公开(公告)号：US20150090844A1

公开(公告)日：2015-04-02

申请号：US14496378

申请日：2014-09-25

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Ralf BRAEUTIGAM

IPC分类号： B64D33/02 ,  B64D27/02

CPC分类号： B64D33/02 ,  B64C27/04 ,  B64D27/02 ,  B64D2033/0253

摘要： A helicopter with a fuselage, at least two engines substantially inside said fuselage, an air intake for each of said two engines and at least two separate lateral air inlet ports for said at least two engines in said fuselage. Said separate lateral air inlet ports being arranged on sides opposed to each other relative to an essentially vertical midplane of said fuselage and oriented with their respective cross section substantially parallel to a forward flight direction of the helicopter. At least one frontal air inlet port with a forward portion is provided separate from said lateral air inlet ports, said frontal air inlet port being located on a gear cowling of the fuselage oriented with its cross section substantially perpendicular to the forward flight direction of the helicopter.

摘要翻译： 具有机身的直升机，基本上位于所述机身内的至少两个发动机，所述两个发动机中的每一个的进气口和用于所述机身中的所述至少两个发动机的至少两个分开的侧向进气口。 所述单独的横向进气口相对于所述机身的基本上垂直的中平面相对地设置，并且其各自横截面基本上平行于直升机的向前飞行方向定向。 具有前部的至少一个前部空气入口与所述侧向空气入口分开设置，所述正面空气入口位于机身的齿轮罩上，其定向成其横截面基本上垂直于直升机的前方飞行方向 。

公开(公告)号：US20160236767A1

公开(公告)日：2016-08-18

申请号：US15043758

申请日：2016-02-15

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Sebastian MORES ,  Frank LOESER ,  Johannes FRESE ,  Ralf BRAEUTIGAM ,  Christian WEHLE

IPC分类号： B64C1/40 ,  B64C27/82 ,  B64D33/04 ,  B64C1/16

CPC分类号： B64C1/40 ,  B64C1/10 ,  B64C1/16 ,  B64C27/82 ,  B64D33/04 ,  B64D33/08 ,  B64D41/00

摘要： An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

摘要翻译： 具有至少限定内部区域和驱动系统容纳区域的机身的飞行器，所述驱动系统容纳区域布置在所述机身内部，并且包括由至少一个相关联的防火墙布置限定的至少一个防火区域，所述防火墙装置 至少一个防火区域，其容纳至少一个相关联的防火墙装置内的至少一个发动机，使得所述相关联的防火墙装置限定所述至少一个发动机与所述机身的内部区域之间的耐火间隔，其中，所述至少一个相关联的防火墙装置 防火墙装置包括至少一个空气管道，用于在独立于至少一个发动机的发热的情况下运送在飞机运行中产生的热空气流。

公开(公告)号：US20150367945A1

公开(公告)日：2015-12-24

申请号：US14730367

申请日：2015-06-04

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Michael STADLER ,  Ralf BRAEUTIGAM

IPC分类号： B64D27/10 ,  B64D33/04 ,  F02C9/18 ,  B64D33/02

CPC分类号： B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0246 ,  F02C6/08 ,  F02C7/055 ,  F02C7/057 ,  F02C9/18 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/46 ,  F05D2270/65

摘要： An aircraft having at least one first and one second engine, each engine comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, said main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through said main air inlet opening into the engine, said by-pass air inlet opening being provided with a by-pass door that is operable by an associated operating element to enable a by-pass air stream through said by-pass air inlet opening into the engine, and said bleed air outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, at least one associated operating element being controllable by an outgoing bleed air stream.

摘要翻译： 一种具有至少一个第一和第二发动机的飞行器，每个发动机包括主空气入口开口，旁通空气入口和排气口，所述主空气入口开口设有入口阻挡过滤器，用于过滤主体 空气流通过所述主空气入口开口进入发动机，所述旁通空气入口开口设有旁路门，该旁路门可由相关联的操作元件操作，以允许旁路空气流通过所述旁路空气入口 并且所述放气口用于在运行时产生离开发动机的输出排出气流，至少一个相关联的操作元件可由输出的排气流控制。