WO2010067172A2 - Apparatus and method for energy recovery on jet-powered airplanes on approach for landing - Google Patents
Apparatus and method for energy recovery on jet-powered airplanes on approach for landing Download PDFInfo
- Publication number
- WO2010067172A2 WO2010067172A2 PCT/IB2009/007664 IB2009007664W WO2010067172A2 WO 2010067172 A2 WO2010067172 A2 WO 2010067172A2 IB 2009007664 W IB2009007664 W IB 2009007664W WO 2010067172 A2 WO2010067172 A2 WO 2010067172A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- generator
- fan
- gearbox
- airplanes
- landing
- Prior art date
Links
- 238000011084 recovery Methods 0.000 title claims abstract description 8
- 238000013459 approach Methods 0.000 title claims abstract description 6
- 238000000034 method Methods 0.000 title claims description 19
- 230000006835 compression Effects 0.000 claims abstract description 7
- 238000007906 compression Methods 0.000 claims abstract description 7
- 239000007858 starting material Substances 0.000 claims abstract description 7
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 230000002441 reversible effect Effects 0.000 claims description 4
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 claims 1
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 229910001416 lithium ion Inorganic materials 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 239000003990 capacitor Substances 0.000 abstract description 4
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 3
- 230000003213 activating effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 241000272173 Calidris Species 0.000 description 1
- 241001481828 Glyptocephalus cynoglossus Species 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- 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
- F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
-
- 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
- F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
-
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- 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
- F05D2220/50—Application for auxiliary power units (APU's)
-
- 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
- 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
- F05D2260/40—Transmission of power
-
- 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
- F05D2260/85—Starting
Definitions
- the fan is uncoupled from the compression and turbine section applying a secondary planetary gear set, and therewith connected to the starter/generator unit to produce power, that might be stored in capacitors or batteries for re-use.
- the invention relates to energy recovery on airplanes with modern turbojet engines and more precisely to the recovery of energy potentials that otherwise need to be braked off in landing flaps, wheelbrakes. and by counterthrust.
- Airplanes use a substantial part of their fuel consumption for climbing onto their cruising altitude, which is then transformed into potential energy as to height and and total weight as factors.
- the angle of descent can be made steeper, so to save time and to allow higher air traffic density.
- This system does as well enable the application of automatic controls, like those to reduce the yawing angle on flight, whilst controlling the mechanical resistance of the generator and fan set, so to ensure safe gliding unto touchdown.
- the planetary gearbox is equipped with another planetary gear set, the drive side of witch is coupled to the generator, whereas the main drive is uncoupled from the compression section.
- the generator by means of chain- or belt drives to the fan axle.
- the generator contains permanent magnetic elements, that are embedded into a disc, which is coupled to the planetary drive and may rotate independently close to a coiled stator disc or cup on the gearbox' housing.
- Similar constructions are well known in the art as combinations of starter/generators in street vehicles with autostop/start arrangements. 40
- other arrangements of rotor and stator are well known in the art and alternatively applicable, but in all cases an arrangement closely behind the fan and largely away from compressor and combustion chamber is mandatory to prevent the permanent magnets from overheating an thus deterioration.
- the generator preferably is reversible, so to be used as starter motor - as well known in the art. This reduces a good deal of cost to be omitted to this section.
- Recuperated energy at descent can be applied to counterthrust after touch down, simply by counter-rotating the uncoupled fan, this way avoiding to re-activate the turbines for the sake of wasting fuel, but even more to avoid critical noise emissions.
- recuperated energy is as well possible for energizing airplanes during their stay on ground, what otherwise APUs are applied for - thus not only saving Energy, but particularly the disgusting noise and exhaust gases of these units.
- some part of the energy may rather be stored in Lihtium-Ion batteries, due to their lower self-discharge. 6
- FIG. 1 One preferred embodiment of the heredisclosed invention is illustrated by Fig. 1 :
- Fig 1 defines the cross-section of a sheath current turbofan engine 1 , containing a planetary gearbox 2 between fan 3, compression unit 4 and combustion chamber 5 before the turbine section 6.
