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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
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.
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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
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.
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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
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.
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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
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.
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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
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.
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Patent Agency Ranking
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.
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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.
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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.
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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
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.
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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.
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