公开(公告)号：US11408436B2

公开(公告)日：2022-08-09

申请号：US16744749

申请日：2020-01-16

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 has an array of twenty-six or fewer fan blades. 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 that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.

公开(公告)号：US11193496B2

公开(公告)日：2021-12-07

申请号：US16740817

申请日：2020-01-13

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 ,  F01D5/14 ,  F01D17/16 ,  F02K3/072 ,  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 has an array of twenty-six or fewer fan blades. 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 that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.

公开(公告)号：US20210355952A1

公开(公告)日：2021-11-18

申请号：US17385150

申请日：2021-07-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F04D29/02 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F02K1/06 ,  F01D15/12 ,  F02C7/36 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56 ,  F02C3/06

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan has a bypass ratio of greater than 8.5. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

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.

公开(公告)号：US11073157B2

公开(公告)日：2021-07-27

申请号：US16515506

申请日：2019-07-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F02C7/36 ,  F04D29/02 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F02K1/06 ,  F01D15/12 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56 ,  F02C3/06

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

公开(公告)号：US11767856B2

公开(公告)日：2023-09-26

申请号：US17551349

申请日：2021-12-15

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

CPC classification number: F04D29/38 ,  F01D5/141 ,  F01D17/162 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/325 ,  F04D29/544 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2260/4031 ,  Y02T50/60

Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between 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 at 100% span is greater than the stagger angle at 50% span.

公开(公告)号：US20210372284A1

公开(公告)日：2021-12-02

申请号：US17396029

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F01D5/14 ,  F04D29/32 ,  F02C3/10 ,  F04D29/38

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.

公开(公告)号：US11041507B2

公开(公告)日：2021-06-22

申请号：US16591046

申请日：2019-10-02

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 ,  F04D29/54 ,  F04D29/56 ,  F02C3/067 ,  F04D29/32

Abstract: A compressor airfoil of a turbine engine 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 leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction. A positive sweep angle is in the rearward direction. The airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.

公开(公告)号：US11867195B2

公开(公告)日：2024-01-09

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

CPC classification number: F04D29/324 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/384 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2260/4031 ,  Y02T50/60

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.

公开(公告)号：US11466572B2

公开(公告)日：2022-10-11

申请号：US17396029

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/38 ,  F02C3/10

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.