- the planetary gearbox 2 is equipped with a secondary planetary gearset 7, that is fixed to the rotor 8 of the generator 9, that turns freely on the bearing 10 around the fax axle 11. Frontal to rotor 8 of the generator 9 the stator is integrated into the housing of the gearbox 13.
- the rotor 8 preferably is equipped with permanent magnetsl4, 15, whereas the stator 12 carries the inductive coils 16 and 17 (but construction could as well be done vice- versa).
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Retarders (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
For recovery of energy potentials of airplanes with modern geared turbofan engines on approach for landing, the fan is uncoupled from the compression and turbine section applying a secondary planetary gear set, and therewith connected to the starter/generator unit to produce power, that might be stored in capacitors or batteries for re-use.
Description
APPARATUS AND METHOD FOR ENERGY RECOVERY ON JET-POWERED AIRPLANES ON APPROACH FOR LANDING
ABSTRACT
For recovery of energy potentials of airplanes with modern geared turbof an engines on approach for landing, the fan is uncoupled from the compression and turbine section applying a secondary planetary gear set, and therewith connected to the starter/generator unit to produce power, that might be stored in capacitors or batteries for re-use.
FIELD OF THE INVENTION
The invention relates to energy recovery on airplanes with modern turbojet engines and more precisely to the recovery of energy potentials that otherwise need to be braked off in landing flaps, wheelbrakes. and by counterthrust.
BACKGROUND OF THE INVENTION
Airplanes use a substantial part of their fuel consumption for climbing onto their cruising altitude, which is then transformed into potential energy as to height and and total weight as factors.
PROBLEM TO BE SOLVED
When in approach to landing, a certain amount of this potential can be recovered by gliding with reduced fuel feed. However, not always an optimum gliding path can be administered, partly because airports are sometimes positioned in geographical basins, or air traffic does not allow it.
Moreover, in all cases a minimum speed must be kept unto touch down, so to avoid instabilities in the airplane's flight attitude. Hitherto, particularly with large aircraft, a substantial amount of this potential energy must be dissipated by landing airbrakes and after touch down with wheel- brakes and the counterthrust of reversed jet engines.
PRIOR ART
Some attempts had been made to spare energy on airplanes, which mostly refer to more efficient wing and engine designs, but few on real energy recovering. Only exceptions are some attempts to recover waste energy of aircraft engines, as in US 4.271.665, but no solution sofar has been found for recovering the potential energy of a landing aircraft.
SUMMARY OF THE INVENTION
It is therefore the object of the heredisclosed invention, to reduce the amount of this dissipated energy, respectively, to recover and reuse these potentials.
This is achieved by reversing the function of the jet engine for braking and recovery of energy.
In this case the angle of descent can be made steeper, so to save time and to allow higher air traffic density.
10
Provided, a higher bypass ratio can be realized - what is the aim at almost all new jet engine developments - possibly flaps for airbraking must no more be activated, and, on a longer term, may be obsolete, due to the breaking effect of the fan and the electric generator. Moreover, reverse thrust could be activated without activating reversing flaps and accelerating the jet engine, simply by electrically reversing the starter/generator of the engines with some 15 recuperation energy shortly before generated and loaded into capacitors.
This system does as well enable the application of automatic controls, like those to reduce the yawing angle on flight, whilst controlling the mechanical resistance of the generator and fan set, so to ensure safe gliding unto touchdown.
20 This is backed by the mainstream of jet engine developments, which are directed towards greater bypass ratios, and the use of fans of larger diameters in combination with geared systems - so to uncouple engine speed and fan speed in favor of lower fan rotation speed, for not to over- stress fan blade tips. These reduction gearboxes usually contain planetary gears between the fan hub an the compres-
_,. sion section of the jet engine.
It therefore is the object of the present invention to recover electric energy from the uncoupled fan with an additional planetary gearset, or - in case of non-geared jet engines - to largely bypass the airstream from the compression section.
