公开(公告)号：US20200172269A1

公开(公告)日：2020-06-04

申请号：US16697929

申请日：2019-11-27

Applicant: Gulfstream Aerospace Corporation

Inventor： Vincent DeChellis ,  Mike Lucas ,  Tongan Wang ,  Nicholas Ward ,  Paul Conti

IPC: B64F5/60 ,  B64D45/00 ,  G01M15/14

Abstract: An aircraft includes a turbine engine, a vibration sensor, and a processor. The vibration sensor is attached to the turbine engine and is configured to output a vibration sensor signal. The processor is programmed to determine whether the vibration sensor signal indicates that fan case liner damage has occurred due to icing conditions. The processor is further programmed to indicate that a fan case inspection should be conducted in response to the vibration sensor signal indicating that fan case liner damage has occurred.

公开(公告)号：US09038774B2

公开(公告)日：2015-05-26

申请号：US14096833

申请日：2013-12-04

Applicant: GULFSTREAM AEROSPACE CORPORATION

Inventor： Tongan Wang ,  John Maxon ,  Andrew Foose ,  David Charles Hornick ,  Josef Fila

IPC: E04B1/82 ,  E04B1/84 ,  E04B2/02 ,  B32B3/12 ,  B64C1/40 ,  H02N2/00 ,  B29C65/00 ,  B64C1/00 ,  G10K11/00 ,  G10K11/02 ,  B32B5/26 ,  B32B5/32 ,  B32B7/02 ,  B29K105/04

CPC classification number: B64C1/40 ,  B29C65/00 ,  B29C66/11 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/43 ,  B29K2105/04 ,  B32B3/12 ,  B32B5/26 ,  B32B5/32 ,  B32B7/02 ,  B32B2250/02 ,  B32B2250/03 ,  B32B2250/04 ,  B32B2250/05 ,  B32B2250/20 ,  B32B2250/22 ,  B32B2266/0257 ,  B32B2266/0285 ,  B32B2266/06 ,  B32B2307/102 ,  B32B2307/718 ,  B32B2605/18 ,  B64C1/00 ,  E04B1/82 ,  E04B1/84 ,  G10K11/00 ,  G10K11/02 ,  Y02T50/46 ,  Y10T428/24149

Abstract: Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.

Abstract translation: 本文提供了用于从声源产生的用于降低沿着声学路径的噪声的用于飞行器的热声部分的实施例。 热声部分包括具有第一特征声阻抗的第一多孔层。 第二多孔层设置成与第一多孔层相邻并且具有大于第一特征声阻抗的第二特征声阻抗。 热声部分被配置成沿着声学路径定位，使得来自声源的噪声的至少一部分被引导通过第一多孔层到第二多孔层以促进噪声的吸收。