WO2005056984A1 - Verfahren zur lärmreduzierung von turbomaschinen mittels veränderung der oberflächenströmung eines stators - Google Patents
Verfahren zur lärmreduzierung von turbomaschinen mittels veränderung der oberflächenströmung eines stators Download PDFInfo
- Publication number
- WO2005056984A1 WO2005056984A1 PCT/DE2004/002172 DE2004002172W WO2005056984A1 WO 2005056984 A1 WO2005056984 A1 WO 2005056984A1 DE 2004002172 W DE2004002172 W DE 2004002172W WO 2005056984 A1 WO2005056984 A1 WO 2005056984A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- stator
- blades
- rotor
- noise
- air
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/148—Blades with variable camber, e.g. by ejection of fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/50—Vibration damping features
Definitions
- the invention relates to a method for noise reduction of turbomachines according to the preamble of patent claim 1 and a rotor-stator assembly thereto according to claim 10.
- Turbomachines are characterized by a sequential arrangement of rotating and stationary blade grids, also referred to as rotor and stator.
- Fig. 1 the arrangement of rotor and stator in an aircraft engine is shown by way of example.
- the working fluid usually air, flows through the following combinations of rotors and stators in the various assemblies a, b, c of turbomachines.
- the fan section is designated by the reference numeral a, which results in the flow direction from the combination of fan R1 and stator S1 in the primary circuit 1 and Austrittsleitrad S2 in the secondary circuit 2.
- the compressor stage b is in the flow direction
- the combination of impeller R3 and stator S3 and the turbine stage c is in the flow direction
- Other turbomachines are e.g. known as compressor, fan, power plant turbine.
- the rotor-stator interaction noise is based on the following mechanism: Due to the periodically rotating wake of a rotating blade grid (rotor), a downstream stationary blade grid (stator) lies in a periodically unsteady flow, causing periodic hydrodynamic pressure fluctuations on these stator blades tonal noise are emitted to the environment.
- stator-rotor interaction noise is based on the following mechanism: If a rotating blade lattice (rotor) penetrates the stationary wake of an upstream stationary blade lattice (stator), the rotor blades experience a periodically unsteady flow, causing periodic pressure fluctuations on these rotor blades, which are more tonal Noise can be radiated to the environment.
- the object of the invention is to provide a method in which by means of active measures, the reduction of the noise emission of turbomachinery can be improved. Another object is to provide a rotor-stator arrangement with which a noise reduction of turbomachinery can be realized.
- the hydrodynamic pressure fluctuations occurring at the blade lattices are reduced by means of changing the surface flow around at least part of at least one stator.
- this process starts directly at the source of the formation of the noise.
- the surface Umstromung one or more blades of the stator is changed. It is particularly advantageous that the aerodynamics of the stator is influenced by deflection of one or more blades of the stator or parts of the blades. Of course, it is possible that the aerodynamics of any number of existing in a turbomachine stators is influenced by the inventive method.
- the control of the individual stator blades of a grid can be made either individually or in phase with each other according to the pitch and the speed of the rotor.
- the driving frequency of periodic processes corresponds advantageously to the fundamental frequency of the tonal noise and results from the product of rotor blade number and speed.
- the phase angle and / or the amplitude of the drive is advantageously correspondingly suitable Error signals regulated. These error signals are supplied in particular by microphones or pressure sensors.
- the rotor-stator arrangement according to the invention comprises means on one or more stators for influencing the aerodynamics of the stator.
- One or more movable surface elements which are mounted on one or more blades of the stator.
- one or more openings for the suction and / or blowing out of air are executed. This also makes it possible to influence the pressure fluctuations that occur. In particular, it is possible by periodically purging and / or sucking on the surface of the stator blades to reduce the pressure fluctuations produced by the circulating wake of an upstream rotating blade lattice.
- the rotor-stator arrangement according to the invention are at the trailing edge of one or more blades of a stator a or more openings for blowing air present.
