EP2739530A1 - Aircraft propulsion architecture integrating an energy recovery system - Google Patents
Aircraft propulsion architecture integrating an energy recovery systemInfo
- Publication number
- EP2739530A1 EP2739530A1 EP12753671.2A EP12753671A EP2739530A1 EP 2739530 A1 EP2739530 A1 EP 2739530A1 EP 12753671 A EP12753671 A EP 12753671A EP 2739530 A1 EP2739530 A1 EP 2739530A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aircraft
- energy
- recovery device
- power
- energy recovery
- 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- Withdrawn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
- 238000011084 recovery Methods 0.000 title claims description 86
- 239000007789 gas Substances 0.000 claims abstract description 31
- 238000002485 combustion reaction Methods 0.000 claims abstract description 17
- 239000012530 fluid Substances 0.000 claims description 14
- 239000012080 ambient air Substances 0.000 claims description 13
- 238000006243 chemical reaction Methods 0.000 claims description 11
- 239000003570 air Substances 0.000 claims description 10
- 238000009396 hybridization Methods 0.000 claims description 9
- 230000010354 integration Effects 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 6
- 238000004378 air conditioning Methods 0.000 claims description 5
- 239000002826 coolant Substances 0.000 claims description 4
- 239000000295 fuel oil Substances 0.000 claims description 4
- 238000005485 electric heating Methods 0.000 claims description 3
- 239000010705 motor oil Substances 0.000 claims description 3
- 230000001131 transforming effect Effects 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000012809 cooling fluid Substances 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 claims 1
- 230000001502 supplementing effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 9
- 239000000446 fuel Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 3
- 230000033228 biological regulation Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 239000005431 greenhouse gas Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000013529 heat transfer fluid Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000005070 sampling Methods 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8209—Electrically driven tail rotors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a propulsion architecture of an aircraft such as a rotary rotor or wing aircraft such as a helicopter incorporating an energy recovery system.
- Aeronautics is a sector historically marked by a constant demand for innovation and technological progress.
- the search for reducing the environmental impact of air transport, greenhouse gas emissions and noise is a natural part of this process.
- Rotary wing aircraft are known for their high greenhouse gas emissions per passenger and kilometer traveled.
- the electrical energy used for hybridization is generally stored in batteries whose weight is penalizing for fuel consumption and payload.
- auxiliary circuits electrical, hydraulic and / or pneumatic circuits
- the energy is taken from the accessory box or box.
- main transmission (BTP) consuming fuel for the supply of these systems.
- the present invention relates to the recovery of thermal energy, its use and its conversion into electrical energy.
- the present invention proposes in particular an aircraft provided with at least one propulsion turbine and comprising a power supply system of at least one equipment, for which the power supply system comprises a thermal energy recovery device installed on the turbine, operating as a hot source energy contained in the exhaust gas of the turbine and as a cold source a fluid such as ambient air, engine oil, fuel oil or other cooling fluid of the turbine.
- the power supply system comprises a thermal energy recovery device installed on the turbine, operating as a hot source energy contained in the exhaust gas of the turbine and as a cold source a fluid such as ambient air, engine oil, fuel oil or other cooling fluid of the turbine.
- the energy recovery device comprises:
- an evaporator for transferring part of the thermal energy contained in the hot source to a working fluid, this evaporator being installed at a nozzle of the turbine;
- an electric generator powered by the transformation machine powered by the transformation machine
- a condenser for condensing the working fluid at the output of the processing machine through heat exchanges with the cold source
- a pump for compressing the working fluid at the outlet of the condenser and circulating it in the evaporator
- the energy recovery device comprises:
- an evaporator installed at the outlet of the turbine, for transferring a portion of the thermal energy contained in the hot source to a working gas, including air;
- the energy recovery device comprises a set of thermoelectric cells directly converting heat from a nozzle of the turbine into electricity.
- the device advantageously comprises a power electronics system integrated downstream of the generator of the energy recovery system, the electronic power system performing one or more of the following functions:
- Maximum Power Point Tracking participate in the adjustment of the voltage, and thus participate in the quality of the electrical energy
- the nominal voltage generated by the power electronics will be 1 15Vac / 400Hz, 28Vdc 270Vdc, 540 Vdc or other;
- the energy recovery device preferably performs the optional electrical power generation in replacement of all or part of the generators powered by power take-offs on a BTP / engine accessories.
- the energy recovery device is connected to a power supply system provided with a reconfiguration system adapted to reconfigure itself so as to feed a main power supply bar of the aircraft by means of the device of energy recovery in case of loss of the main generation
- the energy recovery device advantageously supplies the main electrical network of the aircraft as a replacement or complement (in parallel) of the generation powered by power take-offs on the BTP or the engine accessory box.
