Spinner aft-extended forward return flange

Patent metadata

Field	Value
Publication number	US-10094282-B2
Application number	US-201514693488-A
Country	US
Kind code	B2
Filing date	Apr 22, 2015
Priority date	Jul 30, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

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.

First claim

What is claimed is:

1. 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.

2. The spinner of claim 1 , wherein the aft flange provides an internal interface, the internal interface extending axially about an internal circumference of the spinner.

3. The spinner of claim 2 , gusset plates located at the internal interface.

4. The spinner of claim 1 , wherein the forward flange is configured to interface with the nosecap at a nosecap interface.

5. The spinner of claim 1 , wherein the return flange is formed using a compression molding process.

6. 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.

7. The method of claim 6 , wherein the forming of the forward flange is performed using a compression molding process.

8. The method of claim 6 , wherein the forming of the aft flange is performed using a compression molding process.

9. The method of claim 6 , further comprising forming the gusset plates on an internal interface of the aft flange, the internal interface extending axially about an internal circumference of the spinner.

10. The method of claim 6 , further configuring the forward flange to interface with a nosecap at a nosecap interface.

11. 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.

12. The gas turbine engine of claim 11 , the gusset plates located at an internal interface location provided by the return flange.

13. The gas turbine engine of claim 11 , wherein the nosecap includes a nosecap interface for interfacing the nosecap with the forward flange.

14. The gas turbine engine of claim 13 , wherein the spinner includes geometry to facilitate mating the nosecap with the forward flange.

15. The gas turbine engine of claim 11 , wherein at least one of the forward flange and the aft flange are formed using a compression molding process.

Assignees

• United Technologies Corp

Inventors

• Kling Colin J
• Lussier Darin S

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B29L2031/7504

  Turbines · CPC title

• B29K2101/00

  Use of unspecified macromolecular compounds as moulding material {(use of unspecified rubbers B29K2021/00)} · CPC title

• F05D2230/30

  with deposition of material · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title