GB2496839A - Thermal electrical power generation for aircraft - Google Patents
Thermal electrical power generation for aircraft Download PDFInfo
- Publication number
- GB2496839A GB2496839A GB1118313.4A GB201118313A GB2496839A GB 2496839 A GB2496839 A GB 2496839A GB 201118313 A GB201118313 A GB 201118313A GB 2496839 A GB2496839 A GB 2496839A
- Authority
- GB
- United Kingdom
- Prior art keywords
- text
- thermoelectric generator
- heat
- electrical
- aircraft
- 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- Withdrawn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
- 238000010248 power generation Methods 0.000 title claims abstract description 7
- 239000000446 fuel Substances 0.000 claims abstract description 10
- 239000002918 waste heat Substances 0.000 claims abstract description 9
- 230000007613 environmental effect Effects 0.000 claims abstract description 4
- 239000007787 solid Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 5
- 239000004065 semiconductor Substances 0.000 claims description 5
- 238000001816 cooling Methods 0.000 description 4
- 239000003570 air Substances 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 235000012431 wafers Nutrition 0.000 description 2
- 230000005679 Peltier effect Effects 0.000 description 1
- 230000005678 Seebeck effect Effects 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000002800 charge carrier Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- 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
- B64D41/00—Power installations for auxiliary purposes
-
- 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
-
- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N10/00—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects
- H10N10/10—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects
-
- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N10/00—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects
- H10N10/10—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects
- H10N10/17—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the structure or configuration of the cell or thermocouple forming the device
-
- 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
- B64D41/00—Power installations for auxiliary purposes
- B64D2041/005—Fuel cells
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fuel Cell (AREA)
- Hybrid Cells (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
An electrical power generation and distribution system 1 for an aircraft comprises at least one heat source 2,3,4,5 and a thermoelectric generator 6,7,8,9 arranged to receive waste heat from the at least one heat source and to convert the waste heat to electrical current. The thermoelectric generator is in electrical connection with an electrical distribution bus 10 which is operable to supply power to aircraft electrical systems. One or more of the heat sources may include an engine exhaust section. One or more of the heat sources may include an auxiliary power unit. One or more of the heat sources may include an environmental control system. One or more of the heat sources may include a fuel cell. The thermoelectric generator may comprise one or more solid state thermoelectric elements (3, fig. 2). The thermoelectric generator may comprise alternating elements of n-type and p-type conductive connectors. The thermoelectric generator may comprise an infrared photovoltaic device.
Description
THERMAL ELECTRICAL POWER GENERATION FOR AIRCRAFT
The present invention relates to electrical generation systems for aircraft and methods of generating electrical power. In particular, the present invention relates to electrical generation systems for aircraft that utilise waste heat generated by aircraft systems.
In the prior art, the electrical power needs of aircraft are met by generators that are driven mechanically by the engines. Generally, each engine may have two generators attached to it. Backup sources, such as an auxiliary power unit (APU) and a ram air turbine (RAT) are also known to be provided. Each of these power sources requires aviation fuel to be bumt in order to generate power. In the case of the generators attached to the engines, the increase in friel burn is caused by the extra load on the engine over and above the requirements for moving the aircraft. In the case of the RAT, the increase in fuel bum is caused by the additional aerodynamic drag caused by the exposition of the RAT to the external air stream. An APTJ on the other hand generally comprises an engine that directly burns its own supply of fuel. In each case, fuel must be burned to generate electrical power for the aircraft.
The present invention provides an electrical power generation and distribution system for an aircraft, comprising one or more heat sources, a thermoelectric generator arranged to receive waste heat from at least one heat source and to convert the waste heat to electrical current, the thermoelectric generator being in electrical connection with an electrical distribution bus which is operable to supply power to aircraft electrical systems.
There follows a detailed description of embodiments of the invention by way of example only with reference to the accompanying drawings, in which: Fig. 1 is a schematic representation of a power generation and distribution system embodying the invention; Fig. 2 is a cross-sectional view of a thermoelectric generation device; Fig. 3 is a cross-sectional partial view of a thermoelectric generation device installed on an engine exhaust; Fig. 4 is a plan view of a panel of thermoelectric generation devices; Fig. 5 is a graph of current against temperature difference for a thermoelectric device embodying the invention; and Fig. 6 is a graph of voltage against temperature difference corresponding to the graph of Fig. 5.
