US20230220803A1 - Firewall assemblies for hybrid electric aircraft powerplants - Google Patents
Firewall assemblies for hybrid electric aircraft powerplants Download PDFInfo
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- US20230220803A1 US20230220803A1 US18/120,280 US202318120280A US2023220803A1 US 20230220803 A1 US20230220803 A1 US 20230220803A1 US 202318120280 A US202318120280 A US 202318120280A US 2023220803 A1 US2023220803 A1 US 2023220803A1
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- prime mover
- powerplant
- firewall
- fire zone
- fire
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- 230000000712 assembly Effects 0.000 title description 3
- 238000000429 assembly Methods 0.000 title description 3
- 239000012530 fluid Substances 0.000 claims description 6
- 230000037361 pathway Effects 0.000 claims description 6
- 238000009423 ventilation Methods 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 description 3
- 238000010397 one-hybrid screening Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
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- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- F02C7/24—Heat or noise insulation
- F02C7/25—Fire protection or prevention
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C2/00—Fire prevention or containment
- A62C2/06—Physical fire-barriers
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
- A62C3/07—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
- A62C3/08—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
-
- 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
-
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/11—Thermal or acoustic insulation
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
-
- B64D2027/026—
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/009—Fire detection or protection; Erosion protection, e.g. from airborne particles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/231—Preventing heat transfer
-
- 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
- This disclosure relates to hybrid electric powerplants.
- a nacelle usually forms a firewall between an engine and the wing, engine mount pylon, or other aircraft structure not considered a fire zone.
- traditional assemblies may not be acceptable for power lane redundancy and independence.
- a powerplant can include a first prime mover configured to turn a propulsor, and a second prime mover operatively connected in parallel with the first prime mover to turn the propulsor together with or separately from the first prime mover.
- the powerplant can include a firewall disposed around at least one of the first prime mover or the second prime mover to create a first prime mover fire zone and a second prime mover fire zone separate from the first prime mover fire zone such that the first prime mover is protected against a second prime mover fire, and vice versa.
- the powerplant can be or include a hybrid electric powerplant, where the first prime mover can include an electric motor configured to convert electrical energy into kinetic energy to turn the propulsor and the second prime mover can include a heat engine configured to convert a fuel into kinetic energy to turn the propulsor.
- the powerplant can further comprise a nacelle.
- the electric motor, the heat engine, and the firewall can be disposed within the nacelle.
- the nacelle can form at least a portion of the firewall.
- the firewall may be only an electric motor firewall that is disposed around the electric motor. In such cases, there may be no separate heat engine firewall surrounding the heat engine. All electric motor components within the nacelle can be contained within the firewall.
- Certain embodiments can include a fire extinguisher system comprising at least one fire extinguishing medium source and at least a first outlet and a second outlet.
- the first outlet can be configured to provide extinguishing medium to the electric motor fire zone.
- the second outlet can be configured to provide extinguishing medium to the heat engine fire zone.
- the electric motor fire zone can be fluidly sealed from the heat motor fire zone such that extinguishing medium can be used in either fire zone independent of the other.
- the firewall can include a metallic and/or composite baffle that surrounds the electric motor to form the electric motor fire zone.
- the baffle can be configured to be bolted to a nacelle.
- Certain embodiments can include a ventilation pathway for each fire zone for providing outside air to each fire zone.
- the ventilation pathway can include a dedicated nacelle scoop in fluid communication with each fire zone, for example.
- an aircraft can include at least one hybrid electric aircraft powerplant as disclosed herein, e.g., as described above. Any suitable type of aircraft and/or any other suitable aircraft components are contemplated herein.
- FIG. 1 is a cross-sectional view of an embodiment of a powerplant in accordance with this disclosure.
- FIG. 2 is a plan view of the embodiment of FIG. 1 .
- FIG. 1 an illustrative view of an embodiment of a powerplant in accordance with the disclosure is shown in FIG. 1 and is designated generally by reference character 100 .
- FIG. 2 Other embodiments and/or aspects of this disclosure are shown in FIG. 2 .
- a powerplant 100 (e.g., a hybrid electric powerplant) can include a first prime mover 101 (e.g., an electric motor) configured to convert electrical energy into kinetic energy to turn a propulsor 103 (e.g., a propeller as shown).
