公开(公告)号：US11686220B2

公开(公告)日：2023-06-27

申请号：US17700992

申请日：2022-03-22

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

IPC: F01D25/28 ,  F01D25/24 ,  F01D9/04

CPC classification number: F01D25/28 ,  F01D9/041 ,  F01D25/24 ,  F05D2240/126 ,  F05D2240/14 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of H-frame connecting members rigidly connected to the fan case, and to the core engine. The H-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions which are generally parallel to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

公开(公告)号：US20230151777A1

公开(公告)日：2023-05-18

申请号：US18098920

申请日：2023-01-19

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

IPC: F02K3/06 ,  F02C3/04

CPC classification number: F02K3/06 ,  F02C3/04 ,  F05D2260/96 ,  F05D2220/36 ,  F05D2240/12

Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine including a plurality of radial struts rigidly connected to the fan case, and to the core engine. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

公开(公告)号：US20230151742A1

公开(公告)日：2023-05-18

申请号：US17700992

申请日：2022-03-22

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

IPC: F01D25/28 ,  F01D25/24 ,  F01D9/04

CPC classification number: F01D25/28 ,  F01D25/24 ,  F01D9/041 ,  F05D2240/126 ,  F05D2240/14 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of H-frame connecting members rigidly connected to the fan case, and to the core engine. The H-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions which are generally parallel to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

公开(公告)号：US11608796B1

公开(公告)日：2023-03-21

申请号：US17701026

申请日：2022-03-22

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

IPC: F02C7/20 ,  F02K3/06 ,  F02C3/04

Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine including a plurality of radial struts rigidly connected to the fan case, and to the core engine. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

公开(公告)号：US11572800B2

公开(公告)日：2023-02-07

申请号：US17155876

申请日：2021-01-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco

IPC: F01D25/00 ,  B08B9/032 ,  B08B9/093

Abstract: A fluid wash system for a gas turbine engine is disclosed, the gas turbine engine defining an axial direction and comprising a borescope port that provides access to a component within a core flow path of the gas turbine engine. In various embodiments, the fluid wash system includes a wash line fluidly connected to a pump configured to provide a pressurized flow of wash liquid; a spray nozzle connected to the wash line and configured for extending into the borescope port to provide the pressurized flow of wash liquid to the component within the core flow path; and an attachment mechanism configured to releasable mount the spray nozzle to the borescope port, the attachment mechanism including an alignment mechanism configured to orient the spray nozzle and direct the pressurized flow of wash liquid in a predetermined direction toward the component.

公开(公告)号：US11555420B1

公开(公告)日：2023-01-17

申请号：US17407275

申请日：2021-08-20

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

IPC: F01D25/28 ,  F01D25/24 ,  F01D9/06

Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.