公开(公告)号：US20240287935A1

公开(公告)日：2024-08-29

申请号：US18175918

申请日：2023-02-28

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco

IPC: F02C7/18 ,  F01D21/06

CPC classification number: F02C7/18 ,  F01D21/06 ,  F05D2240/14 ,  F05D2260/221 ,  F05D2260/42 ,  F05D2260/605

Abstract: A core section and nacelle assembly of a gas turbine engine includes a compressor located at an engine central longitudinal axis, a core case enclosing the compressor, and a nacelle located radially outboard of the core case and defining a core compartment between the nacelle and the core case. One or more vent openings are located in the nacelle to circulate a cooling airflow through the core compartment, and one or more fans are positioned at the one or more vent openings to urge the cooling airflow through the one or more vent openings to cool the core compartment.

公开(公告)号：US11927106B2

公开(公告)日：2024-03-12

申请号：US18088196

申请日：2022-12-23

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco ,  David A. Topol

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

CPC classification number: F01D25/28 ,  F01D9/06 ,  F01D25/24 ,  F05D2240/14 ,  F05D2250/191 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

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.

公开(公告)号：US11339720B2

公开(公告)日：2022-05-24

申请号：US16863218

申请日：2020-04-30

Applicant: Raytheon Technologies Corporation

Inventor： Daniel K. Van Ness ,  Anthony R. Bifulco ,  David A. Topol ,  David A. Knaul ,  Michael Raymond LaFavor

IPC: F02C7/24 ,  F04D29/66

Abstract: Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.

公开(公告)号：US20210324748A1

公开(公告)日：2021-10-21

申请号：US16851696

申请日：2020-04-17

Applicant: Raytheon Technologies Corporation

Inventor： David A. Knaul ,  Seung-Woo Choi ,  Michael Raymond LaFavor ,  Anthony R. Bifulco

IPC: F01D5/30

Abstract: A component of a rotor system is provided and includes a disk and a reinforcing ring. The disk includes an airfoil element, a web extending radially inwardly from the airfoil element and an arm element extending axially from the web. The reinforcing ring is formed of fiber reinforced materials and is disposed to fit about the arm element.

公开(公告)号：US11988283B2

公开(公告)日：2024-05-21

申请号：US17496288

申请日：2021-10-07

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco

IPC: F16J15/02 ,  B64D33/02 ,  F16J15/06 ,  F16J15/10 ,  F16J15/46

CPC classification number: F16J15/027 ,  B64D33/02 ,  F05D2240/55 ,  F05D2300/437 ,  F16J15/025 ,  F16J15/062 ,  F16J15/104 ,  F16J15/46

Abstract: A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.

公开(公告)号：US11268388B2

公开(公告)日：2022-03-08

申请号：US16851696

申请日：2020-04-17

Applicant: Raytheon Technologies Corporation

Inventor： David A. Knaul ,  Seung-Woo Choi ,  Michael Raymond LaFavor ,  Anthony R. Bifulco

IPC: F01D5/30 ,  F01D5/34 ,  F01D25/00 ,  F01D5/28 ,  F01D5/06

Abstract: A component of a rotor system is provided and includes a disk and a reinforcing ring. The disk includes an airfoil element, a web extending radially inwardly from the airfoil element and an arm element extending axially from the web. The reinforcing ring is formed of fiber reinforced materials and is disposed to fit about the arm element.

公开(公告)号：US11887571B2

公开(公告)日：2024-01-30

申请号：US17038556

申请日：2020-09-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Anthony R. Bifulco

IPC: G10K11/16 ,  B64D27/10 ,  B64D29/00 ,  B64D33/02 ,  F02C7/045 ,  F02C7/24

CPC classification number: G10K11/16 ,  B64D27/10 ,  B64D29/00 ,  B64D33/02 ,  F02C7/045 ,  F02C7/24 ,  B64D2033/0206

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

公开(公告)号：US11512608B2

公开(公告)日：2022-11-29

申请号：US17119510

申请日：2020-12-11

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Anthony R. Bifulco

IPC: F02C7/24 ,  F01D25/04 ,  F01D9/04 ,  F04D29/32 ,  F01D5/18 ,  F04D29/66 ,  F02C7/045 ,  F01D5/14 ,  F04D29/68

Abstract: A passive transpirational flow acoustic liner assembly for a gas turbine engine includes a guide vane assembly and a conduit configured to deliver airflow received from the guide vane. The guide vane assembly includes an airfoil having a transpirational flow acoustic liner. The acoustic liner includes a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures, a segmented member coupled to the face sheet and having a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures, a backing sheet having a plurality of apertures and being coupled to the segmented member such that the segmented member is positioned between the face sheet and the backing sheet, and a plenum coupled to the backing sheet opposite the segmented member and fluidly connected to the conduit.

公开(公告)号：US20220221056A1

公开(公告)日：2022-07-14

申请号：US17496288

申请日：2021-10-07

Applicant: Raytheon Technologies Corporation

Inventor： Anthony R. Bifulco

IPC: F16J15/02 ,  F01D11/00 ,  F02C7/28 ,  F16J15/46

Abstract: A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.

公开(公告)号：US11286856B2

公开(公告)日：2022-03-29

申请号：US16357392

申请日：2019-03-19

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Anthony R. Bifulco

IPC: F02C7/14 ,  F02C7/143 ,  F01D9/04 ,  F02C7/12 ,  F02C7/18 ,  F02C9/18 ,  F02C3/13 ,  F02C3/32 ,  F02C7/10

Abstract: A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.