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81. 发明公开

KR1020160058017A 연료 전지 시스템 및 에어 컴프레서의 회전수 제어 방법 审中-实审
标题翻译：用于控制空气压缩机转速的燃料电池系统和方法
公开(公告)号：KR1020160058017A
公开(公告)日：2016-05-24
申请号：KR1020150155682
申请日：2015-11-06
申请人： 도요타지도샤가부시키가이샤
发明人： 오다고헤이 , 우마야하라겐지
IPC分类号： H01M8/04
CPC分类号： F04D27/0261 , B60L1/003 , B60L11/1883 , F05B2260/821 , F05B2270/101 , F05B2270/1032 , F05B2270/335 , F05B2270/404 , F05D2260/821 , F05D2270/03 , F05D2270/304 , F05D2270/335 , F05D2270/44 , H01M8/04694 , H01M8/04753 , H01M2250/20 , Y02T90/32 , Y02T90/34
摘要： 에어컴프레서의회전수가오버슈트하는것을억제한다. 연료전지시스템은, 연료전지차량에구비된연료전지에산화제가스를공급하기위한에어컴프레서와, 에어컴프레서의회전수의측정값을취득하는회전수측정값취득부와, 상기연료전지에대한요구전력에기초하여상기에어컴프레서의회전수지령값을산출하고, 상기산출된회전수지령값과상기에어컴프레서의현재의회전수에기초하여상기에어컴프레서의토크지령값을산출하고, 상기산출된토크지령값에기초하여상기에어컴프레서의회전수를제어하는제어부를구비한다. 제어부는, 상기취득한상기회전수의측정값과, 상기산출된토크지령값의이력에기초하여, 상기에어컴프레서의현재의회전수를예측하고, 상기예측된회전수를사용하여토크지령값을산출한다.
摘要翻译：本发明的目的是抑制空气压缩机转速的过冲。燃料电池系统包括：向设置在燃料电池车辆中的燃料电池供应氧化剂气体的空气压缩机; 旋转速度测量值获取单元获取空气压缩机的转速的测量值; 以及控制单元，基于相对于燃料电池的所需功率来计算空气压缩机的转速指令值，基于计算出的转速指令值和当前的空气转速来计算空气压缩机的转矩指令值压缩机，并且基于计算的转矩指令值来控制空气压缩机的转速。控制单元基于所获取的旋转速度的测量值和计算出的转矩指令值的历史来预测空气压缩机的当前转速，并通过使用预测转速来计算转矩指令值。

82. 发明公开

KR1020130090850A 적어도 하나의 터빈 엔진이 제공된 항공기의 터빈 엔진의 건강 검사를 수행하기 위한 방법 및 장치 有权
标题翻译：用于对至少一台涡轮发动机提供的飞机的涡轮发动机的健康进行检查的方法和装置
公开(公告)号：KR1020130090850A
公开(公告)日：2013-08-14
申请号：KR1020130013619
申请日：2013-02-06
申请人： 에어버스 헬리콥터스
发明人： 까미,엠마뉘엘 , 볼췌괘도
IPC分类号： G01M15/14 , B64F5/00
CPC分类号： F02C7/00 , F02C9/00 , F05D2220/329 , F05D2260/80 , F05D2260/821 , F05D2270/303 , F05D2270/304 , F05D2270/332 , F05D2270/335 , F05D2270/803 , G05B23/0221
摘要： PURPOSE: A method and apparatus for inspecting the health of at least one turbine engine in an aircraft are provided to establish a stability reference for not manually but automatically implementing health inspection. CONSTITUTION: A method for automatically inspecting the health of at least one turbine engine in an aircraft includes: a step (STP3) of obtaining at least one monitoring parameter for the turbine engine; and a step (STP4) of evaluating the health of the turbine engine. The method determines whether or not the aircraft flies in a level forward direction. A method for verifying the stability of the monitoring parameter includes: a step of obtaining at least one measuring signal from one of the monitoring parameters due to sampling regulated by a manufacturer; a step of implementing a first filtering for each signal with a high-pass filter for a long first duration, and then verifying whether or not a first amplitude of the filtered signal excesses a first critical value regulated by the manufacturer; and a step of implementing a second filtering for each signal with the high-pass filter for a second duration shorter than the first duration together with the first filtering by the high-pass filter, and then verifying whether or not a second amplitude of the filtered signal smaller than the first amplitude excesses a second critical value regulated by the manufacturer.
摘要翻译：目的：提供一种用于检查飞行器中的至少一个涡轮发动机的健康状况的方法和装置，以建立不是手动的，而是自动执行健康检查的稳定性参考。构成：用于自动检查飞行器中的至少一个涡轮发动机的健康状况的方法包括：获得涡轮发动机的至少一个监测参数的步骤（STP3）; 以及评估涡轮发动机健康的步骤（STP4）。该方法确定飞机是否在向前的方向飞行。一种用于验证监测参数的稳定性的方法包括：由于由制造商监管的采样而从监测参数之一获得至少一个测量信号的步骤; 对具有高通滤波器的每个信号实施第一滤波处理长时间的步骤，然后验证滤波信号的第一幅度是否超过由制造商调节的第一临界值; 以及对于具有高通滤波器的每个信号的第二滤波器，与第一持续时间短于第一持续时间的第二滤波以及由高通滤波器进行的第一滤波，然后验证滤波后的第二幅度小于第一幅度的信号超过制造商调节的第二临界值。