30
In a preferred embodiment of the here disclosed invention at geared jet engines, the planetary gearbox is equipped with another planetary gear set, the drive side of witch is coupled to the generator, whereas the main drive is uncoupled from the compression section. However, it is as well possible to couple the generator by means of chain- or belt drives to the fan axle.
35
In a preferred embodiment of this invention, the generator contains permanent magnetic elements, that are embedded into a disc, which is coupled to the planetary drive and may rotate independently close to a coiled stator disc or cup on the gearbox' housing. Similar constructions are well known in the art as combinations of starter/generators in street vehicles with autostop/start arrangements. 40
However, other arrangements of rotor and stator are well known in the art and alternatively applicable, but in all cases an arrangement closely behind the fan and largely away from compressor and combustion chamber is mandatory to prevent the permanent magnets from overheating an thus deterioration.
The generator preferably is reversible, so to be used as starter motor - as well known in the art. This reduces a good deal of cost to be omitted to this section.
Recuperated energy at descent can be applied to counterthrust after touch down, simply by counter-rotating the uncoupled fan, this way avoiding to re-activate the turbines for the sake of wasting fuel, but even more to avoid critical noise emissions.
In an advanced development of airplanes it might then be possible to stint the investment for reversing thrust on jet engines.
Since there is just a limited time for activating and a short time between recuperation an application of that energy, storing in capacitors is mandatory, which are lightweight in comparison to batteries of the same capacity, and deliver all stored energy within short time.
However, the application of recuperated energy is as well possible for energizing airplanes during their stay on ground, what otherwise APUs are applied for - thus not only saving Energy, but particularly the disgusting noise and exhaust gases of these units. For this application some part of the energy may rather be stored in Lihtium-Ion batteries, due to their lower self-discharge. 6
One preferred embodiment of the heredisclosed invention is ilustrated by Fig. 1 :
Fig 1 defines the cross-section of a sheath current turbofan engine 1 , containing a planetary gearbox 2 between fan 3, compression unit 4 and combustion chamber 5 before the turbine section 6.
The planetary gearbox 2 is equipped with a secondary planetary gearset 7, that is fixed to the rotor 8 of the generator 9, that turns freely on the bearing 10 around the fax axle 11. Frontal to rotor 8 of the generator 9 the stator is integrated into the housing of the gearbox 13. The rotor 8 preferably is equipped with permanent magnetsl4, 15, whereas the stator 12 carries the inductive coils 16 and 17 (but construction could as well be done vice- versa).
Claims
1. Apparatus and method for energy recovery at jet-powered airplanes on approach for landing, wherein the fan of a turbo engine is temporarily coupled to an electric Starter/generator.
2. Apparatus and method as to claim 1, wherein the compression stage is bypassed and thus combustion is off and turbine sections run free.
3. Apparatus and method as to claim 1 , wherein the shaft drive between fan and compression unit and following sections is uncoupled at coasting and the fan shaft coupled to an electric
1Q generator.
4. Apparatus and method as to claim 1 and 3, wherein the uncoupling means is an intermediate gearbox with freewheel clutch.
5. Apparatus and method as to claim 4, wherein the gearbox is of planetary type. 15
6. Apparatus and method as to claim 1 unto 5, wherein the coupling of the fan to the gearbox is provided by a secondary planetary gearset and clutch.
7. Apparatus and method as to claim 1, wherein The generator is mounted within the sheath current and most distantly from the combustion chamber. 20
8. Apparatus and method as to claim 1 and 5 to 6, wherein the generator is positioned between fan and gearbox.
9. Apparatus and method as to claim 1 and ..., wherein the heading of airplanes at descent can yc- be controlled by electrically regulating the mechanical resistance of the generators.
10. Apparatus and method as to claim 1 and ..., wherein the generator is charging an accumulator system for electrical energy.
11. Apparatus and method as to claim 1 and 10, wherein the accumulator system contains ca- 30 pacitors of high capacitance.