- the powerplant 100 can include a second prime mover 105 (e.g., a heat enine) configured to convert a fuel into kinetic energy to turn the propulsor 103 .
- the first prime mover 101 and the second prime mover 105 can be operatively connected in parallel to turn the propulsor together or independently.
- the powerplant 100 can include a firewall 107 disposed around at least one of the electric motor 101 or the heat engine 105 to create an electric motor fire zone 109 and a heat engine fire zone 111 separate from the electric motor fire zone 109 such that the electric motor 101 is protected against a heat engine fire, and vice versa.
- the powerplant 100 can further comprise a nacelle 113 .
- FIGS. 1 and 2 are not exhaustive of the possible embodiments and one having ordinary skill in the art would appreciate, in view of this disclosure, that the engine fire zone 111 can be coextensive in size with the area designated as heat engine 105 , for example (e.g., such that the heat engine 105 has its own separate firewall within the nacelle 113 ). Any other suitable demarcation of fire zones 109 , 111 is contemplated herein.
- the electric motor 101 , the heat engine 105 , and the firewall 107 can be disposed within the nacelle 113 .
- the nacelle 113 can form at least a portion of the firewall 107 (e.g., such that at least a portion of the firewall 107 is integral with the nacelle 113 ).
- a wall of the firewall 107 can be defined by an inside wall of the nacelle 113 .
- the firewall 107 may be only an electric motor firewall 107 , e.g., as shown, that is disposed around the electric motor 101 . In such cases, e.g., as shown, there may be no separate heat engine firewall surrounding the heat engine 105 . In certain embodiments, all electric motor components (e.g., power cables 115 and/or any other suitable electric motor system components) within the nacelle 113 can be contained within the firewall 107 , e.g., as shown, or otherwise be fireproofed. Any other suitable arrangement is contemplated herein.
- Certain embodiments can include a fire extinguisher system 117 , e.g., as shown in FIG. 1 .
- the extinguisher system 117 can include at least one fire extinguishing medium source 119 and at least a first outlet 121 and a second outlet 123 .
- the first outlet 121 can be configured to provide extinguishing medium (e.g., extinguishing fluid and/or any other suitable extinguishing material/means) to the electric motor fire zone 109 .
- the second outlet 123 can be configured to provide extinguishing medium to the heat engine fire zone 111 .
- the at least one fire extinguishing medium source 119 can include a single fluid source connected to both outlets 121 , 123 .
- the location of outlet 123 as depicted is an example embodiment and it is contemplate that the outlet 123 can be directed into any location that is designated as engine fire zone 111 .
- the electric motor fire zone 109 can be fluidly sealed from the heat motor fire zone 105 such that extinguishing medium can be used in either fire zone 109 , 111 independent of the other.
- the firewall 107 can include a metallic and/or composite baffle that surrounds the electric motor 101 or the heat engine 105 to form the electric motor fire zone 109 or the heat engine fire zone 111 , for example.
- the baffle can be configured to be bolted to a nacelle 113 , for example.
- Certain embodiments can include a ventilation pathway for each fire zone 109 , 111 for providing outside air to each fire zone 109 , 111 (e.g., such that the firewall 107 includes at least one fluid inlet and outlet, e.g., one or more holes in the baffle).
- the ventilation pathway can include a dedicated nacelle scoop 125 , 127 in fluid communication with each fire zone 109 , 111 , for example. Any other suitable arrangement is contemplated herein (e.g., one scoop split between both fire zones 109 , 111 .
- a lower extremity of the heat engine fire zone 111 can be defined by a fire floor within the nacelle 113 .
- the fire floor can be on a transverse, mostly horizontal plane (although it may be canted in certain embodiments) and located above the nacelle scoop 127 (e.g., engine inlet air scoop) but below the heat engine 105 . Any other suitable arrangement for a fire floor or any other barrier defining a fire zone 111 is contemplated herein.
- an aircraft can include at least one hybrid electric aircraft powerplant 100 as disclosed herein, e.g., as described above. Any suitable type of aircraft and/or any other suitable aircraft components are contemplated herein.
- Embodiments of a hybrid electric powerplant include two independent power lanes (one fuel and one electric), e.g., connected with a series of gearboxes. Each power lane is capable of producing some percentage of total thrust, for example. During an engine failure (e.g., such as a fire) in one power lane, it is likely that the other remaining power lane is still capable of producing thrust (possible reduced total thrust for the powerplant).
