公开(公告)号：US12038011B2

公开(公告)日：2024-07-16

申请号：US17851918

申请日：2022-06-28

申请人： Raytheon Technologies Corporation

发明人： Allison Clark Nicklous ,  Steven Tyler Englerth

IPC分类号： F04D27/00 ,  F01D17/02 ,  F01D25/04 ,  F01D25/16 ,  F02C7/045 ,  F02C9/24 ,  F02K3/06 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  G01H1/00 ,  G01L19/06 ,  G01M15/12

CPC分类号： F04D27/001 ,  F01D17/02 ,  F01D25/04 ,  F01D25/164 ,  F02C7/045 ,  F02C9/24 ,  F02K3/06 ,  F04D29/329 ,  F04D29/38 ,  F04D29/522 ,  G01H1/006 ,  G01L19/0609 ,  G01M15/12 ,  F05D2260/12 ,  F05D2260/16 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2260/96 ,  F05D2270/334 ,  F05D2270/804

摘要： An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.

公开(公告)号：US20220325719A1

公开(公告)日：2022-10-13

申请号：US17851918

申请日：2022-06-28

申请人： Raytheon Technologies Corporation

发明人： Allison Clark Nicklous ,  Steven Tyler Englerth

IPC分类号： F04D27/00 ,  F01D25/04 ,  G01M15/12 ,  F02C9/24 ,  F01D25/16 ,  F01D17/02 ,  G01H1/00 ,  F02C7/045 ,  F02K3/06 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  G01L19/06

摘要： An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.