WO2003025378A2 - Anordnung zum vermischen von zwei ursprünglich getrennt geführten fluidströmen in einem zweikreis-strahltriebwerk - Google Patents
Anordnung zum vermischen von zwei ursprünglich getrennt geführten fluidströmen in einem zweikreis-strahltriebwerk Download PDFInfo
- Publication number
- WO2003025378A2 WO2003025378A2 PCT/DE2002/003157 DE0203157W WO03025378A2 WO 2003025378 A2 WO2003025378 A2 WO 2003025378A2 DE 0203157 W DE0203157 W DE 0203157W WO 03025378 A2 WO03025378 A2 WO 03025378A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- mixing tube
- mixing
- openings
- axis
- perforated collar
- Prior art date
Links
Classifications
-
- 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
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- 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
Definitions
- the invention relates to an arrangement for mixing two originally separate fluid flows in a two-circuit jet engine.
- so-called flower mixers are known to be used in dual-circuit jet engines in order to mix the hot core jet of the jet engine and the cold secondary stream before it emerges from the jet engine nozzle.
- the hot core jet of the jet engine is guided through a so-called mixing tube, while the cold side stream flows along the outside of the mixing tube surface.
- the mixing of the two fluid streams is forced by a special shaping of the downstream lateral surface of the mixing tube.
- the downstream shaped surface of the mixing tube has so-called flowers (lobes) that extend radially outwards. After flowing through or flowing around the downstream section of the mixing tube, these flowers (lobes) guide the hot core jet into the cold side stream, as well as the cold side stream into the hot core jet.
- a disadvantage of these known flower mixers is the fact that the flower mixers tend to vibrate at the downstream end due to the large radial extension of the flowers (lobes) and that deformations occur due to material heating and pressure differences. Attempts have therefore been made to overcome these disadvantages by means of so-called ribs (struts), which support the flower mixer on the outlet cone or the jet housing of the jet engine. However, these struts represent an additional source of weight.
- the invention has for its object to remedy this situation by a new design of the arrangement for mixing the hot core jet of the jet engine with the cold secondary flow.
- this object is achieved according to the invention in that the mixing tube is designed in the form of a truncated cone in the flow direction of the core jet and side stream, and in that the mixing tube at the downstream end in the circumferential direction of the mixing tube shell in a direction perpendicular to the longitudinal axis of the Mixing tube lying cross-sectional plane has openings through which the hot core jet flowing through the mixing tube penetrates into the cold side stream flowing around the mixing tube jacket.
- the design of the mixing tube leads to significant advantages. By making the openings in the surface of the mixing tube, flower mixers with the large radial extension of their flowers are eliminated. This significantly reduces the tendency to vibrate, eliminating the struts that were previously required. This also eliminates the risk of possible interference with the engine mount.
- the smaller radial extension also has the advantage that the new mixing tube according to the invention is also suitable for cramped installation.
- the closed ring jacket at the downstream end of the mixing tube leads to a stable, low-vibration construction, so that disturbances due to fluctuations in operating pressure and temperature have little influence on the mixing tube. Since support ribs are no longer necessary to fix the mixing tube, this omission of the support ribs also means a lighter construction and thus a lower weight of the jet engine.
- the simplified shape of the mixing tube also leads to less expensive production, since the time-consuming deep-drawing processes required to produce the flowers are eliminated.
- the openings in the mixing tube jacket have elliptically shaped passage surfaces with a main axis and a secondary axis.
- the main axis of the elliptical passage surfaces runs on the mixing tube jacket in the direction of flow of the hot core jet and the cold secondary stream, the secondary axis is arranged perpendicular to it.
- a combination of the new mixing tube according to the invention with well-known conventional flower mixers is possible. It is also conceivable to replace existing mixers with mixers according to the invention, since the changes in the new mixer with regard to mixer efficiency (smaller) and overall pressure loss (smaller) are neutral with respect to the thrust gain.
