초록 ▼

A casing for the fan section of an aircraft gas turbine engine of the turbofan type. The casing includes an inner filler material and is defined by an outer shell and an inner liner that is spaced radially inwardly from the outer shell. The inner liner is held in position relative to the outer shell

A casing for the fan section of an aircraft gas turbine engine of the turbofan type. The casing includes an inner filler material and is defined by an outer shell and an inner liner that is spaced radially inwardly from the outer shell. The inner liner is held in position relative to the outer shell by a plurality of radially-inwardly-extending support pins. The pins are carried by the outer shell and are slidably received in and extend at least partially into the inner liner. The support pins retain the inner liner against axial and rotational movement relative to the outer shell, while allowing relative radial movement therebetween in response to thermal expansion and contraction, as well as in response to aircraft maneuver loads imposed on the engine.

대표청구항 ▼

1. A casing for surrounding a rotatable turbomachine member that includes a rotor and a plurality of substantially radially-extending, circumferentially spaced rotor blades, said casing comprising:a. an annular outer shell formed from a material having a first coefficient of thermal expansion; b. an

1. A casing for surrounding a rotatable turbomachine member that includes a rotor and a plurality of substantially radially-extending, circumferentially spaced rotor blades, said casing comprising:a. an annular outer shell formed from a material having a first coefficient of thermal expansion; b. an annular inner liner carried within and spaced radially inwardly of the outer shell and substantially coaxial therewith, the annular inner liner formed from a material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion and capable of radially expanding and radially contracting relative to the outer shell as a result of changes in inner liner temperature, the annular liner surrounding and spaced radially outwardly from outer tips of the rotor blades by a predetermined distance to limit gas flow between the rotor blade tips and the inner liner; c. a plurality of substantially radially inwardly extending support members fixedly carried by the outer shell and extending at least partially into substantially radial openings carried by the inner liner to support the inner liner against axial and rotational movement relative to the outer shell, and to allow relative radial sliding movement between the outer shell and the inner liner along the support members and without relative rotation between the support members and the inner liner.