公开(公告)号：EP2855272A4

公开(公告)日：2016-01-20

申请号：EP13796593

申请日：2013-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PEEL JASON ,  VITALE JACK V ,  GIDDINGS GREG R

IPC: B64D41/00 ,  A62C2/06 ,  B64C1/40 ,  F02C7/25

CPC classification number: B64D41/00 ,  B64D2041/002

Abstract: An auxiliary power unit has a gas turbine engine, a generator, and a gear box. A mount bracket is mechanically attached to the gear box. The bracket is for connecting to a plurality of struts. The struts are for connecting to an aircraft housing. A shield box is formed of a flame resistant rigid material. The shield box encloses the mount bracket to provide flame protection to the mechanical attachment.

公开(公告)号：EP2946088A4

公开(公告)日：2016-01-20

申请号：EP13871803

申请日：2013-01-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WONG CHUNG ,  VITALE JACK V ,  OSORIO OMAR I ,  CHEN DAIH-YEOU

IPC: F02C1/00 ,  F01D25/14 ,  F02C6/00 ,  F02C7/228 ,  F02C7/25

CPC classification number: F02C7/25 ,  F01D25/145 ,  F02C7/22 ,  F05D2220/50 ,  F05D2230/54 ,  F05D2240/15 ,  F05D2250/231 ,  F05D2250/37 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/675 ,  Y10T29/49828

Abstract: A gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an engine case, a multiple of fuel injectors mounted to the engine case, and a fire shield mounted to the engine case to surround at least one, but less than all, of the multiple of fuel injectors. In a further embodiment of the foregoing embodiment, the fire shield includes a sheet metal alloy layer. In the alternative or additionally thereto, in the foregoing embodiment the fire shield includes a composite cloth on an interior of the sheet metal alloy layer with respect to the engine case.

Abstract translation: 根据本公开的一个公开的非限制性实施例的燃气涡轮发动机包括发动机壳体，安装到发动机壳体上的多个燃料喷射器，以及安装到发动机壳体上的防火罩，以围绕至少一个但小于 全部是燃油喷射器的数量。 在上述实施例的另一实施例中，防火罩包括金属板合金层。 在替代或附加地，在前述实施例中，防火罩包括相对于发动机壳体在金属板合金层内部的复合布。

公开(公告)号：EP3055220A4

公开(公告)日：2017-06-14

申请号：EP14853060

申请日：2014-10-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BELL MELISSA A ,  ROLLINS MICHAEL J ,  HAGSHENAS BEHZAD ,  VITALE JACK V

IPC: B64D41/00 ,  B64D33/02

CPC classification number: B64D33/02 ,  B64D15/16 ,  B64D41/00 ,  B64D2033/0206 ,  B64D2033/0213 ,  B64D2033/0233 ,  F02C7/045 ,  F02C7/05 ,  F02C7/057

Abstract: An auxiliary power unit for an aircraft includes a turbine engine. An inlet includes an opening and a passageway between the opening and the turbine engine. An acoustic aplitter is supported within the passageway for attenuating noise within the inlet. An inlet door is movable between a closed position and a fully open position. A portion of the inlet door aligns with a part of the passageway in at least a first position and divides the passageway to deflect ice and noise in at least a second position. An air inlet and a method are also disclosed.

Abstract translation: 飞机的辅助动力装置包括涡轮发动机。 入口包括开口和开口与涡轮发动机之间的通道。 通道内支撑有声学分切器，用于衰减入口内的噪声。 入口门可在关闭位置和完全打开位置之间移动。 入口门的一部分在至少第一位置处与通道的一部分对齐，并且分隔通道以在至少第二位置偏转冰和噪音。 还公开了一种进气口和一种方法。