公开(公告)号：US10024238B2

公开(公告)日：2018-07-17

申请号：US14594663

申请日：2015-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

IPC: F02C7/18 ,  F02C6/08 ,  F01D25/08 ,  F01D25/12 ,  F01D9/06 ,  F01D5/18 ,  F01D5/08

Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

公开(公告)号：US20160327082A1

公开(公告)日：2016-11-10

申请号：US14706636

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Justin J. Phillips ,  Todd A. Davis

IPC: F16B33/00

CPC classification number: F16B33/004 ,  F01D11/005 ,  F01D25/243 ,  F05D2260/31

Abstract: Aspects of the disclosure are directed to an assembly associated with an engine of an aircraft, comprising a bolt comprising at least one groove, and at least one seal seated within the at least one groove, where the at least one seal is configured to seal radially against a counter bore that the bolt is coupled to. Aspects of the disclosure are directed to a bolt comprising a head, a first groove formed in a first side of the head and configured to seat a first seal, and an internal feature formed in the head and interfacing with a surface of the head, where the internal feature is configured to enable the bolt to be tightened.

Abstract translation: 本公开的方面涉及与飞机的发动机相关联的组件，包括至少一个凹槽的螺栓和位于至少一个凹槽内的至少一个密封件，其中所述至少一个密封件构造成径向地密封 抵靠螺栓连接的反向孔。 本公开的方面涉及一种螺栓，其包括头部，形成在头部的第一侧中并构造成安置第一密封件的第一凹槽以及形成在头部中并与头部表面相接合的内部特征， 内部功能被配置为使螺栓能够拧紧。

公开(公告)号：US20150285147A1

公开(公告)日：2015-10-08

申请号：US14594663

申请日：2015-01-12

Applicant: United Technologies Corporation

Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/221 ,  F05D2260/232 ,  Y02T50/671 ,  Y02T50/676

Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

Abstract translation: 公开了一种用于向燃气涡轮发动机的涡轮部分提供缓冲冷却的冷却空气的冷却系统。 冷却系统可以包括构造成将冷却空气朝向涡轮机部分传送的第一管道，被配置为冷却从第一管道转向以提供缓冲空气的排出气流的热交换器，以及配置成引导至少一部分 的缓冲空气通过绕过燃气涡轮发动机的轴承室的至少一个通道。 冷却系统还可以包括歧管，其配置成允许从第一导管排出的冷却空气和离开旁路导管的缓冲空气混合并提供缓冲冷却的冷却空气;以及喷嘴组件，其配置成将缓冲冷却的冷却空气输送到 涡轮段。