GB2035151A - Vortex separators - Google Patents

Vortex separators Download PDF

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Publication number
GB2035151A
GB2035151A GB7933030A GB7933030A GB2035151A GB 2035151 A GB2035151 A GB 2035151A GB 7933030 A GB7933030 A GB 7933030A GB 7933030 A GB7933030 A GB 7933030A GB 2035151 A GB2035151 A GB 2035151A
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GB
United Kingdom
Prior art keywords
separator
primary duct
duct
liquid
vaned
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.)
Granted
Application number
GB7933030A
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GB2035151B (en
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB7933030A priority Critical patent/GB2035151B/en
Publication of GB2035151A publication Critical patent/GB2035151A/en
Application granted granted Critical
Publication of GB2035151B publication Critical patent/GB2035151B/en
Expired legal-status Critical Current

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Classifications

    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04C—APPARATUS USING FREE VORTEX FLOW, e.g. CYCLONES
    • B04C3/00—Apparatus in which the axial direction of the vortex flow following a screw-thread type line remains unchanged ; Devices in which one of the two discharge ducts returns centrally through the vortex chamber, a reverse-flow vortex being prevented by bulkheads in the central discharge duct
    • B04C3/04—Multiple arrangement thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04C—APPARATUS USING FREE VORTEX FLOW, e.g. CYCLONES
    • B04C3/00—Apparatus in which the axial direction of the vortex flow following a screw-thread type line remains unchanged ; Devices in which one of the two discharge ducts returns centrally through the vortex chamber, a reverse-flow vortex being prevented by bulkheads in the central discharge duct
    • B04C3/06—Construction of inlets or outlets to the vortex chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
    • F02M35/02—Air cleaners
    • F02M35/022—Air cleaners acting by gravity, by centrifugal, or by other inertial forces, e.g. with moistened walls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
    • B04C—APPARATUS USING FREE VORTEX FLOW, e.g. CYCLONES
    • B04C3/00—Apparatus in which the axial direction of the vortex flow following a screw-thread type line remains unchanged ; Devices in which one of the two discharge ducts returns centrally through the vortex chamber, a reverse-flow vortex being prevented by bulkheads in the central discharge duct
    • B04C2003/006—Construction of elements by which the vortex flow is generated or degenerated

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Separating Particles In Gases By Inertia (AREA)
  • Cyclones (AREA)

Abstract

A vortex separator for separating liquid droplets from a gas stream e.g. air ingested by the compressor of a jet engine, comprises a primary duct 12 provided at its inlet with a vaned vortex generator 13 which includes, on the flanks of its vanes 14, grooves 15 which collect the droplets into coalesced streams and directs them to an area adjacent the duct wall. A secondary duct 12b provides an exit for substantially liquid free gas and defines with the primary duct an outlet for the coalesced liquid streams. The grooves on the flanks of each vane may be replaced by a single fence. <IMAGE>