- the flow of a downstream rotating blade grid is harmonized by a continuous blowing of air at the trailing edge of the stator blades, whereby the resulting pressure fluctuations are reduced.
- the means for influencing the aerodynamics of a stator are mechanically, electrically, piezoelectrically or pneumatically operated actuators.
- the actuators used in the inventive method and in the rotor-stator arrangement according to the invention are not used to generate an anti-sound field, which compensates the sound field generated by the turbomachine.
- the actuators serve to deflect the stator or parts of the stator, in particular the blades or parts of the blades.
- An active system according to the present invention may be conveniently linked together with passive systems. So it is e.g. It is possible to switch on the system according to the invention to any existing passive systems in aircraft engines during noise-relevant flight phases (take-off and landing).
- system according to the invention can also be used in non-flying turbomachinery, e.g. Power plant turbines.
- An advantage of the invention is that the system is maintenance and easy to install, since the actuator is in the fixed system of the stators.
- FIG. 2 exemplary blades of a stator with means according to the invention for changing the aerodynamics of the stator
- Fig. 3 exemplary blades of a stator with openings for sucking and blowing air.
- FIG. 2 shows exemplary blades of a stator with means according to the invention for aerodynamic modification of the stator.
- the reference numeral 11 indicates an arbitrary axis about which the blade S is movably arranged.
- a blade S can fold with leading edges 12 and / or trailing edge flaps 13 equipped.
- a blade S may have one or more means 14 which are applied to the surface of the blade S. These means 14 may e.g. Be actuators.
- FIG. 3 shows in the upper part a representation of an exemplary blade S which has openings 15 and 16 in the area of the front edge and in the middle area. From these openings 15 and 16, on the one hand, air can be sucked in or air can be blown out.
- an exemplary blade S is shown, which has an opening 17 in the region of the trailing edge, through which air can be continuously blown out.
- the means 15, 16, 17 for blowing in and out of air can be combined with each other. So it can be e.g. It can also be provided that adjacent blades of a stator have differently arranged openings for blowing in or blowing out air.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006541788A JP2007513282A (ja) | 2003-12-06 | 2004-09-30 | ステータの表面流れを変えることによりターボエンジンの騒音を減少させる方法 |
EP04786884A EP1700004A1 (de) | 2003-12-06 | 2004-09-30 | Verfahren zur lärmereduzierung von turbomaschinen mittels veränderung der oberflächenströmung eines stators |
US10/581,860 US7758296B2 (en) | 2003-12-06 | 2004-09-30 | Method for reducing the noise of turbo engines |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10357075.6 | 2003-12-06 | ||
DE10357075A DE10357075B4 (de) | 2003-12-06 | 2003-12-06 | Verfahren zur Lärmreduzierung von Turbomaschinen |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005056984A1 true WO2005056984A1 (de) | 2005-06-23 |
Family
ID=34638436
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2004/002172 WO2005056984A1 (de) | 2003-12-06 | 2004-09-30 | Verfahren zur lärmreduzierung von turbomaschinen mittels veränderung der oberflächenströmung eines stators |
Country Status (5)
Country | Link |
---|---|
US (1) | US7758296B2 (de) |
EP (1) | EP1700004A1 (de) |
JP (1) | JP2007513282A (de) |
DE (1) | DE10357075B4 (de) |
