公开(公告)号：US11193497B2

公开(公告)日：2021-12-07

申请号：US16787731

申请日：2020-02-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F04D29/32 ,  F04D29/54 ,  F01D5/14 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02

Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. A fan section has an array of twenty-six or fewer fan blades. An airfoil includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with the leading edge angle of less than 40° at 100% span.

公开(公告)号：US10914315B2

公开(公告)日：2021-02-09

申请号：US16681187

申请日：2019-11-12

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 ,  F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/56

Abstract: A gas turbine engine includes a combustor section, a compressor section, and a turbine section. A high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. A low pressure compressor is counter-rotating relative to the fan blades and downstream from the fan section. The airfoil outside of the compressor section is rotatable relative to an engine static structure. The airfoil includes pressure and suction sides extending from a 0% span position to a 100% span position. A relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. The leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.

公开(公告)号：US10890195B2

公开(公告)日：2021-01-12

申请号：US16667321

申请日：2019-10-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F04D29/54 ,  F04D29/32 ,  F01D5/14 ,  F02K3/072 ,  F02C7/36

Abstract: A compressor airfoil of a turbine engine that has a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.

公开(公告)号：US20220235792A1

公开(公告)日：2022-07-28

申请号：US17722449

申请日：2022-04-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F04D29/32 ,  F04D29/54 ,  F01D5/14 ,  F01D9/02 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/38

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 is included. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has an axial stacking offset at a 10% span position that is positive and greater than or equal to an axial stacking offset at the 100% span position. The axial stacking offsets measured relative to an aftward direction.