公开(公告)号：US11549387B2

公开(公告)日：2023-01-10

申请号：US17688957

申请日：2022-03-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D5/06 ,  F01D25/16 ,  F01D25/24 ,  F01D9/06 ,  F02C6/08 ,  F01D25/08 ,  F04D29/32 ,  F02C7/36

Abstract: A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first bearing structure mounted to the front center body case structure, a bearing compartment passage structure in communication with the first bearing structure through the front center body case structure, and a turbine section.

公开(公告)号：US20210071576A1

公开(公告)日：2021-03-11

申请号：US16939462

申请日：2020-07-27

Applicant: Raytheon Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

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

Abstract: A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

公开(公告)号：US11560839B2

公开(公告)日：2023-01-24

申请号：US17469025

申请日：2021-09-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： William K. Ackermann ,  Peter M. Munsell

IPC: F02C6/08 ,  F01D25/12 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18

Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.

公开(公告)号：US11499476B2

公开(公告)日：2022-11-15

申请号：US16939462

申请日：2020-07-27

Applicant: Raytheon Technologies Corporation

Inventor： Peter M. Munsell ,  Philip S. Stripinis

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

Abstract: A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

公开(公告)号：US20220341341A1

公开(公告)日：2022-10-27

申请号：US17688957

申请日：2022-03-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D5/06 ,  F01D25/16 ,  F01D25/24 ,  F01D9/06 ,  F02C6/08 ,  F02C7/36 ,  F01D25/08 ,  F04D29/32

Abstract: A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first bearing structure mounted to the front center body case structure, a bearing compartment passage structure in communication with the first bearing structure through the front center body case structure, and a turbine section.

公开(公告)号：US11293299B2

公开(公告)日：2022-04-05

申请号：US17164908

申请日：2021-02-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D5/06 ,  F01D25/24 ,  F01D25/16 ,  F01D9/06 ,  F02C6/08 ,  F02C7/36 ,  F01D25/08 ,  F04D29/32

Abstract: A turbofan gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.

公开(公告)号：US20210396177A1

公开(公告)日：2021-12-23

申请号：US17469025

申请日：2021-09-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： William K. Ackermann ,  Peter M. Munsell

IPC: F02C6/08 ,  F01D25/12 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18

Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.

公开(公告)号：US20210310366A1

公开(公告)日：2021-10-07

申请号：US17164908

申请日：2021-02-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Peter M. Munsell ,  Philip S. Stripinis

IPC: F01D15/12 ,  F01D5/06 ,  F01D25/16 ,  F01D25/24 ,  F01D9/06 ,  F02C6/08 ,  F02C7/36 ,  F01D25/08 ,  F04D29/32

Abstract: A turbofan gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.