Spinner aft-extended forward return flange
AssigneeUnited Technologies Corporation
InventorsColin J. Kling, Darin S. Lussier
Life of this patent
Estimating the term…
Abstract
A spinner for a fan assembly of a gas turbine engine, a method of fabricating a spinner for a fan assembly of a gas turbine engine, and a gas turbine engine are disclosed. The fan section may include a nosecap. The spinner may include a forward end, an aft end, and a return flange associated with the forward end. The return flange may include a forward flange extending forward towards the nosecap and an aft flange extending aft towards the aft end.
Claims15
A spinner for a fan section of a gas turbine engine, the spinner configured to be receptive of a nosecap and comprising:
- an outer shell extending from a forward end to an aft end;
- the aft end configured to be installed at a forward end of a fan hub of a fan section;
- a return flange disposed at the forward end, the return flange including;
- a radially extending base portion configured to receive a nosecap thereat;
- an annular forward flange extending forward from the base portion towards the nosecap;
- and
- an annular aft flange extending aft from the base portion towards the aft end;
- and
- circumferentially spaced gusset plates extending from the outer shell to the aft flange.
A method of fabricating a spinner, the spinner having an outer shell extending from a forward end to an aft end, and a return flange associated with the forward end, the method comprising:
- forming a radially-extending base portion of the return flange configured to receive a nosecap thereat;
- forming an annular forward flange of the return flange, the forward flange extending forward from the base portion;
- forming an annular aft flange of the return flange, the aft flange extending aft from the base portion towards the aft end;
- and
- forming circumferentially spaced gusset plates extending from the outer shell to the aft flange;
- wherein the aft end is configured to be installed at a forward end of a fan hub of a fan section.
A gas turbine engine, comprising:
- a fan assembly section including a nosecap and a spinner, the spinner configured to be receptive of the nosecap and having a an outer shell extending from a forward end to an aft end, and a return flange disposed at the forward end of the spinner, the return flange including;
- a radially-extending base portion configured to receive a nosecap thereat;
- an annular forward flange extending forward from the base portion towards the nosecap and an annular aft flange extending aft from the base portion towards the aft end;
- circumferentially spaced gusset plates extending from the outer shell to the aft flange;
- a compressor section downstream of the fan assembly section;
- a combustor section downstream of the compressor section;
- and
- a turbine section downstream of the combustor section;
- wherein the aft end is installed at a forward end of a fan hub of the fan assembly section.
Dependencies are inferred from the claim text.