EP3356230A1 - Dispositif de dégivrage pour lèvre d'entrée d'air de nacelle de turboréacteur d'aéronef - Google Patents
Dispositif de dégivrage pour lèvre d'entrée d'air de nacelle de turboréacteur d'aéronefInfo
- Publication number
- EP3356230A1 EP3356230A1 EP16787496.5A EP16787496A EP3356230A1 EP 3356230 A1 EP3356230 A1 EP 3356230A1 EP 16787496 A EP16787496 A EP 16787496A EP 3356230 A1 EP3356230 A1 EP 3356230A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- lip
- coolant
- heat transfer
- transfer fluid
- phase
- 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- Withdrawn
Links
- 239000013529 heat transfer fluid Substances 0.000 claims abstract description 41
- 238000010438 heat treatment Methods 0.000 claims abstract description 17
- 239000012530 fluid Substances 0.000 claims abstract description 15
- 239000002826 coolant Substances 0.000 claims description 62
- 238000010257 thawing Methods 0.000 claims description 20
- 239000012808 vapor phase Substances 0.000 claims description 20
- 239000012071 phase Substances 0.000 claims description 12
- 239000007791 liquid phase Substances 0.000 claims description 7
- 230000001276 controlling effect Effects 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 2
- 238000005276 aerator Methods 0.000 claims 1
- 239000003921 oil Substances 0.000 description 9
- 238000009833 condensation Methods 0.000 description 8
- 230000005494 condensation Effects 0.000 description 8
- 238000011144 upstream manufacturing Methods 0.000 description 5
- 238000001704 evaporation Methods 0.000 description 3
- 230000008020 evaporation Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 239000010705 motor oil Substances 0.000 description 3
- 230000004224 protection Effects 0.000 description 3
- 238000009834 vaporization Methods 0.000 description 3
- 230000008016 vaporization Effects 0.000 description 3
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 150000002894 organic compounds Chemical class 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- F02C7/047—Heating to prevent icing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/06—Liquid application
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/02—De-icing means for engines having icing phenomena
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat 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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2220/00—Application
- F05D2220/60—Application making use of surplus or waste energy
- F05D2220/62—Application making use of surplus or waste energy with energy recovery turbines
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/208—Heat transfer, e.g. cooling using heat pipes
-
- 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
- An aircraft is propelled by one or more propulsion units each comprising a turbojet engine which is housed in a nacelle.
- a nacelle generally has a substantially tubular structure which surrounds the turbojet engine and which comprises an air inlet upstream of the engine, a median section intended to surround a fan of said turbojet engine and a downstream section surrounding the combustion chamber of the turbojet engine and which can be equipped with thrust reversal means.
- the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the fan blades.
- the assembly is attached upstream of a fan casing belonging to the middle section of the assembly.
- ice may form on the nacelle, particularly at the outer surface of the air intake lip.
- the presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
- a solution for de-icing or preventing any formation of frost on the outer surface is to maintain the relevant surface at a sufficient temperature according to the desired objective (melting frost or total evaporation of water on the outer surface of the lip).
- it is widely known to collect hot air at the compressor of the turbojet engine and bring it to the level of the air intake lip to heat the walls.
- the lip and the bulkhead before the air inlet constitute a substantially ring-shaped closed volume called "D" shaped conduit or lip duct (D-duct in English), in which the hot air defrost circulates in the concept of the state of art mentioned here.
- this solution requires circulating air at a high temperature in the lip so as to ensure sufficient heat flow defrosting, this air being conveyed by pipes whose mass is relatively high.
- thermal protection elements are necessary to protect certain parts, particularly those made of composite materials, from high heat. These protections also add mass to the basket.
- the D-shaped duct consists of the air intake lip, the outer face of which must be defrosted, and the front wall of the air inlet which closes the rear part of the duct. This partition is not in contact with the outside air and is often overheated by defrosting air. The traditional hot-air concept thus generates significant thermal overloads.
