WO2014167329A1 - Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique - Google Patents

Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique Download PDF

Info

Publication number
WO2014167329A1
WO2014167329A1 PCT/GB2014/051111 GB2014051111W WO2014167329A1 WO 2014167329 A1 WO2014167329 A1 WO 2014167329A1 GB 2014051111 W GB2014051111 W GB 2014051111W WO 2014167329 A1 WO2014167329 A1 WO 2014167329A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
air inlet
vane
channel
inlet filter
Prior art date
Application number
PCT/GB2014/051111
Other languages
English (en)
Original Assignee
Veotec Ltd
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 Veotec Ltd filed Critical Veotec Ltd
Publication of WO2014167329A1 publication Critical patent/WO2014167329A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D45/00—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces
    • B01D45/04—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by utilising inertia
    • B01D45/08—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by utilising inertia by impingement against baffle separators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D46/00—Filters or filtering processes specially modified for separating dispersed particles from gases or vapours
    • B01D46/42—Auxiliary equipment or operation thereof
    • B01D46/4263—Means for active heating or cooling
    • 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
    • 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
    • F02C7/047—Heating to prevent icing
    • 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
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
    • 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

  • This invention relates to apparatus and methods for heating gas turbine air inlets by electrically heating an air inlet vane separator arranged upstream of a gas turbine air inlet.
  • Gas turbines have been used in recent times as power sources for vehicles such as ships and aircraft as well as in electrical power generation applications.
  • the basic operating principle of a gas turbine requires the intake of atmospheric air to a compressor. If the gas turbine is being operated in an environment where the atmosphere is polluted, dusty, moist or salty, it is necessary to filter out such impurities using an air inlet filter and/or vane separator / coalescer combination to maintain turbine performance and protect the turbine from damage.
  • aspects of the present invention provide elegant, power-efficient solutions to the problem of ice formation on the inlet to a gas turbine compressor as well as to the problem of ice formation in gas turbine air inlet filters.
  • a vane for a gas turbine air inlet filter has a body that, when in position in the gas turbine air inlet filter, extends substantially in a direction of airflow, and has a length extending substantially perpendicular to the direction of airflow.
  • the vane has a plurality of channels (preferably two), each for holding an electrical trace heat element. These are disposed towards and along an upstream edge of the vane and are arranged in-line parallel to the direction of airflow.
  • Each of the channels may further comprise: an incident channel section at its upstream edge extending across the direction of airflow and along the vane length; a channel end section extending in the direction of the airflow, defining a first lateral channel limit; and a channel joining section extending in the direction of the airflow, defining a second lateral channel limit opposite the respective channel end section.
  • the first lateral channel limit of a first channel is preferably in line with the second lateral channel limit of a second channel when viewed along the direction of airflow.
  • a downstream edge of a channel joining section of at least one channel may comprise a step extending laterally in the direction of the first lateral channel limit, partially holding the electrical trace heat element in the channel.
  • Some embodiments may provide that a downstream edge of a most downstream channel of the plurality of channels is joined at an angle to an incident coalescing section and a downstream edge of the incident coalescing section is joined at an angle to a downstream separating section such that the incident and downstream coalescing sections form a single corrugation when viewed along the length of the vane, and wherein a downstream edge of the downstream coalescing section is joined at an angle to a tail section, which extends substantially along the direction of airflow.
  • inventions may further comprise drain channels for collecting water, each having a concave surface facing an upstream direction and positioned at the downstream edge of each of the incident coalescing section, the downstream coalescing section and the tail section.
  • the electrical trace heat element is preferably an electrical trace heating tape capable of providing at least 80Wm _1 of power per unit length.
  • a gas turbine air inlet filter is provided that comprises a plurality of vanes as described above.
  • the separator When connected to a gas turbine air inlet, the separator may be capable of providing sufficient heat to raise the temperature of air entering the gas turbine inlet system such that, without further heat input from a compressor bleed system, cooling due to acceleration of air flow downstream of the inlet filter and into the gas turbine inlet (e.g. a bellmouth gas turbine air inlet) does not lower the temperature at the gas turbine inlet to a temperature at which ice may form.
  • a method of heating a gas turbine air inlet having a gas turbine air inlet filter comprises: providing sufficient heat at the gas turbine air inlet filter by means of electrical trace heating to raise the temperature at the gas turbine air inlet filter such that, without heat input from a compressor bleed system, cooling due to acceleration of the airflow