- 1 is a sectional view of a mixing tube of a two-circuit
- Jet engine in the form of a truncated cone with openings and distributed over the circumference of the truncated cone
- FIG. 2 shows an enlarged illustration of an opening from FIG. 1.
- the direction of flow of the fluid streams to be mixed i.e. a hot core jet 16 and a cold secondary stream 18, is indicated by the arrows S.
- the mixing tube 10 has the shape of a truncated cone in the flow direction S.
- the other components of a jet engine in addition to the mixing tube 10 are not shown for reasons of clarity.
- a plurality of openings 20 are made in the mixing tube shell 12 in the circumferential direction of the mixing tube shell 12 in a cross-sectional area perpendicular to the longitudinal axis 14 of the mixing tube 10.
- FIG. 2 An enlarged view of one of the openings 20 located at the downstream end of the mixing tube 10 is shown in FIG. 2.
- the openings 20 have an elliptically shaped passage surface 22 with a major axis 24 and a minor axis 26. While the main axis 24 of the passage surfaces 22 runs on the mixing tube surface 12 in the flow direction S, the secondary axis 26 is arranged perpendicular to it.
- the elliptical passage surfaces 22 also have a perforated collar 28 on the outside of the mixing tube jacket surface 12.
- the height of the perforated collar 28 is designed such that the maximum height of the perforated collar 28 is located on the upstream apex 30 of the main axis 24 of the elliptical passage surfaces 22 and decreases from there in the flow direction S.
- a region of the downstream apex 32 of the main axis 24 of the elliptical passage surfaces 22 is formed without a perforated collar 28. Alternatively, it can be bent inwards (relative to the mixing tube jacket 12).
- the transition from the outside of the mixing tube jacket surface 12 to the perforated collar 28 is made concave in the present embodiment, other continuous shapes are also possible.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2460549A CA2460549C (en) | 2001-09-14 | 2002-08-29 | Device for mixing two flows of fluid, which are initially guided separate from one another, in a two-circuit reaction engine |
JP2003528979A JP4148893B2 (ja) | 2001-09-14 | 2002-08-29 | 2サーキットジェットエンジンにおいて、最初に互いに独立して案内される2つの流体流を混合する装置 |
EP02769890A EP1425504A2 (de) | 2001-09-14 | 2002-08-29 | Anordnung zum vermischen von zwei ursprünglich getrennt geführten fluidströmen in einem zweikreis-strahltriebwerk |
US10/489,599 US7299635B2 (en) | 2001-09-14 | 2002-08-29 | Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10145489.9 | 2001-09-14 | ||
DE10145489A DE10145489B4 (de) | 2001-09-14 | 2001-09-14 | Anordnung zum Vermischen von zwei ursprünglich getrennt geführten Fluidströmen in einem Zweikreis-Strahltriebwerk |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2003025378A2 true WO2003025378A2 (de) | 2003-03-27 |
WO2003025378A3 WO2003025378A3 (de) | 2003-05-30 |
Family
ID=7699133
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2002/003157 WO2003025378A2 (de) | 2001-09-14 | 2002-08-29 | Anordnung zum vermischen von zwei ursprünglich getrennt geführten fluidströmen in einem zweikreis-strahltriebwerk |
Country Status (6)
Country | Link |
---|---|
US (1) | US7299635B2 (de) |
EP (1) | EP1425504A2 (de) |
JP (1) | JP4148893B2 (de) |
CA (1) | CA2460549C (de) |
DE (1) | DE10145489B4 (de) |