In Fig. 1, there is shown an electrical generation and distribution system 1 comprising a plurality of sources of heat 2,3,4,5 each connected to a respective thermoelectric generator 6,7,8,9. Primary sources of heat 3,4 are shown in the middle of the arrangement, and comprise first and second engines for driving the aircraft. The engines are the greatest producers of heat on the aircraft. A secondary source of heat comprises an environmental control system (ECS) 2 which is provided on the left of the arrangement shown in Fig, 1, the ECS being responsible for maintaining temperature and pressure conditions in the aircraft. The ECS 2 includes a number of heat exchangers which output heat usable by the thermoelectric generator 6 connected thereto. A further secondary source of heat comprises an APU 5 which is connected to another thermoelectric generator 9. The connection between thc APU 5 and the thermoelectric generator 9 is formed preferably by incorporating the generator into a thermal management system of the APU. The generator 9 therefore advantageously provides cooling to the APU.
Each thermoelectric generator 6,7,8,9 is connected to an individual heat source 2,3,4,5, although in an alternative embodiment, the beat sources may each have a plurality of generators, arranged about the heat source to maximise the capture of heat from that source 2,3,4,5. Each generator 6,7,8,9 comprises a plurality of solid state thermoelectric elements.
The thermoelectric generators 6,7,8,9 are connected to the electrical power distribution system 10 of the aircraft, which distributes the electrical power to the various loads of the aircraft. In a preferred embodiment, the thermally derived power is used to operate the cabin systems and other non-essential loads.
An additional sourcc of heat can be provided by fuel cells used to generate electricity for the aircraft. Fuel cells may operate at an efficiency of around 50%, whilst the efficiency of thermoelectric systems generally approaches 37% thus leading to an overall efficiency approaching 68.5% for a combined system of fuel cells and thermoelectric devices to capture their waste heat.
Fig. 2 is a cross-sectional view of a portion of a thermoelectric generator 6,7,8,9 comprising a plurality of solid state thermoelectric elements 13,14,15,16,17,18. The thermoelectric elements are doped alternately with n-type and p-type material arid are sandwiched between thermally conductive layers 11 and 12. Thus the elements numbered 13,15 arid 17 are n-type material, whilst those numbered 14,16 and 18 arc type material. In one embodiment, the thermally conductive layers II and 12 comprise ceramic wafers. A heat source is situated close to the ceramic wafer 12, which is shown at thc top of the generator in Fig.2. In practice, the generator 6,7,8,9 can be oriented at any suitable angle to harness heat 26 from the heat source. Electrically conductive interconnection members 19, 20, 21,22,23,24,25 are situated alternately between the ends of the thermoelectric elements 13-18 to allow a flow of current. Heat 26 from the heat source causes charge carriers to diffuse from the hot end of the thermoelectric elements to the cooler end thereof in accordance with the Seebeck Effect. This leads to a flow of current through the device.
Fig. 3 shows a cross-section of part of a thermoelectric generator 3,4 affixed to an exhaust section 31 of an aircraft engine. The engine can be any type of aircraft engine.
In practice, the thermoelectric generator 3,4 can extend completely around the exhaust section. In use, hot exhaust emissions pass through the exhaust section of the engine, and heat 26 is transferred from the emissions via the exhaust section 31 to the heat receiving surface 12 of the thermoelectric generator 3,4. It is believed to be possible to generate 70kW of electrical energy per engine. Even higher temperature differentials can be found in the combustor region of the engine, and if suitably temperature resistant materials are developed, this could also be used as a thermal power source.
The outer surface of the generator 3,4, ie the thermally conductive layer 11 is advantageously exposed to the ambient air outside the aircraft, thus ensuring continued cooling of the outer surface and hence maintenance of the temperature difference across the generator that is required to generate electricity.
Fig. 4 is a plan view of a form of the thermoelectric generator 3,4 that may be used in accordance with an embodiment of the invention. The thermoelectric generator 3,4 comprises a panel, which can have dimensions of 3m by im. In the manufacture of the thermoelectric generator, the panel 3, 4 is constructed of a plurality of semiconductor elements which are connected together serially whereby the potential difference across each clement is summed in operation.
