|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64D-033/04 F02K-001/78 F02K-001/70 F01D-005/14 F01D-009/02 F01D-025/24 B64D-029/00 B64D-029/02 B64D-029/06|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 39|
A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.
1. A gas turbine engine comprising: a convergent-divergent nozzle including an outlet having a trailing edge; andan aerodynamic track fairing adjacent to said convergent-divergent nozzle, said aerodynamic track fairing defining a compound edge extending aft from the trailing edge, the aerodynamic fairing including an aft portion that extends toward an aft end of said aerodynamic track fairing to define a primary curvature and a forward portion extending between the trailing edge and said aft portion, the forward portion of the compound edge defining a su...