US3557830A - Device for forced mixing of parallel fluid flows - Google Patents

Device for forced mixing of parallel fluid flows Download PDF

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Publication number
US3557830A
US3557830A US3557830DA US3557830A US 3557830 A US3557830 A US 3557830A US 3557830D A US3557830D A US 3557830DA US 3557830 A US3557830 A US 3557830A
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United States
Prior art keywords
flow
flows
partition
discs
triangular
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Expired - Lifetime
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English (en)
Inventor
John A Raw
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GKN Aerospace Sweden AB
SVENSKA FIYGMOTOR AB
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Svenska Flygmotor AB
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    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/87571—Multiple inlet with single outlet
    • Y10T137/87652—With means to promote mixing or combining of plural fluids

Definitions

  • Nilson Att0rneySommers & Young ABSTRACT A device for forced mixing of parallel fluid flows by means of guide vanes such as for mixing hot and cold gaseous flows in turbine-jet engines, said guide vanes consisting of a plurality of triangular discs turned with a corner opposite the direction of flow and having the base as trailing edge and located with said corner spaced from a partition between said flows, at the end edge of which partition said discs are mounted at such angle of attack to the direction of flow that they are approaching the border area between said flows as seen from said corner towards said trailing edge, the side edges of said triangular discs being located each in a side plane disc disposed in the direction of flow and by means of which said triangular disc is supported from said partition.
  • the present invention concerns a device for forced mixing of parallel fluid flows by means of guide vanes, such as for mixing hot and cold gaseous flows in turbine-jet engines.
  • the general rule is that two flows of gas or liquid separated by a partition but then in parallel relationship entering into a common passage, have approximately the same static pressure but may have different temperatures, velocity and density. Said flows are intermixed in the border area therebetween substantially due to viscous effects.
  • the contact area between the two flows must be increased.
  • Said deflection can be achieved by substantially two ways. One of them is by extend ing the partition between the inlet channels of the gas flows, as is known in prior art, eg to the peripheral wall of the intermixing length and is provided with apertures or nozzles for inlet of one of the flowing fluids into the other with a velocity component at right angles to the direction of flow of the latter.
  • This kind of deflecting device can provide a rapid mixing but then at the expense of high pressure loss.
  • the arrangement is heavy, which is a substantial drawback in aeronautical applications.
  • the second way is to fold said flows at the end of the partition by local deflection and thus increase the mixing area therebetween.
  • Said deflection can be provided by folding the final portion of the partition or by guide vanes immediately downstream the same,
  • the change of the direction of flow or the angle the flow is deflected is the parameter best distinguishing how difficult this process actually is.
  • the possibility of achieving an effective deflection of the flows and thus a good mixing is limited in this last-mentioned kind of deflection device by the circumstance that already at a relatively small deflection angle of about the boundary layer increase on the downstream side of the guide vane, i.e. the side turned opposite the direction of flow, results in a flow separation. Said flow separation involves pressure losses and reduced deflection.
  • the main object of the present invention is to eliminate the above-mentioned difficulties and the invention is based on the aerodynamic discovery now well known in the aeronautical field, viz that 'a plane triangular disclike body with a corner or peak directed opposite the direction of flow and having the base at trailing edge gives raise to a vortex flow if said body is mounted at an angle of incidence relative to said direction of flow.
  • Said vortex flow is formed on the downstream side of said disc and consists of two counterrotating vortexes. Due to their high speed of rotation, said vortexes create a high flow velocity adjacent the downstream surface or the suction surface.
  • said vortex flow involves a pressure loss per se but the latter can be limited to its extent in a surprisingly simple way by ar-' ranging side plane discs in the direction of flow along the side edges of the triangle.
  • the reason for said limiting effect of said side discs is that they prevent an overflow from the pressure side of said guide vane to the suction side thereof, and thereby the vortex intensity is limited.
  • the invention is substantially distinguished in that the guide vanes consist of a plurality of triangular discs, preferably with two equal sides and mounted equally spaced along the end edge of a partition between said flows, said triangular discs being tumed with the corner or peak opposite the direction of flow and the base as trailing edge and located with said peak or corner spaced from that partition, said discs furthermore being mounted at an angle to the direction of flow so that they, as seen from the comer towards the trailing edge, are approaching the border area between said flows, said two equal edges of the triangular disc being situated each in a side plane disc, which is located in the direction of flow and by means of which said triangular disc is supported from said partition between the flows.
  • the angle of deflection of the flow can be increased without any risks for flow separation of the flowing fluid from the downstream surface of the guide vane.
  • this involves that the very mixing process occurs within a substantially shorter length.
  • the suggested shape of the guide vane also involves that the mixing device is simple and light and inexpensive in manufacture, particularly due to the fact that each guide vane can be produced in one single piece of sheet material.
  • a favorable secondary effect of the two vortexes created on the downstream surface of the disc also is that they vigorously contribute to the very mixing and in its turn this involves that less numerous guide vane units in principle must be used for achieving the same desired mixing effect as hitherto for a certain given passage length.
  • FIG. 1 illustrates an embodiment, partially in section, through a turbine-jet engine in the portion thereof, where a cold fan flow is mixed with the hot gas flow from the turbine in parallel relationship and where said two flows are to be mixed as fast and completely as possible;
  • FIG. 2 illustrates the arrangement of a plurality of guide vanes according to the invention along the end edge of a partition between the gas flows;
  • FIG. 3 is a plane view in detail of a guide vane according to the invention.
  • each type of guide vane is the ability thereof to change the direction of flow of the fluid, and therefore comparisons if made must concern said deflection angle.
  • a guide vane of previously known type with an extension in the direction of flow comparable with the guide vane according to the present invention can give a maximum deflection angle of about 15 in the exemplifying embodiment mentioned in the following.
  • the partition 3 at the rear edge of the partition 3 now are arranged along the channel periphery suitably spaced guide vanes consisting of triangular discs 6, preferably having two equal sides and the base as trailing edge. Owing to said shape and for previously mentioned reasons said discs cause an exceptionally great deflection of the direction of flow.
  • the two side edges of the discs 6 are located each in a side plane disc 7, disposed in the direction of flow and by means of which the triangular disc 6 is supported from the partition 3.
  • said side plane discs 7 at the same time provide an obstacle for preventing the overflow from the pressure side of the guide vane to the suction side thereof and thus limit the extent of the unavoidable pressure losses.
  • it is suitable to make them together with the side plane discs in one single piece of any suitable sheet material. It is also suitable to form attaching flanges 8 at the front portion of the free edges of the side plane discs 7 in the direction of flow for securing the guide vanes to the rear edge of the partition 3.
  • a device for forced mixing of parallel fluid flows by means of guide vanes such as for mixing hot and cold gas flows in turbine-jet engines, characterized in that said guide vanes consist of a plurality of triangular discs spaced along the end edge of a partition between said flows and having two equal sides turned with a comer or peak opposite the direction of flow and the base as trailing edge and disposed with said corner or peak spaced from said partition, said discs being arranged at an angle of attack to the direction of flow so that they are, as seen from the corner or peak towards the base, approaching or getting closer to the border area between said flows, the two side. edges of the triangular disc each are located in a side plane disc which is disposed in the direction of flow and by means of which said triangular disc is supported from the partition between the flows.
  • a device characterized in that said triangular disc and said side plane discs are made integrally of sheet metal and that at the front portion of the free edge of the side plane discs extending in the direction of flow is formed an attachment flange for the securing of the guide vane to the partition.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US3557830D 1968-06-17 1969-06-17 Device for forced mixing of parallel fluid flows Expired - Lifetime US3557830A (en)