12. Apparatus and method as to claim 1 and ..., wherein the accumulator system contains lithium ion batteries.
13. Apparatus and method as to claim 1 and 10, wherein the generator can be switched to func- 35 tion as starter motor.
14. Apparatus and method as to claim 1 and 10, wherein the generator can be switched to function as driving motor.
15. Apparatus and method as to claim 1 and 10, wherein the stored electrical energy is applied for executing antithrust after touchdown.
16. Apparatus and method as to claim 15, wherein antithrust is generated by electrically actuat- ing the fan in reverse direction.
17. Apparatus and method as to claim 14 and 16, wherein the generator in its function as a motor drives the fan in reverse.
* * * * *
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE200810062088 DE102008062088B4 (en) | 2008-12-12 | 2008-12-12 | Device for energy recovery in aircraft engines during landing approach. |
| DE1020080620882-13 | 2008-12-12 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO2010067172A2 true WO2010067172A2 (en) | 2010-06-17 |
| WO2010067172A3 WO2010067172A3 (en) | 2011-01-13 |
Family
ID=42194009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/IB2009/007664 WO2010067172A2 (en) | 2008-12-12 | 2009-12-07 | Apparatus and method for energy recovery on jet-powered airplanes on approach for landing |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE102008062088B4 (en) |
| WO (1) | WO2010067172A2 (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013209388A1 (en) * | 2013-05-22 | 2014-11-27 | Robert Bosch Gmbh | Hybrid propulsion for powered aircraft, powered aircraft with hybrid drive and related operating procedures |
| EP2947278A1 (en) * | 2014-05-20 | 2015-11-25 | United Technologies Corporation | Geared turbofan with high speed generator |
| GB2531429A (en) * | 2014-10-01 | 2016-04-20 | Goodrich Corp | Electric architecture with power storage cells |
| FR3037038A1 (en) * | 2015-06-08 | 2016-12-09 | Andre Chaneac | TURBO REACTOR DRIVING A BLOWER AND A GENERATOR, ITS MOUNTING ON A VERTICAL LANDING AEROFEF AND LANDFILLING |
| CN106560605A (en) * | 2015-10-06 | 2017-04-12 | 熵零股份有限公司 | Planetary mechanism propfan engine |
| EP3190052A1 (en) * | 2016-01-05 | 2017-07-12 | The Boeing Company | Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations |
| DE102016207517A1 (en) * | 2016-05-02 | 2017-11-02 | Siemens Aktiengesellschaft | Propulsion system for aircraft with electric generator |
| DE202017103131U1 (en) * | 2017-05-23 | 2018-08-24 | ENGIRO GmbH | Aircraft with at least one range extender |
| EP3392465A3 (en) * | 2017-04-21 | 2018-11-14 | Rolls-Royce plc | An auxiliary rotation device for a gas turbine engine and a method of cooling a rotor of a gas turbine engine using an auxiliary rotation device |
| WO2019155173A1 (en) | 2018-02-09 | 2019-08-15 | Safran | Hybrid propulsion for an aircraft |
| EP3530928A1 (en) * | 2018-02-26 | 2019-08-28 | The Boeing Company | Hybrid turbine jet engines and methods of operating the same |
| US10760498B2 (en) * | 2018-01-04 | 2020-09-01 | General Electric Company | System and method for removing rotor bow in a gas turbine engine using mechanical energy storage device |
| US11073109B2 (en) | 2018-10-01 | 2021-07-27 | Rolls-Royce Plc | Gas turbine engine |
| US20210396148A1 (en) * | 2020-06-22 | 2021-12-23 | Florida Turbine Technologies, Inc. | Multi-spool geared turbofan arrangement with integrated starter/generator |
