公开(公告)号：US20140174055A1

公开(公告)日：2014-06-26

申请号：US14102764

申请日：2013-12-11

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02C9/18 ,  F01D1/02 ,  F01D5/02 ,  F01D9/041 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C3/113 ,  F02C7/20 ,  F02C7/36 ,  F02K3/025 ,  F02K3/06 ,  F02K3/075 ,  F02K7/06 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/606 ,  Y02T50/671

Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

Abstract translation: 涡轮风扇发动机被公开并且包括与风扇部分连通的风扇和压缩机，燃烧器，涡轮机和联接到风扇并由涡轮机旋转的减速机构。 涡轮机包括包括三级或更多级的第一涡轮机部分和包括至少两级的第二涡轮部分。 第一涡轮部分中的翼型件与旁路区域的比例小于约170。

公开(公告)号：US20140119903A1

公开(公告)日：2014-05-01

申请号：US13662802

申请日：2012-10-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler

IPC: F01D25/08

CPC classification number: F01D25/08 ,  F02C7/052 ,  Y02T50/675

Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.

Abstract translation: 燃气涡轮发动机包括在入口端处的鼻锥体，并且在机舱的径向内侧间隔开。 压缩机在鼻锥的下游。 核心入口将鼻锥下游的空气输送到压缩机中。 入口颗粒分离器包括用于沿核心入口径向向外输送空气的歧管。 通过入口颗粒分离器输送的空气在通过出口之前通过热交换器。