WO2014135171A1 - New source of electric power for aircraft - Google Patents
New source of electric power for aircraft Download PDFInfo
- Publication number
- WO2014135171A1 WO2014135171A1 PCT/EG2014/000008 EG2014000008W WO2014135171A1 WO 2014135171 A1 WO2014135171 A1 WO 2014135171A1 EG 2014000008 W EG2014000008 W EG 2014000008W WO 2014135171 A1 WO2014135171 A1 WO 2014135171A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- combustion chamber
- temperature difference
- aircraft
- thermoelectric generators
- efficiency
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 abstract description 9
- 239000000446 fuel Substances 0.000 abstract description 7
- 239000000463 material Substances 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 7
- 238000001816 cooling Methods 0.000 description 4
- 238000010790 dilution Methods 0.000 description 2
- 239000012895 dilution Substances 0.000 description 2
- 239000000498 cooling water Substances 0.000 description 1
- 238000011089 mechanical engineering Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000013021 overheating 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- 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
-
- 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
- F05D2220/70—Application in combination with
- F05D2220/76—Application in combination with an electrical generator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05004—Special materials for walls or lining
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/13003—Energy recovery by thermoelectric elements, e.g. by Peltier/Seebeck effect, arranged in the combustion plant
Definitions
- thermoelectric generator in the exhaust outlet of vehicle, where the exhaust gases at high temperatures that makes thermoelectric generator can Produces electricity through the temperature difference between the cooling water from radiator and exhaust gases in the engine, this temperature difference makes thermoelectric generator operate and produce electricity from wasted energy of exhaust. That will decrease emission, reduce fuel consumption up to 10% and improve engine efficiency of the car up to approximately 5%, which is considered a major achievement added to the thermoelectric generator, as shown in the fig No.l . ⁇ some information from references ⁇ .
- New in this idea is to take advantage of the temperature difference inside the combustion chamber of a jet engine, which is mandatory in the design in order to cooling parts of the combustion chamber, where the materials of combustion chamber can damage from the high temperatures resulting from the burning of fuel as shown in the Fig 2.
- the temperature difference inside the combustion chamber can generate electricity by installing thermoelectric generators on all the area of combustion chamber and room of exhaust, and generators on all the area of combustion chamber and room of exhaust, and then fed electricity to the aircraft. That will be a new source of electrical energy, which reduces fuel consumption, decrease emission and improve jet engine efficiency.
- thermoelectric generators Basically depends on the temperature difference between the two sides, the difference in temperatures available very well in the combustion chamber of aircraft engines and exhaust gases, which the hot side will be on flame temperature and the cool part to excess air, where the excess air flow to cool and prevent over heating in the combustion chamber. During that the electricity will generate, because part of the energy will be transferring from the hot side to the cold side, some of this heat will convert to electricity and the other is transferred to excess air by conduction.
- thermoelectric generators have efficiency, maximum working temperature and density that must take into account in the design.
- thermoelectric generator thermoelectric generator
- TEG thermoelectric generator
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
the Temperature difference in the combustion chamber and the exhaust outlet in aircraft engines and gas turbines in power stations, can make us to install thermoelectric generators with optimal design to produce the largest electrical energy as possible and reduce thermal resistance of heat transfer as possible to protect the walls of the combustion chamber from damage, select suitable thermoelectric materials with efficiency as high as possible and has high temperature limit, this Temperature difference with thermoelectric generators lead to generate electricity and also to improve efficiency, reduce pollution and decrease fuel consumption
Description
New Source Of Electric Power For Aircraft
Technical Field:
Mechanical engineering , increase jet engine and gas turbine Efficiency Background Art :
There was a research based on the installation of the thermoelectric generator in the exhaust outlet of vehicle, where the exhaust gases at high temperatures that makes thermoelectric generator can Produces electricity through the temperature difference between the cooling water from radiator and exhaust gases in the engine, this temperature difference makes thermoelectric generator operate and produce electricity from wasted energy of exhaust. That will decrease emission, reduce fuel consumption up to 10% and improve engine efficiency of the car up to approximately 5%, which is considered a major achievement added to the thermoelectric generator, as shown in the fig No.l . {some information from references } .
• The problem in the previous invention
Electricity being generated from the exhaust gases only as shown in the Fig No. 1, but in aircraft engines can produce electricity by the exhaust gases and also by the temperature difference in the combustion chamber of the jet engine, in that conditions the efficiency more than in vehicles and the generated power also, because the higher temperature and the thermoelectric generator installed in two positions. Disclosure Of Invention
New in this idea is to take advantage of the temperature difference inside the combustion chamber of a jet engine, which is mandatory in the design in order to cooling parts of the combustion chamber, where the materials of combustion chamber can damage from the high temperatures resulting from the burning of fuel as shown in the Fig 2. The temperature difference inside the combustion chamber can generate electricity by installing thermoelectric generators on all the area of combustion chamber and room of exhaust, and
generators on all the area of combustion chamber and room of exhaust, and then fed electricity to the aircraft. That will be a new source of electrical energy, which reduces fuel consumption, decrease emission and improve jet engine efficiency.
• Detailed description thermoelectric generators Basically depends on the temperature difference between the two sides, the difference in temperatures available very well in the combustion chamber of aircraft engines and exhaust gases, which the hot side will be on flame temperature and the cool part to excess air, where the excess air flow to cool and prevent over heating in the combustion chamber. During that the electricity will generate, because part of the energy will be transferring from the hot side to the cold side, some of this heat will convert to electricity and the other is transferred to excess air by conduction.
Each type of thermoelectric generators have efficiency, maximum working temperature and density that must take into account in the design.