  • a vane is provided with plural trace elements, and means are provided for independently switching off one or some of the trace elements, e.g. when the gas turbine is running at a reduced flow rate.
  • a control system such that the humidity of air at a gas turbine inlet is measured and a trace heat element is modulated (or one or some of plural trace heat elements is or are modulated) in response to measured humidity to maintain a desired heat input level or to maintain a desired temperature at the gas turbine inlet.
  • Figure 1 is a schematic view of a prior art gas turbine air inlet heating system.
  • Figure 2 is an alternative prior art gas turbine air inlet heating system.
  • Figure 3 is an exemplary prior art vane for a turbine inlet filter in cross-section from a view perpendicular to the airflow.
  • Figure 4 shows a revised design of air inlet filter vane in accordance with the present invention.
  • Figure 5 shows a sectional view of the same vane as Figure 4.
  • Figure 6 shows a sectional view of a vane in accordance with the present invention in which the heat tape channels have been crimped.
  • Figure 7 shows a cutaway view of a length of heat tape.
  • Figure 8 shows an exemplary gas turbine air inlet filter.
  • Figure 9 shows a gas turbine air inlet heating system employing the air intake filter of Figure 8.
  • Figure 1 shows a prior art gas turbine inlet heating system 100 in which air entering the system is heated by a compressor bleed system. Air enters inlet filter 102 where moisture and/or dust particles are substantially removed. The air then flows through duct 104 and enters gas turbine inlet 106. From here it enters the gas turbine 108 and may be used in a large variety of engine or power generation applications. Although only one inlet filter 102 and duct 104 are shown, one skilled in the art will appreciate that multiple inlet filters 102 and ducts 104 may feed into a single gas turbine 108.
  • the heating system of Figure 1 uses compressor bleed inlet heating. As a result of the compressive forces that air discharged from the compressor of a gas turbine has been subjected to, this air has a substantially higher temperature than that of the air entering the turbine 108. In a compressor bleed heating system, a portion 110 of the compressor discharge air is fed back to the inlet filter 102 where it mixes with the ambient air. The temperature of the mixed air entering the air inlet filter 102 should be sufficient that ice can no longer form on the gas turbine inlet filter 102 and may even be sufficient to prevent ice forming at the gas turbine inlet 106.
  • a system such as that of Figure 1 however has a major disadvantage in that, by extracting air on which work has been done, the extracted air is no longer used in the application for which the turbine 108 was designed (e.g. in electrical power generation or to power a vehicle). Efficiency of the gas turbine 108 is therefore reduced. Furthermore, while the system of Figure 1 is effective in preventing ice formation on the air inlet filter 102, the air must be heated considerably at the filter 102 to prevent ice formation at the gas turbine inlet 106 and therefore requires a substantial amount of discharge air to be extracted from the compressor.
  • Figure 2 shows an alternative design for a prior art gas turbine inlet heating system 200, which may offer some efficiency savings over the system of Figure 1.
  • This system 200 differs from that of Figure 1 in that the inlet filter 102 is heated by its own electrical heater system 202.
  • a compressor bleed inlet heating system 210 is still used but it is fed into the duct 104 downstream of the inlet filter 102 at point 204.
  • the electrical heater system 202 uses less compressor power (from an electric generator coupled to the turbine) than compressor bleed heating 110 to produce a comparable temperature rise. However, because compressor bleed heating is still used, considerable compressor power is wasted.
  • Figure 3 shows a vane 300 viewed in cross-section along a length of the vane perpendicular to the airflow, a plurality of which may be used in a gas turbine inlet filter like filter 102 of Figure 2.
  • air flows from heat tape channel 302 towards water separating drain channels 303, 304 and 305 and then through to a gas turbine (not shown).
  • the upstream limit of heat tape channel 302 is defined by incident channel section 312.
  • the lateral extent of heat tape channel 302 is defined between lateral end section 314 and lateral joining section 316.
  • electrical trace heat tape may be placed in heat tape channel 302 and kept in contact with all three sections 312, 314 and 316.
  • Typical trace heat tape produces a power per unit length ranging from 5Wm " 1 to 60Wm _1 . For applications where one merely requires the heating of the gas turbine inlet filter, this is entirely sufficient.
  • lateral joining section 316 is joined at an angle to incident section 306.
  • incident section 306 is joined at its downstream edge to downstream section 308 at an angle such that sections 306 and 308 form a single corrugation.
  • Downstream section 308 is connected at an angle to tail section 310, which is substantially parallel to the airflow.
  • Drain channel 303 is formed at the intersection between sections 306 and 308; drain channel 304 is formed at the intersection between sections 303 and 310; and drain channel 305 is formed at the downstream edge of section 310.
  • T 2 2.5°C value of temperature
  • T 2 2.5°C value of temperature
  • This phenomenon is largely independent of ambient conditions. Warmer conditions (above freezing) are not problematic. Sub-zero conditions imply dryer air. It has been found that raising the temperature at the air inlet filter from 0°C to 2.5°C independent of other conditions is sufficient to raise the temperature at the bellmouth to a temperature at which ice can no longer form.
  • Example values are shown in Table 2.