- Embodiments integrate a nacelle firewall 107 in such a way that fully segregates the two power lanes in addition to separating the engine compartment from the wing. This creates two independent engine compartments as far as a fire/failure is concerned.
- Embodiments can be applied to a turbomachine type heat engine hybrid powerplant (e.g., a turboprop hybrid), or any other suitable type of heat engine hybrid powerplant (e.g., turbofan hybrid).
- Embodiments can increase the range of the aircraft in a failure mode, possibly increasing the chances of finding a safe place to land.
- any numerical values disclosed herein can be exact values or can be values within a range. Further, any terms of approximation (e.g., “about”, “approximately”, “around”) used in this disclosure can mean the stated value within a range. For example, in certain embodiments, the range can be within (plus or minus) 20%, or within 10%, or within 5%, or within 2%, or within any other suitable percentage or number as appreciated by those having ordinary skill in the art (e.g., for known tolerance limits or error ranges).
- a reference to “A and/or B”, when used in conjunction with open-ended language such as “comprising” can refer, in one embodiment, to A only (optionally including elements other than B); in another embodiment, to B only (optionally including elements other than A); in yet another embodiment, to both A and B (optionally including other elements); etc.
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Abstract
Description
- This application is a divisional of U.S. patent application Ser. No. 17/110,180 filed Dec. 2, 2020, which claims priority to and the benefit of U.S. Provisional Application No. 62/943,027, filed Dec. 3, 2019, the entire contents of which are herein incorporated by reference.
- This disclosure relates to hybrid electric powerplants.
- A nacelle usually forms a firewall between an engine and the wing, engine mount pylon, or other aircraft structure not considered a fire zone. However, in a hybrid electric powerplant, traditional assemblies may not be acceptable for power lane redundancy and independence.
- Such conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is still a need in the art for firewall assemblies for hybrid electric aircraft powerplants. The present disclosure provides a solution for this need.
- A powerplant can include a first prime mover configured to turn a propulsor, and a second prime mover operatively connected in parallel with the first prime mover to turn the propulsor together with or separately from the first prime mover. The powerplant can include a firewall disposed around at least one of the first prime mover or the second prime mover to create a first prime mover fire zone and a second prime mover fire zone separate from the first prime mover fire zone such that the first prime mover is protected against a second prime mover fire, and vice versa. In embodiments, the powerplant can be or include a hybrid electric powerplant, where the first prime mover can include an electric motor configured to convert electrical energy into kinetic energy to turn the propulsor and the second prime mover can include a heat engine configured to convert a fuel into kinetic energy to turn the propulsor.
- The powerplant can further comprise a nacelle. The electric motor, the heat engine, and the firewall can be disposed within the nacelle. In certain embodiments, the nacelle can form at least a portion of the firewall.
- The firewall may be only an electric motor firewall that is disposed around the electric motor. In such cases, there may be no separate heat engine firewall surrounding the heat engine. All electric motor components within the nacelle can be contained within the firewall.
- Certain embodiments can include a fire extinguisher system comprising at least one fire extinguishing medium source and at least a first outlet and a second outlet. The first outlet can be configured to provide extinguishing medium to the electric motor fire zone. The second outlet can be configured to provide extinguishing medium to the heat engine fire zone.
- The electric motor fire zone can be fluidly sealed from the heat motor fire zone such that extinguishing medium can be used in either fire zone independent of the other. The firewall can include a metallic and/or composite baffle that surrounds the electric motor to form the electric motor fire zone. The baffle can be configured to be bolted to a nacelle.
- Certain embodiments can include a ventilation pathway for each fire zone for providing outside air to each fire zone. The ventilation pathway can include a dedicated nacelle scoop in fluid communication with each fire zone, for example.
- In accordance with at least one aspect of this disclosure, an aircraft can include at least one hybrid electric aircraft powerplant as disclosed herein, e.g., as described above. Any suitable type of aircraft and/or any other suitable aircraft components are contemplated herein.
- These and other features of the embodiments of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description taken in conjunction with the drawings.
