公开(公告)号：US10024183B2

公开(公告)日：2018-07-17

申请号：US14775388

申请日：2014-03-14

Applicant: United Technologies Corporation

Inventor： Julian Partyka ,  Jonathan P. Sandoval

IPC: F01D11/00 ,  F01D5/30 ,  F02C7/28 ,  F01D5/02

Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

公开(公告)号：US20160186666A1

公开(公告)日：2016-06-30

申请号：US14844097

申请日：2015-09-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Julian Partyka ,  David R. Pack ,  James D. Hill

IPC: F02C9/18 ,  F02C7/12

CPC classification number: F02C9/18 ,  F01D11/001 ,  F01D11/006 ,  F01D11/04 ,  F02C6/18 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20

Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.

Abstract translation: 用于燃气涡轮发动机的涡轮部分包括具有第一转子组件放气源的第一转子组件和与第一转子组件放气源流体连通的后腔。 第二转子组件包括前腔。 叶片放气源与前腔流体连通。 密封件在第一转子组件和第二转子组件之间延伸。

公开(公告)号：US20160017737A1

公开(公告)日：2016-01-21

申请号：US14775388

申请日：2014-03-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Julian Partyka

IPC: F01D11/00 ,  F01D5/30 ,  F01D5/12

CPC classification number: F01D11/001 ,  F01D5/027 ,  F01D5/3007 ,  F01D5/3015 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2250/73 ,  F05D2260/15 ,  Y02T50/673

Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

Abstract translation: 用于燃气涡轮发动机转子的盘密封装置包括其中具有纵向开口槽的叶片保持盘和与所述刀片保持盘并置的密封盘和容纳在刀片保持盘槽内的单个防旋转突出部。 密封盘还包括一对平衡槽，其紧邻防旋转翼片设置，以抵消其重量以保持转子平衡。 开口环纵向设置在叶片保持和密封盘之间，用于使它们之间的纵向载荷反应。 开口环的端部抵靠开口环和叶片保持和密封盘之间的防旋转侧面。

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。