公开(公告)号：US09752439B2

公开(公告)日：2017-09-05

申请号：US14996351

申请日：2016-01-15

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 ,  F04D29/32

CPC classification number: F01D5/141 ,  F04D29/324 ,  F05D2220/32 ,  F05D2260/40311 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have 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.

公开(公告)号：US20170167503A1

公开(公告)日：2017-06-15

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

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

CPC classification number: F04D29/324 ,  F01D5/141 ,  F02C3/06 ,  F02C7/36 ,  F02K3/06 ,  F04D29/325 ,  F04D29/38 ,  F04D29/544 ,  F05D2220/3216 ,  F05D2220/323 ,  F05D2240/301 ,  F05D2240/35 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/4031 ,  Y02T50/672 ,  Y02T50/673

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：US20160348691A1

公开(公告)日：2016-12-01

申请号：US15114922

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: F04D29/38 ,  F01D25/24 ,  F02K3/06 ,  F04D29/32 ,  F02C3/04 ,  F02C7/36

Abstract: An 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 a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span.

Abstract translation: 涡轮发动机的翼型包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型在交错角度和跨度位置之间有一个关系，这个关系定义了一个交错角度的曲线，该角度大于从0％跨度到至少50％跨度的35°。

公开(公告)号：US20160341211A1

公开(公告)日：2016-11-24

申请号：US15113870

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 ,  F01D25/24 ,  F04D29/38 ,  F02K3/06 ,  F02C3/04 ,  F02C7/36

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 tangential stacking offset and span position that defines a curve that is non-linear.

Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型在定义非线性曲线的切向堆积偏移和跨度位置之间具有关系。

公开(公告)号：US20160208818A1

公开(公告)日：2016-07-21

申请号：US15084643

申请日：2016-03-30

Applicant: United Technologies Corporation

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F04D29/54 ,  F02K3/06 ,  F04D29/56 ,  F04D25/04 ,  F04D29/32

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.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的压缩机部分包括包括围绕轴线布置的多个转子叶片的低压压缩机，高压压缩机和穿过低压的芯流道 压缩机。 在低压压缩机处的芯流动路径相对于轴线限定内径和外径。 外径相对于轴线具有倾斜角度。

公开(公告)号：US20160069187A1

公开(公告)日：2016-03-10

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 ,  F02C7/36 ,  F02C3/107 ,  F01D5/02 ,  F01D15/12

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。

公开(公告)号：US20200173463A1

公开(公告)日：2020-06-04

申请号：US16667321

申请日：2019-10-29

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 ,  F02K3/072 ,  F01D5/14

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：US10669890B2

公开(公告)日：2020-06-02

申请号：US16404217

申请日：2019-05-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

IPC: F01D25/14 ,  F01D5/08 ,  F01D25/26 ,  F02C7/14 ,  F02C7/24 ,  F02C7/36 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/24 ,  F02C3/04

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.

公开(公告)号：US20190323380A1

公开(公告)日：2019-10-24

申请号：US16404217

申请日：2019-05-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

IPC: F01D25/14 ,  F01D5/12 ,  F02C7/24 ,  F02C7/36 ,  F02C3/04 ,  F01D25/26 ,  F01D5/08 ,  F02C7/14 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24

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.

公开(公告)号：US20170175758A1

公开(公告)日：2017-06-22

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

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

CPC classification number: F04D29/324 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02 ,  F04D29/325 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/3217 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2260/4031 ,  Y02T50/672 ,  Y02T50/673

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.