公开(公告)号：US20230332622A1

公开(公告)日：2023-10-19

申请号：US18207805

申请日：2023-06-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D25/04 ,  F04D29/32 ,  F04D29/68 ,  F04D29/54 ,  F04D29/52 ,  F04D19/02 ,  F04D29/56 ,  F02K3/04

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11773866B2

公开(公告)日：2023-10-03

申请号：US17590115

申请日：2022-02-01

Applicant: Raytheon Technologies Corporation

Inventor： Simon W. Evans ,  Yuan Dong ,  Sean Nolan

IPC: F04D29/38 ,  F01D5/14 ,  F04D19/02 ,  F04D29/32

CPC classification number: F04D29/384 ,  F01D5/145 ,  F04D19/02 ,  F04D29/324 ,  F05D2210/30 ,  F05D2220/3216 ,  F05D2240/307 ,  F05D2260/821 ,  F05D2270/3013 ,  Y02T50/60

Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

公开(公告)号：US20230131276A1

公开(公告)日：2023-04-27

申请号：US17892529

申请日：2022-08-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11725670B2

公开(公告)日：2023-08-15

申请号：US17892529

申请日：2022-08-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11428242B2

公开(公告)日：2022-08-30

申请号：US16715528

申请日：2019-12-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US20220154728A1

公开(公告)日：2022-05-19

申请号：US17590115

申请日：2022-02-01

Applicant: Raytheon Technologies Corporation

Inventor： Simon W. Evans ,  Yuan Dong ,  Sean Nolan

IPC: F04D29/38 ,  F01D5/14 ,  F04D19/02 ,  F04D29/32

Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.