WO (1) | WO2003025378A2 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009138068A1 (de) * | 2008-05-15 | 2009-11-19 | Mtu Aero Engines Gmbh | Mischdüsenaufbau |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080072566A1 (en) * | 2006-09-27 | 2008-03-27 | Pratt & Whitney Canada Corp. | Bleed holes oriented with gaspath and flared for noise reduction |
US7870722B2 (en) * | 2006-12-06 | 2011-01-18 | The Boeing Company | Systems and methods for passively directing aircraft engine nozzle flows |
DE102007004741A1 (de) | 2007-01-31 | 2008-08-07 | Mtu Aero Engines Gmbh | Gasturbine mit einem Nachleitkranz und mit einem Mischer |
US8516791B2 (en) * | 2007-07-30 | 2013-08-27 | General Electric Company | Methods and apparatus for mixing fluid in turbine engines |
US8438835B2 (en) * | 2007-07-30 | 2013-05-14 | General Electric Company | Methods and apparatus for mixing fluid in turbine engines |
FR3002287B1 (fr) * | 2013-02-18 | 2016-07-01 | Snecma | Procede de melange entre un ecoulement primaire et un ecoulement secondaire dans une turbomachine, dispositif et turbomachine correspondants |
US9759159B2 (en) | 2014-05-26 | 2017-09-12 | Pratt & Whitney Canada Corp. | Integrated turbine exhaust struts and mixer of turbofan engine |
US10018150B2 (en) | 2014-05-26 | 2018-07-10 | Pratt & Whitney Canada Inc. | Integrated TEC/mixer strut axial position |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1086315A (fr) * | 1953-07-06 | 1955-02-11 | Perfectionnements apportés aux réacteurs combinés | |
US2987883A (en) * | 1959-06-22 | 1961-06-13 | Boeing Co | Jet engine noise suppression nozzle with aerodynamic supplemental fluting |
US3002341A (en) * | 1957-12-31 | 1961-10-03 | Boeing Co | Jet engine noise suppression nozzles |
US3153319A (en) * | 1952-07-25 | 1964-10-20 | Young Alec David | Jet noise suppression means |
US3196608A (en) * | 1959-06-23 | 1965-07-27 | Rolls Royce | Apparatus to admix by-pass air with exhaust gases in a by-pass gas-turbine engine |
US3587777A (en) * | 1969-10-23 | 1971-06-28 | Rohr Corp | Turbofan propulsion apparatus with silencer and operating method |
US3612212A (en) * | 1969-08-11 | 1971-10-12 | Rohr Corp | Method and apparatus for suppressing the noise of a jet engine |
US4292803A (en) * | 1979-01-19 | 1981-10-06 | Rohr Industries, Inc. | Turbo fan engine mixer |
US5758488A (en) * | 1993-05-11 | 1998-06-02 | Roderick Thomson | Core flow expansion chamber device system for reduction of jet turbine engine noise |
Family Cites Families (18)
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---|---|---|---|---|
US3065818A (en) * | 1957-09-14 | 1962-11-27 | Rolls Royce | Jet noise suppressor nozzle |
US2971327A (en) * | 1957-11-26 | 1961-02-14 | Westinghouse Electric Corp | Discharge control of an overexpanding propulsion nozzle |
US3592291A (en) * | 1969-11-17 | 1971-07-13 | Rohr Corp | Method and apparatus for suppressing the noise and augmenting the thrust of a jet engine |
US3830431A (en) * | 1973-03-23 | 1974-08-20 | Nasa | Abating exhaust noises in jet engines |
US4398667A (en) * | 1976-12-23 | 1983-08-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus and method for jet noise suppression |
US4165609A (en) * | 1977-03-02 | 1979-08-28 | The Boeing Company | Gas turbine mixer apparatus |
US4214441A (en) * | 1978-09-12 | 1980-07-29 | The United States Of America As Represented By The Secretary Of The Navy | Infrared suppressor device |
US4215536A (en) * | 1978-12-26 | 1980-08-05 | The Boeing Company | Gas turbine mixer apparatus |
