Abstract: A synchronizing ring assembly includes a synchronizing ring portion that has a first and a second distal end, the first and the second distal end each form an integrated surge bumper.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.

Abstract: A synchronizing ring assembly includes a synchronizing ring portion that has a first and a second distal end, the first and the second distal end each form an integrated surge bumper.

Abstract: A synchronizing assembly including: a synchronizing ring having a countersunk orifice; and a bumper assembly comprising: a bumper at least partially enclosing a cavity, the bumper comprising an outward side, an inward side opposite the outward side, a first side extending between the outward side and the inward side, a first opening on the outward side extending into the bumper to define a first portion of the cavity; and a second opening on the first side extending into the bumper to define a second portion of the cavity; and a bolt comprising a bolt head and a bolt shank, wherein the bolt shank extends through the first opening and the bolt head is secured within the second portion of the cavity, wherein the bumper further comprises a raised boss extending away from the outward surface, the raised boss configured to mate with the countersunk orifice of the synchronizing ring.

Abstract: A synchronizing assembly including: a synchronizing ring having a countersunk orifice; and a bumper assembly comprising: a bumper at least partially enclosing a cavity, the bumper comprising an outward side, an inward side opposite the outward side, a first side extending between the outward side and the inward side, a first opening on the outward side extending into the bumper to define a first portion of the cavity; and a second opening on the first side extending into the bumper to define a second portion of the cavity; and a bolt comprising a bolt head and a bolt shank, wherein the bolt shank extends through the first opening and the bolt head is secured within the second portion of the cavity, wherein the bumper further comprises a raised boss extending away from the outward surface, the raised boss configured to mate with the countersunk orifice of the synchronizing ring.

Abstract: A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.