|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/04 F02C-007/045 F02K-003/06 B64D-033/02|
|§371/§102 date||20091027 (20091027)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 11|
A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.
1. A nacelle for a gas turbine engine system, comprising: a housing having a pressure side and a suction side; anda passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side and the passage includes a first curved section having an inlet at the pressure side, a linear section connected with the first curved section, and a second curved section connected with the linear section and having an outlet at the suction side, the outlet having a cross sectional area smaller than a cross sec...