WO (1) | WO2005056984A1 (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2022949A2 (de) * | 2007-07-27 | 2009-02-11 | United Technologies Corporation | Leitschaufelsystem mit variabler Geometrie für den Ausgang des Gebläses eines Turbofans und entsprechendes Betriebsverfahren |
EP1898055A3 (de) * | 2006-09-01 | 2011-06-15 | United Technologies Corporation | Leitschaufel mit variabler Geometrie für ein Gasturbinentriebwerk |
US8459035B2 (en) | 2007-07-27 | 2013-06-11 | United Technologies Corporation | Gas turbine engine with low fan pressure ratio |
EP2383442A3 (de) * | 2010-04-30 | 2014-04-02 | Rolls-Royce plc | Gasturbinenmotor |
FR3019209A1 (fr) * | 2014-03-27 | 2015-10-02 | Snecma | Aube mobile comportant des moyens reducteurs de bruit |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10357075B4 (de) | 2003-12-06 | 2006-01-12 | Dornier Gmbh | Verfahren zur Lärmreduzierung von Turbomaschinen |
KR101161490B1 (ko) | 2007-06-06 | 2012-07-12 | 하이어 디멘션 머티리얼즈, 인크. | 절단, 마멸 및/또는 관통 내성을 가진 니트 장갑 |
US20120222398A1 (en) * | 2007-07-27 | 2012-09-06 | Smith Peter G | Gas turbine engine with geared architecture |
US20150192298A1 (en) * | 2007-07-27 | 2015-07-09 | United Technologies Corporation | Gas turbine engine with improved fuel efficiency |
US20150132106A1 (en) * | 2007-07-27 | 2015-05-14 | United Technologies Corporation | Gas turbine engine with low fan pressure ratio |
US8042483B2 (en) * | 2009-09-18 | 2011-10-25 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for control of stator wakes |
GB0916787D0 (en) * | 2009-09-24 | 2009-11-04 | Rolls Royce Plc | Variable shape rotor blade |
US10227896B2 (en) | 2016-03-17 | 2019-03-12 | Rolls-Royce Corporation | Flow segregator for infrared exhaust suppressor |
US20170328206A1 (en) * | 2016-05-16 | 2017-11-16 | United Technologies Corporation | Method and Apparatus to Enhance Laminar Flow for Gas Turbine Engine Components |
US10731469B2 (en) * | 2016-05-16 | 2020-08-04 | Raytheon Technologies Corporation | Method and apparatus to enhance laminar flow for gas turbine engine components |
CN107725482A (zh) * | 2016-08-10 | 2018-02-23 | 上海电气燃气轮机有限公司 | 改善压气机变工况性能的分段调节出口导叶及其调节机构 |
US10519976B2 (en) * | 2017-01-09 | 2019-12-31 | Rolls-Royce Corporation | Fluid diodes with ridges to control boundary layer in axial compressor stator vane |
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US3572960A (en) * | 1969-01-02 | 1971-03-30 | Gen Electric | Reduction of sound in gas turbine engines |
GB1345835A (en) * | 1971-06-03 | 1974-02-06 | Snecma | Air intake devices for fans or compressors |
US4131387A (en) | 1976-02-27 | 1978-12-26 | General Electric Company | Curved blade turbomachinery noise reduction |
EP0610091A1 (de) * | 1993-02-05 | 1994-08-10 | General Electric Company | Verfahren zum Betrieb eines Mantelstromtriebwerkes mit schwenkbaren Leitschaufeln |
US5355417A (en) | 1992-10-21 | 1994-10-11 | The Center For Innovative Technology | Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors |
US5420383A (en) | 1993-10-22 | 1995-05-30 | United Technologies Corporation | Anti-sound arrangement for multi-stage blade cascade |
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US6292763B1 (en) * | 1996-08-27 | 2001-09-18 | Diversitech, Inc. | Methods for designing variable cycle gas turbine engines |
EP1277966A2 (de) | 2001-07-18 | 2003-01-22 | General Electric Company | Gezahnte Schaufel |
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DE19909899A1 (de) * | 1999-03-06 | 2000-09-07 | Abb Research Ltd | Schaufeln mit veränderbarer Profilgeometrie |
