公开(公告)号：US20200149544A1

公开(公告)日：2020-05-14

申请号：US16740817

申请日：2020-01-13

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 ,  F04D29/38 ,  F02K3/06 ,  F02C7/36 ,  F02C3/04 ,  F02K3/072 ,  F01D17/16 ,  F01D5/14

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：US10557477B2

公开(公告)日：2020-02-11

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 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06

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.

公开(公告)号：US10544802B2

公开(公告)日：2020-01-28

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: F02K3/06 ,  F04D29/54 ,  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：US20170175759A1

公开(公告)日：2017-06-22

申请号：US15116000

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 ,  F04D29/52 ,  F04D19/02 ,  F02K3/06 ,  F02C3/04 ,  F02C7/36

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 a tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to a pressure side-leaning trailing edge.

公开(公告)号：US20160131151A1

公开(公告)日：2016-05-12

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: F04D29/32 ,  F01D5/14

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.

Abstract translation: 根据本公开的示例的涡轮发动机的翼型布置包括相邻的翼型件，其包括在从0％跨度位置到100％跨度位置的径向方向上延伸的压力和吸力侧。 翼型件具有间隙/弦比和跨度位置之间的关系，其限定具有具有负斜率的部分的间隙/弦比的曲线。

公开(公告)号：US20220106965A1

公开(公告)日：2022-04-07

申请号：US17551349

申请日：2021-12-15

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 ,  F01D5/14 ,  F01D17/16 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F04D29/32 ,  F04D29/54 ,  F02K3/06

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：US10711613B1

公开(公告)日：2020-07-14

申请号：US15869129

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William R. Edwards ,  Mark E. Simonds ,  Steven J. Feigleson ,  Lisa I. Brilliant

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/28

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 2.58-2.88 inch (65.4-73.1 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 1.59-1.89 inch (40.3-48.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2088±10% Hz, a second mode with a frequency of 3099±10% Hz, a third mode with a frequency of 6890±10% Hz, a fourth mode with a frequency of 7207±10% Hz, a fifth mode with a frequency of 11241±10% Hz, a sixth mode with a frequency of 11916±10% Hz and a seventh mode with a frequency of 12600±10% Hz.

公开(公告)号：US20200149545A1

公开(公告)日：2020-05-14

申请号：US16741918

申请日：2020-01-14

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 ,  F04D29/32 ,  F02K3/06 ,  F02C7/36 ,  F02C3/04 ,  F01D25/24 ,  F01D17/16 ,  F01D5/14 ,  F04D29/54

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：US20200096005A1

公开(公告)日：2020-03-26

申请号：US16681187

申请日：2019-11-12

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 ,  F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/56

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.

公开(公告)号：US10280794B2

公开(公告)日：2019-05-07

申请号：US14769392

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

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

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.