Fig. 5 shows a graph of current against temperature difference for a thermoelectric generator. With increasing temperature difference across the generator, the current produced rises non-linearly. According to Fig.6, the vohage across the generator rises abruptly at an activation temperature difference TA and then levels off, increasing little for subsequent rises in temperature difference. The generator produces a DC voltage which is useful for many aircraft loads that run on DC power.
The generators 6-9 can advantageously be operated in a cooling mode. If an external current is applied to the generators cooling occurs in accordance with the Peltier effect.
In an alternative embodiment, the thermoelectric generator can comprise an Infra-Red photovoltaic generator. The thermoelectric elements 13-18 form part of an array which can extend both along and across the array, to form a lattice of elements.
Advantageously, embodiments of the present invention reduce fuel usage, by exploiting waste heat rather than throwing it away. The invention therefore reduces environmental damage and reduces costs. Further, the present invention has the advantage of allowing greater flexibility to the distribution of the energy around the aircraft. For example, energy can be used closer to the location at which it is generated. Also rectification of AC currents can be avoided by generating DC currents as needed.
Claims (1)
- <claim-text>CLAIMS: I. An ekctrical power generation and distribution system for an aircraft comprising one or more heat sources, a thermoelectric generator arranged to receive waste heat from at least one heat source and to convert the waste heat to electrical current, the thermoelectric generator being in electrical connection with an electrical distribution bus which is operable to supply power to aircraft electrical systems.</claim-text> <claim-text>2. A system according to claim 1, wherein the one or more heat sources include an engine exhaust section.</claim-text> <claim-text>3. A system according to claim 1 or 2, wherein the one or more heat sources include an auxiliary power unit.</claim-text> <claim-text>4. A system according to any of the preceding claims, wherein the one or more heat sources include an environmental control system.</claim-text> <claim-text>5. A system according to any of the preceding claims, wherein the one or more heat sources include a fuel cell.</claim-text> <claim-text>6. A system according to any of the prcccding claims, wherein the thermoelectric generator comprises one or more solid state thermoelectric elements.</claim-text> <claim-text>7. A system according to any of the preceding claims, wherein the thermoelectric generator comprises alternating elements of n-type and p-type semiconductor material.</claim-text> <claim-text>8. A system according to claim 7, wherein the semiconductor elements are electrically connected to adjacent elements by electrically conductive connectors.</claim-text> <claim-text>9. A system according to claim 8, wherein the semiconductor elements are electrically connected in series.</claim-text> <claim-text>10. A system according to claim 8 or 9, wherein the semiconductor elements are thermally connected in parallel.S</claim-text> <claim-text>11. A system according to any of the prcccding claims, wherein in use a DC voltage is produced by the generator.</claim-text> <claim-text>12. A system according to any of the preceding claims, wherein the thermoelectric generator comprises an infra-red photovoltaie device.</claim-text> <claim-text>13. An electrical power generation and distribution system substantially as herein described with reference to the accompanying drawings.</claim-text>
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1118313.4A GB2496839A (en) | 2011-10-24 | 2011-10-24 | Thermal electrical power generation for aircraft |
BR102012025929-0A BR102012025929A2 (en) | 2011-10-24 | 2012-10-10 | ELECTRIC POWER DISTRIBUTION AND GENERATION SYSTEM FOR AN AIRCRAFT |
