle structure d’absorption acoustique |
US20200388265A1 (en) * | 2019-06-10 | 2020-12-10 | Toyota Motor Engineering & Manufacturing North America, Inc. | Sound isolation device |
FR3099963A1 (fr) * | 2019-08-13 | 2021-02-19 | Airbus Operations | Elément acoustique à double enceinte et encombrement réduit, en particulier pour panneau acoustique d’aéronef |
FR3117658B1 (fr) * | 2020-12-15 | 2023-08-11 | Safran Aircraft Engines | Panneau de traitement acoustique à encombrement réduit pour turboréacteur |
US11715450B2 (en) * | 2020-12-22 | 2023-08-01 | Rohr, Inc. | Acoustic panel core cell with funnel shaped septum |
US11970992B2 (en) | 2021-06-03 | 2024-04-30 | General Electric Company | Acoustic cores and tools and methods for forming the same |
US11635026B1 (en) * | 2021-12-21 | 2023-04-25 | Rolls-Royce Deutschland Ltd & Co Kg | Fan case assembly for a gas turbine engine |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3819009A (en) * | 1973-02-01 | 1974-06-25 | Gen Electric | Duct wall acoustic treatment |
GB1470036A (en) * | 1975-01-17 | 1977-04-14 | Lockheed Aircraft Corp | Dual range sound absorber |
GB2005384A (en) * | 1977-10-04 | 1979-04-19 | Rolls Royce | Multi-layer acoustic lining |
Family Cites Families (18)
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US3174580A (en) * | 1961-04-28 | 1965-03-23 | Kurt W Schulz | Acoustical tile construction |
US3437173A (en) * | 1966-11-25 | 1969-04-08 | Gen Electric | Gas turbine engine with screech attenuating means |
US3819007A (en) * | 1973-04-27 | 1974-06-25 | Lockheed Aircraft Corp | Controllable laminar sound absorptive structure |
US3887031A (en) * | 1973-06-11 | 1975-06-03 | Lockheed Aircraft Corp | Dual-range sound absorber |
GB1522558A (en) * | 1976-04-05 | 1978-08-23 | Rolls Royce | Duct linings |
US4106587A (en) * | 1976-07-02 | 1978-08-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Sound-suppressing structure with thermal relief |
US4135603A (en) * | 1976-08-19 | 1979-01-23 | United Technologies Corporation | Sound suppressor liners |
FR2376994A1 (fr) * | 1977-01-11 | 1978-08-04 | Snecma | Perfectionnements aux dispositifs a cavites resonnantes pour la reduction du bruit dans un conduit en presence d'un flux gazeux |
US4231447A (en) * | 1978-04-29 | 1980-11-04 | Rolls-Royce Limited | Multi-layer acoustic linings |
US4452335A (en) * | 1982-05-03 | 1984-06-05 | United Technologies Corporation | Sound absorbing structure for a gas turbine engine |
US5185504A (en) * | 1992-06-30 | 1993-02-09 | Jen Wang H | Acoustic board |
FR2686628A1 (fr) * | 1992-01-28 | 1993-07-30 | Perfojet Sa | Structure textile complexe a base de nappes fibreuses non tissees et procede et installation pour son obtention. |
US5386689A (en) | 1992-10-13 | 1995-02-07 | Noises Off, Inc. | Active gas turbine (jet) engine noise suppression |
JP3076945B2 (ja) * | 1993-06-15 | 2000-08-14 | 松下電器産業株式会社 | 吸音装置 |
EP0636780A1 (de) * | 1993-06-25 | 1995-02-01 | Nordam | Lärmdämpfende Auskleidung für Strahlmotoren |
ATE195802T1 (de) | 1995-04-20 | 2000-09-15 | Contraves Space Ag | Akustischer schutz an nutzlastverkleidungen für trägerraketen |
CH691465A5 (de) * | 1995-04-20 | 2001-07-31 | Dornier Gmbh | Schallschutz für Nutzlastverkleidungen bei Trägerraketen und Verfahren zum Herstellen eines Schallschutzes. |
JPH09170494A (ja) * | 1995-12-20 | 1997-06-30 | Ishikawajima Harima Heavy Ind Co Ltd | 吸音ライナ |
-
2004
- 2004-03-17 DE DE102004012929A patent/DE102004012929B3/de not_active Expired - Fee Related
-
2005
- 2005-01-20 US US10/592,932 patent/US7819224B2/en not_active Expired - Fee Related
- 2005-01-20 JP JP2007503184A patent/JP4659021B2/ja not_active Expired - Fee Related
- 2005-01-20 EP EP05714879A patent/EP1726004A1/de not_active Withdrawn
- 2005-01-20 WO PCT/DE2005/000073 patent/WO2005091272A1/de active Application Filing
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3819009A (en) * | 1973-02-01 | 1974-06-25 | Gen Electric | Duct wall acoustic treatment |
GB1470036A (en) * | 1975-01-17 | 1977-04-14 | Lockheed Aircraft Corp | Dual range sound absorber |
GB2005384A (en) * | 1977-10-04 | 1979-04-19 | Rolls Royce | Multi-layer acoustic lining |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007292064A (ja) * | 2006-03-24 | 2007-11-08 | Snecma | ターボジェットノズルの中心体 |
DE102011008920A1 (de) * | 2011-01-19 | 2012-07-19 | Rolls-Royce Deutschland Ltd & Co Kg | Schallabsorber, insbesondere für einen Gasturbinenabgaskonus und Verfahren zu dessen Herstellung |
US8783412B2 (en) | 2011-01-19 | 2014-07-22 | Rolls-Royce Deutschland Ltd & Co Kg | Sound absorber for a gas turbine exhaust cone, and method for the production thereof |
Also Published As
Publication number | Publication date |
---|---|
DE102004012929B3 (de) | 2005-04-21 |
EP1726004A1 (de) | 2006-11-29 |
US7819224B2 (en) | 2010-10-26 |
JP2007529666A (ja) | 2007-10-25 |
US20080308345A1 (en) | 2008-12-18 |
JP4659021B2 (ja) | 2011-03-30 |
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