Back to results
US 9,169,045 B2Granted
Gas turbine engine blade containment arrangement
AssigneeROLLS-ROYCE plc
InventorDaniel N. S. Clark
Life of this patent
Estimating the term…
Abstract
A gas turbine engine blade containment arrangement comprises a casing, a first layer of cellular material arranged within the casing, a septum layer within the first layer of cellular material, a second layer of cellular material within the septum layer, a strong and ductile layer within the second layer of cellular material and a layer of abradable material within the strong and ductile layer.
Claims29
A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement,
- the fan comprising a fan rotor having a plurality of fan blades,
- the fan casing surrounding the fan rotor and fan blades,
- the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being arranged radially between the fan casing and the fan, the fan blade containment arrangement being axially shorter than the fan casing, the fan blade containment arrangement comprising a first layer of cellular material radially within an inner surface of the fan casing, a septum layer radially within an inner surface of the first layer of cellular material, a second layer of cellular material radially within an inner surface of the septum layer, a ductile layer radially within an inner surface of the second layer of cellular material and a layer of abradable material radially within an inner surface of the ductile layer, the ductile layer being axially shorter than the fan casing, the ductile layer having a higher yield stress than the layer of abradable material, the ductile layer having ductility which is greater than a crush initiation limit of the first and second layers of cellular material and the ductile layer being arranged to contain at least a portion of a detached blade without rupturing.
A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement,
- the fan comprising a fan rotor having a plurality of swept fan blades,
- the fan casing surrounding the fan rotor and fan blades, the fan casing consisting of a casing having a flange at an upstream end and a flange at a downstream end,
- the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being arranged radially between the fan casing and the fan, the fan blade containment arrangement being axially shorter than the fan casing, the fan blade containment arrangement comprising a first layer of cellular material abutting a radially inner surface of the fan casing, a septum layer abutting a radially inner surface of the first layer of cellular material, a second layer of cellular material abutting a radially inner surface of the septum layer, a ductile layer abutting a radially inner surface of the second layer of cellular material and a layer of abradable material abutting a radially inner surface of the ductile layer, the ductile layer being axially shorter than the fan casing, wherein the first layer of cellular material is weaker than the second layer of cellular material, the ductile layer being arranged to contain at least a portion of a detached fan blade without rupturing.
A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement,
- the fan comprising a fan rotor having a plurality of fan blades,
- the fan casing surrounding fan rotor and the fan blades, the fan casing having a flange at an upstream end and a flange at a downstream end,
- the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being axially shorter than the fan casing, a first layer of cellular material abutting a radially inner surface of the fan casing, a septum layer abutting a radially inner surface of the first layer of cellular material, a second layer of cellular material abutting a radially inner surface of the septum layer, a ductile layer abutting a radially inner surface of the second layer of cellular material and a layer of abradable material abutting a radially inner surface of the ductile layer, the ductile layer being axially shorter than the fan casing, the second layer of cellular material being arranged on a radially outer surface of the whole of an axial length of the ductile layer, the layer of abradable material being arranged on the radially inner surface of the whole of the axial length of the ductile layer, the ductile layer being arranged to contain at least a portion of a detached fan blade.
A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement,
- the fan comprising a fan rotor having a plurality of swept fan blades, the fan blades comprising a composite material,
- the fan casing surrounding the fan rotor and fan blades, the fan casing comprising a composite material, the fan casing having a flange at an upstream end and a flange at a downstream end,
- the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being arranged radially between the fan casing and the fan, the fan blade containment arrangement being axially shorter than the fan casing, the fan blade containment arrangement comprising a first layer of cellular material abutting a radially inner surface of the fan casing, a septum layer abutting a radially inner surface of the first layer of cellular material, a second layer of cellular material abutting a radially inner surface of the septum layer, a ductile layer abutting a radially inner surface of the second layer of cellular material and a layer of abradable material abutting a radially inner surface of the ductile layer, the ductile layer being axially shorter than the fan casing, the ductile layer being arranged to contain at least a portion of a detached fan blade.
Dependencies are inferred from the claim text.