CA2792589A CA2792589A1 (en) | 2011-10-24 | 2012-10-18 | Thermal electrical power generation for aircraft |
DE102012109992A DE102012109992A1 (en) | 2011-10-24 | 2012-10-19 | Thermoelectric power generation for aircraft |
FR1259978A FR2981637B1 (en) | 2011-10-24 | 2012-10-19 | THERMAL PRODUCTION SYSTEM OF ELECTRICITY FOR AIRCRAFT |
JP2012232459A JP2013091487A (en) | 2011-10-24 | 2012-10-22 | Thermal electrical power generation for aircraft |
CN2012104090915A CN103061856A (en) | 2011-10-24 | 2012-10-24 | Thermal electrical power generation for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1118313.4A GB2496839A (en) | 2011-10-24 | 2011-10-24 | Thermal electrical power generation for aircraft |
Publications (2)
Publication Number | Publication Date |
---|---|
GB201118313D0 GB201118313D0 (en) | 2011-12-07 |
GB2496839A true GB2496839A (en) | 2013-05-29 |
Family
ID=45373306
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1118313.4A Withdrawn GB2496839A (en) | 2011-10-24 | 2011-10-24 | Thermal electrical power generation for aircraft |
Country Status (7)
Country | Link |
---|---|
JP (1) | JP2013091487A (en) |
CN (1) | CN103061856A (en) |
BR (1) | BR102012025929A2 (en) |
CA (1) | CA2792589A1 (en) |
DE (1) | DE102012109992A1 (en) |
FR (1) | FR2981637B1 (en) |
GB (1) | GB2496839A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014135171A1 (en) * | 2013-03-07 | 2014-09-12 | Atta Moustafa Mahmoud Abd El-Daym | New source of electric power for aircraft |
US10291156B2 (en) | 2015-10-30 | 2019-05-14 | Ge Aviation Systems Llc | Combined hybrid thermionic and thermoelectric generator |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5832697B2 (en) * | 2013-03-27 | 2015-12-16 | Jfeスチール株式会社 | Thermoelectric power generation apparatus and thermoelectric power generation method using the same |
US20140360547A1 (en) * | 2013-06-06 | 2014-12-11 | Hamilton Sundstrand Corporation | Energy recovery and regeneration system |
US9666781B2 (en) * | 2013-08-19 | 2017-05-30 | The Boeing Company | Methods for recovering waste energy from bleed air ducts |
CN104092409A (en) * | 2014-07-17 | 2014-10-08 | 北京航空航天大学 | Combined thermoelectric conversion device |
CN105281607A (en) * | 2015-11-16 | 2016-01-27 | 滨州学院 | Hot waste water generator |
CN105515448A (en) * | 2016-01-19 | 2016-04-20 | 哈尔滨工业大学 | Hypersonic speed aircraft skin cooling and semiconductor thermoelectric power generation integrated system |
DE102016107303A1 (en) * | 2016-04-20 | 2017-10-26 | Rolls-Royce Deutschland Ltd & Co Kg | Energy conversion system of a turbomachine, transmission or bearing housing of a turbomachine and turbomachinery |
CN108768212B (en) * | 2018-06-12 | 2020-03-17 | 西安交通大学 | Energy recovery device of underwater vehicle |
DE102018116155A1 (en) * | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
CN113014144B (en) * | 2021-04-12 | 2023-03-21 | 西北工业大学 | Forced cooling thermoelectric power generation system of miniature turbojet engine |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001082167A (en) * | 1999-09-13 | 2001-03-27 | Toyota Motor Corp | Power generating device |
US20050022855A1 (en) * | 2003-07-30 | 2005-02-03 | Raver Bernard J. | Thermoelectric power generator for a gas turbine engine |
EP1746257A2 (en) * | 2005-07-19 | 2007-01-24 | United Technologies Corporation | Vehicle and corresponding operating method |
GB2447333A (en) * | 2007-03-09 | 2008-09-10 | Boeing Co | Thermoelectric energy harvesting arrangement |
DE102007036930A1 (en) * | 2007-08-04 | 2009-04-09 | Mtu Aero Engines Gmbh | Gas-turbine engine e.g. civilian aircraft engine or military aircraft engine, has thermoelectric generator generating electrical energy from temperature difference between hot current via core engine and cold current via bypass channel |
US20090159110A1 (en) * | 2007-12-21 | 2009-06-25 | Kwok David W | Thermoelectric generation system |
US20100242437A1 (en) * | 2009-03-25 | 2010-09-30 | United Technologies Corporation | Fuel-cooled flexible heat exchanger with thermoelectric device compression |