Applications Claiming Priority (1)

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SE819168A SE320225B (en)) 1968-06-17 1968-06-17

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GB (1) GB1269562A (en))
SE (1) SE320225B (en))

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4164375A (en) * 1976-05-21 1979-08-14 E. T. Oakes Limited In-line mixer
US4577836A (en) * 1983-06-14 1986-03-25 Valeo Flap for a heater or air conditioner installation for a motor vehicle cabin
US4930308A (en) * 1986-08-11 1990-06-05 The Dee Howard Co. Double-flow turboshaft engine with variable confluent nozzle
US5422443A (en) * 1991-10-18 1995-06-06 Hughes Missile Systems Company Rocket exhaust disrupter shapes
US5803602A (en) * 1995-12-01 1998-09-08 Abb Research Ltd. Fluid mixing device with vortex generators
US6135629A (en) * 1998-05-11 2000-10-24 Deutsche Babcock Anlagen Gmbh Device for stirring up gas flowing through a duct having a structural insert positioned at an acute angle to a main gas stream
US20040037162A1 (en) * 2002-07-20 2004-02-26 Peter Flohr Vortex generator with controlled wake flow
US6779786B2 (en) * 2000-06-19 2004-08-24 Balcke-Durr Gmbh Mixer for mixing at least two flows of gas or other newtonian liquids
US20070186988A1 (en) * 2003-09-05 2007-08-16 Zhaoyan Liu Three-dimensionally intersecting diverter as an inner member for a pipe, barrel or tower
US20090320486A1 (en) * 2008-06-26 2009-12-31 Ephraim Jeff Gutmark Duplex tab exhaust nozzle
US20100180573A1 (en) * 2009-01-21 2010-07-22 Rolls-Royce Plc A gas turbine engine
US20100180574A1 (en) * 2009-01-21 2010-07-22 Rolls-Royce Plc Gas turbine engine
US20120047873A1 (en) * 2010-08-31 2012-03-01 General Electric Company Duplex tab obstacles for enhancement of deflagration-to-detonation transition
US8461704B2 (en) 2008-05-23 2013-06-11 Rolls-Royce Plc Gas turbine engine apparatus
US9115602B2 (en) 2011-10-19 2015-08-25 Siemens Aktiengesellschaft Exhaust diffuser including flow mixing ramp for a gas turbine engine
US10760451B2 (en) * 2015-05-22 2020-09-01 General Electric Company Manufacture and installation of diffuser flow mixing lobes