- the present invention aims in particular to solve these drawbacks and relates for this purpose to a device for deicing air intake lip nacelle aircraft turbojet, the lip forming a volume which is delimited by a front wall to defrost , a leading edge, and a rear wall, the device comprising a de-icing circuit in which circulates a heat-transfer fluid which operates in two-phase form, the circuit comprising at least:
- a device for circulating the coolant in the de-icing circuit which comprises at least one circulation pump
- a heat transfer fluid heating system which is designed to bring said fluid into a vapor phase
- a heat transfer fluid outlet conduit which opens into the lip, through the rear wall, to evacuate the coolant out of the lip.
- the invention makes it possible to limit the temperature of the coolant by injecting it into the lip at a temperature close to its dew point. This feature makes it possible to limit the risks of overheating on the lip and the surrounding structures and the thermal protections associated with the deicing device.
- the defrosting device makes it possible to replace the hot air used in the state of the art with a gas having the capacity to condense on the internal face of the air inlet. This phenomenon makes it possible to obtain a high thermal flux on the lip of the air inlet while remaining at much lower temperatures than with "dry" air.
- the inlet duct is arranged to inject the fluid in the vapor phase into the interior of the lip so that the fluid comes into direct contact with the front wall of the lip.
- close to the condensation point of the fluid means a temperature between the dew point and 20 percent above the dew point, the temperature being expressed in Kelvin.
- the heat transfer fluid is for example a fluorinated organic compound whose condensation temperature is around 373K (at ambient atmospheric pressure).
- the circulation device comprises a turbine which is supplied with vapor-phase heat transfer fluid through an intake duct and which drives the pump in motion.
- This characteristic makes it possible to use the energy of the heat transfer fluid to drive the heat transfer fluid circulating pump.
- the circulation device comprises a motor which drives the pump in motion.
- the deicing device is equipped with a regulation system which comprises:
- a temperature sensor which measures the temperature of the heat transfer fluid at the outlet of the heating system and which communicates with the central unit.
- This characteristic makes it possible in particular to regulate the pressure and the temperature of the coolant injected into the lip.
- the regulating system comprises a pressure relief valve which makes it possible to reduce the pressure in the deicing circuit and in the lip.
- the control system comprises a manometer for controlling the pressure in the lip which communicates with the central unit.
- control system comprises a plurality of control valves which are adapted to regulate the pressure of the coolant in the de-icing circuit and to regulate the pressure of the heat transfer fluid injected into the lip.
- the heating system comprises an electric boiler which is designed to heat the coolant.
- the heating system comprises a heat exchanger which is supplied with oil heated by the turbojet, and which is adapted to transfer thermal energy from said oil to the coolant.
- This characteristic makes it possible to heat the coolant by the energy dissipated by the turbojet engine.
- the reservoir is formed by a sump which is formed in a lower part of the lip, and which is adapted so that the coolant flows by gravity into said reservoir, and in that the outlet conduit draws the coolant in the liquid phase in the tank to evacuate the heat transfer fluid contained in the lip.
- a fan ensures a circumferential circulation of the heat transfer fluid in the vapor phase in the lip.
- the invention also relates to an aircraft turbojet engine nacelle equipped with a deicing device according to any one of the preceding claims.
- FIG. 1 is a schematic perspective view, which illustrates a nacelle equipped with a simplified defrosting device, according to a first embodiment of the invention
- FIG. 2 is a schematic perspective view, which illustrates the device of Figure 1 equipped with a control system, according to a second embodiment of the invention
- FIG. 3 is a schematic perspective view, which illustrates the device of Figure 1 equipped with an oil / heat transfer heat exchanger, according to a third embodiment of the invention
- - Figure 4 is a schematic perspective view, which illustrates the device of Figure 1 equipped with a steam turbine, according to a fourth embodiment of the invention
- FIG. 5 is a schematic perspective detail view, which illustrates the condensation of the coolant on the inner front wall of the air inlet lip
- FIG. 6 is a schematic perspective detail view of a nacelle according to the invention, the air intake lip is equipped with a fan.
- upstream and downstream must be understood in relation to the circulation of heat transfer fluid inside the defrosting circuit.
- FIG. 1 shows a de-icing device 10 for a nacelle air inlet nacelle air intake lip 12 of an aircraft turbojet engine.
