公开(公告)号：US10941708B2

公开(公告)日：2021-03-09

申请号：US15452632

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Steven D. Sandahl

IPC: F02C7/045 ,  F01D25/06 ,  F01D5/26 ,  F02K3/06 ,  B65D33/02 ,  B64D33/02

Abstract: Disclosed is a gas turbine engine including a fan, a nacelle including a flutter damper forward of the fan, the flutter damper including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber in fluid communication with the acoustic liner, and the chamber configured for peak acoustical energy absorption at a frequency range associated with fan flutter modes, and the engine includes (i) the nacelle and a core cowl forming a convergent-divergent fan exit nozzle; (ii) a variable area fan nozzle capable of being in an opened and closed, the opened position having a larger fan exit area than the closed position; and/or (iii) the fan being shrouded.

公开(公告)号：US20180258856A1

公开(公告)日：2018-09-13

申请号：US15452632

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Steven D. Sandahl

IPC: F02C7/045 ,  F01D25/06

CPC classification number: F02C7/045 ,  B64D2033/0206 ,  F01D5/26 ,  F01D25/06 ,  F02K3/06 ,  F05D2260/96 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673

Abstract: Disclosed is a gas turbine engine including a fan, a nacelle including a flutter damper forward of the fan, the flutter damper including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber in fluid communication with the acoustic liner, and the chamber configured for peak acoustical energy absorption at a frequency range associated with fan flutter modes, and the engine includes (i) the nacelle and a core cowl forming a convergent-divergent fan exit nozzle; (ii) a variable area fan nozzle capable of being in an opened and closed, the opened position having a larger fan exit area than the closed position; and/or (iii) the fan being shrouded.