-
公开(公告)号：US10570916B2
公开(公告)日：2020-02-25
申请号：US15115360
申请日：2015-02-16
Applicant: UNITED 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 having a geared architecture 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：US10465702B2
公开(公告)日：2019-11-05
申请号：US15114745
申请日：2015-02-17
Applicant: UNITED 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 having a geared architecture includes pressure and suction sides extending 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, and a positive sweep angle is in the rearward direction.
-
公开(公告)号：US10352331B2
公开(公告)日：2019-07-16
申请号：US15115779
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: An airfoil of a turbine engine 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 camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
-
公开(公告)号：US20170159670A1
公开(公告)日：2017-06-08
申请号：US15115360
申请日：2015-02-16
Applicant: UNITED 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 , Y02T50/672 , Y02T50/673
Abstract: A compressor airfoil of a turbine engine having a geared architecture 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：US09567858B2
公开(公告)日：2017-02-14
申请号：US14626130
申请日：2015-02-19
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC: F01D5/14
CPC classification number: F01D5/141 , F04D29/324 , F05D2220/32 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
Abstract translation: 根据本公开的示例的涡轮发动机的翼型尤其包括在径向方向上从0％跨度位置延伸到100％跨度位置的压力和吸力侧。 翼型具有间隙/弦比和跨度位置之间的关系，其定义具有带有负斜率的部分的间隙/弦比的曲线。
-
Patent Agency Ranking
26.发明申请公开(公告)号：US20140248129A1
公开(公告)日：2014-09-04
申请号：US14067354
申请日：2013-10-30
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
IPC: F02C3/13
CPC classification number: F02C3/13 , F01D5/143 , F01D25/162 , F02C7/36 , F02C9/18 , F02K3/04 , Y02T50/673
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
-
公开(公告)号：US20200291955A1
公开(公告)日：2020-09-17
申请号：US16744749
申请日：2020-01-16
Applicant: UNITED 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 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：US20200240436A1
公开(公告)日：2020-07-30
申请号：US16715528
申请日：2019-12-16
Applicant: United 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：US20200149546A1
公开(公告)日：2020-05-14
申请号：US16591046
申请日：2019-10-02
Applicant: UNITED 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.
-
公开(公告)号：US10605259B2
公开(公告)日：2020-03-31
申请号：US15115714
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: An airfoil of a turbine engine 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 a leading edge angle of less than 40° at 100% span.
-
-
-
-
-
-
-
-
-
Search Results
38
records
(took 0.02 seconds)