83. 发明授权

KR101829568B1 다축 컴바인드 사이클 플랜트, 그 제어 장치, 및 그 운전 방법 有权
标题翻译：多轴联合循环设备，其控制装置及其操作方法
公开(公告)号：KR101829568B1
公开(公告)日：2018-02-14
申请号：KR1020167026436
申请日：2015-03-26
申请人： 미츠비시 히타치 파워 시스템즈 가부시키가이샤 , 미츠비시 히타치 파워 시스템스 유럽 리미티드
发明人： 마츠모토가즈나리 , 스즈키줌페이 , 루비오엘비오 , 라티아파블로 , 다니엘카를로스모라
IPC分类号： F01K23/10 , F02C9/42 , F02C9/28
CPC分类号： F01K23/101 , F01D25/10 , F01K7/16 , F01K7/165 , F01K11/02 , F01K13/02 , F02C6/18 , F02C9/28 , F02C9/42 , F05D2220/31 , F05D2220/32 , F05D2220/72 , F05D2260/82 , F05D2260/821 , F05D2260/85 , F05D2270/114 , Y02E20/16
摘要： 다축컴바인드사이클플랜트의운전방법에서는, 가스터빈의출력조절만으로다축컴바인드사이클플랜트의출력을조절하는저부하모드와, 가스터빈의출력조절및 증기터빈의출력조절로다축컴바인드사이클플랜트의출력을조절할수 있는고부하모드를요구부하에따라서전환한다(S15). 저부하모드에서는, 증기터빈이사전결정되어있는최초부하를유지할수 있는대기유량의증기를증기터빈에공급하여, 증기터빈에최초부하를가한다(S21 내지 23).
摘要翻译：多轴keombain德操作循环电厂中，低负载模式用于控制多轴keombain解循环与燃气涡轮机的只输出控制和循环设备的多轴线keombain DE输出与燃气涡轮机的输出控制和蒸汽涡轮机的输出控制设备的输出的方法（S15）。在低负载模式中，蒸汽涡轮机被提供给空气的蒸汽流率，可以保持第一负载，这是现有的蒸汽涡轮机来确定，所述蒸汽涡轮机进所述第一负载（S21〜23）。

