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US 7,255,528 B2Granted
Liner for a gas turbine engine casing
AssigneeROLLS-ROYCE plc
InventorRichard G Stretton
Life of this patent
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AssigneeROLLS-ROYCE plc
InventorRichard G Stretton
Estimating the term…
A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). A set of acoustic panels (72C) is also provided. A set of acoustic panels (72B) is secured to the metal casing (40) by resilient fingers (80, 84) on the upstream and downstream ends (82,86) of the acoustic panels (72B) which locate on the annular member (54) and the acoustic panels (72C).
A gas turbine engine casing comprising a generally cylindrical, or frustoconical, casing, the casing including at least one member secured to the casing, the member having a first portion extending radially from the casing and a second portion extending axially from the first portion of the member, at least one liner panel being positioned radially from the casing, a first end of the liner panel being removably securable on the member by at least one resilient spring finger, the at least one resilient spring finger being biased to move axially away from the first end of the liner panel to locate the at least one resilient spring finger on the second portion of the member wherein the at least one resilient spring finger being movably axially towards the center of the liner panel to remove the at least one resilient spring finger from the second portion of the member.
An acoustic liner panel comprising a perforate skin and a structure to form an acoustic treatment structure, a first end of the acoustic liner panel being removably securable on a member by at least one resilient member, the at least one resilient member being biased to move away from the first end of the acoustic liner panel to locate on the member.
A gas turbine engine liner panel comprising a first end of the acoustic liner panel being removably securable on a member by at least one resilient member, the at least one resilient member being biased to move away from the first end of the acoustic liner panel to locate on the member.
Dependencies are inferred from the claim text.