Turbofan case for controlling blade deflection
AssigneeGeneral Electric Company
InventorNicholas Joseph Kray
Life of this patent
Estimating the term…
Abstract
A containment structure configured to provide close tolerance for a rotation structure. The containment structure includes an annular inner casing having an inner annular surface being formed of an abradable material. The rotation structure is configured to be received within the annular inner casing such that the rotation structure is normally spaced-apart from the inner annular surface. The inner annular surface surrounds the rotation structure and has a first width. The rotation structure has a second width and the first width is greater than the second width. At least a section of the inner annular surface of the abradable material is cylindrical.
Claims24
A containment structure configured to provide close tolerance for a rotation structure, the containment structure comprising:
- an annular inner casing having an inner annular surface being formed of an abradable material;
- the rotation structure being configured to be received within the annular inner casing such that the rotation structure is normally spaced-apart from the inner annular surface and the inner annular surface surrounds the rotation structure;
- the inner annular surface having a first width;
- the rotation structure having a second width such that the first width is greater than the second width;
- wherein at least a section of the inner annular surface of the abradable material is cylindrical.
A fan containment structure comprising:
- an annular inner fan casing having a leading edge, a trailing edge, and an inner annular surface;
- the inner annular surface being formed of an abradable material and having a first tapered section and a second cylindrical section;
- a fan that is configured to be received within the annular inner fan casing such that the fan is surrounded by the inner annular surface.
The fan containment structure of clean 13, wherein the prime mover is a gas turbine engine.
A method for determining the geometric configuration of a fan containment structure of a turbofan engine comprising the steps of:
- modeling the operation of a turbofan engine;
- simulating a rub load condition;
- measuring blade deflection relative to an axis of the engine as referenced by the position of a fan;
- and
- determining the axial distance X of the deflection.
A fan assembly for use in a turbine engine, the fan assembly comprising;
- a containment structure that includes an abradable annular surface;
- a fan that is positioned within the containment structure and that includes a disk and a plurality of blades mounted to the disk;
- the blades having a leading edge that defines a normal;
- and wherein the abradable annular surface has a cylindrical section that is positioned forward of the normal plane.
Dependencies are inferred from the claim text.