EP1425504A2 - Dispositif pour melanger deux courants fluidiques qui sont a l'origine conduits de maniere separee dans un moteur a reaction a double circuit - Google Patents

Dispositif pour melanger deux courants fluidiques qui sont a l'origine conduits de maniere separee dans un moteur a reaction a double circuit

Info

Publication number
EP1425504A2
EP1425504A2 EP02769890A EP02769890A EP1425504A2 EP 1425504 A2 EP1425504 A2 EP 1425504A2 EP 02769890 A EP02769890 A EP 02769890A EP 02769890 A EP02769890 A EP 02769890A EP 1425504 A2 EP1425504 A2 EP 1425504A2
Authority
EP
European Patent Office
Prior art keywords
mixing tube
mixing
openings
axis
perforated collar
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.)
Withdrawn
Application number
EP02769890A
Other languages
German (de)
English (en)
Inventor
Karl Katheder
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1425504A2 publication Critical patent/EP1425504A2/fr
Withdrawn legal-status Critical Current

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

La présente invention concerne un dispositif pour mélanger deux courants fluidiques (16, 18) qui sont à l'origine conduits de manière séparée dans un moteur à réaction. Un tuyau de mélange (10) entoure un faisceau central très chaud (16) et un courant secondaire froid (18) s'écoule sur la surface de revêtement profilée externe (12) de ce tuyau de mélange. Ledit tuyau de mélange (10) se présente sous forme d'un cône tronqué qui se resserre dans la direction d'écoulement (S) et comprend, à l'extrémité en aval, dans la direction périphérique du revêtement (12) du tuyau de mélange, des ouvertures (20) qui sont situées dans un plan de section transversale perpendiculaire à l'axe longitudinal (14) du tuyau de mélange (10). Ces ouvertures permettent de faire pénétrer le faisceau central très chaud (16) qui traverse le tuyau de mélange (10) dans le courant secondaire froid (18) qui s'écoule autour du revêtement (12) du tuyau de mélange. Lesdites ouvertures (20) présentent des surfaces de transit à profil elliptique (22) qui comprennent un axe principal (24) et un axe secondaire (26). Ledit axe principal (24) des surfaces de transit (22) à la surface de revêtement (12) du tuyau de mélange (10) s'étend dans la direction d'écoulement (S) des fluides (16, 18) et l'axe secondaire (26) s'étend perpendiculairement à celle-ci.
EP02769890A 2001-09-14 2002-08-29 Dispositif pour melanger deux courants fluidiques qui sont a l'origine conduits de maniere separee dans un moteur a reaction a double circuit Withdrawn EP1425504A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10145489A DE10145489B4 (de) 2001-09-14 2001-09-14 Anordnung zum Vermischen von zwei ursprünglich getrennt geführten Fluidströmen in einem Zweikreis-Strahltriebwerk
DE10145489 2001-09-14
PCT/DE2002/003157 WO2003025378A2 (fr) 2001-09-14 2002-08-29 Dispositif pour melanger deux courants fluidiques qui sont a l'origine conduits de maniere separee dans un moteur a reaction a double circuit

Publications (1)

Publication Number Publication Date
EP1425504A2 true EP1425504A2 (fr) 2004-06-09

Family

ID=7699133

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02769890A Withdrawn EP1425504A2 (fr) 2001-09-14 2002-08-29 Dispositif pour melanger deux courants fluidiques qui sont a l'origine conduits de maniere separee dans un moteur a reaction a double circuit

Country Status (6)

Country Link
US (1) US7299635B2 (fr)
EP (1) EP1425504A2 (fr)
JP (1) JP4148893B2 (fr)
CA (1) CA2460549C (fr)
DE (1) DE10145489B4 (fr)
WO (1) WO2003025378A2 (fr)

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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
DE102008023816A1 (de) * 2008-05-15 2009-11-19 Mtu Aero Engines Gmbh Mischdüsenaufbau
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

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Title
See references of WO03025378A2 *

Also Published As

Publication number Publication date
DE10145489A1 (de) 2003-04-10
CA2460549C (fr) 2011-01-04
DE10145489B4 (de) 2008-11-06
US20050022502A1 (en) 2005-02-03
WO2003025378A3 (fr) 2003-05-30
CA2460549A1 (fr) 2003-03-27
WO2003025378A2 (fr) 2003-03-27
JP2005502819A (ja) 2005-01-27
JP4148893B2 (ja) 2008-09-10
US7299635B2 (en) 2007-11-27

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