公开(公告)号：EP3498986A1

公开(公告)日：2019-06-19

申请号：EP18213725.7

申请日：2018-12-18

Applicant: United Technologies Corporation

Inventor： DARDONA, Sameh ,  CONSIGLIO, Andrew

IPC: F01D17/02 ,  F01D11/20 ,  H04B7/24 ,  F01D17/04

Abstract: A sensor assembly (62) for a gas turbine engine includes a substrate layer (64) formed on a localized surface (LS) of a rotatable gas turbine engine component (60), and at least one pair of transducers (66) deposited on the substrate layer (64).

公开(公告)号：EP3290653B1

公开(公告)日：2019-04-17

申请号：EP17189255.7

申请日：2017-09-04

Applicant: United Technologies Corporation

Inventor： CONSIGLIO, Andrew ,  GYSLING, Daniel L.

IPC: F01D17/04

公开(公告)号：EP3290653A1

公开(公告)日：2018-03-07

申请号：EP17189255.7

申请日：2017-09-04

Applicant: United Technologies Corporation

Inventor： CONSIGLIO, Andrew ,  GYSLING, Daniel L.

IPC: F01D17/04

CPC classification number: F04D27/001 ,  F01D17/04 ,  F01D21/003 ,  F01D21/14 ,  F04D29/325 ,  F05D2220/36 ,  F05D2270/334 ,  F05D2270/808 ,  G01H1/006 ,  G01M15/14

Abstract: An aeromechanical identification system (62) for turbomachine includes at least one actuator (64) mounted on a stationary structure (14) to excite rotatable airfoils (42). At least one sensor (66) is mounted proximate the airfoils (42) for measuring a response of the airfoils (42) responsive to excitation from the at least one actuator (64). A controller (68) is configured to determine a damping characteristic of an aeromechanical mode of the rotating airfoils (42) based on the excitation and the response. A gas turbine engine (20) and a method of determining a flutter boundary for an airfoil (42) of a turbomachine are also disclosed.

Abstract translation: 用于涡轮机械的航空机械识别系统（62）包括安装在固定结构（14）上以激励可旋转翼型（42）的至少一个致动器（64）。 至少一个传感器（66）安装在翼型件（42）附近，用于响应于来自至少一个致动器（64）的激励来测量翼型件（42）的响应。 控制器（68）被配置成基于激励和响应来确定旋转翼型件（42）的气动模式的阻尼特性。 还公开了一种燃气涡轮发动机（20）和一种确定涡轮机翼型（42）的颤振边界的方法。