  • trace heat tape cannot deliver more than 60Wm " . Higher power would lead to degradation of the tape insulation (in a stand-alone tape).
  • the power output of the trace heat tape can be varied to account for changes in operational conditions. For example, when a gas turbine is operated at a reduced flow rate, the power required by the trace heat tape is correspondingly reduced. By supplying only the power necessary to raise the temperature of the gas turbine inlet to a temperature at which ice cannot form, efficiency savings can be made compared to operating the heat tape at a power output in normal operation. Other scenarios affecting the required temperature change at an air inlet separator will be apparent to one skilled in the art; for instance, the temperature at the gas turbine air inlet may be affected by radiation and/or conduction from hot parts of the gas turbine.
  • one or more of the lengths of heat tape of each vane may be independently switched off.
  • Other more sophisticated control systems may also be employed to alter the power output of one or more lengths of heat tape.
  • the power input to each length of heat tape may be adjusted manually by an operator or, more preferably, properties of the airflow or the environment may be measured by a system of sensors, and the power output of one or more lengths of heat tape modulated accordingly.
  • the property of the airflow may be the humidity and the system of sensors may be a humidity sensor.
  • FIG 4 shows a gas turbine inlet separator vane 400 in accordance with an embodiment of the present invention viewed along the length of the vane. It shares all of the features of vane 300 in Figure 3 but there are several additional features that deserve closer attention. Firstly, there are now two heat tape channels: upstream heat tape channel 402 and downstream heat tape channel 404. While only two heat tape channels are shown, one skilled in the art will appreciate that any number (in particular three or four) of heat tape channels can be included depending on design requirements.
  • the upstream limit of upstream heat tape channel 402 is defined by upstream incident channel section 412.
  • the lateral extent of upstream heat tape channel 402 is defined between upstream lateral end section 414 and upstream lateral joining section 416.
  • the upstream limit of downstream heat tape channel 404 is defined by downstream incident channel section 417 and the lateral extent of heat tape channel 302 is defined between downstream lateral end section 415 and downstream lateral joining section 419.
  • Electrical trace heat tape may be placed in each of heat tape channels 402 and 404 where it may be kept in contact with all three of its channel sections 412, 414, 415, 416, 417 and 419.
  • Upstream lateral joining section 416, downstream incident channel section 417 and downstream lateral end section 415 meet at trifurcation point 410 such that downstream heat tape channel 404 lies substantially behind upstream heat tape channel 402 when viewed from the upstream direction. This presents the channels 402 and 404 in an in-line configuration, one behind the other, thereby minimising airflow resistance.
  • the heat tape lengths are inserted into channels 402 and 404, which are subsequently crimped by applying pressure to their respective lateral end sections thereby tightly securing each length of heat tape.
  • the act of crimping may cause the vane to bend laterally.
  • upstream lateral end section 414 and downstream lateral end section 415 are arranged on opposite sides of their respective heat tape channels. crimping both end sections enables the bending of one end section to be substantially cancelled out by the bending due to the crimping of the other end section.
  • This benefit also applies where there are three tape channels.
  • Upstream heat tape channel 402 does not present any particular problem in this regard, as it is generally easily accessible at the front of the vane assembly.
  • step section 408 of downstream lateral joining section 419 extending laterally towards heat tape channel 404 presents an elegant solution to this potential problem.
  • a length of heat tape may easily be guided in from opening 418 at the downstream edge, but step section 408 provides sufficient resistance to stop the tape moving back out.
  • the person assembling may then crimp the downstream channel, substantially permanently securing the heat tape.
  • the inclusion of two heat tape channels enables twice the length of heat tape to be used. If the same or greater power is supplied to each section of heat tape, the heating of the airflow can be doubled. However, using twice the length of 60Wm _1 tape in an environment with an ambient temperature of around 0°C may not be enough to counteract the cooling due to the acceleration of the airflow once it has left the air inlet filter. In isolation, tape which outputs power per unit length greater than 60Wm _1 (i.e. tape with a larger number of turns per unit length of resistance wire) may degrade due to excess heating. However, when in contact with an air inlet vane the material of the vane acts as a heat sink. Thus, tape with a greater power per unit length than 60Wm _1 may be used without degrading the insulation. In a preferred embodiment, two parallel lengths of 80Wm _1 tape may be used per vane.
  • FIG. 5 shows a sectional view of the vane of Figure 4.
  • Incident section 306 and drain channel 303 are shown with microgrooves 504.
  • These microgrooves 504 increase the surface area of the vane sections on which they are formed, thereby increasing the likelihood of water coalescing on said sections. Furthermore, water coalescing on the grooves may drain down and be removed from the airflow in much the same way as for drain channels 304.
  • incident section 306 and drain channel 303 are the first surfaces the airflow may be incident upon, it is of most use to include microgrooves 504 on these sections. However, one skilled in the art will recognise that microgrooves 504 may be present on any of the vane surface sections.