- the energy recovery device supplies an independent electric bus, in addition to the main distribution bars powered by BTP sources, thus creating an additional source independent of the others.
- the energy recovery device also supplies hydraulic and / or mechanical / pneumatic auxiliaries.
- the aircraft of the invention is a helicopter with main rotor and tail rotor.
- the energy recovery device advantageously constitutes a system for hybridizing the main and / or rear rotor, the electrical generation of the energy recovery device being associated in replacement or in addition to the batteries used for the hybridization and placed in series or in parallel with the latter.
- An integrated power electronics system downstream of the generator of the energy recovery device advantageously manages the paralleling of the recovery generator with at least one main generator of the aircraft if necessary.
- the present invention further proposes a system for driving at least one rotor of an aircraft by electrical energy in addition to or in replacement of a mechanical system for which the electrical energy is supplied at least partially by at least one device recovery of thermal energy from hot gases of an internal combustion engine of the aircraft.
- the thermal energy recovery device comprises a thermodynamic machine using a thermodynamic cycle between a hot source, the exhaust gas of the internal combustion engine, and a cold source, the ambient air.
- the thermodynamic machine preferably comprises a first heat exchanger on the hot source, a second heat exchanger on the cold source, a coolant flowing between the first and second heat exchangers and a unit for converting heat energy into mechanical energy between the heat exchangers.
- the recovery device comprises an electric generator providing a mechanical / electrical conversion coupled to said transformation unit.
- the recovery device supplies all or part of the auxiliary circuits such as the electrical, hydraulic or pneumatic circuits of the aircraft.
- the recovered energy supplying all or part of the auxiliary circuits such as the electrical, hydraulic or pneumatic circuits, the removal of energy on the accessory box and BTP will thus be eliminated or decreased.
- the recovery device advantageously comprises a mechanical / pneumatic conversion device for feeding the aircraft's pneumatic circuits and / or a mechanical / hydraulic conversion device for feeding the hydraulic circuits of the aircraft.
- the hot gases are the exhaust gas from at least one propulsion piston engine of the aircraft.
- the first exchanger is advantageously coupled to an exhaust pipe of the piston engine.
- the hot gases are the gases generated by at least one propulsion turbine of the aircraft.
- the rotor is advantageously a rotary wing aircraft rotor and in particular a helicopter rear rotor.
- FIG. 2 a diagram of a propulsion system architecture of an aircraft according to the invention
- the proposed system is adapted to produce electrical energy from the thermal energy of the exhaust gases of an internal combustion engine of an aircraft and in particular a helicopter to supply partially or totally electrical systems and / or the main and / or rear rotors with electric or all-electric hybrid propulsion.
- the energy recovery systems installed on the aircraft operate thanks to the presence of a hot source, the energy contained in the exhaust gases of the turbine, and a cold source, for example the ambient air, the engine oil, fuel oil or any other coolant.
- the system for converting heat losses into energy, for example electric comprises in particular:
- a turbine or any other machine for example with pistons, for converting thermal energy into mechanical energy
- a condenser for condensing the working fluid at the turbine outlet through heat exchanges with the cold source
- a pump for compressing the working fluid at the outlet of the condenser and circulating it in the evaporator
- control system to adjust the power produced to the desired power, for example via the control of the flow / pressure of the pump.
- thermoelectric cells taking ambient air and compressing it upstream of the evaporator, and its associated control system.
- Another variant is the use of a set of thermoelectric cells.
- a power electronics system will eventually be integrated downstream of the generator of the energy recovery system. It performs one or more of the following functions:
- the assembly consisting of the recovery system, its possible power electronics converter associated with one or more of the aforementioned functions are called "electrical generation of the energy recovery system.”
- electrical generation of the energy recovery system Concerning the power supply of the electrical circuits of board (except system of hybridization), three architectures are envisaged.
- a third solution is that the electrical generation of the recovery system feeds an independent essential bus, in addition to the main and essential distribution bars powered by BTP sources, thus creating an additional source independent of the others.
- This power structure significantly improves the operational reliability but especially the safety of the electrical system thus allowing the installation of loads with a large number of independent sources, in particular electric flight actuators.
- auxiliary electrical systems In addition to the power supply of auxiliary electrical systems, another possible use is the supply of hydraulic auxiliaries (hydraulic pump by example) or mechanical / pneumatic (air conditioning compressor for example).
- hydraulic auxiliaries hydraulic pump by example
- mechanical / pneumatic air conditioning compressor for example
- the electrical generation of the recovery system is associated in replacement or in addition to the batteries used for the hybridization and placed in series or in parallel with these latest.
