公开(公告)号：US20190145431A1

公开(公告)日：2019-05-16

申请号：US16245516

申请日：2019-01-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Ignatius THERATIL ,  Krishna Prasad BALIKE ,  Sean Michael KELLY ,  Richard IVAKITCH ,  Peter TOWNSEND ,  Ronald DUTTON ,  Paul STONE ,  Robert VENDITTI ,  Daniel FUDGE ,  Milica KOJOVIC ,  Aldo ABATE

IPC: F04D29/66 ,  F01D5/16

Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.

公开(公告)号：US20170241432A1

公开(公告)日：2017-08-24

申请号：US15436091

申请日：2017-02-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Ignatius THERATIL ,  Krishna Prasad BALIKE ,  Aldo ABATE ,  Sean KELLY ,  Peter TOWNSEND ,  Ronald DUTTON ,  Anthony BROWN ,  Paul STONE ,  Myron KLEIN ,  Milica KOJOVIC ,  Robert VENDITTI

IPC: F04D29/32 ,  F02K3/06 ,  F04D19/00

CPC classification number: F04D29/327 ,  F02K3/06 ,  F04D19/002 ,  F04D21/00 ,  F04D29/324 ,  F04D29/666 ,  F05D2220/36 ,  F05D2240/302 ,  F05D2240/303 ,  F05D2240/307 ,  F05D2260/961

Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.

公开(公告)号：US20150260103A1

公开(公告)日：2015-09-17

申请号：US14207957

申请日：2014-03-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hong YU ,  Ronald DUTTON

IPC: F02C7/20

CPC classification number: F01D5/142 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F04D29/544 ,  Y02T50/673

Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

Abstract translation: 位于转子上游的燃气涡轮发动机中的支柱和IGV构型包括多个径向支柱，例如用于承载发动机负载，以及多个与支柱轴向间隔开的入口引导叶片。 入口导叶的数量大于支柱的数量。 支柱与入口导叶周向对准。

公开(公告)号：US20200024954A1

公开(公告)日：2020-01-23

申请号：US16122295

申请日：2018-09-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Hong YU ,  Ronald DUTTON

IPC: F01D5/14 ,  F04D29/54 ,  F01D9/04 ,  F01D25/16

Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

公开(公告)号：US20180156235A1

公开(公告)日：2018-06-07

申请号：US15370497

申请日：2016-12-06

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Yau-Wai LI ,  Peter TOWNSEND ,  Ronald DUTTON ,  Bernadette MASON

IPC: F04D29/54 ,  F02K3/06 ,  F04D29/32

CPC classification number: F04D29/542 ,  F01D9/041 ,  F02K3/06 ,  F04D29/666 ,  F05D2230/60

Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.

公开(公告)号：US20150211546A1

公开(公告)日：2015-07-30

申请号：US14163588

申请日：2014-01-24

Applicant: Pratt & Whitney Canada Corp.

Inventor： Kari HEIKURINEN ,  Ronald DUTTON

IPC: F04D29/54

CPC classification number: F04D29/541 ,  F01D5/143 ,  F01D5/145 ,  F04D19/028 ,  F04D29/547 ,  F04D29/681 ,  F05D2270/17

Abstract: A multi-stage axial compressor with an inner wall including a step portion for each of the compressor stages. Each step portion is defined along a respective stage. Each step portion may extend over at least a majority of an axial length of the stage. Each step portion may optionally include a point aligned with a maximum thickness of the airfoil portions of the rotor blades and a point aligned with a maximum thickness of the stator vanes. Adjacent step portions are connected by a transition portion converging toward a central axis of the compressor from the upstream step to the downstream step. Each transition portion has a steeper slope than that of the adjacent step portions. A method of directing flow through a multi-stage axial flow compressor is also discussed.

Abstract translation: 一种具有内壁的多级轴流压缩机，包括用于每个压缩机级的台阶部分。 每个步骤部分沿着相应的阶段被限定。 每个台阶部分可以延伸至阶段的轴向长度的至少大部分。 每个步骤部分可以可选地包括与转子叶片的翼型部分的最大厚度对准的点和与定子叶片的最大厚度对准的点。 相邻的台阶部分通过从上游步骤向下游步骤朝向压缩机的中心轴线收敛的过渡部分连接。 每个过渡部分具有比相邻台阶部分更斜的斜率。 还讨论了引导流过多级轴流压缩机的方法。