84. 发明公开

KR1020170136622A 센서를 사용하지 않고 압력 검출 정확도를 증가시키는 방법 审中-实审
标题翻译：如何在不使用传感器的情况下提高压力检测精度
公开(公告)号：KR1020170136622A
公开(公告)日：2017-12-11
申请号：KR1020177032809
申请日：2016-04-25
申请人： 콘티넨탈 오토모티브 게엠베하
发明人： 비헨트게라드
IPC分类号： F02D41/30 , F02M37/08 , F04B49/06 , F04D15/00
CPC分类号： B60K15/077 , B60K2015/03243 , F02D41/3082 , F02M37/08 , F04B49/065 , F04B2203/0201 , F04B2203/0209 , F04B2205/05 , F04D15/0088 , F05D2260/821 , F05D2270/304 , F05D2270/335
摘要： 본발명은, 작동가능한전기모터및 상기전기모터에의해구동될수 있는유체공급펌프를포함하는, 자동차의유체전달시스템내의압력값을결정하는방법으로서, - 상기전기모터의회전속력을결정하는단계; - 상기전기모터의작동전류를결정하는단계; - 상기전기모터의상기회전속력및 상기작동전류의함수로서압력값을획득하는단계; - 상기획득된압력값을제어유닛에서적어도하나의외부상태변수로처리하는단계; 및 - 상기획득된압력값을보정하는단계를포함하는, 상기유체전달시스템내의압력값을결정하는방법에관한것이다.
摘要翻译：本发明涉及一种用于确定汽车的流体输送系统中的压力值的方法，该方法包括：可致动的电动机和可由电动机驱动的流体供给泵，所述方法包括以下步骤： - 确定电动机的工作电流; - 获得作为所述电动机修整机会全速和所述工作电流的函数的压力值; - 将所获得的压力值作为控制单元中的至少一个外部状态变量进行处理; 并且 - 校准获得的压力值。[0002]

85. 发明授权

KR101451950B1 항공기 성능의 최적화 방법, 장치, 및 항공기 有权
标题翻译：优化飞机，设备和飞机性能的方法
公开(公告)号：KR101451950B1
公开(公告)日：2014-10-16
申请号：KR1020130013617
申请日：2013-02-06
申请人： 에어버스 헬리콥터스
发明人： 에브라트,장-필리프 , 코프론,알반
IPC分类号： B64F5/00 , F02C9/28 , B64D27/10 , F02C6/20
CPC分类号： G01M15/14 , B64C27/04 , F02C9/00 , F05D2220/329 , F05D2260/80 , F05D2260/821 , F05D2270/303 , F05D2270/304 , F05D2270/332 , F05D2270/335 , F05D2270/803 , Y02T50/671
摘要： 본 발명은 적어도 하나의 터빈을 포함하는 터빈 조립체와, 가스 발생기를 구비한 적어도 하나의 터빈 엔진을 가지는 회전익 항공기의 성능을 최적화하는 방법에 관한 것이다. 규정 단계에서는, 항공기에 관한 제 1 성능 레벨 및 제 2 성능 레벨이 규정된다. 건강 검사 단계(STP2) 동안에는, 상기 가스 발생기의 회전 속도의 함수로서 제 1 파워 마진이 결정되고, 상기 터빈 조립체의 온도의 함수로서 제 2 파워 마진이 결정된다. 평가 단계(STP3) 동안에는, 목표 성능 레벨이 제 1 성능 레벨 또는 제 2 성능 레벨과 같은지를 결정하기 위해, 각각의 파워 마진이 제 1 임계치와 비교된다. 표시 단계(STP4) 동안에는, 목표 성능 레벨이 표시된다.

86. 发明授权

KR101839188B1 연료 전지 시스템 및 에어 컴프레서의 회전수 제어 방법 有权
标题翻译：用于控制燃料电池系统和空气压缩机的转数的方法
公开(公告)号：KR101839188B1
公开(公告)日：2018-03-15
申请号：KR1020150155682
申请日：2015-11-06
申请人： 도요타지도샤가부시키가이샤
发明人： 오다고헤이 , 우마야하라겐지
IPC分类号： H01M8/04
CPC分类号： F04D27/0261 , B60L1/003 , B60L11/1883 , F05B2260/821 , F05B2270/101 , F05B2270/1032 , F05B2270/335 , F05B2270/404 , F05D2260/821 , F05D2270/03 , F05D2270/304 , F05D2270/335 , F05D2270/44 , H01M8/04694 , H01M8/04753 , H01M2250/20 , Y02T90/32 , Y02T90/34
摘要： 에어컴프레서의회전수가오버슈트하는것을억제한다. 연료전지시스템은, 연료전지차량에구비된연료전지에산화제가스를공급하기위한에어컴프레서와, 에어컴프레서의회전수의측정값을취득하는회전수측정값취득부와, 상기연료전지에대한요구전력에기초하여상기에어컴프레서의회전수지령값을산출하고, 상기산출된회전수지령값과상기에어컴프레서의현재의회전수에기초하여상기에어컴프레서의토크지령값을산출하고, 상기산출된토크지령값에기초하여상기에어컴프레서의회전수를제어하는제어부를구비한다. 제어부는, 상기취득한상기회전수의측정값과, 상기산출된토크지령값의이력에기초하여, 상기에어컴프레서의현재의회전수를예측하고, 상기예측된회전수를사용하여토크지령값을산출한다.
摘要翻译：由此抑制空气压缩机的转数的过冲。该燃料电池系统包括：空气压缩机，用于向设置在燃料电池车辆中的燃料电池供应氧化剂气体;转速测量值获取单元，用于获取空气压缩机的总数的测量值; 基于计算出的转矩指令值，基于计算出的转矩指令值，基于计算出的转速指令值和空气压缩机的当前的总转数来计算空气压缩机的转矩指令值，以及用于控制空气压缩机的总转数的控制单元。控制单元，的基础上所获得的测量值的转数和所计算出的转矩指令值的历史，并且计算与所述空气压缩机的预测的预测国会转移和当前的旋转数下的转矩指令值。