- the operating principle of the energy recovery systems requires a heat energy evacuation out of the recovery system via a heat exchanger.
- this energy is released into the atmosphere but an option is to recover all or part of this energy to heat the air (for example the cabin - the heating system), fuel oil or any other part or component of the energy. 'aircraft.
- FIG. 1 represents a traditional architecture of a twin-rotor helicopter with main rotor and rear rotor for which the two internal combustion engines 1 a, 1 b, piston engines or turbines drive a main gearbox 4 called BTM through a primary mechanical connection 20 such as a transmission shaft.
- the BTM 4 distributes mechanical power through a secondary mechanical link 21 to a main rotor 2, a rear mechanical drive gearbox 5 of a rear rotor 3, an electric generator 7, a hydraulic pressure generator 1 1 and a pneumatic pressure generator 12.
- the electric power delivered by the generator 7 is distributed by an electrical distribution network 10 supplying the various electrical components of the helicopter.
- FIG. 2 corresponds to a twin rotor helicopter architecture with main rotor and rear rotor comprising the system of the invention.
- the thermal energy recovery devices 6a, 6b are, for example, turbines 104 according to FIG. 4, the heat taps being hot exchangers 103 according to this same figure.
- the recovered energy is used to power the electric generators 7a, 7b, the hydraulic pressure generators 11a, 11b and the pneumatic pressure generators 12a, 12b.
- the one or more electric generators 7a, 7b will supply an electrical network 50 supplying the electrical distribution networks 10a, 10b and a power electronics 8 for controlling an electric motor 9 driving the rear rotor 3 of the helicopter.
- an electric motor 9 coupled to the main shaft 30 is connected to the power electronics 8 to power the latter if the thermal power recovered is insufficient.
- the system of the invention here performs a hybrid thermal / electrical propulsion of the helicopter and can also perform, if the power recovered is sufficient, a supply of the auxiliary circuits of the aircraft and in particular the electrical network, the circuit pneumatic, for example air conditioning compressors and / or the hydraulic circuit, for example hydraulic pumps.
- the energy recovery system describes a thermodynamic cycle between a hot source, the exhaust gas of the internal combustion engine, and a cold source, the ambient air.
- It includes, in particular, at the level of the heat energy recuperator (s) 6a, 6b a motor element or a turbine, a steam turbine, a Stirling engine steam engine, or another engine with external combustion coupled to a generator 7a, 7b providing a mechanical conversion. electric.
- thermoelectric generator replaces the motor element with a thermoelectric generator.
- the system also includes a mechanical / hydraulic conversion system
- the coupling of the thermal / electrical energy converter to an electric motor 9 of the rear rotor 3 allows greater flexibility in terms of rotational speeds compared to a direct mechanical adaptation to the gearbox 5 of the prior architecture.
- the new architecture enabled by the invention also allows a reduction in the weight of the batteries to be shipped due to the supply at least partly direct electric motors by the heat recovery system.
- the heat exchanger between the hot source exhaust gas and the cold source cold source ambient air can be used for a secondary function, that of heating the ambient air and thus supply the cabin with hot air. It is therefore no longer necessary to take hot air from the turbine engine compressor output as in a conventional turbine engine architecture, which improves the efficiency of the turbine.
- the solution is based on an integration of a heat recovery / conversion system into electrical energy, a thermodynamic cycle machine coupled to a generator in the turbine nozzle or the exhaust line.
- a second heat exchanger at the cold source located downstream of the conversion system to evacuate the heat of the thermodynamic cycle but can also heat the ambient air to supply the cabin with hot air which reduces the need air sampling in the helicopter turbine and improve its energy efficiency.
- a turbine heat exchanger system is installed and a single system for converting the recovered thermal energy into electrical energy for the aircraft.
- FIG. 3 represents an example of the electrical circuit of FIG. 1, in more detail for which the generators 7a, 7b feed a distribution and regulation device 13 comprising a calculator defining control laws to allow good distribution / power distribution.
- the recovery system can be used to perform one or more of the following functions:
- Main rotor supply in this case the BTP 4 will supply a generator similar to the generator 9 inserted between the BTP and an electric motor driving the main rotor,
- the recovery system will power a distributed electrical grid at the voltage of 270Vdc, 1 15Vac / 200Vac, 28Vdc or any other desired AC or DC voltage level.
- FIG. 4 represents a possible diagram of integration of a thermal energy recovery system on a turbine-type internal combustion engine 1 comprising, in known manner, stages 100, 101 of compressors and an outlet nozzle 102.
