-
公开(公告)号：US20160214727A1
公开(公告)日：2016-07-28
申请号：US14969640
申请日：2015-12-15
Applicant: General Electric Company
Inventor： Jeffrey Anthony HAMEL , Kurt David MURROW
CPC classification number: B64D27/24 , B64C21/06 , B64D27/18 , B64D27/20 , B64D2027/026 , B64D2205/00 , Y02T50/166 , Y02T50/62 , Y10S903/905 , Y10S903/906 , Y10S903/907
Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
Abstract translation: 在一个方面，本主题涉及一种用于飞机的气电推进系统。 该系统可以包括涡轮风扇喷气发动机，耦合到涡轮风扇喷气发动机的飞机后部的机身部分的电动边界层摄入风扇，以及电动联接到涡轮风扇喷气发动机和边界的发电机 层摄取风扇。 发电机将来自涡轮风扇喷气发动机的旋转能量转换为电能，并将至少一部分电能提供给边界层摄取风扇。 在本主题的另一方面，公开了一种通过气电推进系统推进飞行器的方法。
-
公开(公告)号：US20170023018A1
公开(公告)日：2017-01-26
申请号：US14803862
申请日：2015-07-20
Applicant: General Electric Company
Inventor： Brandon Wayne MILLER , Jeffrey Anthony HAMEL
CPC classification number: F04D29/5846 , F01D5/081 , F02C7/14 , F02C7/141 , F02C7/16 , F04D19/02 , F04D29/324 , F04D29/541 , F05D2220/32 , F05D2260/212 , Y02T50/676
Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.
Abstract translation: 提供一种燃气涡轮发动机，其包括由一个或多个轴联接的压缩机部分和涡轮机部分。 压缩机部分逐渐地压缩空气并且包括能够围绕燃气涡轮发动机的轴向方向旋转的转子叶片的后段。 燃气涡轮发动机包括冷却系统，用于在压缩机部分内或从压缩机部分冷却压缩空气。 冷却系统包括用于存储大量冷却流体的流体箱和与流体罐流体连通的一个或多个流体管线。 一个或多个流体管线包括邻近转子叶片的后段定位的出口，用于将冷却流体喷射到靠近转子叶片后部的压缩空气中。
-
公开(公告)号：US20170022900A1
公开(公告)日：2017-01-26
申请号：US14803870
申请日：2015-07-20
Applicant: General Electric Company
Inventor： Brandon Wayne MILLER , Jeffrey Anthony HAMEL
CPC classification number: F02C7/16 , F01D5/081 , F01D9/065 , F01D25/12 , F02C3/10 , F02C3/30 , F02C7/14 , F05D2220/36 , F05D2260/212 , Y02T50/675
Abstract: A gas turbine engine including a compressor section, a turbine section, and a combustion section positioned between the compressor section and the turbine section is provided. The gas turbine engine also includes a cooling system having a tank and one or more fluid lines in fluid communication with the tank. The one or more fluid lines are configured to carry a flow of consumable cooling liquid provide such consumable cooling liquid to one or more components of the compressor section, the turbine section, and/or the combustion section not directly exposed to a core air flowpath defined through the gas turbine engine.
Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，涡轮部分和位于压缩机部分和涡轮部分之间的燃烧部分。 燃气涡轮发动机还包括具有罐和与罐流体连通的一个或多个流体管线的冷却系统。 一个或多个流体管线被构造成携带可消耗的冷却液体流，将这种可消耗的冷却液体提供给压缩机部分，涡轮部分和/或燃烧部分的一个或多个部件，其不直接暴露于限定的核心空气流动路径 通过燃气涡轮发动机。
-
-
Search Results
3
records
(took 0.013 seconds)