  • Figure 6 shows the same vane as Figure 5 but now the vane is shown in a crimped state.
  • the trailing edges of lateral end sections 414 and 415 display a slight inward curvature 614 and 615 towards their respective heat tape channels. With heat tape in place, the act of crimping allows the heat tape to be secured substantially and permanently within the heat tape channel. Because lateral end sections 414 and 415 are on opposing sides of the vane, crimping each lateral end section can lead to downstream heat tape channel 404 remaining substantially behind upstream heat tape channel 402 when viewed from the upstream direction, giving the advantage that integrity of share is maintained and filter performance losses are mitigated.
  • Figure 7 shows a cutaway view of a length of electrical trace heat tape 700.
  • Electrical bus wires 702 are contained within and extend down the length of a piece of insulating material 708.
  • Resistance wire 704 is wrapped around the insulating material and is contacted to the electrical bus wires at contacts 706 arranged periodically along the length of the tape.
  • a voltage is applied to the bus wires, which in turn causes a current to flow within the resistance wire. It is this current flow in the resistance wire that causes resistive heating to occur and thereby heat the surrounding environment.
  • the vane and surrounding airflow would be heated.
  • the resistance wire 704 and insulating material 708 are insulated from grounding braid layer 712 by inner insulation layer 710. Grounding braid layer 712 is insulated in turn by outer insulation layer 714.
  • a preferred embodiment of the present invention would therefore have a heat power output per unit length of 160Wm _1 per vane.
  • a heating power of nearly lOkW per m can be applied to the gas flow. This may be sufficient to overcome the cooling associated with an accelerated airflow in conditions with near- freezing ambient temperatures. Ice formation on the gas turbine inlet downstream of the vane assembly gas turbine inlet filter can be prevented without extracting any energy from a compressor bleed inlet system. This provides a huge efficiency advantage over the prior art systems.
  • compressor power loss in the present invention is due to the fact that energy for the electrical trace heating may be derived from an electrical generator powered by the gas turbine.
  • FIG. 8 shows an assembled gas turbine air inlet filter including an expanded view of its internal structure.
  • a plurality of vanes 802 and filter element 804 is provided in filter housing 806.
  • Plurality of vanes 802 may comprise vanes in accordance with that of Figure 4.
  • Electrical trace heat tape 808 extends down channels at the leading edge of the vanes and may be controlled by heating control console 810. In cold conditions, heat tape 808 prevents ice formation on the vanes. In warmer conditions, heating control console 810 may turn off heating of the heat tape 808.
  • Moisture from an incident airflow will coalesce on the surface of the vanes particularly in drain channels 812. From here, the water will drain down due to gravity and flow out through drain 814. After moisture has been removed from the airflow by the plurality of vanes 802, the air passes through filter element 804, where dust particles and other impurities not removed by the vane section 802 are extracted.
  • Figure 9 shows a gas turbine air inlet heating system employing the air intake filter of Figure 8.
  • a humidity sensor 901 that gives a humidity measurement to a control circuit 902.
  • This provides control signals 904 to a driver 906 that drives the element or elements of an electrical heater system 908.
  • the heater system may have two heater elements, an upstream element and a downstream element. Each of these is a continuous circuit extending in a serpentine manner across multiple vanes 802 of the intake filter.
  • the driver 906 can drive each of these independently. (There may be three or four such elements.)
  • both (or all) heating elements are driven by the driver circuit 906 to heat the incoming air.
  • the control circuit 902 provides a signal to the driver 906 to shut down (partially or completely) one (or more) of the heater element(s).
  • the downstream heater element(s) is (are) switched off.
  • the upstream heater element provides sufficient heat in these circumstances to heat the incoming air to a temperature at which ice will not form even after undergoing isentropic acceleration in the bellmouth at the gas turbine inlet 106.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention porte sur une palette pour un filtre d'entrée d'air de turbine à gaz ayant un corps qui, lorsqu'il est en position dans le filtre d'entrée d'air de turbine à gaz, s'étend sensiblement dans une direction de flux d'air. La palette a une longueur s'étendant sensiblement perpendiculairement à la direction du flux d'air et a une pluralité de canaux, dont chacun sert à tenir un élément chauffant de trace électrique. Les canaux sont disposés en direction et le long d'un bord amont de la palette et sont disposés en ligne, parallèlement à la direction du flux d'air. L'invention porte aussi sur un procédé de chauffage d'une entrée d'air de turbine à gaz. La chaleur est fournie au niveau du filtre d'entrée d'air de turbine à gaz au moyen d'un chauffage à trace électrique pour élever la température au niveau du filtre d'entrée d'air de turbine à gaz de telle sorte qu'il ne se forme pas de givre, en dépit du refroidissement dû à l'accélération du flux d'air en aval du filtre d'entrée d'air de turbine à gaz et dans l'entrée de turbine à gaz.
PCT/GB2014/051111 2013-04-09 2014-04-09 Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique WO2014167329A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1306440.7 2013-04-09
GB1306440.7A GB2512878B (en) 2013-04-09 2013-04-09 Gas turbine inlet anti-icing using electrical power