Description

SPECIFICATION Separator This invention relates to separators and in particular to separators suitable for separating liquid droplets from a gas stream.
It is frequently desirable to separate liquid droplets from a gas stream if those droplets are detrimental in any way to the function served by that gas stream. For instance, the engines of helicopters adapted to operate in marine environments are prone to the ingestion of sea water spray. This is particularly troublesome in the case of gas turbine engine powered helicopters. In addition to causing corrosion problems, the sea water spray can, if it is of a sufficiently high concentration, cause the build up of various salt deposits on the compressor of the engine. If these deposits become sufficiently thick, the efficiency of the compressor, and in turn the engine is inevitably impaired. Engine power losses re sult which, in extreme cases, may be so great as to provide a serious threat to the safety of the helicopter and its crew.
It is an object of the present invention to provide a separator suitable for separating at least some liquid droplets from a liquid droplet carrying gas stream.
According to the present invention, a separator suitable for separating liquid droplets from a liquid droplet carrying gas stream comprises a substantially circular cross-section primary duct containing vaned means adapted to induce any liquid droplet carrying gas stream passing through said primary duct into a vortex about the axis of said duct and to provide at least one surface upon which some of said liquid droplets will impinge and coalesce, said vaned means being adapted to direct any such coalesced liquid to the radially outer regions of said primary duct whereby any gas stream exhausted from the radially inner regions of said primary duct will have a reduced liquid droplet concentration or be substantially liquid droplet free.
Said at least one surface of said vaned means may be provided with a plurality of grooves, adapted to direct coalesced liquid to the radially outer regions of said primary duct.
Alternatively said at least one surface of said vaned means may be provided with at least one fence adapted to direct coalesced liquid to the radially outer regions of said primary duct.
Said vaned means may comprise a plurality of vanes mounted on a common support member positioned along the longitudinal axes of said primary duct, said vanes extending between said support member and the internal wall of said primary duct.
Preferably means are provided downstream of said vaned means which means are adapted to split any gas stream exhausted from the radially inner regions of said primary duct from any gas stream exhausted from the radially outer regions of said primary duct.
Said gas stream splitting means preferably comprises a secondary duct having an end portion of frusto conical form, the smaller diameter end of said frusto conical end portion being positioned within said primary duct and adjacent the downstream end of said vaned means.
The radially outer surface of said secondary duct and the radially inner surface of said primary duct downstream of said vaned means may each be provided with means adapted to break up any of said coalesced liquid into droplets.
Said means adapted to break up said coalesced liquid into droplets may comprise a plurality of axial grooves.
Said separator may comprise one of a plurality of similar separators grouped together in support means and provided with a common drain for liquid separated from said gas stream.
The invention will now be described, by way of example, with reference to the accompanying drawings in which : Figure 1 is a sectioned side view of a bank of separators in accordance with the present invention mounted in a support frame.
Figure 2 is a sectioned perspective view of one of the separators shown in Fig. 1, Figure 3 is a sectioned perspective view of an alternative form of separator to that shown in Fig. 2.
With reference to Fig. 1, a support frame 10 carried a bank of similar separators 11, one of which can be more easily seen in Fig.
2.
The separator 11 comprises a circular crosssection primary duct 1 2 which contains a vaned structure 1 3. The vaned structure 1 3 is made up of four vanes 1 4 which are mounted on a common support member 1 5. Although in this particular example four vanes have been employed, it will be appreciated that in certain circumstances, different numbers of vanes may be necessary. The support member 1 5 is generally cylindrical in form and positioned along the axis of the primary duct 1 2.
The vanes 1 4 extend between the support member 1 5 and the internal wall 1 2a of the primary duct 1 2 so as to maintain the support member 1 5 in position along the axis of the primary duct 12. The vanes 14 are so shaped that any gas stream passing through the primary duct 1 2 in the direction indicated by arrow A will be induced into a vortex about the axis of the primary duct 1 2.
Each vane 14 is provided on one of its faces 1 4a with a series of adjacent grooves 1 6 which extend in a generally axial direction.
More specifically, the grooves 1 6 are equally spaced apart along the leading edge 1 7 of the vane 14 and extend to the radially outer region of the trailing edge 1 8 of the vane 14.
The arrangement is such that any liquid droplets carried by the gas stream flowing through the primary duct 1 2 will be centrifugally urged by the vortex motion of the gas stream in a generally radial direction. Some of the droplets wili be urged to the radially outer reaches of the primary duct 1 2 while the remainder will impinge upon the vanes 14.
The impinging liquid droplets will coalesce on the vanes 14 and be directed to the radially outer reaches of the primary duct 12 by the grooves 1 6. Consequently the gas stream exhausted from the radially outer regions of the duct 12 will have a high liquid concentration and the other exhausted from the radially inner regions of the duct will have a reduced liquid concentration or will be substantially liquid droplet free.
In order to split these two gas stream portions, a secondary duct 1 2 b is positioned downstream of the vaned structure 1 3. The end of the secondary duct 1 2b is of frusto conical form with its smaller diameter portion positioned within the primary duct 1 2 and adjacent the downstream end of the vaned structure 13. Thus the gas stream portion which has a low liquid concentration or is liquid free will pass into the secondary duct 126 whilst the remaining portion having a high liquid concentration will pass around the outside of the secondary duct 1 2b.
Referring back to Fig. 1 the gas flow having a reduced or eliminated liquid droplet content will emerge from the secondary duct 12b and pass out of the support frame 10. The gas flow having a high liquid concentration will, however, exhaust into the support frame 10 where the liquid is removed through a drain 19.
In the separator 11 shown in Fig. 2, the grooves 1 6 on the face 1 4a of each vane have been replaced by a single fence 20.
Thus each vane 14 is provided with a single fence 20 which extends along the face 1 4a from the radially inner region of the leading edge 1 7 to the radially outer region of the trailing edge 18 of the vane 14. The fences 20 function in a similar fashion to the grooves 1 6 in that they direct coalesced liquid to the radially outer reaches of the primary duct 12.
Although the present invention has been described with reference to vanes 14 provided with adjacent grooves 1 6 or fences 20 on one of its faces 1 4a it will be appreciated that they could also be provided on both faces of each vane 14.
In order to break up the liquid emerging from the radially outer reaches of the vaned structure B into droplets, the radially outer surface of the frusto conical end portion of the secondary duct 12b and the radially inner surface of the primary duct 1 2 downstream of the vaned structure 1 3 may be provided with a plurality of axial grooves 21 (Fig. 3). By breaking the liquid down into droplet form in this manner, more efficient liquid dispersal is achieved. It will be appreciated, however, that other suitable formations could be provided in order to achieve the same result.
The support frame 10 and its associated separators 11 and secondary ducts 18 may be utilised for instance in separating sea water spray from air passing into the engine inlets of helicopters adapted to operate in marine environments. The support frame 10 could be conveniently located in front of a helicopter engine inlet with the secondary ducts 18 positioned so as to direct air having a low or zero sea water spray content into the engine inlet.