US4226297A (en) * | 1979-01-12 | 1980-10-07 | United Technologies Corporation | Acoustic treated exhaust plug for turbine engine |
US4819425A (en) * | 1982-03-18 | 1989-04-11 | The Boeing Company | Primary-secondary ventilated flow mixer nozzle for high bypass turbo fan jet propulsion system |
GB2160265A (en) | 1984-06-12 | 1985-12-18 | Rolls Royce | Turbofan exhaust mixers |
US4817379A (en) * | 1985-01-09 | 1989-04-04 | Bagley Charles S | Jet propulsion engine and method |
US5117628A (en) * | 1990-01-25 | 1992-06-02 | General Electric Company | Mixed flow augmentor pre-mixer |
US5184459A (en) * | 1990-05-29 | 1993-02-09 | The United States Of America As Represented By The Secretary Of The Air Force | Variable vane valve in a gas turbine |
US5884843A (en) * | 1996-11-04 | 1999-03-23 | The Boeing Company | Engine noise suppression ejector nozzle |
US6640537B2 (en) * | 2000-12-18 | 2003-11-04 | Pratt & Whitney Canada Corp. | Aero-engine exhaust jet noise reduction assembly |
US6845607B2 (en) * | 2002-01-09 | 2005-01-25 | The Nordam Group, Inc. | Variable area plug nozzle |
BR0307845B1 (pt) * | 2002-02-22 | 2012-09-18 | bocal de exaustão de misturador duplex. |
-
2001
- 2001-09-14 DE DE10145489A patent/DE10145489B4/de not_active Expired - Fee Related
-
2002
- 2002-08-29 US US10/489,599 patent/US7299635B2/en not_active Expired - Fee Related
- 2002-08-29 CA CA2460549A patent/CA2460549C/en not_active Expired - Fee Related
- 2002-08-29 JP JP2003528979A patent/JP4148893B2/ja not_active Expired - Fee Related
- 2002-08-29 EP EP02769890A patent/EP1425504A2/de not_active Withdrawn
- 2002-08-29 WO PCT/DE2002/003157 patent/WO2003025378A2/de active Application Filing
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3153319A (en) * | 1952-07-25 | 1964-10-20 | Young Alec David | Jet noise suppression means |
FR1086315A (fr) * | 1953-07-06 | 1955-02-11 | Perfectionnements apportés aux réacteurs combinés | |
US3002341A (en) * | 1957-12-31 | 1961-10-03 | Boeing Co | Jet engine noise suppression nozzles |
US2987883A (en) * | 1959-06-22 | 1961-06-13 | Boeing Co | Jet engine noise suppression nozzle with aerodynamic supplemental fluting |
US3196608A (en) * | 1959-06-23 | 1965-07-27 | Rolls Royce | Apparatus to admix by-pass air with exhaust gases in a by-pass gas-turbine engine |
US3612212A (en) * | 1969-08-11 | 1971-10-12 | Rohr Corp | Method and apparatus for suppressing the noise of a jet engine |
US3587777A (en) * | 1969-10-23 | 1971-06-28 | Rohr Corp | Turbofan propulsion apparatus with silencer and operating method |
US4292803A (en) * | 1979-01-19 | 1981-10-06 | Rohr Industries, Inc. | Turbo fan engine mixer |
US5758488A (en) * | 1993-05-11 | 1998-06-02 | Roderick Thomson | Core flow expansion chamber device system for reduction of jet turbine engine noise |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009138068A1 (de) * | 2008-05-15 | 2009-11-19 | Mtu Aero Engines Gmbh | Mischdüsenaufbau |
Also Published As
Publication number | Publication date |
---|---|
US7299635B2 (en) | 2007-11-27 |
EP1425504A2 (de) | 2004-06-09 |
JP4148893B2 (ja) | 2008-09-10 |
DE10145489B4 (de) | 2008-11-06 |
CA2460549C (en) | 2011-01-04 |
WO2003025378A3 (de) | 2003-05-30 |
CA2460549A1 (en) | 2003-03-27 |
JP2005502819A (ja) | 2005-01-27 |
US20050022502A1 (en) | 2005-02-03 |
DE10145489A1 (de) | 2003-04-10 |
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