公开(公告)号：US20220025776A1

公开(公告)日：2022-01-27

申请号：US16935285

申请日：2020-07-22

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott

IPC: F01D11/00 ,  F01D25/12 ,  F16J15/324

Abstract: A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

公开(公告)号：US12163897B2

公开(公告)日：2024-12-10

申请号：US17702610

申请日：2022-03-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Ron I. Prihar ,  Garrett Kernozicky ,  Zhong Ouyang

IPC: G01N21/95 ,  G01B5/008 ,  G01N21/91 ,  G05B19/418 ,  F01D5/14

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from a first scanner; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; and commanding, via the processor, a contact probe to perform a non-destructive inspection on the areas of interest.

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：US11408349B2

公开(公告)日：2022-08-09

申请号：US17119480

申请日：2020-12-11

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Dilip Prasad

IPC: F02C7/24 ,  F01D9/04 ,  F02C7/045 ,  F02C7/042

Abstract: A vane for use in a gas turbine engine includes an airfoil having a suction side and a pressure side, and a transpirational flow acoustic liner disposed in the airfoil. The 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 a backing sheet coupled to the segmented member the segmented member such that the segmented member is positioned between the face sheet and the backing sheet. The segmented member includes a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures. The backing sheet has a plurality of second apertures.

公开(公告)号：US11371374B2

公开(公告)日：2022-06-28

申请号：US16935285

申请日：2020-07-22

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott

IPC: F01D25/12 ,  F01D11/00 ,  F16J15/324

Abstract: A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

公开(公告)号：US20210139155A1

公开(公告)日：2021-05-13

申请号：US17028578

申请日：2020-09-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F02C7/20 ,  F01D25/28 ,  F02K3/06

Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

公开(公告)号：US11753964B2

公开(公告)日：2023-09-12

申请号：US17320593

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Armando Amador ,  Todd A. Davis

IPC: F01D25/18 ,  F16J15/16 ,  F01D11/00 ,  F01D25/12

CPC classification number: F01D25/183 ,  F01D11/00 ,  F01D25/12 ,  F16J15/162 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/232

Abstract: A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat on a first piece of the second member, the seat having a seat face in sliding sealing engagement with the seal face; and a radially outwardly closed collection channel for collecting centrifuged oil; a second piece encircling and attached to the first piece and having a circumferential array of apertures; and cooperating with the first piece to define a plenum; and a flowpath from the collection channel passing radially outward axially spaced from the seat face to cool the seat face and passing axially away from the seat face in the plenum.

公开(公告)号：US11377221B2

公开(公告)日：2022-07-05

申请号：US17028578

申请日：2020-09-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F02C7/20 ,  F01D25/28 ,  F02K3/06

Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

公开(公告)号：US20220162993A1

公开(公告)日：2022-05-26

申请号：US17101623

申请日：2020-11-23

Applicant: Raytheon Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Jorn Axel Glahn

IPC: F02C7/27 ,  F02C7/28

Abstract: A gas turbine engine includes at least one shaft that interconnects a compressor section and a turbine section. A starter turbine provides torque to the at least one shaft during an engine start event. The starter turbine includes an air inlet and an outlet. A buffer air system is in fluid communication with the starter turbine and is configured to receive air associated with the outlet to supplement sealing of a bearing compartment sealing system.