Claims (9)

1. A separator suitable for separating liquid droplets from a liquid droplet carrying gas stream comprising a substantially circular cross-section primary duct containing vaned means adapted to induce any liquid droplet carrying gas stream passing through said primary duct into a vortex about the axis of said duct and to provide at least one surface upon which some of said liquid droplets will impinge and coalesce, said vaned means being adapted to direct any such coalesced liquid to the radially outer regions of said primary duct whereby any gas stream exhausted from the radially inner regions of said primary duct will have a reduced liquid droplet concentration or be substantially liquid droplet free.
2. A separator as claimed in claim 1 wherein said at least one surface of said vaned means is provided with a plurality of grooves adapted to direct coalesced liquid to the radially outer regions of said primary duct.
3. A separator as claimed in claim 1 wherein said at least one surface of said vaned means is provided with at least one fence adapted to direct coalesced liquid to the radially outer regions of said primary duct.
4. A separator as claimed in any one of claims 1 to 3 wherein said vaned means comprises a plurality of vanes mounted on a common support member positioned along the longitudinal axis of said primary duct, said vane extending between said support member and the internal wall of said primary duct.
5. A separator as claimed in any one of claims 1 to 4 wherein means are provided downstream of said vaned means which means are adapted to split any gas stream exhausted from the radially inner regions of said primary duct from any gas stream exhausted from the radially outer region of said primary duct.
6. A separator as claimed in claim 5 wherein said gas stream splitting means comprises a secondary duct having an end portion of frusto conical form, the smaller diameter end of said frusto conical end portion being positioned within said primary duct and adja cent the downstream end of said vaned means.
7. A separator as claimed in any one preceding claim wherein the radially outer surface of said secondary duct and the radially inner surface of said primary duct downstream of said vaned means are each provided with means adapted to break up any of said coalesced liquid into droplets.
8. A separator as claimed in claim 7 wherein said means adapted to break up said coalesced liquid into droplets comprises a plurality of axial grooves.
9. A separator as claimed in any one preceding claim wherein said separator comprises one of plurality of similar separators grouped together in support means and provided with a common drain for liquid separated from said gas stream.
1 0. A separator substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
GB7933030A 1978-11-28 1979-09-24 Vortex separators Expired GB2035151B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7933030A GB2035151B (en) 1978-11-28 1979-09-24 Vortex separators

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB7846429 1978-11-28
GB7933030A GB2035151B (en) 1978-11-28 1979-09-24 Vortex separators

Publications (2)

Publication Number Publication Date
GB2035151A true GB2035151A (en) 1980-06-18
GB2035151B GB2035151B (en) 1982-08-04

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3603978A1 (en) * 1985-02-15 1986-08-21 TLV Co. Ltd., Tokio/Tokyo CONDENSATE DISCHARGE
US4654061A (en) * 1985-05-31 1987-03-31 Union Oil Company Of California Geothermal steam separator
US4723970A (en) * 1985-02-15 1988-02-09 Tlv Co., Ltd. Gas-water separator
FR2642662A1 (en) * 1989-02-09 1990-08-10 Abg Semca Device and process for separating solid particles present in a gas and apparatus comprising such a device
GB2404887A (en) * 2003-08-13 2005-02-16 Dyson Ltd Grooved outlet for cyclonic separating apparatus
US7357825B2 (en) 2001-09-28 2008-04-15 Shell Oil Company Cyclonic fluid separator with vortex generator in inlet section
US9283502B2 (en) 2011-08-31 2016-03-15 Orbital Atk, Inc. Inertial extraction system
EP2607656A3 (en) * 2011-12-21 2017-06-28 General Electric Company Gas turbine engine particle separator
US11420144B2 (en) * 2019-05-09 2022-08-23 S&B Filters, Inc Multi-vane vortex tubes for motor vehicles

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3603978A1 (en) * 1985-02-15 1986-08-21 TLV Co. Ltd., Tokio/Tokyo CONDENSATE DISCHARGE
GB2171617A (en) * 1985-02-15 1986-09-03 Tlv Co Ltd Gas-water separator
US4723970A (en) * 1985-02-15 1988-02-09 Tlv Co., Ltd. Gas-water separator
US4654061A (en) * 1985-05-31 1987-03-31 Union Oil Company Of California Geothermal steam separator
FR2642662A1 (en) * 1989-02-09 1990-08-10 Abg Semca Device and process for separating solid particles present in a gas and apparatus comprising such a device
US7357825B2 (en) 2001-09-28 2008-04-15 Shell Oil Company Cyclonic fluid separator with vortex generator in inlet section
GB2404887A (en) * 2003-08-13 2005-02-16 Dyson Ltd Grooved outlet for cyclonic separating apparatus
US7513924B2 (en) 2003-08-13 2009-04-07 Dyson Technology Limited Cyclonic separating apparatus
US9283502B2 (en) 2011-08-31 2016-03-15 Orbital Atk, Inc. Inertial extraction system
EP2607656A3 (en) * 2011-12-21 2017-06-28 General Electric Company Gas turbine engine particle separator
US11420144B2 (en) * 2019-05-09 2022-08-23 S&B Filters, Inc Multi-vane vortex tubes for motor vehicles

Also Published As

Publication number Publication date
GB2035151B (en) 1982-08-04

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19930924