DE10053361C1 (de) * | 2000-10-27 | 2002-06-06 | Mtu Aero Engines Gmbh | Schaufelgitteranordnung für Turbomaschinen |
DE10357075B4 (de) | 2003-12-06 | 2006-01-12 | Dornier Gmbh | Verfahren zur Lärmreduzierung von Turbomaschinen |
-
2003
- 2003-12-06 DE DE10357075A patent/DE10357075B4/de not_active Expired - Fee Related
-
2004
- 2004-09-30 US US10/581,860 patent/US7758296B2/en not_active Expired - Fee Related
- 2004-09-30 WO PCT/DE2004/002172 patent/WO2005056984A1/de active Application Filing
- 2004-09-30 JP JP2006541788A patent/JP2007513282A/ja active Pending
- 2004-09-30 EP EP04786884A patent/EP1700004A1/de not_active Withdrawn
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US3572960A (en) * | 1969-01-02 | 1971-03-30 | Gen Electric | Reduction of sound in gas turbine engines |
GB1345835A (en) * | 1971-06-03 | 1974-02-06 | Snecma | Air intake devices for fans or compressors |
US4131387A (en) | 1976-02-27 | 1978-12-26 | General Electric Company | Curved blade turbomachinery noise reduction |
US5355417A (en) | 1992-10-21 | 1994-10-11 | The Center For Innovative Technology | Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors |
EP0610091A1 (de) * | 1993-02-05 | 1994-08-10 | General Electric Company | Verfahren zum Betrieb eines Mantelstromtriebwerkes mit schwenkbaren Leitschaufeln |
US5420383A (en) | 1993-10-22 | 1995-05-30 | United Technologies Corporation | Anti-sound arrangement for multi-stage blade cascade |
US5613649A (en) | 1994-07-21 | 1997-03-25 | United Technologies Corporation | Airfoil noise control |
US6004095A (en) | 1996-06-10 | 1999-12-21 | Massachusetts Institute Of Technology | Reduction of turbomachinery noise |
US6292763B1 (en) * | 1996-08-27 | 2001-09-18 | Diversitech, Inc. | Methods for designing variable cycle gas turbine engines |
US6139259A (en) * | 1998-10-29 | 2000-10-31 | General Electric Company | Low noise permeable airfoil |
EP1277966A2 (de) | 2001-07-18 | 2003-01-22 | General Electric Company | Gezahnte Schaufel |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1898055A3 (de) * | 2006-09-01 | 2011-06-15 | United Technologies Corporation | Leitschaufel mit variabler Geometrie für ein Gasturbinentriebwerk |
EP2022949A2 (de) * | 2007-07-27 | 2009-02-11 | United Technologies Corporation | Leitschaufelsystem mit variabler Geometrie für den Ausgang des Gebläses eines Turbofans und entsprechendes Betriebsverfahren |
EP2022949A3 (de) * | 2007-07-27 | 2011-12-14 | United Technologies Corporation | Leitschaufelsystem mit variabler Geometrie für den Ausgang des Gebläses eines Turbofans und entsprechendes Betriebsverfahren |
US8347633B2 (en) | 2007-07-27 | 2013-01-08 | United Technologies Corporation | Gas turbine engine with variable geometry fan exit guide vane system |
US8459035B2 (en) | 2007-07-27 | 2013-06-11 | United Technologies Corporation | Gas turbine engine with low fan pressure ratio |
EP3165718A1 (de) * | 2007-07-27 | 2017-05-10 | United Technologies Corporation | Gasturbinenmotor mit ventilatorausgangleitschaufelsystem mit variabler geometrie |
EP2383442A3 (de) * | 2010-04-30 | 2014-04-02 | Rolls-Royce plc | Gasturbinenmotor |
US8870530B2 (en) | 2010-04-30 | 2014-10-28 | Rolls-Royce Plc | Gas turbine engine |
FR3019209A1 (fr) * | 2014-03-27 | 2015-10-02 | Snecma | Aube mobile comportant des moyens reducteurs de bruit |
Also Published As
Publication number | Publication date |
---|---|
DE10357075A1 (de) | 2005-07-07 |
DE10357075B4 (de) | 2006-01-12 |
US7758296B2 (en) | 2010-07-20 |
EP1700004A1 (de) | 2006-09-13 |
US20070274823A1 (en) | 2007-11-29 |
JP2007513282A (ja) | 2007-05-24 |
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