• Marketing method
It is certain that any airline needs to reduce fuel consumption and pollution, to reduce ticket price and far away pollution limits, that can save billions of dollar. So that aircraft manufacturers of interest to improve jet engine efficiency reduce pollution and fuel consumption. To compete in the world market.
Brief Description of the Drawing
Figer 1
1. C 15 Engine
2. Exhaust Flow
3. Cooling pump
4. Secondary cooling loop
5. TEG ( thermoelectric generator )
6. Radiator
Figer 2
1. Air from Compressor
2. Diffuser
3. Fuel nozzle
4. Air swirler
5. Primary zone
6. Primary hole
7. Cooling slot
8. Intermediate hole
9. Intermediate zone
10. Dilution zone
11. Dilution hole
12. Gases to Turbine
13. TEG (thermoelectric generator) on all the area of the combustion chamber and room of exhaust.
Claims
Claims
The first element: which consists of
The combustion chamber with thermoelectric generators as shown in FIG No. 2.
The second element: which consists of
Part Number 13 Fig 2, thermoelectric generators installation inside the combustion chamber of aircraft engines and gas turbines
The third element: which consists of
Room of exhaust with thermoelectric generators.
The fourth element: which consists of
installation of thermoelectric generators inside the room of exhaust
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EG2013030384 | 2013-03-07 | ||
| EG2013030384 | 2013-03-07 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO2014135171A1 true WO2014135171A1 (en) | 2014-09-12 |
| WO2014135171A4 WO2014135171A4 (en) | 2014-12-04 |
Family
ID=51490652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EG2014/000008 WO2014135171A1 (en) | 2013-03-07 | 2014-03-03 | New source of electric power for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2014135171A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114576007A (en) * | 2022-03-01 | 2022-06-03 | 北京盈天航空动力科技有限公司 | Microminiature turbojet engine waste heat recovery motor structure |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7658070B2 (en) * | 2004-09-21 | 2010-02-09 | Drs Sustainment Systems, Inc. | Method and apparatus for improving the energy conversion efficiency of electrical power generators |
| US20110067742A1 (en) * | 2009-07-24 | 2011-03-24 | Bell Lon E | Thermoelectric-based power generation systems and methods |
| US20120118345A1 (en) * | 2010-11-15 | 2012-05-17 | The Boeing Company | Thermal integration of thermoelectronic device |
| GB2496839A (en) * | 2011-10-24 | 2013-05-29 | Ge Aviat Systems Ltd | Thermal electrical power generation for aircraft |
-
2014
- 2014-03-03 WO PCT/EG2014/000008 patent/WO2014135171A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7658070B2 (en) * | 2004-09-21 | 2010-02-09 | Drs Sustainment Systems, Inc. | Method and apparatus for improving the energy conversion efficiency of electrical power generators |
| US20110067742A1 (en) * | 2009-07-24 | 2011-03-24 | Bell Lon E | Thermoelectric-based power generation systems and methods |
| US20120118345A1 (en) * | 2010-11-15 | 2012-05-17 | The Boeing Company | Thermal integration of thermoelectronic device |
| GB2496839A (en) * | 2011-10-24 | 2013-05-29 | Ge Aviat Systems Ltd | Thermal electrical power generation for aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114576007A (en) * | 2022-03-01 | 2022-06-03 | 北京盈天航空动力科技有限公司 | Microminiature turbojet engine waste heat recovery motor structure |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114872908B (en) * | 2022-06-08 | 2024-03-26 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
| CN114954964B (en) * | 2022-06-08 | 2024-04-16 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2014135171A4 (en) | 2014-12-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20040045594A1 (en) | Turbine engine with thermoelectric waste heat recovery system | |
| JP2012039858A5 (en) | ||
| PL2288796T3 (en) | Device for producing electrical energy from exhaust gas heat | |
| CN102891635A (en) | Automobile thermoelectric power generation device | |
| ATE529616T1 (en) | EXHAUST SYSTEM FOR AN INTERNAL COMBUSTION ENGINE | |
| CN103061856A (en) | Thermal electrical power generation for aircraft | |
| RU2487305C1 (en) | Trigeneration plant based on microturbine motor | |
| CN105604661A (en) | Device for power generation by waste heat of automobile exhaust pipes | |
| JP2013170579A (en) | Gas turbine inlet system with solid-state heat pump | |
| WO2014135171A1 (en) | New source of electric power for aircraft | |
| KR101401065B1 (en) | Thermoelectric generator of vehicle | |
| CN202361611U (en) | Gas fired water heater | |
| JP2014129809A (en) | Vehicle stacked thermoelectric generator | |
| CN103166523A (en) | Method and device for recovering waste heat of heating furnace wall and generating electricity | |
| CN105226998A (en) | A kind of temperature difference electricity generation device and electric power system utilizing boiler slag-cooling hydro-thermal amount | |
| ES2604935T3 (en) | Method of operation of a power plant with Solar Energy System | |
| CN104578977A (en) | Automobile exhaust thermoelectricity generating set | |
| CN205070847U (en) | Utilize cold thermal temperature difference power generation devices of pulp water of boiler and power supply system | |
| CN205400867U (en) | Vehicle vent -pipe waste heat power generation device | |
| KR20130039149A (en) | Annular thermoelectric generator which surrounds external exhaust pipe | |
| CN103401478A (en) | Gas combustion heat power generation and supply device | |
| KR101340849B1 (en) | Thermoelectric generator of vehicle | |
| CN206023618U (en) | A kind of residual heat of tail gas of automobile temperature difference electricity generation device of employing phase-change material | |
| CN103673289B (en) | Gas-fired heat pump water heater | |
| CN218850653U (en) | Aeroengine waste heat recovery thermoelectric generation system |
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: 14760275 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: 14760275 Country of ref document: EP Kind code of ref document: A1 |