Snap fit nose cone assembly

Patent metadata

Field	Value
Publication number	US-10507904-B2
Application number	US-201615342526-A
Country	US
Kind code	B2
Filing date	Nov 3, 2016
Priority date	Nov 3, 2016
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements disposed around the circumference of a base portion, each of the hub mounting elements comprising a flexible flange extending toward the central axis and having a ridge protruding from a radially outward facing surface. The flexible flange is configured to deflect toward the central axis upon engagement with the hub.

First claim

What is claimed is:

1. A nose cone configured to be mounted to a hub in a turbo machine, said nose cone comprising:
a flange extending radially around a central axis and axially from an apex portion of said nose cone to a base portion of said nose cone, said flange forming an annular hub mating surface at said base portion and having an outer surface defining an air flow path; and
a plurality of hub mounting elements disposed around the circumference of said base portion, each of said hub mounting elements comprising a flexible flange extending toward the central axis and having a ridge protruding from a radially outward facing surface;
two or more apertures defined by said flange forming said annular hub mating surface, each of said apertures configured to receive a fastener therethrough;
wherein each of said two or more apertures include a countersink configured to receive a balance weight; and
wherein said flexible flange is configured to deflect radially inward toward the central axis upon engagement with said hub and remain deflected upon engagement with said hub.

2. The nose cone of claim 1 wherein said flexible flange extends axially beyond said hub mating surface.

3. The nose cone of claim 1 comprising an annular mounting member extending radially inward from said flange proximate said hub mating surface, said flexible flanges extending axially from said mounting member.

4. The nose cone of claim 3 wherein said flexible flange extends axially beyond said hub mating surface.

5. The nose cone of claim 1 wherein said flange extending radially around the central axis forms a parabolic outer surface of the nose cone.

6. The nose cone of claim 1 wherein said flange extending radially around the central axis forms a frustoconical outer surface of the nose cone.

7. The nose cone of claim 1 wherein a leading edge of said flexible flange is chamfered.

8. The nose cone of claim 1 further comprising a circumferential alignment flange extending axially from said flange forming said annular hub mating surface.

9. The nose cone of claim 3 further comprising a circumferential alignment flange extending axially from said mounting member.

10. A nose cone assembly in a turbo machine, said assembly comprising:
a turbo machine component comprising an annular hub extending radially around a central axis and forming a planar mounting surface, said hub comprising:
one or more mounting portions disposed around the circumference of said hub, said mounting portions extending radially inward from said hub and forming a mounting surface which defines a groove;
and
a nose cone mounted on said hub, said nose cone comprising a flange extending radially around the central axis and axially from an apex portion of said nose cone to a base portion of said nose cone, said flange forming an annular hub mating surface at said base portion and having an outer surface defining an air flow path;
a plurality of hub mounting elements disposed around the circumference of said base portion, each of said hub mounting elements comprising a flexible flange extending toward the central axis and having a ridge protruding from a radially outward facing surface, wherein said flexible flange is deflected radially inward and engaged with said hub, and wherein each ridge is engaged with a groove of a respective one of said one or more mounting portions;
two or more mounting flanges disposed around the circumference of said hub, each of said mounting flanges extending axially forward from said planar mounting surface and defining an aperture configured to receive a fastener; and
two or more apertures defined by said flange forming said annular hub mating surface, each of said apertures configured to receive a fastener therethrough and being engaged with said aperture of a respective one of said mounting flanges by said fastener,
wherein one or more of said apertures defined by said flange forming said annular hub mating surface each include a countersink configured to receive a balance weight.

11. The nose cone assembly of claim 10 wherein said mounting surface further defines a guide channel proximate said groove.

12. The nose cone assembly of claim 11 wherein said nose cone further comprises an alignment flange abutting an alignment tab of said hub.

13. The nose cone assembly of claim 10 wherein an engaged position of said flexible flange is inwardly deflected relative to an unengaged position.

14. The nose cone assembly of claim 10 wherein said hub comprises a plurality of blades extending radially outward from a rotor.

15. A method of coupling a nose cone to a hub in a turbo machine having a central axis,
said nose cone comprising
a plurality of hub mounting elements disposed around the circumference of a base portion of said nose cone, each of said hub mounting elements comprising a flexible flange extending toward the central axis and having a ridge protruding from a radially outward facing surface, and
two or more apertures defined by said nose cone configured to receive a fastener therethrough, wherein each of said two or more apertures include a countersink configured to receive a balance weight;

said hub comprising one or more mounting portions disposed around the circumference of said hub, said mounting portions extending radially inward from said hub and forming a mounting surface which defines a groove;
the method comprising:
positioning said nose cone axially forward of and concentric with said hub, with each ridge of said plurality of hub mounting elements axially aligned with a respective groove of said plurality of mounting portions; and
moving said nose cone in an axially aft direction until said flexible flanges deflect in an inward direction and each ridge of said plurality of hub mounting elements is engaged in a respective groove of said plurality of mounting portions, wherein said flexible flanges remain deflected in the inward direction.

16. The method of claim 15 wherein an engaged position of said flexible flange is inwardly deflected relative to an unengaged position.

Assignees

• Rolls Royce Corp

Inventors

• Scott Matthew A

Classifications

• F02C7/04 Primary

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

• F05D2230/60

  Assembly methods · CPC title

• F04D29/329

  Details of the hub · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• B64C11/14 Primary

  Spinners · CPC title