- the lip 12 forms an annular volume of longitudinal section in the form of a "D" 90 which is delimited by a front wall 16 to be defrosted, forming a leading edge, and a rear wall. 18 which separates the volume delimited by the lip 12 and the section of the nacelle which is connected to the lip 12.
- the deicing device 10 comprises a de-icing circuit 20 in which circulates a heat-transfer fluid 22 which operates in two-phase form, that is to say that the heat transfer fluid 22 adopts two different phases, namely a liquid phase and a vapor phase.
- the circuit 20 generally forms a closed loop which comprises the lip 12 and which makes it possible to circulate the coolant 22 through the lip 12.
- the circuit 20 comprises a tank 24 of coolant 22, which is formed by a sump formed in a lower portion of the lip 12, so that the coolant 22 flows by gravity to the tank 24.
- the defrosting circuit 20 comprises a circulation device 26 for the coolant 22, a heating system 28 for the coolant 22, an inlet conduit 30 for the coolant 22 that opens into the lip 12, through the partition rear 18, for injecting the heat transfer fluid 22 in the vapor phase inside the lip 12, and an outlet conduit 34 of the coolant 22 which opens into the lip 12, through the rear wall 18, to evacuate the coolant 22 outside the lip 12.
- the inlet duct 30 is connected to a plurality of inlet orifices for injecting the heat transfer fluid in a distributed manner inside the lip 12.
- the circulation device 26 for the coolant 22 comprises a circulating pump 36 which is supplied with heat transfer fluid 22 through the outlet duct 34 and which is driven by a 38 electric motor.
- the pump 36 is of the liquid or two-phase type with a gas / liquid separation capacity.
- the heating system 28 comprises an electric boiler 40 which is designed to heat the coolant.
- the electric boiler 40 comprises an electrical resistance which is mounted in a balloon in which the coolant 22 circulates to bring the coolant 22 from a liquid phase to a vapor phase.
- the electric boiler 40 is connected to an outlet of the pump 36 via a duct 41 to be supplied with heating fluid 22 in the liquid phase, and an outlet of the boiler electrical 40 is connected to the lip 12 by the inlet conduit 30 provided for this purpose.
- the deicing device 10 is equipped with a control system which comprises a central control unit 42, and a temperature sensor 44 which measures the temperature of the heat transfer fluid 22 at the exit of the system. 28, preferably at the outlet of the electric boiler 40.
- the temperature sensor 44 communicates with the central control unit 42 which regulates the temperature of the coolant 22 by controlling the boiler 40.
- the motor 38 of the pump 36 is controlled by the central unit 42 to regulate the suction pressure of the pump 36 in the lip 12.
- control system comprises a pressure relief valve 46 which reduces the pressure in the lip 12 in case of overpressure.
- the pressure relief valve 46 is mounted on a wall of the lip 12, for example on the rear wall 18, for discharging the heat-exchange fluid 22 in the vapor phase towards the outside of the lip 12.
- control system comprises a manometer 48 for controlling the pressure in the lip 12 which communicates with the central unit 42, this characteristic enabling the central unit 42 to regulate the pressure within the lip 12 by acting on the pump 36 and the heating system 28 of the coolant 22.
- the coolant 22 is drawn into the tank 24 by the pump 36, by means of the outlet duct 34.
- the pump 36 circulates the coolant 22 to the inlet of the electric boiler 40 which raises the temperature of the coolant 22 to a temperature allowing the fluid 22 to adopt a vapor phase.
- the coolant 22, still in the vapor phase, is injected into the lip 12 via the inlet duct 30, and the coolant 22 condenses on the cold wall before 16 of the lip 12 to transmit its calories to the front walls 16, in order to deice the lip 12, as can be seen in FIG.
- the heat transfer fluid 22 condensed in liquid phase flows on the front wall 16 of the lip 12, to the tank 24 located at the bottom of the lip 12.
- the regulation of the pressure in the lip 12 is controlled by the regulation of the speed of the motor 38 of the pump 36 and by the regulation of the temperature of the electric boiler 40.