- So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, embodiments thereof will be described in detail herein below with reference to certain figures, wherein:
-
FIG. 1 is a cross-sectional view of an embodiment of a powerplant in accordance with this disclosure; and -
FIG. 2 is a plan view of the embodiment ofFIG. 1 . - Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, an illustrative view of an embodiment of a powerplant in accordance with the disclosure is shown in
FIG. 1 and is designated generally byreference character 100. Other embodiments and/or aspects of this disclosure are shown inFIG. 2 . - Referring to
FIGS. 1 and 2 , a powerplant 100 (e.g., a hybrid electric powerplant) can include a first prime mover 101 (e.g., an electric motor) configured to convert electrical energy into kinetic energy to turn a propulsor 103 (e.g., a propeller as shown). Thepowerplant 100 can include a second prime mover 105 (e.g., a heat enine) configured to convert a fuel into kinetic energy to turn thepropulsor 103. In embodiments, the firstprime mover 101 and the secondprime mover 105 can be operatively connected in parallel to turn the propulsor together or independently. - The
powerplant 100 can include afirewall 107 disposed around at least one of theelectric motor 101 or theheat engine 105 to create an electricmotor fire zone 109 and a heatengine fire zone 111 separate from the electricmotor fire zone 109 such that theelectric motor 101 is protected against a heat engine fire, and vice versa. Thepowerplant 100 can further comprise anacelle 113. It is noted thatFIGS. 1 and 2 are not exhaustive of the possible embodiments and one having ordinary skill in the art would appreciate, in view of this disclosure, that theengine fire zone 111 can be coextensive in size with the area designated asheat engine 105, for example (e.g., such that theheat engine 105 has its own separate firewall within the nacelle 113). Any other suitable demarcation offire zones - The
electric motor 101, theheat engine 105, and thefirewall 107 can be disposed within thenacelle 113. In certain embodiments, thenacelle 113 can form at least a portion of the firewall 107 (e.g., such that at least a portion of thefirewall 107 is integral with the nacelle 113). For example, a wall of thefirewall 107 can be defined by an inside wall of thenacelle 113. - The
firewall 107 may be only anelectric motor firewall 107, e.g., as shown, that is disposed around theelectric motor 101. In such cases, e.g., as shown, there may be no separate heat engine firewall surrounding theheat engine 105. In certain embodiments, all electric motor components (e.g.,power cables 115 and/or any other suitable electric motor system components) within thenacelle 113 can be contained within thefirewall 107, e.g., as shown, or otherwise be fireproofed. Any other suitable arrangement is contemplated herein. - Certain embodiments can include a
fire extinguisher system 117, e.g., as shown inFIG. 1 . Theextinguisher system 117 can include at least one fire extinguishingmedium source 119 and at least afirst outlet 121 and a second outlet 123. Thefirst outlet 121 can be configured to provide extinguishing medium (e.g., extinguishing fluid and/or any other suitable extinguishing material/means) to the electricmotor fire zone 109. The second outlet 123 can be configured to provide extinguishing medium to the heatengine fire zone 111. In certain embodiments, the at least one fire extinguishingmedium source 119 can include a single fluid source connected to bothoutlets 121, 123. As appreciated by those having ordinary skill in the art, the location of outlet 123 as depicted is an example embodiment and it is contemplate that the outlet 123 can be directed into any location that is designated asengine fire zone 111. - The electric
motor fire zone 109 can be fluidly sealed from the heatmotor fire zone 105 such that extinguishing medium can be used in eitherfire zone firewall 107 can include a metallic and/or composite baffle that surrounds theelectric motor 101 or theheat engine 105 to form the electricmotor fire zone 109 or the heatengine fire zone 111, for example. The baffle can be configured to be bolted to anacelle 113, for example. - Certain embodiments can include a ventilation pathway for each
fire zone fire zone 109, 111 (e.g., such that thefirewall 107 includes at least one fluid inlet and outlet, e.g., one or more holes in the baffle). For example, the ventilation pathway can include adedicated nacelle scoop fire zone fire zones - In certain embodiments (e.g., in turboprop embodiments), a lower extremity of the heat
engine fire zone 111 can be defined by a fire floor within thenacelle 113. The fire floor can be on a transverse, mostly horizontal plane (although it may be canted in certain embodiments) and located above the nacelle scoop 127 (e.g., engine inlet air scoop) but below theheat engine 105. Any other suitable arrangement for a fire floor or any other barrier defining afire zone 111 is contemplated herein. - In accordance with at least one aspect of this disclosure, an aircraft can include at least one hybrid
electric aircraft powerplant 100 as disclosed herein, e.g., as described above. Any suitable type of aircraft and/or any other suitable aircraft components are contemplated herein. - Embodiments of a hybrid electric powerplant include two independent power lanes (one fuel and one electric), e.g., connected with a series of gearboxes. Each power lane is capable of producing some percentage of total thrust, for example. During an engine failure (e.g., such as a fire) in one power lane, it is likely that the other remaining power lane is still capable of producing thrust (possible reduced total thrust for the powerplant).