87. 发明公开

KR1020130090849A 적어도 하나의 터빈 엔진을 가지는 항공기의 터빈 엔진의 건강 검사를 수행하기 위한 방법 및 장치 有权
标题翻译：一种用于执行具有至少一个这种发动机的飞机的涡轮发动机的健康检查的方法和装置
公开(公告)号：KR1020130090849A
公开(公告)日：2013-08-14
申请号：KR1020130013618
申请日：2013-02-06
申请人： 에어버스 헬리콥터스
发明人： 까미,엠마뉘엘
IPC分类号： G01M15/14 , B64F5/00
CPC分类号： G06F17/00 , F02C9/00 , F05D2220/329 , F05D2260/80 , F05D2260/821 , F05D2270/303 , F05D2270/304 , F05D2270/332 , F05D2270/335 , F05D2270/803 , G05B23/0283 , G07C5/0816
摘要： PURPOSE: A method and apparatus for inspecting the health of at least one turbine engine in an aircraft are provided to optimize health inspection for the turbine engine of the rotary wing aircraft and to easily track the health inspection. CONSTITUTION: A method for inspecting the health of at least one turbine having a gas generator and a turbine assembly having at least one turine in order to monitor an air craft having a rotary wing (300) includes: an obtaining step (STP1) for health inspection of stabilizing the aircraft, and obtaining the monitoring value of at least one monitoring parameter for the turbine engine; and an evaluating step (STP2) for the health inspection of determining at least one operation margin for the turbine engine with comparing the monitoring value with a limit value regulated by a manufacturer. In a generation step (STP0) before the obtaining step and the evaluating step, an effect in mounting the turbine engine in the aircraft is evaluated by multiple test values for the reduced rotational velocity of the gas generator. The reduced rotational velocity is identical to the reduced rotational velocity of the gas generator adjusted by external temperature at the periphery of the aircraft. The test values are in a range from a minimum test value to a maximum test value.
摘要翻译：目的：提供一种用于检查飞行器中的至少一个涡轮发动机的健康状况的方法和装置，以优化用于旋翼飞机的涡轮发动机的健康检查并且容易地跟踪健康检查。构成：用于检查具有气体发生器的至少一个涡轮机的健康状况的方法和具有至少一个机架的涡轮机组件，以便监测具有旋翼（300）的飞行器的方法包括：用于健康的获得步骤（STP1）检查飞机的稳定性，并获得涡轮发动机的至少一个监测参数的监测值; 以及用于通过将监测值与由制造商调节的限制值进行比较来确定涡轮发动机的至少一个操作余量的健康检查的评估步骤（STP2）。在获取步骤和评估步骤之前的生成步骤（STP0）中，通过用于气体发生器的降低的旋转速度的多个测试值来评估在涡轮机中安装涡轮发动机的效果。降低的转速与由飞机外围的外部温度调节的气体发生器的旋转速度降低相同。测试值在从最小测试值到最大测试值的范围内。