- FIG. 2 shows the deicing device 10 according to a second embodiment which differs from the deicing device 10 according to the first embodiment in that it comprises a plurality of control valves.
- the deicing device 10 comprises a first discharge control valve 50 of the pump 36 to the heating system 28, which is stitched on the outlet duct 34, upstream of the pump 36, and a second outlet control valve 52 of the pump 36 to the heating system 28, which is stitched on the duct 41 downstream of the pump 36.
- first discharge control valve 50 and the second discharge control valve 52 make it possible to regulate the pressure in the electric boiler 40.
- the defrosting device 10 comprises a control valve 54 for injecting the coolant 22 into the lip 12, which is stitched onto the inlet duct 30, to regulate the injection pressure of the heat transfer fluid 22 injected into the the lip 12.
- the two discharge control valves 50, 52 and the injection control valve 54 are controlled by the central unit 42.
- FIG. 3 shows the deicing device 10 according to a third embodiment which differs from the deicing device 10 according to the second embodiment in that the heating system 28 comprises a heat exchanger 56 which is associated with the electric boiler 40.
- the heat exchanger 56 is supplied with oil heated by the engine (not shown) arranged in the nacelle 14, and which is adapted to transfer heat energy from the oil to the coolant 22.
- the heat exchanger 56 is arranged directly upstream of the electric boiler 40.
- a first oil supply duct 58 connects an inlet of the heat exchanger 56 to an oil supply source and a second discharge duct 60 connects an outlet of the exchanger 56, to enable the flow of the oil through the heat exchanger 56.
- a valve 62 controlled by the central unit 42 regulates the flow of engine oil which passes through the heat exchanger 56.
- the temperature of the engine oil is preferably at least equal to the vaporization temperature of the coolant 22, so that the heat exchanger 56 can bring the coolant from a liquid phase to a phase steam.
- FIG. 4 shows the deicing device 10 according to a fourth embodiment which differs from the deicing device 10 according to the third embodiment in that the circulation device 26 comprises a turbine 64 which is supplied with heat transfer fluid 22 in the vapor phase by an intake duct 66 connected to the electric boiler 40, and which drives the pump 36 in motion.
- the circulation device 26 comprises a turbine 64 which is supplied with heat transfer fluid 22 in the vapor phase by an intake duct 66 connected to the electric boiler 40, and which drives the pump 36 in motion.
- the heat-transfer liquid 22 in the vapor phase passes through the turbine 64, which functions as a steam engine.
- a regulation valve 67 is interposed between the electric boiler 40 and the turbine 64, this valve being controlled by the central unit 42.
- Tentrée Tsat. (1 + ⁇ ) + W / Cp
- the temperature of the coolant 22 is set by the dew point chosen in the lip 12.
- the rear wall 18 remains at a temperature substantially close to the temperature of the heat transfer fluid 22 in the vapor phase injected into the lip 12.
- the temperature of the lip 12 remains equal to the condensation temperature of the coolant 22 if the energy supplied to the heat transfer fluid 22 is greater than the external drop vaporization energy, which verifies the following equation:
- the deicing device 10 according to the invention has several advantages.
- the defrosting device 10 is self-regulating in temperature in the lip 12 as a function of the pressure in this zone.
- the lip 12 and its environment can not exceed the temperature of the injected vapor phase heat transfer fluid 22 which is regulated by the heating system 28 and which is controlled by the properties of the coolant 22.
- the quality of the condensation flow compensates for the need for temperature that can remain below 1 10 degrees Celsius, or even less, with a much better efficiency than an air system or an electric Joule system.
- the heat energy of the engine oil is recovered by the phase change heat exchanger 56 in an efficient manner in most cases of flight of the aircraft.
- the electric boiler 40 can be used.
- the electric boiler 40 also makes it possible to overheat the coolant 22 if the turbine 64 requires a power, and therefore an inlet temperature, that is too high to come from the heat exchanger 56.
- the invention makes it possible to dispense with a heavy electrical resistance element requiring complex regulation.
- the electric boiler has a compact volume of the order of one liter.
- the turbine and the pump are the only moving parts of the system with the valves.