Publications (1)

Publication Number Publication Date
WO2014167329A1 true WO2014167329A1 (fr) 2014-10-16

Family

ID=48483630

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2014/051111 WO2014167329A1 (fr) 2013-04-09 2014-04-09 Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique

Country Status (2)

Country Link
GB (1) GB2512878B (fr)
WO (1) WO2014167329A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2811227B1 (fr) * 2013-06-06 2018-03-28 General Electric Technology GmbH Configuration de séparateur d'humidité

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DK3120091T3 (da) 2014-03-21 2020-08-31 Veotec Americas LLC Fremgangsmåde til fremstilling af et luftseparatorsystem
GB2551500B (en) * 2016-06-17 2020-09-16 Veotec Ltd Combination air filter and separator and filter replacement method
CN106468246A (zh) * 2016-11-23 2017-03-01 四川大学 风力发电机的径向加热融冰叶片和融冰设备及其融冰方法
CN106351790A (zh) * 2016-11-23 2017-01-25 四川大学 风力发电机的横向加热融冰叶片和融冰设备及其融冰方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3912471A (en) * 1974-07-01 1975-10-14 Ind Air Inc High velocity moisture eliminator
US4198215A (en) * 1977-06-03 1980-04-15 Ulrich Regehr Fin deflector for separating liquid from a liquid/vapor mixture
GB2071517A (en) * 1980-03-12 1981-09-23 Rolls Royce Heated filter vane
GB2199260A (en) * 1986-12-23 1988-07-06 Burgess Manning Limited Vane-type separator
EP0462687A1 (fr) * 1990-06-20 1991-12-27 Peerless Manufacturing Company Aile-séparatrice à haute capacité

