公开(公告)号：ES2709848T3

公开(公告)日：2019-04-17

申请号：ES14769728

申请日：2014-03-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NAGER ERIC ANDREW ,  NAPIER JAMES C ,  REHMAN FAROOQ ,  JONES ANTHONY C

IPC: F02K1/82 ,  B64D41/00 ,  F01D25/30 ,  F02C7/24 ,  F02C7/32 ,  F02K1/34

Abstract: Revestimiento (25) de escape para una APU (21) en un avión con motor de turbina de gas que tiene un cono de cola que termina con una salida (29) para descargar el escape, en el que el revestimiento comprende: una primera sección en el revestimiento (25) con una sección transversal constante que tiene un diámetro (D1) desde la APU (21) a un punto próximo al cono de la cola; caracterizado porque el revestimiento comprende además un segundo diámetro (D2) más grande en el revestimiento (25), en el que el revestimiento se ensancha al segundo diámetro D2 y tiene una sección transversal continuamente creciente desde el extremo aguas abajo de la primera sección a la salida del revestimiento (25).

公开(公告)号：EP2961971A4

公开(公告)日：2016-11-09

申请号：EP14756466

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NAPIER JAMES C ,  FRANCISCO JAY M

IPC: F02C9/18 ,  F02C9/16 ,  F04D27/02

CPC classification number: F02C9/18 ,  F04D27/0238 ,  F05D2260/96 ,  F05D2270/101

Abstract: An anti-surge mechanism has a duct for tapping compressed air and delivering that air into an exhaust flow. A selectively open valve allows the tapped air to flow into the exhaust flow through a plurality of holes. The holes are sized to tune a frequency of a sound created by the tapped air to a frequency range outside of normal human hearing. A gas turbine engine is also disclosed.

公开(公告)号：EP2971733A4

公开(公告)日：2016-04-20

申请号：EP14769728

申请日：2014-03-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NAGER ERIC ANDREW ,  NAPIER JAMES C ,  REHMAN FAROOQ ,  JONES ANTHONY C

IPC: F02K1/82 ,  B64D41/00 ,  F01D25/30 ,  F02C7/24 ,  F02C7/32 ,  F02K1/34

CPC classification number: B64D33/06 ,  B64D41/00 ,  B64D2041/002 ,  F01D25/30 ,  F02C7/24 ,  F02C7/32 ,  F05D2220/50 ,  F05D2260/96 ,  Y02T50/44

Abstract: An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

Abstract translation: 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部的点开始的第二增加的横截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。

公开(公告)号：EP2932069A4

公开(公告)日：2015-12-23

申请号：EP13862994

申请日：2013-12-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JEWESS GORDON F ,  SIRINIVASAN NAVINDARAN ,  MICHALIK MAREK ,  MCLAUGHLIN JAMES J ,  NAPIER JAMES C ,  KOWIEL KRZYSZTOF ,  MIASKIEWICZ AGATA

IPC: F01D25/16 ,  F01D25/04 ,  F02K1/04

CPC classification number: F01D25/162 ,  F01D25/04 ,  F02K1/04 ,  F05D2220/50

Abstract: A retainer for a gas turbine engine includes a center body, a plurality of struts, and a ring. The plurality of struts are connected to and extend outward from the center body. The ring is connected to the plurality of struts and is positioned aft of the center body with respect to a direction of airflow through the gas turbine engine.