- Embodiments integrate a
nacelle firewall 107 in such a way that fully segregates the two power lanes in addition to separating the engine compartment from the wing. This creates two independent engine compartments as far as a fire/failure is concerned. Embodiments can be applied to a turbomachine type heat engine hybrid powerplant (e.g., a turboprop hybrid), or any other suitable type of heat engine hybrid powerplant (e.g., turbofan hybrid). - In the event of an engine failure, the typical procedure results in an engine being shut down and the pilot landing as soon as possible with less than all engines. This process is safer if the pilot only had to shut down, e.g., a “half” of a powerplant (e.g., since the other power lane can still operate in a fire failure of a first power lane). Embodiments can increase the range of the aircraft in a failure mode, possibly increasing the chances of finding a safe place to land.
- Those having ordinary skill in the art understand that any numerical values disclosed herein can be exact values or can be values within a range. Further, any terms of approximation (e.g., “about”, “approximately”, “around”) used in this disclosure can mean the stated value within a range. For example, in certain embodiments, the range can be within (plus or minus) 20%, or within 10%, or within 5%, or within 2%, or within any other suitable percentage or number as appreciated by those having ordinary skill in the art (e.g., for known tolerance limits or error ranges).
- The articles “a”, “an”, and “the” as used herein and in the appended claims are used herein to refer to one or to more than one (i.e., to at least one) of the grammatical object of the article unless the context clearly indicates otherwise. By way of example, “an element” means one element or more than one element.
- The phrase “and/or,” as used herein in the specification and in the claims, should be understood to mean “either or both” of the elements so conjoined, i.e., elements that are conjunctively present in some cases and disjunctively present in other cases. Multiple elements listed with “and/or” should be construed in the same fashion, i.e., “one or more” of the elements so conjoined. Other elements may optionally be present other than the elements specifically identified by the “and/or” clause, whether related or unrelated to those elements specifically identified. Thus, as a non-limiting example, a reference to “A and/or B”, when used in conjunction with open-ended language such as “comprising” can refer, in one embodiment, to A only (optionally including elements other than B); in another embodiment, to B only (optionally including elements other than A); in yet another embodiment, to both A and B (optionally including other elements); etc.
- As used herein in the specification and in the claims, “or” should be understood to have the same meaning as “and/or” as defined above. For example, when separating items in a list, “or” or “and/or” shall be interpreted as being inclusive, i.e., the inclusion of at least one, but also including more than one, of a number or list of elements, and, optionally, additional unlisted items. Only terms clearly indicated to the contrary, such as “only one of” or “exactly one of,” or, when used in the claims, “consisting of,” will refer to the inclusion of exactly one element of a number or list of elements. In general, the term “or” as used herein shall only be interpreted as indicating exclusive alternatives (i.e., “one or the other but not both”) when preceded by terms of exclusivity, such as “either,” “one of,” “only one of,” or “exactly one of.”
- Any suitable combination(s) of any disclosed embodiments and/or any suitable portion(s) thereof are contemplated herein as appreciated by those having ordinary skill in the art in view of this disclosure.
