Methods and apparatus for varying gas turbine engine inlet...

F - Mech Eng,Light,Heat,Weapons – 02 – C

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F02C 9/20 (2006.01) F01D 5/14 (2006.01) F01D 17/16 (2006.01) F02C 7/042 (2006.01) F04D 29/56 (2006.01) F04D 29/64 (2006.01)

Patent

CA 2418879

A method for assembling an articulated fan front frame for a gas turbine engine (10) facilitates improving engine performance. The method includes forming a strut (60) including a pair of sidewalls (80) connected at a leading edge (82) and a trailing edge (84), forming a flap (62) including a first sidewall (112) and a second sidewall (114) connected at a leading edge and a trailing edge, and extending in radial span between a root endwall (86) and a tip endwall (88), wherein each endwall extends between the first and second sidewalk, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap (120) is defined between the flap and the strut.

Méthode d'assemblage du carter d'admission articulé de la soufflante d'un moteur à turbine à gaz (10) pour améliorer le rendement du moteur. La méthode comprend la fabrication d'un mât (60) comprenant une paire de parois latérales (80) fixées à un bord d'attaque (82) et à un bord de fuite (84), ainsi que la fabrication d'un volet (62) constitué d'une première paroi latérale (112) et d'une seconde paroi latérale (114), fixées à un bord d'attaque et à un bord de fuite et se prolongeant entre la paroi de l'emplanture (86) et la paroi du bout (88), chacune de ces deux parois d'extrémité se prolongeant entre les deux parois latérales et au moins une des deux extrémités (emplanture et bout) étant profilée en direction radiale en se prolongeant entre les bords d'attaque et de fuite du volet. Le volet est couplé de façon à pouvoir pivoter en aval du mât, de manière à ce qu'un espace (120) soit dégagé entre le volet et le mât.

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