CN103057716B - 飞行器中的多源电功率分配 - Google Patents

飞行器中的多源电功率分配 Download PDF

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CN103057716B
CN103057716B CN201210409472.3A CN201210409472A CN103057716B CN 103057716 B CN103057716 B CN 103057716B CN 201210409472 A CN201210409472 A CN 201210409472A CN 103057716 B CN103057716 B CN 103057716B
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power source
aircraft
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CN103057716A (zh
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A.希普利
V.B.邦诺
S.J.利纳克尔
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GE Aviation Systems Ltd
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • 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
    • B64D2221/00—Electric power distribution systems onboard aircraft
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2300/00—Systems for supplying or distributing electric power characterised by decentralized, dispersed, or local generation
    • H02J2300/30—The power source being a fuel cell
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
    • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
    • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
    • 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
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02B90/10—Applications of fuel cells in buildings

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Stand-By Power Supply Arrangements (AREA)
  • Supply And Distribution Of Alternating Current (AREA)
  • Fuel Cell (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

本发明涉及飞行器中的多源电功率分配。一种方法包括向飞行器提供电功率，其包括从多个功率源中选择性地获得功率，该功率源包括由发动机驱动的一个或多个发电机(2,3,4,5)，以及从包括一个或多个电存储装置(23,26)、一个或多个燃料电池(24,25)以及一个或多个热电功率源(22,27)的组中选择的至少一个其它的功率源。本文公开了相应的功率分配系统。

Description

飞行器中的多源电功率分配
技术领域
本发明涉及用于飞行器的电功率分配系统和向飞行器系统提供电功率的方法。
背景技术
传统上，为了向重要的和不重要的电负载提供电功率，飞行器依靠由推进式燃气涡轮发动机驱动的发电机，并且在某些情况下依靠辅助功率单元(APU)，其独立于发电机而产生功率。在这些系统故障的情况下，使用“冲压空气涡轮”(RAT)来维持给予重要的飞行器负载的功率。重要的飞行器负载包括航空电子系统(例如)以及任何其它的对飞行关键的设备。不重要的飞行器负载包括舱室照明、食物准备和娱乐系统(例如)以及其它对飞行并不关键的设备。RAT包括涡轮/推进器，其能够从飞行器的底架(under-carriage)可伸缩地释放，以便延伸到外部气流中以由此被驱动，并且因此驱动发电机。RAT效率低，因为几乎所有的时间，它们都没有被利用，它们还给飞行器增加了重量。另外，按年度执行在飞行器(on-board)上没有乘客的情况下的测试飞行要求对RAT进行功能性测试。RAT和APU两者是产生功率的低效率的方式，并且由于环境和成本的考虑，存在在任何可能的情况下减少航空燃料消耗的需要。
发明内容
本发明提供了一种向飞行器提供电功率的方法，其包括从多个功率源选择性地获得(source)功率，功率源包括由发动机驱动的一个或多个发电机以及从包括一个或多个电存储装置、一个或多个燃料电池以及一个或多个热电功率源的组中选择的至少一个其它的功率源。
另外，本发明提供了一种用于飞行器的电功率分配系统，其包括：多个不同的电功率源，其包括一个或多个由发动机驱动的发电机以及从包括一个或多个电存储装置、一个或多个燃料电池以及一个或多个热电功率源的组中选择的至少一个其它的功率源；以及电功率总线，借助于电功率总线，电功率源可连接到飞行器的负载，该系统具有可操作来从各个功率源中选择性地获得功率的控制器。
附图说明
参照附图，仅以示例的方式，下文有本发明的实施例的详细描述，其中：
图1为说明功率分配系统的实施例的结构的示意图；以及
图2示出了图1中示出的功率分配系统的备选实施例。
具体实施方式
图1示意性地示出了飞行器功率分配系统1，其包括彼此独立地由飞行器的发动机驱动的四个发电机2、3、4、5。大体上，使用的是每个发动机一个发电机。各个发电机2、3、4、5的输出连接到相应的局部高压功率总线8、9、10、11。发电机产生高压AC或DC电流，其需要被转换成用于操作飞行器的舱室和紧急功率系统的适当的水平。图1中和贯穿附图示出的一对相对的平行线32示意性地表示用于在系统的不同构件之间建立电气连接的开关。在优选的实施例中，对每个发电机提供了至少一根高压功率总线8、9、10、11，而不是一根高功率总线用于所有的发电机。以这种方式，因为系统不依赖于仅仅一根高功率总线，提供了更大的冗余度。高压功率总线各自连接到将电压降低到28V的转换装置12、13、14、15，并且转换装置被连接到局部低压功率总线16、17、18、19。再一次，通过为每个转换装置12、13、14、15提供一根低压功率总线实现更大的冗余度。从低压功率总线16到19，为了将功率分配到舱室各处以及为了操作紧急系统，电流传到一个或多个舱室和紧急功率总线20、21。功率分配系统1具有多个不同的功率源，其不仅包括发动机驱动的发电机2、3、4、5，而且还包括热电产生装置22、27，包括电池的电存储装置23、26以及燃料电池24、25中的至少一个。在另一方面中，燃料电池通过使用铝催化剂28、29生产的氢提供功率，铝催化剂28、29容许在飞行器（on-board）上从航空燃料生产氢。氢存储在氢存储容器30、31中。基于通过燃料的催化作用生产氢的速率来选择存储容量。
在以GE航空系统有限公司(GE Aviation System Ltd)的名义和具有申请参考249731/16389的共同未决的英国专利申请中示出和描述了热电产生装置，其公开通过参照结合在本文中。该功率源包括安装在发动机排气区段的一批热电偶，其利用否则将会被抛弃的废排气热。
如由参考标号6和7所示出的，RAT和APU已经被除去，因为不再需要它们。
在图2示出的实施例中，在没有热电产生装置的情况下，依赖于电池23、26和第一以及第二燃料电池24、25的组合。燃料电池24、25适合于大约3小时的操作或者飞行持续时间(无论哪一个更长)。通过提供一对燃料电池，确保了双重冗余(duel redundancy)，从而容许了对安全性很关键的功率性能，并且再次，不需要RAT和APU。电池23、26可用来在燃料电池起动期间提供补充(fill-in)功率。
由功率分配系统的控制器控制从功率源的适当的一个或多个来选择性地获得功率或协调功率。在正常的条件下，以任何期望的组合从燃料电池、电池和/或热电功率源中获得功率。在正常的条件下，可做出功率源的选择以便最大化功率分配系统的效率，即最小化燃料耗用。燃料电池在运转中产生水，其根据本发明的一个实施例可用在飞行器的厕所和洗手设施中。这相应地容许减少在起飞时携带的水的量。燃料电池和热电功率源因此在正常操作中是获得功率的优选的装置，使得在利用热电功率源的效率的同时可产生水。
可由各功率源产生的相对功率水平大概为：每个发动机驱动的发电机90-120kW，每个燃料电池15-30kW，每个电池15kW(大约½小时寿命)以及每个发动机70kW(通过热电废热产生)。
在紧急条件下，使功率离开不重要的负载转向重要负载。本文描述的功率分配系统可被改装到现有的飞行器，由此可除去RAT和APU。本发明还与其中保留RAT和APU中的一个或两者的飞行器兼容，在该情况下，功率分配系统将会提供高水平的冗余，并且由此提供安全性。