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3043239C2 (de) * 1980-11-15 1985-11-28 Balcke-Dürr AG, 4030 Ratingen Verfahren und Vorrichtung zum Vermischen mindestens zweier fluider Teilströme
SE454245B (sv) * 1984-12-18 1988-04-18 Flaekt Ab Anordning for att i en kontaktreaktor och med hjelp av en eller flera virvelbildningar mojliggora en blandning av ett forsta medium med ett andra medium

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999672A (en) * 1958-04-09 1961-09-12 Curtiss Wright Corp Fluid mixing apparatus
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
US3377804A (en) * 1966-06-13 1968-04-16 Gen Electric Flow mixers particularly for gas turbine engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999672A (en) * 1958-04-09 1961-09-12 Curtiss Wright Corp Fluid mixing apparatus
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
US3377804A (en) * 1966-06-13 1968-04-16 Gen Electric Flow mixers particularly for gas turbine engines

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4164375A (en) * 1976-05-21 1979-08-14 E. T. Oakes Limited In-line mixer
US4577836A (en) * 1983-06-14 1986-03-25 Valeo Flap for a heater or air conditioner installation for a motor vehicle cabin
US4930308A (en) * 1986-08-11 1990-06-05 The Dee Howard Co. Double-flow turboshaft engine with variable confluent nozzle
US5422443A (en) * 1991-10-18 1995-06-06 Hughes Missile Systems Company Rocket exhaust disrupter shapes
US5803602A (en) * 1995-12-01 1998-09-08 Abb Research Ltd. Fluid mixing device with vortex generators
US6135629A (en) * 1998-05-11 2000-10-24 Deutsche Babcock Anlagen Gmbh Device for stirring up gas flowing through a duct having a structural insert positioned at an acute angle to a main gas stream
US6779786B2 (en) * 2000-06-19 2004-08-24 Balcke-Durr Gmbh Mixer for mixing at least two flows of gas or other newtonian liquids
US20040037162A1 (en) * 2002-07-20 2004-02-26 Peter Flohr Vortex generator with controlled wake flow
US7753080B2 (en) 2003-09-05 2010-07-13 Zhaoyan Liu Three-dimensionally intersecting diverter as an inner member for a pipe, barrel or tower
US20070186988A1 (en) * 2003-09-05 2007-08-16 Zhaoyan Liu Three-dimensionally intersecting diverter as an inner member for a pipe, barrel or tower
US8461704B2 (en) 2008-05-23 2013-06-11 Rolls-Royce Plc Gas turbine engine apparatus
WO2010011381A1 (en) * 2008-06-26 2010-01-28 General Electric Company Duplex tab exhaust nozzle
GB2474377A (en) * 2008-06-26 2011-04-13 Gen Electric Duplex tab exhaust nozzle
US8087250B2 (en) 2008-06-26 2012-01-03 General Electric Company Duplex tab exhaust nozzle
GB2474377B (en) * 2008-06-26 2012-02-29 Gen Electric Duplex tab exhaust nozzle
US20090320486A1 (en) * 2008-06-26 2009-12-31 Ephraim Jeff Gutmark Duplex tab exhaust nozzle
US20100180573A1 (en) * 2009-01-21 2010-07-22 Rolls-Royce Plc A gas turbine engine
US20100180574A1 (en) * 2009-01-21 2010-07-22 Rolls-Royce Plc Gas turbine engine
US8578700B2 (en) * 2009-01-21 2013-11-12 Rolls-Royce Plc Gas turbine engine with fluid mixing arrangement
US20120047873A1 (en) * 2010-08-31 2012-03-01 General Electric Company Duplex tab obstacles for enhancement of deflagration-to-detonation transition
US8881500B2 (en) * 2010-08-31 2014-11-11 General Electric Company Duplex tab obstacles for enhancement of deflagration-to-detonation transition
US9115602B2 (en) 2011-10-19 2015-08-25 Siemens Aktiengesellschaft Exhaust diffuser including flow mixing ramp for a gas turbine engine
US10760451B2 (en) * 2015-05-22 2020-09-01 General Electric Company Manufacture and installation of diffuser flow mixing lobes

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Publication number Publication date
GB1269562A (en) 1972-04-06
SE320225B (en)) 1970-02-02

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