公开(公告)号：US10598041B2

公开(公告)日：2020-03-24

申请号：US15789153

申请日：2017-10-20

Applicant: United Technologies Corporation

Inventor： William W. Rice ,  Alfred F. Covino ,  Richard C. Hendricks ,  Douglas H. Thomesen ,  Bryan J. Hackett

IPC: F01D21/00 ,  F02C7/04 ,  G01M15/14 ,  F01D17/08 ,  F02C7/32 ,  F02C3/04

Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

公开(公告)号：US20160348531A1

公开(公告)日：2016-12-01

申请号：US15114013

申请日：2015-01-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William W. Rice ,  Michael Ian Walker ,  Douglas H. Thomesen

IPC: F01D21/00 ,  B22F5/04 ,  G01M15/14 ,  B33Y80/00 ,  G01P5/175 ,  B22F3/105 ,  B33Y10/00

CPC classification number: F01D21/003 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B33Y10/00 ,  B33Y80/00 ,  F01D17/08 ,  F02C7/00 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2250/292 ,  F05D2260/83 ,  F05D2300/10 ,  G01M15/14 ,  G01P5/14 ,  G01P5/175 ,  Y02P10/295 ,  Y02T50/672

Abstract: A pressure probe includes a non-deflecting airfoil, a sensing feature, and an interior passage. The non-deflecting airfoil is made of a metal and configured for use in a gas turbine engine. The airfoil extends from a base to a tapered portion, and thence to a linear portion, along a primary axis. The sensing feature is formed monolithically with the airfoil, as by additive manufacturing. The interior passage is operatively connected to the sensing feature and passes through both the airfoil and the base.

Abstract translation: 压力探头包括非偏转翼型件，感测特征件和内部通道。 非偏转翼型件由金属制成并构造用于燃气涡轮发动机。 翼型件从基部延伸到锥形部分，并且因此沿主轴线延伸到直线部分。 感测特征与翼型件一体形成，如通过添加剂制造。 内部通道可操作地连接到感测特征并且通过翼型件和底座两者。

公开(公告)号：US20190120079A1

公开(公告)日：2019-04-25

申请号：US15789153

申请日：2017-10-20

Applicant: United Technologies Corporation

Inventor： William W. Rice ,  Alfred F. Covino ,  Richard C. Hendricks ,  Douglas H. Thomesen ,  Bryan J. Hackett

IPC: F01D21/00 ,  F02C7/04 ,  F02C7/32

CPC classification number: F01D21/003 ,  F01D17/08 ,  F02C3/04 ,  F02C7/04 ,  F02C7/32 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2260/83 ,  G01M15/14

Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

公开(公告)号：US10151214B2

公开(公告)日：2018-12-11

申请号：US15114013

申请日：2015-01-23

Applicant: United Technologies Corporation

Inventor： William W. Rice ,  Michael Ian Walker ,  Douglas H. Thomesen

IPC: F01D17/04 ,  F01D17/08 ,  F02C7/00 ,  G01M15/14 ,  G01P5/14 ,  F01D21/00 ,  G01P5/175 ,  B22F5/00 ,  B22F3/105 ,  B22F5/04 ,  B33Y10/00 ,  B33Y80/00

Abstract: A pressure probe includes a non-deflecting airfoil, a sensing feature, and an interior passage. The non-deflecting airfoil is made of a metal and configured for use in a gas turbine engine. The airfoil extends from a base to a tapered portion, and then to a linear portion, along a primary axis. The sensing feature is formed monolithically with the airfoil, as by additive manufacturing. The interior passage is operatively connected to the sensing feature and passes through both the airfoil and the base.