Claims (10)

1.一种向飞行器提供电功率的方法，包括从多个功率源选择性地获得功率，所述功率源包括由发动机驱动的一个或多个发电机，以及选自包括一个或多个电存储装置、一个或多个燃料电池以及一个或多个热电功率源的组的至少一个其它的功率源，并且其中在非紧急条件下，从各功率源选择性地获得功率以便最小化航空燃料的总消耗，且在紧急条件下，使功率离开不重要的负载转向重要的负载，且其中，同时从所述功率源中的两个或者更多个中获得功率。
2.根据权利要求1所述的方法，其特征在于，所述功率源还包括辅助功率单元。
3.根据权利要求1所述的方法，其特征在于，包括在非紧急条件下使用所述热电功率源作为主功率源。
4.根据权利要求1所述的方法，其特征在于，包括在非紧急条件下使用所述燃料电池作为主功率源。
5.根据上述权利要求中任一项所述的方法，其特征在于，在发动机驱动的所述发电机故障的情况下，使用所述至少一个其它的功率源的任何一个或多个。
6.根据权利要求1－4中任一项所述的方法，其特征在于，所述电存储装置包括电池。
7.根据权利要求1－4中任一项所述的方法，其特征在于，同时从所有的所述功率源获得功率。
8.根据权利要求1－4中任一项所述的方法，其特征在于，还包括在所述飞行器的舱室中使用由所述燃料电池产生的水。
9.一种用于飞行器的电功率分配系统，其包括：多个不同的电功率源，其包括一个或多个发动机驱动的发电机，以及选自包括一个或多个电存储装置、一个或多个燃料电池以及一个或多个热电功率源的组的至少一个其它的功率源；以及电功率总线，借助于所述电功率总线，所述电功率源能够连接到所述飞行器的负载，所述系统具有可操作来从所述功率源中的各个选择性地获得功率的控制器，并且其中所述控制器在非紧急条件下可操作来从各功率源选择性地获得功率以最小化航空燃料的总消耗，且在紧急条件下，功率离开不重要的负载转向重要的负载，且其中，所述控制器可操作来同时从所述功率源中的两个或更多个获得功率。
10.根据权利要求9所述的功率分配系统，其特征在于，所述热电功率源和/或所述燃料电池在非紧急条件下是主功率源。
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