US20110131999A1 (en) * | 2009-12-07 | 2011-06-09 | Lijun Gao | Thermoelectric generator on an aircraft bleed system |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001023666A (en) * | 1999-07-08 | 2001-01-26 | Toyota Motor Corp | Waste heat recovering device and its control method |
JP2001082166A (en) * | 1999-09-13 | 2001-03-27 | Toyota Motor Corp | Electric power generating device |
JP2002257313A (en) * | 2001-02-27 | 2002-09-11 | Tokyo Gas Co Ltd | Combustible gas treatment system |
US8481843B2 (en) * | 2003-09-12 | 2013-07-09 | Board Of Trustees Operating Michigan State University | Silver-containing p-type semiconductor |
JP2007505028A (en) * | 2003-09-12 | 2007-03-08 | ボード オブ トラスティース オペレイティング ミシガン ステイト ユニバーシティー | Thermoelectric composition containing silver |
US20070277866A1 (en) * | 2006-05-31 | 2007-12-06 | General Electric Company | Thermoelectric nanotube arrays |
US7488888B2 (en) * | 2006-09-15 | 2009-02-10 | The Boeing Company | Energy harvesting devices |
US8127555B2 (en) * | 2007-12-13 | 2012-03-06 | Pratt & Whitney Rocketdyne, Inc. | Flowpath heat exchanger for thermal management and power generation within a hypersonic vehicle |
JP4878382B2 (en) * | 2009-05-14 | 2012-02-15 | 独立行政法人 宇宙航空研究開発機構 | Solar thermal collector in solar combined power generation system and solar thermal power generation module using the solar thermal collector |
US8568938B2 (en) * | 2009-08-28 | 2013-10-29 | The Boeing Company | Thermoelectric generator and fuel cell for electric power co-generation |
DE102009058156B4 (en) * | 2009-12-15 | 2014-11-13 | Mann + Hummel Gmbh | Cooling device in a vehicle |
-
2011
- 2011-10-24 GB GB1118313.4A patent/GB2496839A/en not_active Withdrawn
-
2012
- 2012-10-10 BR BR102012025929-0A patent/BR102012025929A2/en not_active IP Right Cessation
- 2012-10-18 CA CA2792589A patent/CA2792589A1/en not_active Abandoned
- 2012-10-19 FR FR1259978A patent/FR2981637B1/en active Active
- 2012-10-19 DE DE102012109992A patent/DE102012109992A1/en not_active Withdrawn
- 2012-10-22 JP JP2012232459A patent/JP2013091487A/en active Pending
- 2012-10-24 CN CN2012104090915A patent/CN103061856A/en active Pending
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001082167A (en) * | 1999-09-13 | 2001-03-27 | Toyota Motor Corp | Power generating device |
US20050022855A1 (en) * | 2003-07-30 | 2005-02-03 | Raver Bernard J. | Thermoelectric power generator for a gas turbine engine |
EP1746257A2 (en) * | 2005-07-19 | 2007-01-24 | United Technologies Corporation | Vehicle and corresponding operating method |
GB2447333A (en) * | 2007-03-09 | 2008-09-10 | Boeing Co | Thermoelectric energy harvesting arrangement |
DE102007036930A1 (en) * | 2007-08-04 | 2009-04-09 | Mtu Aero Engines Gmbh | Gas-turbine engine e.g. civilian aircraft engine or military aircraft engine, has thermoelectric generator generating electrical energy from temperature difference between hot current via core engine and cold current via bypass channel |
US20090159110A1 (en) * | 2007-12-21 | 2009-06-25 | Kwok David W | Thermoelectric generation system |
US20100242437A1 (en) * | 2009-03-25 | 2010-09-30 | United Technologies Corporation | Fuel-cooled flexible heat exchanger with thermoelectric device compression |
US20110131999A1 (en) * | 2009-12-07 | 2011-06-09 | Lijun Gao | Thermoelectric generator on an aircraft bleed system |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014135171A1 (en) * | 2013-03-07 | 2014-09-12 | Atta Moustafa Mahmoud Abd El-Daym | New source of electric power for aircraft |
US10291156B2 (en) | 2015-10-30 | 2019-05-14 | Ge Aviation Systems Llc | Combined hybrid thermionic and thermoelectric generator |
Also Published As
Publication number | Publication date |
---|---|
BR102012025929A2 (en) | 2014-03-18 |
CN103061856A (en) | 2013-04-24 |
GB201118313D0 (en) | 2011-12-07 |
FR2981637A1 (en) | 2013-04-26 |
DE102012109992A1 (en) | 2013-04-25 |
FR2981637B1 (en) | 2016-12-09 |
CA2792589A1 (en) | 2013-04-24 |
JP2013091487A (en) | 2013-05-16 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |