초록 ▼

A method is described for identifying the primary load path of a particular engine. An elastomeric mount may then be made laterally soft in a first (in the disclosed case, the tangential) direction and more rigid in the direction of the primary load path. Efforts can then be directed to dynamically

A method is described for identifying the primary load path of a particular engine. An elastomeric mount may then be made laterally soft in a first (in the disclosed case, the tangential) direction and more rigid in the direction of the primary load path. Efforts can then be directed to dynamically softening the mount in the primary load path. Specific apparatus may include passive fluid devices, active fluid devices, passive non-fluid devices and active non-fluid devices. In the case of a fluid mount, another feature of the invention is to have an auxiliary fill port of the volume compensator in alignment with at least one and, preferably both, of the primary fill port for the mount and the inertia track to facilitate filling.

대표청구항 ▼

[ What is claimed is:] [1.] Apparatus for mounting a turbine engine to a portion of an aircraft structure, said apparatus comprisinga) a first elastomeric mount attachable to said engine and said portion of an aircraft structure, said mount being significantly softer statically in a first lateral di

[ What is claimed is:] [1.] Apparatus for mounting a turbine engine to a portion of an aircraft structure, said apparatus comprisinga) a first elastomeric mount attachable to said engine and said portion of an aircraft structure, said mount being significantly softer statically in a first lateral direction than in a second lateral direction said mount having a static spring rate in said first lateral direction which is generally 10% or less of the static spring rate in said second lateral direction and having a third static spring rate in a third orthogonal direction that is about one half or less of said spring rate in said second lateral direction, said second lateral direction defining a primary load path for transmission of vibratory forces from said turbine engine to said portion of an aircraft structure;b) auxiliary means associated with said second lateral direction to dynamically soften said mount in said second lateral direction to reduce or cancel vibratory forces transmitted between said engine and said portion of an aircraft structure, wherein said auxiliary means is selected from the group consisting of i)passive non-fluid means, ii) active non-fluid means, and iii) active fluid means.