- the mass of the deicing device 10 is substantially smaller than that of an air or electrical system, the flow of the heat-transfer fluid 22 being four times greater than that of the air, and the associated mass flow rate is four times lower for the same efficiency. .
- a fan 80 may advantageously be added to the "D" shaped duct 90 in order to circulate the fluid 22 in the gas phase in this duct and to homogenize the heat flow at the wall 16.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1559184A FR3041703B1 (fr) | 2015-09-29 | 2015-09-29 | Dispositif de degivrage pour levre d’entree d’air de nacelle de turboreacteur d’aeronef |
PCT/FR2016/052501 WO2017055766A1 (fr) | 2015-09-29 | 2016-09-29 | Dispositif de dégivrage pour lèvre d'entrée d'air de nacelle de turboréacteur d'aéronef |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3356230A1 true EP3356230A1 (fr) | 2018-08-08 |
Family
ID=54608834
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16787496.5A Withdrawn EP3356230A1 (fr) | 2015-09-29 | 2016-09-29 | Dispositif de dégivrage pour lèvre d'entrée d'air de nacelle de turboréacteur d'aéronef |
Country Status (5)
Country | Link |
---|---|
US (1) | US20180216529A1 (fr) |
EP (1) | EP3356230A1 (fr) |
CA (1) | CA2998954A1 (fr) |
FR (1) | FR3041703B1 (fr) |
WO (2) | WO2017055766A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180229850A1 (en) * | 2017-02-15 | 2018-08-16 | Pratt & Whitney Canada Corp. | Anti-icing system for gas turbine engine |
FR3094345B1 (fr) | 2019-03-27 | 2021-03-05 | Thales Sa | Équipement aéronautique pour un aéronef |
FR3094749B1 (fr) * | 2019-04-03 | 2021-11-19 | Safran Nacelles | Système de refroidissement de turboréacteur pour aéronef |
US11384687B2 (en) | 2019-04-04 | 2022-07-12 | Pratt & Whitney Canada Corp. | Anti-icing system for gas turbine engine |
CN114056580B (zh) * | 2022-01-14 | 2022-05-10 | 成都飞机工业(集团)有限责任公司 | 一种带油箱增压的唇口热气防冰系统及防冰方法 |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR864818A (fr) * | 1939-12-22 | 1941-05-06 | Perfectionnements apportés aux systèmes de dégivrage pour engins à moteur, notamment à ceux pour aérodynes | |
US4671348A (en) * | 1985-05-21 | 1987-06-09 | Mcdonnell Douglas Corporation | Transverse flow edge heat pipe |
US20070234704A1 (en) * | 2005-09-01 | 2007-10-11 | General Electric Company | Methods and apparatus for operating gas turbine engines |
US7823374B2 (en) * | 2006-08-31 | 2010-11-02 | General Electric Company | Heat transfer system and method for turbine engine using heat pipes |
US20140190162A1 (en) * | 2009-10-27 | 2014-07-10 | Flysteam, Llc | Heat Recovery System for a Gas Turbine Engine |
FR2987602B1 (fr) * | 2012-03-02 | 2014-02-28 | Aircelle Sa | Nacelle de turbomoteur equipe d'un echangeur de chaleur |
-
2015
- 2015-09-29 FR FR1559184A patent/FR3041703B1/fr active Active
-
2016
- 2016-09-29 EP EP16787496.5A patent/EP3356230A1/fr not_active Withdrawn
- 2016-09-29 WO PCT/FR2016/052501 patent/WO2017055766A1/fr unknown
- 2016-09-29 CA CA2998954A patent/CA2998954A1/fr not_active Abandoned
- 2016-09-29 WO PCT/FR2016/052500 patent/WO2017055765A1/fr active Application Filing
-
2018
- 2018-03-29 US US15/940,375 patent/US20180216529A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
FR3041703A1 (fr) | 2017-03-31 |
WO2017055766A1 (fr) | 2017-04-06 |
FR3041703B1 (fr) | 2019-08-16 |
WO2017055765A1 (fr) | 2017-04-06 |
US20180216529A1 (en) | 2018-08-02 |
CA2998954A1 (fr) | 2017-04-06 |
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