- The embodiments of the present disclosure, as described above and shown in the drawings, provide for improvement in the art to which they pertain. While the subject disclosure includes reference to certain embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the spirit and scope of the subject disclosure. cm What is claimed is:
Claims (15)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US18/120,280 US20230220803A1 (en) | 2019-12-03 | 2023-03-10 | Firewall assemblies for hybrid electric aircraft powerplants |
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Application Number | Priority Date | Filing Date | Title |
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US201962943027P | 2019-12-03 | 2019-12-03 | |
US17/110,180 US11603800B2 (en) | 2019-12-03 | 2020-12-02 | Firewall assemblies for hybrid electric aircraft powerplants |
US18/120,280 US20230220803A1 (en) | 2019-12-03 | 2023-03-10 | Firewall assemblies for hybrid electric aircraft powerplants |
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Application Number | Title | Priority Date | Filing Date |
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US17/110,180 Continuation US11603800B2 (en) | 2019-12-03 | 2020-12-02 | Firewall assemblies for hybrid electric aircraft powerplants |
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US20230220803A1 true US20230220803A1 (en) | 2023-07-13 |
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US17/110,180 Active 2041-09-08 US11603800B2 (en) | 2019-12-03 | 2020-12-02 | Firewall assemblies for hybrid electric aircraft powerplants |
US18/120,280 Pending US20230220803A1 (en) | 2019-12-03 | 2023-03-10 | Firewall assemblies for hybrid electric aircraft powerplants |
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US11065979B1 (en) | 2017-04-05 | 2021-07-20 | H55 Sa | Aircraft monitoring system and method for electric or hybrid aircrafts |
US10479223B2 (en) | 2018-01-25 | 2019-11-19 | H55 Sa | Construction and operation of electric or hybrid aircraft |
US11148819B2 (en) | 2019-01-23 | 2021-10-19 | H55 Sa | Battery module for electrically-driven aircraft |
US11063323B2 (en) | 2019-01-23 | 2021-07-13 | H55 Sa | Battery module for electrically-driven aircraft |
EP4086176A1 (en) | 2021-05-07 | 2022-11-09 | Airbus SAS | Electric propulsion unit of an aircraft comprising a cooling system incorporating at least one front air inlet and aircraft comprising at least one such electric propulsion unit |
US11691742B1 (en) * | 2022-02-04 | 2023-07-04 | Pratt & Whitney Canada Corp | Containment zone for an electric machine in a hybrid powerplant for an aircraft |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4177693A (en) * | 1978-06-22 | 1979-12-11 | Avco Corporation | Drive system |
US20160236767A1 (en) * | 2015-02-16 | 2016-08-18 | Airbus Helicopters Deutschland GmbH | Aircraft with a fuselage that defines at least an interior region and a drive system accommodating region |
US20180111469A1 (en) * | 2014-11-07 | 2018-04-26 | Obrist Technologies Gmbh | Hybrid vehicle and Generating set |
US20200115045A1 (en) * | 2018-09-28 | 2020-04-16 | Airbus Helicopters | Electrically or hybrid powered multirotor aircraft with optimized energy consumption |
US10633104B2 (en) * | 2017-05-17 | 2020-04-28 | General Electric Company | Hybrid-electric propulsion system for an aircraft |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5115996A (en) | 1990-01-31 | 1992-05-26 | Moller International, Inc. | Vtol aircraft |
US10408123B2 (en) * | 2015-02-20 | 2019-09-10 | Pratt & Whitney Canada Corp. | Engine assembly with modular compressor and turbine |
US10227137B2 (en) | 2016-03-22 | 2019-03-12 | Ge Aviation Systems Llc | Hybrid power system for an aircraft |
CA3109112A1 (en) * | 2020-02-14 | 2021-08-14 | Bombardier Inc. | Excess thrust control for an aircraft |
-
2020
- 2020-12-02 US US17/110,180 patent/US11603800B2/en active Active
- 2020-12-03 EP EP20211526.7A patent/EP3831718B1/en active Active
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Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4177693A (en) * | 1978-06-22 | 1979-12-11 | Avco Corporation | Drive system |
US20180111469A1 (en) * | 2014-11-07 | 2018-04-26 | Obrist Technologies Gmbh | Hybrid vehicle and Generating set |
US20160236767A1 (en) * | 2015-02-16 | 2016-08-18 | Airbus Helicopters Deutschland GmbH | Aircraft with a fuselage that defines at least an interior region and a drive system accommodating region |
US10427775B2 (en) * | 2015-02-16 | 2019-10-01 | Airbus Helicopters Deutschland GmbH | Aircraft with a fuselage that defines at least an interior region and a drive system accommodating region |
US10633104B2 (en) * | 2017-05-17 | 2020-04-28 | General Electric Company | Hybrid-electric propulsion system for an aircraft |
US20200115045A1 (en) * | 2018-09-28 | 2020-04-16 | Airbus Helicopters | Electrically or hybrid powered multirotor aircraft with optimized energy consumption |
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US20210163142A1 (en) | 2021-06-03 |
EP3831718A1 (en) | 2021-06-09 |
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