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：US11209013B2

公开(公告)日：2021-12-28

申请号：US16741918

申请日：2020-01-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Lisa I. Brilliant ,  Joseph C. Straccia ,  Stanley J. Balamucki ,  Mark A. Stephens ,  Kate Hudon

IPC: F04D29/38 ,  F04D29/54 ,  F01D5/14 ,  F01D17/16 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/32

Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is provided in the compressor section outside the high pressure compressor section and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.