초록 ▼

A method is described for enabling operation of an aircraft turbo-engine to be continued in spite of the accidental occurrence of an unbalance in a tor of the engine, such as may be caused by the breakage of a fan blade. The method involves constructing the bearing support of at least one of the bea

A method is described for enabling operation of an aircraft turbo-engine to be continued in spite of the accidental occurrence of an unbalance in a tor of the engine, such as may be caused by the breakage of a fan blade. The method involves constructing the bearing support of at least one of the bearings of the rotor so that the support has at least two levels of stiffness, arranging for the support to change from a normal stiffness level to a lower stiffness level in response to the occurrence of an unbalance in excess of a pre-determined minimum value, and setting the clearance between the tips of the rotor blades and the inner wall of the surrounding casing so that it is at least equal to the radial displacement of the rotor under the action of a pre-determined maximum unbalance when the rotor is rotating at the flight idling speed of the engine and the bearing support is at the lower stiffness level. A bearing support construction for implementing the method is also described.

대표청구항 ▼

[ I claim:] [1.] A method enabling operation of an aircraft turbo-engine to be continued at a rotational speed at least equal to the flight idling speed of said turbo-engine after the accidental occurrence of an unbalance in a rotor of said turbo-engine, provided said unbalance remains below a pre-e

[ I claim:] [1.] A method enabling operation of an aircraft turbo-engine to be continued at a rotational speed at least equal to the flight idling speed of said turbo-engine after the accidental occurrence of an unbalance in a rotor of said turbo-engine, provided said unbalance remains below a pre-established maximum, the said turbo-engine including a fixed structure, a casing within which said rotor rotates with a radial clearance between the tips of the blades of said rotor and the inner wall of said casing, bearings rotatably mounting said rotor, and bearing supports connecting said bearings to said fixed structure of said turbo-engine, said method comprising the steps of:a) constructing the bearing support of at least one of said bearings so as to possess at least two stiffness levels including a "normal" stiffness level corresponding to a natural frequency of said rotor above said flight idling speed of said turbo-engine, and a "lower" stiffness level corresponding to a natural frequency of said rotor below said flight idling speed;b) arranging for said bearing support to change from said normal stiffness level to said lower stiffness level in response to the occurrence of an unbalance at least equal to a pre-established minimum; and,c) setting said radial clearance to be at least equal to the radial displacement of said rotor under the action of said pre-established maximum unbalance when said rotor is rotating at said flight idling speed and said bearing support is at said lower stiffness level.