Abstract: A component made of superalloy is provided with a localized coating formed from three layers by a brazing heat treatment, the layers comprising an outer layer having a composition adapted to the specific surface properties sought, an inner layer having a composition which includes flux elements, and an intermediate layer obtained by the deposition of a mixture of the materials used for the other two layers.
Type:
Grant
Filed:
June 28, 1994
Date of Patent:
December 19, 1995
Assignee:
Societe Nationale d'Etude et de Construction de Motors d'Aviation "S.N.E.C.M.A."
Abstract: A system for controlling oxidizer intake diaphragms for a gas turbine engine combustion chamber is disclosed having a single, linear actuator for each pair of intake diaphragms. The movable member of each of an adjacent pair of intake diaphragms is connected to a movable piston rod of the linear actuator. A cam mechanism urges the piston rod in a first direction so as to simultaneously move the movable members of each of the pair of diaphragms. Pressurized gases from the combustion chamber act on the piston to urge it in a second, opposite direction. The forces of the pressurized gases also maintain contact between the cam member and the piston to insure accurate movement of the movable members. A plurality of such linear actuators may be disposed around the periphery of the combustion chamber, each actuator controlling a pair of adjacent intake diaphragms. The actuators may be interconnected by a flexible drive shaft to insure uniformity of movement of all of the cam elements in the system.
Type:
Grant
Filed:
May 1, 1991
Date of Patent:
November 3, 1992
Assignee:
Societe Nationale d'Etude et de Construction de Motors d'Aviation "S.N.E.C.M.A."
Abstract: A blow-off device for a gas turbine bypass engine having a primary air flow path separated from an outer secondary air flow path by a partition includes a plurality of discharge passages passing through the partition from the primary air flow path to the secondary air flow path, each of the discharge passages having a first hinged flap in the outer wall of the primary air flow path, a second hinged flap in the inner wall of the secondary air flow path, and a connecting rod mechanically interlinking the first and second flaps, the connecting rod being hinged at one of its end to the first flap and at its other end to the second flap.
Type:
Grant
Filed:
June 29, 1990
Date of Patent:
June 9, 1992
Assignee:
Societe Nationale d'Etude et de Construction de Motors d'Aviation "S.N.E.M.C.A."