|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/134C; 244/1340R; 060/039093|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 12 인용 특허 : 0|
An anti-icing system for an aircraft engine nacelle comprises a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle; a plurality of fasteners for attaching the spray tube to a support structure of the aircraft engine; and a supply duct for delivering the hot gasses from the aircraft engine to the spray tube. The spray tube includes two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansions and contractions caused by the hot gasses. Each of the fasteners comprises a supp...
Having thus described the preferred embodiment of the invention, what is claimed as new and desired to be protected by Letters Patent includes the following: 1. An anti-icing system for a nacelle inlet of an aircraft engine, the system comprising:a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle inlet, the spray tube including two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansion of the spray tube caused by the hot gasses;a plurality of fasteners for attaching t...