| US11884172B2 (en) | 2020-07-30 | 2024-01-30 | Hamilton Sundstrand Corporation | Battery charging for hybrid electric powerplants |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3444495A1 (en) | 2017-08-18 | 2019-02-20 | Rolls-Royce Deutschland Ltd & Co KG | Mechanical clutch device and method for operating a mechanical clutch device |
| US10954813B2 (en) | 2017-08-18 | 2021-03-23 | Rolls-Royce Deutschland Ltd & Co Kg | Planetary gearbox system and method for operating a planetary gearbox system |
| DE102018203423A1 (en) * | 2018-03-07 | 2019-09-12 | Rolls-Royce Deutschland Ltd & Co Kg | Shaft assembly and aircraft engine with a shaft assembly |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040255590A1 (en) * | 2003-06-23 | 2004-12-23 | Pratt & Whiney Canada Corp. | Differential geared turbine engine with torque modulation capability |
| US20060137355A1 (en) * | 2004-12-27 | 2006-06-29 | Pratt & Whitney Canada Corp. | Fan driven emergency generator |
| WO2008082335A1 (en) * | 2006-12-29 | 2008-07-10 | Volvo Aero Corporation | A power transmission device for a gas turbine engine |
| EP1990519A2 (en) * | 2007-05-08 | 2008-11-12 | Pratt & Whitney Canada Corp. | Method of operating a gas turine engine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2775734B1 (en) * | 1998-03-05 | 2000-04-07 | Snecma | METHOD AND DEVICE FOR REVERSE DRIVE FOR A MOTOR WITH VERY HIGH DILUTION RATES |
| US7802757B2 (en) * | 2005-11-09 | 2010-09-28 | Pratt & Whitney Canada Corp. | Method and system for taxiing an aircraft |
| DE102006039608A1 (en) * | 2006-08-24 | 2008-04-10 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for energy extraction in a two-shaft engine |
| US7942079B2 (en) * | 2007-02-16 | 2011-05-17 | Hamilton Sundstrand Corporation | Multi-speed gearbox for low spool driven auxiliary component |
-
2008
- 2008-12-12 DE DE200810062088 patent/DE102008062088B4/en not_active Expired - Fee Related
-
2009
- 2009-12-07 WO PCT/IB2009/007664 patent/WO2010067172A2/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040255590A1 (en) * | 2003-06-23 | 2004-12-23 | Pratt & Whiney Canada Corp. | Differential geared turbine engine with torque modulation capability |
| US20060137355A1 (en) * | 2004-12-27 | 2006-06-29 | Pratt & Whitney Canada Corp. | Fan driven emergency generator |
| WO2008082335A1 (en) * | 2006-12-29 | 2008-07-10 | Volvo Aero Corporation | A power transmission device for a gas turbine engine |
| EP1990519A2 (en) * | 2007-05-08 | 2008-11-12 | Pratt & Whitney Canada Corp. | Method of operating a gas turine engine |
Non-Patent Citations (1)
| Title |
|---|
| GREGG C BRUCE ET AL: "Large Lithium Ion Batteries for Aerospace and Aircraft Applications" IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE, IEEE SERVICE CENTER, PISCATAWAY, NJ, US, vol. 16, no. 9, 1 September 2001 (2001-09-01), pages 24-28, XP011091554 ISSN: 0885-8985 * |
Cited By (31)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013209388B4 (en) | 2013-05-22 | 2021-07-22 | Robert Bosch Gmbh | Hybrid propulsion for power-powered aircraft, power-powered aircraft with hybrid drive and associated operating method |
| DE102013209388A1 (en) * | 2013-05-22 | 2014-11-27 | Robert Bosch Gmbh | Hybrid propulsion for powered aircraft, powered aircraft with hybrid drive and related operating procedures |
| US9915164B2 (en) | 2014-05-20 | 2018-03-13 | United Technologies Corporation | Geared turbofan with high speed generator |
| EP2947278A1 (en) * | 2014-05-20 | 2015-11-25 | United Technologies Corporation | Geared turbofan with high speed generator |
| US11236632B2 (en) | 2014-05-20 | 2022-02-01 | Raytheon Technologies Corporation | Geared turbofan with high speed generator |
| GB2531429A (en) * | 2014-10-01 | 2016-04-20 | Goodrich Corp | Electric architecture with power storage cells |