- the thermal energy recovery device comprises a thermodynamic machine 200 using a thermodynamic cycle between a hot source, the exhaust gas of the internal combustion engine and a cold source, the ambient air.
- thermodynamic machine or closed-cycle steam turbine including a Rankine cycle comprises a first heat exchanger 103, heat exchanger, on the hot source, here the nozzle 102 of the internal combustion engine, a second heat exchanger 105 on the cold source, for example a radiator in contact with the outside air through which the aircraft passes, a heat transfer fluid circulating between the first and the second exchangers by a tubular circuit 107 and a unit for converting thermal energy into mechanical energy here in the form of a turbine 104.
- thermodynamic machine further comprises a pump 106 circulating the fluid in the coolant circuit 107.
- the turbine 104 drives here an electric generator 108 which will be used as described above.
- An advantage of the system of the invention is to reduce the exhaust temperature of the engine gas engine of the aircraft which decreases its infrared signature.
- the invention which is not limited to the example shown, corresponding to a twin-engine apparatus, but which is particularly applicable to a single-engined aircraft, applies in particular to helicopters or rotary-wing drones and makes it possible to improve the overall efficiency of the propulsion system of the aircraft, especially in the case where the turbine or turbines of this aircraft provide work and not thrust.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1157122A FR2978728B1 (en) | 2011-08-03 | 2011-08-03 | AIRCRAFT PROPULSION ARCHITECTURE INTEGRATING AN ENERGY RECOVERY SYSTEM |
PCT/EP2012/065221 WO2013017680A1 (en) | 2011-08-03 | 2012-08-03 | Aircraft propulsion architecture integrating an energy recovery system |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2739530A1 true EP2739530A1 (en) | 2014-06-11 |
Family
ID=46785368
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12753671.2A Withdrawn EP2739530A1 (en) | 2011-08-03 | 2012-08-03 | Aircraft propulsion architecture integrating an energy recovery system |
Country Status (5)
Country | Link |
---|---|
US (1) | US9885289B2 (en) |
EP (1) | EP2739530A1 (en) |
CA (1) | CA2843802C (en) |
FR (1) | FR2978728B1 (en) |
WO (1) | WO2013017680A1 (en) |
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FR2962404B1 (en) * | 2010-07-08 | 2012-07-20 | Eurocopter France | ELECTRICAL ARCHITECTURE FOR AN AIRCRAFT WITH A HYBRID MOTORIZED TURNING SAIL |
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2012
- 2012-08-03 WO PCT/EP2012/065221 patent/WO2013017680A1/en active Application Filing
- 2012-08-03 EP EP12753671.2A patent/EP2739530A1/en not_active Withdrawn
- 2012-08-03 US US14/236,621 patent/US9885289B2/en active Active
- 2012-08-03 CA CA2843802A patent/CA2843802C/en active Active
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Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10377479B2 (en) | 2016-06-03 | 2019-08-13 | Bell Helicopter Textron Inc. | Variable directional thrust for helicopter tail anti-torque system |
US10526085B2 (en) | 2016-06-03 | 2020-01-07 | Bell Textron Inc. | Electric distributed propulsion anti-torque redundant power and control system |
US10703471B2 (en) | 2016-06-03 | 2020-07-07 | Bell Helicopter Textron Inc. | Anti-torque control using matrix of fixed blade pitch motor modules |
US10787253B2 (en) | 2016-06-03 | 2020-09-29 | Bell Helicopter Textron Inc. | Variable directional thrust for helicopter tail anti-torque system |
US11174018B2 (en) | 2016-06-03 | 2021-11-16 | Textron Innovations Inc. | Anti-torque control using fixed blade pitch motors |
US11655022B2 (en) | 2016-06-03 | 2023-05-23 | Textron Innovations Inc. | Anti-torque control using fixed blade pitch motors |
US11186185B2 (en) | 2017-05-31 | 2021-11-30 | Textron Innovations Inc. | Rotor brake effect by using electric distributed anti-torque generators and opposing electric motor thrust to slow a main rotor |
US11932125B2 (en) | 2017-05-31 | 2024-03-19 | Textron Innovations Inc. | Rotor break effect by using electric distributed anti-torque generators and opposing electric motor thrust to slow a main rotor |
Also Published As
Publication number | Publication date |
---|---|
FR2978728B1 (en) | 2014-07-04 |
CA2843802A1 (en) | 2013-02-07 |
WO2013017680A1 (en) | 2013-02-07 |
US9885289B2 (en) | 2018-02-06 |
CA2843802C (en) | 2019-08-27 |
FR2978728A1 (en) | 2013-02-08 |
US20140290208A1 (en) | 2014-10-02 |
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