|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/53B ; 244/53R ; 181/215 ; 181/220|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 22 인용 특허 : 10|
The present invention comprises a cowling structure for a gas turbine aircraft engine which allows the aerodynamic characteristics of the inlet passageway to the engine to be varied in accordance with flight conditions. This structure includes an annular lip portion positioned at the front edge of the cowling defining an aerodynamically sharp contour and which is mounted on a set of support struts constructed for allowing the lip portion to be translated forwardly and backwardly from the forward edge of the cowling. The structure further comprises a mech...
In a gas turbine engine for an aircraft having an air intake passageway defined by a cowling which functions for directing ambient air into said engine, a variable geometry inlet structure adapted for noise reduction, comprising: an annular lip positioned at the front edge of said cowling for defining an aerodynamically sharp contour along the front edge of said cowling; means for axially translating said lip forwardly from and backwardly to the front edge of said cowling including a set of circumferentially spaced struts for mounting said lip, said stru...