| GB2531429B (en) * | 2014-10-01 | 2017-02-08 | Goodrich Corp | Electric architecture with power storage cells |
| US9982606B2 (en) | 2014-10-01 | 2018-05-29 | Goodrich Corporation | Electric architecture with power storage cells |
| FR3037038A1 (en) * | 2015-06-08 | 2016-12-09 | Andre Chaneac | TURBO REACTOR DRIVING A BLOWER AND A GENERATOR, ITS MOUNTING ON A VERTICAL LANDING AEROFEF AND LANDFILLING |
| CN106560605A (en) * | 2015-10-06 | 2017-04-12 | 熵零股份有限公司 | Planetary mechanism propfan engine |
| US10336461B2 (en) | 2016-01-05 | 2019-07-02 | The Boeing Company | Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations |
| JP2017122452A (en) * | 2016-01-05 | 2017-07-13 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Aircraft engine and associated method for driving fan with low pressure shaft during taxiing |
| JP7025117B2 (en) | 2016-01-05 | 2022-02-24 | ザ・ボーイング・カンパニー | Aircraft engine and related methods for driving a fan with a low pressure shaft during taxiing |
| EP3190052A1 (en) * | 2016-01-05 | 2017-07-12 | The Boeing Company | Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations |
| AU2016256682B2 (en) * | 2016-01-05 | 2021-07-01 | The Boeing Company | Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations |
| DE102016207517A1 (en) * | 2016-05-02 | 2017-11-02 | Siemens Aktiengesellschaft | Propulsion system for aircraft with electric generator |
| US11092031B2 (en) | 2016-05-02 | 2021-08-17 | Rolls-Royce Deutschland Ltd & Co Kg | Drive system for an aircraft |
| EP3392465A3 (en) * | 2017-04-21 | 2018-11-14 | Rolls-Royce plc | An auxiliary rotation device for a gas turbine engine and a method of cooling a rotor of a gas turbine engine using an auxiliary rotation device |
| DE202017103131U1 (en) * | 2017-05-23 | 2018-08-24 | ENGIRO GmbH | Aircraft with at least one range extender |
| US10760498B2 (en) * | 2018-01-04 | 2020-09-01 | General Electric Company | System and method for removing rotor bow in a gas turbine engine using mechanical energy storage device |
| WO2019155173A1 (en) | 2018-02-09 | 2019-08-15 | Safran | Hybrid propulsion for an aircraft |
| FR3077804A1 (en) * | 2018-02-09 | 2019-08-16 | Safran | HYBRID PROPULSION FOR AN AIRCRAFT |
| US11608188B2 (en) | 2018-02-09 | 2023-03-21 | Safran | Hybrid propulsion for an aircraft |
| CN110195656A (en) * | 2018-02-26 | 2019-09-03 | 波音公司 | Hybrid turbine jet engine and the method for operating it |
| EP3530928A1 (en) * | 2018-02-26 | 2019-08-28 | The Boeing Company | Hybrid turbine jet engines and methods of operating the same |
| CN110195656B (en) * | 2018-02-26 | 2023-02-21 | 波音公司 | Hybrid turbojet engine and method of operating same |
| US11073109B2 (en) | 2018-10-01 | 2021-07-27 | Rolls-Royce Plc | Gas turbine engine |
| US20210396148A1 (en) * | 2020-06-22 | 2021-12-23 | Florida Turbine Technologies, Inc. | Multi-spool geared turbofan arrangement with integrated starter/generator |
| WO2021260531A1 (en) * | 2020-06-22 | 2021-12-30 | Florida Turbine Technologies, Inc. | Multi-spool geared turbofan arrangement with integrated starter/generator |
| US11286805B2 (en) | 2020-06-22 | 2022-03-29 | Florida Turbine Technologies, Inc. | Multi-spool geared turbofan arrangement with integrated starter/generator |
| US11884172B2 (en) | 2020-07-30 | 2024-01-30 | Hamilton Sundstrand Corporation | Battery charging for hybrid electric powerplants |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102008062088B4 (en) | 2015-03-05 |
| WO2010067172A3 (en) | 2011-01-13 |
| DE102008062088A1 (en) | 2010-06-24 |
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