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1. 发明专利

JP2009209932A System and method for passive cooling of gas turbine engine control component 审中-公开
标题翻译：气体涡轮发动机控制组件的被动冷却系统和方法
公开(公告)号：JP2009209932A
公开(公告)日：2009-09-17
申请号：JP2009041707
申请日：2009-02-25
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： DIAZ CARLOS , LABORIE DANIEL , LEIVA ORLY
IPC分类号： F02C7/18 , F01D25/12
CPC分类号： F01D25/12 , F02C7/12 , F05D2270/54 , H05K7/20136 , Y02T50/672 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a system and a method for cooling an engine control component for a gas turbine engine.
SOLUTION: This system for cooling a gas tube engine control component 60 include a control component, ducts 63 and 64 in fluid communication with the component and the atmosphere, and a valve assembly 67 arranged in the ducts and adjusting an air flow to the component. This method includes (a) a step of arranging a system for cooling the component including at least one duct in fluid communication with the component and the atmosphere and the valve assembly arranged in the ducts and adjusting the air flow to the component, (b) a step of placing the system under a first condition when requiring to cool the component, (c) a step of opening the valve assembly in response to the first condition, (d) a step of placing the system under a second condition when not requiring to cool the component, and (e) a step of closing the valve assembly in response to the second condition.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于冷却用于燃气涡轮发动机的发动机控制部件的系统和方法。解决方案：用于冷却气体管引擎控制部件60的系统包括控制部件，与部件和大气流体连通的管道63和64以及布置在管道中的阀组件67，并将空气流调节到组件。该方法包括以下步骤：（a）布置用于冷却组件的步骤，所述组件包括至少一个与组件和大气流体连通的管道和布置在管道中的阀组件并调节到组件的空气流量;（b）当要求冷却部件时将系统放置在第一状态的步骤，（c）响应于第一状态打开阀组件的步骤，（d）在不需要时将系统置于第二状态的步骤以冷却所述部件，以及（e）响应于所述第二状态来关闭所述阀组件的步骤。版权所有（C）2009，JPO＆INPIT

2. 发明专利

JP2011236894A Gas turbine engine airfoil integrated heat exchanger 有权
标题翻译：气体涡轮发动机气翼集成热交换器
公开(公告)号：JP2011236894A
公开(公告)日：2011-11-24
申请号：JP2011094558
申请日：2011-04-21
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KNIGHT III GLEN , LUKOVIC BOJAN , LABORIE DANIEL , SCHEFFEL KENNETH S
IPC分类号： F02C7/14
CPC分类号： F01D5/18 , F01D9/041 , F01D9/065 , F01D25/12 , F01D25/18 , F02K3/06 , F05D2260/20 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To provide an aerofoil structure of a gas turbine engine including an integral heat exchanger apparatus.SOLUTION: The heat exchanger apparatus includes: (a) an airfoil 42 having an opposed pressure side 54 and suction side 52, a root 50, a tip 48, and a spaced-apart leading edge 44 and a trailing edge 46; (b) a plenum integrally formed within the airfoil 42 which is configured to receive a flow of circulating working fluid; and (c) inlet and outlet ports communicating with the plenum and an exterior of the airfoil 42.
摘要翻译：要解决的问题：提供一种包括一体式热交换器装置的燃气涡轮发动机的机翼结构。解决方案：热交换器装置包括：（a）具有相对的压力侧54和吸力侧52，根部50，尖端48和间隔开的前缘44和后缘46的翼型件42; （b）整体形成在翼型件42内的增压室，其构造成容纳循环的工作流体流; （c）与通风室连通的入口和出口以及翼型42的外部。版权所有（C）2012，JPO＆INPIT

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