Aerodynamic fairings secondarily attached to nosecone

Patent metadata

Field	Value
Publication number	US-9481448-B2
Application number	US-201314035571-A
Country	US
Kind code	B2
Filing date	Sep 24, 2013
Priority date	Mar 11, 2013
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

First claim

What is claimed is:

1. A one-piece aerodynamic fan nosecone assembly comprising:
a fan nosecone having a leading edge and a trailing edge with an aerodynamic exterior surface extending between the leading and trailing edge;
a plurality of aerodynamic fairings spaced apart and affixed to said aerodynamic exterior surface of the fan nosecone, at least one of the fairings including:
a base having an aerodynamic portion, and
an attachment feature that mounts an underside of the base to the fan nosecone;
and an insert having a portion projecting from the base that enhances aerodynamic sealing between the fan nosecone and a blade member, wherein the insert includes a filler material.

2. The nosecone assembly as claimed in claim 1 , further comprising a mechanical connection between the fan nosecone and at least one fairing.

3. The nosecone assembly as claimed in claim 1 , further comprising a pair of male members extending downwardly from a lower portion of each fairing, each said male member having a locking feature for securing the fairing to the surface of the fan nosecone.

4. The nosecone assembly as claimed in claim 1 , further comprising a chemical bond connecting at least one faring to the fan nosecone.

5. The nosecone assembly as claimed in claim 1 , wherein the at least one of the fairings includes a surface coating extending over a portion of the base.

6. The nosecone assembly as claimed in claim 1 , wherein the base includes a cavity that is sized to receive a portion of the insert.

7. The nosecone assembly as claimed in claim 1 , further comprising a seal that is formed as part of the fairing, the seal is located between the fan nosecone and a blade member that is located approximate to the fan nosecone.

8. A spinner for a turbo machine comprising:
a nosecone member having a leading edge and a trailing edge with an aerodynamic exterior surface extending between the leading and trailing edges; and
an aerodynamic edge fairing affixed to said aerodynamic exterior surface of the nosecone member, the fairing comprising:
a base with an aerodynamic surface,
a seal having a portion that extends within a cavity of the base, and an offset portion that extends past the trailing edge of the nosecone member, and
an attachment portion that mounts the fairing to the nosecone member.

9. The spinner as claimed in claim 8 , further comprising a coating extending over the aerodynamic surface of the base.

10. The spinner as claimed in claim 8 , further comprising a plurality of fairings that are equally spaced apart from one another around a periphery of the nosecone member.

11. The spinner as claimed in claim 8 , wherein the seal is made of an elastomer or organic material composite.

12. The spinner as claimed in claim 8 , wherein the base is made of a composite, metallic or plastic material.

13. The spinner as claimed in claim 8 , wherein the nosecone member is made using a filament winding manufacturing process.

14. The spinner as claimed in claim 8 , further comprising an insert having a portion projecting from the base that enhances aerodynamic sealing between the nosecone member and a blade member.

15. A method of manufacturing a nosecone component comprising the steps of:
providing an aerodynamic nosecone having a leading edge portion and a trailing edge portion, a contoured surface extending between the edge portions;
providing at least one aerodynamic fairing, said fairing having a base with a profiled surface, an attachment surface and a cavity, the fairing further having a filler material with a first portion that is located within the cavity and a second portion that is located outside of the cavity; and
attaching at least one aerodynamic fairing to the nosecone at a location near the trailing edge portion such that the second portion of the filler material extends beyond the trailing edge of the nosecone.

16. The method as claimed in claim 15 , further comprising providing a hole in the contoured surface of the nosecone and providing an attachment feature on the base, inserting the attachment feature of the base into the hole in the contoured surface of the nosecone.

17. The method as claimed in claim 15 , wherein the step of attaching at least one aerodynamic fairing includes chemically bonding the fairing to the nosecone.

18. The method as claimed in claim 15 , wherein the step of attaching at least one aerodynamic fairing includes mechanically connecting the fairing to the nosecone.

19. The method as claimed in claim 15 , wherein the step of attaching at least one aerodynamic fairing to the nosecone results in a minimal gap between the second portion of the filler material and a leading edge of a blade member to direct laminar air flow around the leading edge of a blade member.

Assignees

• Rolls Royce Corp

Inventors

• Totten Trevor John
• Rivers Jonathan Michael
• Engebretsen Eric William

Classifications

• F02C7/04

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

• Y10T29/49336

  Blade making · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• B64C11/14 Primary

  Spinners · CPC title