公开(公告)号：US12116900B2

公开(公告)日：2024-10-15

申请号：US18105623

申请日：2023-02-03

Applicant: Raytheon Technologies Corporation

Inventor： Jorn A. Glahn ,  Gregory M. Dooley ,  Collin P. Fitzgerald

IPC: F01D25/16

CPC classification number: F01D25/16 ,  F05D2220/32 ,  F05D2240/54 ,  F05D2240/55

Abstract: An assembly is provided for a turbine engine. This assembly includes a rotating structure rotatable about an axis, a stationary structure and a bearing. The stationary structure forms a bearing compartment, a buffer cavity, a low pressure cavity and a high pressure cavity with the rotating structure. The buffer cavity surrounds the bearing compartment. The low pressure cavity surrounds the buffer cavity. The high pressure cavity surrounds the low pressure cavity. The bearing is within the bearing compartment. The bearing rotatably couples the rotating structure to the stationary structure.

公开(公告)号：US20240263567A1

公开(公告)日：2024-08-08

申请号：US18105623

申请日：2023-02-03

Applicant: Raytheon Technologies Corporation

Inventor： Jorn A. Glahn ,  Gregory M. Dooley ,  Collin P. Fitzgerald

IPC: F01D25/16

CPC classification number: F01D25/16 ,  F05D2220/32 ,  F05D2240/54 ,  F05D2240/55

Abstract: An assembly is provided for a turbine engine. This assembly includes a rotating structure rotatable about an axis, a stationary structure and a bearing. The stationary structure forms a bearing compartment, a buffer cavity, a low pressure cavity and a high pressure cavity with the rotating structure. The buffer cavity surrounds the bearing compartment. The low pressure cavity surrounds the buffer cavity. The high pressure cavity surrounds the low pressure cavity. The bearing is within the bearing compartment. The bearing rotatably couples the rotating structure to the stationary structure.

公开(公告)号：US20240209782A1

公开(公告)日：2024-06-27

申请号：US18086755

申请日：2022-12-22

Applicant: Raytheon Technologies Corporation

Inventor： Jorn A. Glahn

IPC: F02C7/18 ,  F02C3/06

CPC classification number: F02C7/18 ,  F02C3/06 ,  F05D2220/323 ,  F05D2260/201

Abstract: An electrically boosted cooling air system including a high pressure compressor; at least one cooling air supply line coupling the high pressure compressor with at least one of a high pressure turbine and a low pressure turbine; and an electrically powered fan fluidly coupled with the at least one cooling air supply line; wherein the electrically powered fan is configured to provide at least one of a pressure increase and a flow rate increase for cooling air supplied from the high pressure compressor.

公开(公告)号：US10794275B2

公开(公告)日：2020-10-06

申请号：US15794175

申请日：2017-10-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jorn A. Glahn ,  William K. Ackermann ,  Clifton J. Crawley ,  Philip S. Stripinis

IPC: F02C6/08 ,  F01D25/18 ,  F02C7/14 ,  F02C7/12

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.

公开(公告)号：US11905841B1

公开(公告)日：2024-02-20

申请号：US18105632

申请日：2023-02-03

Applicant: Raytheon Technologies Corporation

Inventor： Jorn A. Glahn ,  Collin P. Fitzgerald ,  Gregory M. Dooley

IPC: F01D25/22 ,  F01D25/16 ,  F02C7/06

CPC classification number: F01D25/22 ,  F01D25/16 ,  F02C7/06 ,  F05D2220/32

Abstract: A method of operation is provided during which buffer air flows into a buffer cavity in a turbine engine. The buffer cavity surrounds a bearing compartment in the turbine engine. Leakage air flows across a buffer seal device in the turbine engine. The buffer air and the leakage air are combined to provide combined air. The combined air is vented to a pressure sink such that: a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold during operation of the turbine engine; and a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold during the operation of the turbine engine.