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4704145A (en) * 1986-06-27 1987-11-03 Avco Corporation Modular multi-channel particle separator
GB2380255A (en) * 2001-07-07 2003-04-02 Surface Heating Systems Ltd Deicing of louvres in an air duct

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3912471A (en) * 1974-07-01 1975-10-14 Ind Air Inc High velocity moisture eliminator
US4198215A (en) * 1977-06-03 1980-04-15 Ulrich Regehr Fin deflector for separating liquid from a liquid/vapor mixture
GB2071517A (en) * 1980-03-12 1981-09-23 Rolls Royce Heated filter vane
GB2199260A (en) * 1986-12-23 1988-07-06 Burgess Manning Limited Vane-type separator
EP0462687A1 (fr) * 1990-06-20 1991-12-27 Peerless Manufacturing Company Aile-séparatrice à haute capacité

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2811227B1 (fr) * 2013-06-06 2018-03-28 General Electric Technology GmbH Configuration de séparateur d'humidité
US10765981B2 (en) 2013-06-06 2020-09-08 General Electric Technology Gmbh Moisture separator configuration

Also Published As

Publication number Publication date
GB2512878B (en) 2016-03-23
GB2512878A (en) 2014-10-15
GB201306440D0 (en) 2013-05-22

Similar Documents

Publication Publication Date Title
WO2014167329A1 (fr) Antigivrage d'entrée de turbine à gaz utilisant l'énergie électrique
US20110005188A1 (en) Air intake lip for turbojet nacelle
US7469862B2 (en) Aircraft engine nacelle inlet having access opening for electrical ice protection system
US10202966B2 (en) Wind turbine rotor blade having a spark gap
US9719423B2 (en) Inlet air chilling system with humidity control and energy recovery
US7938368B2 (en) Nosecone ice protection system for a gas turbine engine
US8540185B2 (en) Modular air inlet lip with electric defrosting for a turbojet pod
EP2760741B1 (fr) Ensemble de lèvre pour nacelle de turboréacteur à dégivrage électrique
US20150345390A1 (en) Systems and methods for de-icing inlet screens and dehumidifying inlet air filters for gas turbine engines
BR102013017906A2 (pt) sistema para proteção contra gelo de um componente e método de proteção de um componente em uma aeronave contra formação do gelo
EP3032153B1 (fr) Soupape chauffée
US8919700B2 (en) De-icing device, in particular for an aircraft nacelle
CN103958347A (zh) 用于冷却飞行器机翼的系统和方法
US10436148B2 (en) Convergent-divergent nozzle
EP2620617A2 (fr) Système de chauffage résistif anti-givrage d'admission de turbine de chambre de combustion
EP3528926B1 (fr) Véhicule pourvu au niveau d'admission d'un filtre à air comprenant un dispositif de chauffage
CN2913183Y (zh) 带防冰腔的升压式低压除水环控装置
CN110481792A (zh) 一种新型等离子体冰形调控装置、方法及防结冰型飞行器
GB2380255A (en) Deicing of louvres in an air duct
CN214366553U (zh) 一种风机叶片除冰系统
US20150136752A1 (en) Electrical heating assembly for a defrosting device
US20130312385A1 (en) Gas turbine system having a plasma actuator flow control arrangement
KR102356834B1 (ko) 가열 기능을 구비하는 선박용 루버 장치
CN107565247A (zh) 供电接头、制造供电接头的方法、电防冰系统、飞机电防冰翼面以及组装方法
WO2024018168A1 (fr) Appareil de refroidissement

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14725916

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14725916

Country of ref document: EP

Kind code of ref document: A1