88. 发明公开

KR1020130090848A 항공기 성능의 최적화 방법, 장치, 및 항공기 有权
标题翻译：优化飞机，设备和飞机性能的方法
公开(公告)号：KR1020130090848A
公开(公告)日：2013-08-14
申请号：KR1020130013617
申请日：2013-02-06
申请人： 에어버스 헬리콥터스
发明人： 에브라트,장-필리프 , 코프론,알반
IPC分类号： B64F5/00 , F02C9/28 , B64D27/10 , F02C6/20
CPC分类号： G01M15/14 , B64C27/04 , F02C9/00 , F05D2220/329 , F05D2260/80 , F05D2260/821 , F05D2270/303 , F05D2270/304 , F05D2270/332 , F05D2270/335 , F05D2270/803 , Y02T50/671
摘要： PURPOSE: An apparatus, method and aircraft for optimizing the performance of the aircraft are provided to optimize vehicle performance by health check of a turbine engine in order to maximize power margin. CONSTITUTION: A method for optimizing performance of an aircraft comprises following steps. Each turbine engine (2) comprises a gas generator (2') and a turbine assembly with one or more turbines (2", 2"'), and manufacturers determine the first minimum performance level and the second maximum performance level of an aircraft (1). Current power transferred to each turbo engine (2) is determined during a health check step. Current temperature and rotary speed of gas are measured in the turbine assembly. The first power margin is determined to ensure the first performance level at the current rotary speed. The health check for each turbine engine is performed by determining a second power margin and second minimum power in order to ensure the first performance level.
摘要翻译：目的：提供一种用于优化飞机性能的装置，方法和飞机，以通过涡轮发动机的健康检查来优化车辆性能，以最大化功率余量。构成：优化飞机性能的方法包括以下步骤。每个涡轮发动机（2）包括气体发生器（2'）和具有一个或多个涡轮机（2“，2”'）的涡轮机组件，制造商确定飞机的第一最低性能水平和第二最大性能水平（ 1）。在健康检查步骤期间确定传送到每个涡轮发动机（2）的当前功率。在涡轮组件中测量气体的当前温度和转速。确定第一功率余量以确保当前转速下的第一性能水平。通过确定第二功率裕度和第二最小功率来执行每个涡轮发动机的健康检查，以确保第一性能水平。

89. 发明申请

US20180258785A1 Adaptive Active Clearance Control Logic 有权
公开(公告)号：US20180258785A1
公开(公告)日：2018-09-13
申请号：US15454581
申请日：2017-03-09
申请人： General Electric Company
发明人： Timothy Leo Schelfaut
IPC分类号： F01D11/20 , F01D5/12 , B64D27/10
CPC分类号： B64D27/10 , F01D11/24 , F05D2260/81 , F05D2260/821 , F05D2270/707 , F05D2270/708 , F05D2270/709 , F05D2270/71
摘要： Systems and methods for adjusting blade tip clearance targets and utilizing the adjusted targets to optimize the clearances between the blade tips and surrounding shrouds of a turbine engine are provided. In one exemplary aspect, one or more engine controllers utilize a machine-learned model to customize blade tip clearance targets based on the way an engine has been uniquely operated in the past for a particular flight mission. Present flight data associated with a present flight of a given flight mission is obtained. A model blade tip clearance target is adjusted based at least in part on the machine-learned model and the present flight data. The machine-learned model is trained at least in part on past flight data indicative of the manner in which the turbine engine has been operated for one or more past flights of the flight mission. An adjusted blade tip clearance target is then generated.

90. 发明授权

US09976552B2 Performance prediction device and performance prediction method for compressor 有权
公开(公告)号：US09976552B2
公开(公告)日：2018-05-22
申请号：US15134800
申请日：2016-04-21
申请人： HITACHI, LTD.
发明人： Manabu Yagi , Hideo Nishida , Haruo Miura , Kazutoshi Yanagihara
IPC分类号： F04B51/00 , F04D15/00 , F04D27/00
CPC分类号： F04B51/00 , F04D15/0044 , F04D27/001 , F05D2260/821
摘要： A performance prediction device includes: an actual measured data obtaining unit that obtains actual measured data of a compressor; a test gas physical property correction formula database in which test gas physical property correction formulae are stored; a test parameter calculation unit that calculates test parameters of the compressor; and a test parameter correction unit that selects at least one of the test gas physical property correction formulae from the test gas physical property correction formula database based on types and a mix ratio of gases included in a test gas to be used in the prediction and corrects the test parameters by using the selected test gas physical property correction formula.

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