公开(公告)号：US10570915B2

公开(公告)日：2020-02-25

申请号：US15113916

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

IPC: F04D29/32 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/38

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 a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span.

公开(公告)号：US20170175760A1

公开(公告)日：2017-06-22

申请号：US15116287

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

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

CPC classification number: F04D29/324 ,  F01D5/141 ,  F01D17/162 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02 ,  F04D29/325 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2240/303 ,  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 extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.

公开(公告)号：US20170167266A1

公开(公告)日：2017-06-15

申请号：US15115501

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

IPC: F01D5/14

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 stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.

公开(公告)号：US20160341217A1

公开(公告)日：2016-11-24

申请号：US15114503

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

IPC: F04D29/54 ,  F02C7/36 ,  F04D29/32

CPC classification number: F04D29/544 ,  F01D5/141 ,  F02C7/36 ,  F02K3/072 ,  F04D29/324 ,  F05D2220/3217 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/40311 ,  Y02T50/672 ,  Y02T50/673

Abstract: A compressor airfoil of a turbine engine having 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.

Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼型包括压力和吸力侧面，并且在径向方向上从0％跨度位置延伸到100％跨度位置。 翼型件具有后缘角度和跨度位置之间的关系，其限定了对应于不减小的后缘角度的0％跨度至20％跨度的非负斜率的曲线。

公开(公告)号：US20160003098A1

公开(公告)日：2016-01-07

申请号：US14769392

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

IPC: F01D25/14 ,  F02C3/04 ,  F01D25/24 ,  F01D5/12 ,  F01D9/04 ,  F02C7/36 ,  F01D5/02

CPC classification number: F01D25/145 ,  F01D5/02 ,  F01D5/08 ,  F01D5/12 ,  F01D9/041 ,  F01D25/24 ,  F01D25/26 ,  F02C3/04 ,  F02C7/14 ,  F02C7/24 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/231 ,  F05D2260/40311 ,  Y02T50/676

Abstract: A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer.

Abstract translation: 公开了一种具有发动机轴的燃气涡轮发动机及其制造方法。 燃气涡轮发动机可以包括构造成驱动空气的风扇，具有芯流动路径并被配置成吸入和压缩沿着核心流动路径流动的空气的低压压缩机部分，构造成驱动风扇的线轴和配置的齿轮架构 调整风扇转速。 燃气涡轮发动机还可以包括限定包围齿轮架构的隔室的壳体。 壳体设置在芯流路和轴之间，并且包括与低压压缩机部分的芯流动路径热连通的屏蔽中间部分。 屏蔽的中间部分包括外层和邻近外层的绝缘体。

公开(公告)号：US20150233250A1

公开(公告)日：2015-08-20

申请号：US14623605

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

IPC: F01D5/14 ,  F02C7/36

CPC classification number: F01D5/141 ,  F05D2220/36 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil of a turbine engine includes, pressure and suction sides extending in a radial direction from a 0% span 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 of less than 0.80 from 80% span to 100% span.

Abstract translation: 涡轮发动机的翼型包括从0％跨度到100％跨度位置沿径向延伸的压力和吸力侧。 翼型具有间隙/弦比和跨度位置之间的关系，其定义了从80％跨度到100％跨度的间隙/弦比小于0.80的曲线。

公开(公告)号：US09038366B2

公开(公告)日：2015-05-26

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: F02K3/02 ,  F02C1/06 ,  F02C3/13 ,  F01D25/16 ,  F02K3/04 ,  F02C7/36 ,  F02C9/18 ,  F01D5/14

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：US10808539B2

公开(公告)日：2020-10-20

申请号：US15218376

申请日：2016-07-25

Applicant: United Technologies Corporation

Inventor： Taryn Narrow ,  Matthew E. Bintz ,  Lucas D. Sorensen ,  Daniel J. Monahan ,  Steven D. Roberts ,  Jordan T. Wall ,  Yuan Dong ,  Lisa I. Brilliant ,  Andrew J. Murphy

IPC: F01D5/14 ,  F04D29/52 ,  F01D11/12 ,  F01D5/02 ,  F01D5/12 ,  F01D5/20 ,  F02C3/04

Abstract: A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

公开(公告)号：US10774651B1

公开(公告)日：2020-09-15

申请号：US15869124

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopolous ,  Lisa I. Brilliant

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/28 ,  F01D5/34

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.

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

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

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.