Turbine engine nosecone with deformation region

Patent metadata

Field	Value
Publication number	US-9353685-B2
Application number	US-201213725359-A
Country	US
Kind code	B2
Filing date	Dec 21, 2012
Priority date	Dec 21, 2012
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

An assembly for a turbine engine including a nosecone that extends along an axis between a tip end and a second end. The nosecone includes a base region and a deformation region configured integral with the base region. The base region is arranged axially between the deformation region and the second end. The deformation region is adapted to deform relative to the base region upon impact of an object, and includes a stress concentrator.

First claim

What is claimed is:

1. An assembly for a turbine engine, comprising:
a nosecone extending along an axis between a tip end and a second end;
the nosecone comprising a base region and a deformation region configured integral and monolithically with the base region;
the base region arranged axially between the deformation region and the second end; and
the deformation region adapted to deform relative to the base region upon impact of an object, and comprising a stress concentrator.

2. The assembly of claim 1 , wherein the deformation region is adapted to deform by at least one of crumpling and fracturing upon impact of the object.

3. The assembly of claim 1 , wherein
the nosecone comprises a sidewall;
at least a first portion of the sidewall has a first thickness;
at least a second portion of the sidewall has a second thickness that is less than the first thickness; and
the stress concentrator comprises a transition between the first portion and the second portion.

4. The assembly of claim 3 , wherein
the first portion is located within the base region; and
the second portion is located within the deformation region.

5. The assembly of claim 3 , wherein the first portion and the second portion are located within the deformation region.

6. The assembly of claim 3 , wherein the transition tapers from the first portion to the second portion.

7. The assembly of claim 3 , wherein the transition comprises a step between the first portion and the second portion.

8. The assembly of claim 1 , wherein
the nosecone comprises a sidewall; and
the stress concentrator comprises a flange that extends radially inwards from the sidewall and is arranged adjacent the base region.

9. An assembly for a turbine engine, comprising:
a nosecone extending along an axis between a tip end and a second end;
the nosecone comprising a base region and a deformation region configured integral with the base region;
the base region arranged axially between the deformation region and the second end; and
the deformation region adapted to deform relative to the base region upon impact of an object, and comprising a stress concentrator;
wherein the nosecone comprises a sidewall; and
wherein the stress concentrator comprises a groove that extends circumferentially within the sidewall at least partially around the axis.

10. An assembly for a turbine engine, comprising:
a nosecone extending along an axis between a tip end and a second end;
the nosecone comprising a base region and a deformation region configured integral with the base region;
the base region arranged axially between the deformation region and the second end; and
the deformation region adapted to deform relative to the base region upon impact of an object, and comprising a stress concentrator;
wherein the nosecone comprises a sidewall; and
wherein the stress concentrator comprises a groove that extends axially within the sidewall.

11. The assembly of claim 1 , wherein
the stress concentrator is one of a plurality of stress concentrators included in the deformation region; and
at least some of the plurality of stress concentrators are arranged in a radial array.

12. The assembly of claim 1 , wherein
the nosecone comprises a sidewall;
the stress concentrator is one of a plurality of stress concentrators included in the deformation region; and
at least some of the plurality of stress concentrators each extend circumferentially within the sidewall at least partially around the axis.

13. The assembly of claim 1 , wherein the nosecone comprises:
a sidewall; and
a mounting flange connected to the sidewall and located at the second end.

14. The assembly of claim 1 , further comprising an annular nosecone mount fastened to the nosecone at the second end.

15. The assembly of claim 1 , wherein
the nosecone comprises a nosecone segment and a cap segment fastened to the nosecone segment; and
the cap segment comprises the base region and the deformation region.

16. The assembly of claim 1 , further comprising:
a plurality of engine rotors arranged along the axis and including a first rotor and a second rotor, each of the engine rotors comprising a plurality of rotor blades arranged around and connected to a rotor disk;
wherein the first rotor is driven by the second rotor; and
wherein the nosecone is connected to the first rotor.

17. The assembly of claim 16 , further comprising a gear train that connects the first rotor and the second rotor together.

18. The assembly of claim 1 , further comprising:
a stator;
wherein the nosecone is connected to the stator.

19. An assembly for a turbine engine, comprising:
a nosecone extending along an axis between a tip end and a second end;
the nosecone comprising a base region and a deformation region configured integral and monolithically with the base region;
the base region arranged axially between the deformation region and the second end; and
the nosecone further comprising means for deforming the deformation region relative to the base region upon impact of an object.

20. An assembly for a turbine engine, comprising:
a nosecone extending along an axis between a tip end and a second end;
the nosecone comprising a sidewall, a base region and a deformation region configured integral with the base region;
the base region arranged axially between the deformation region and the second end; and
the deformation region comprising a plurality of stress concentrators;
wherein a first of the stress concentrators comprises a groove that extends at least one of circumferentially within the sidewall at least partially around the axis; and axially within the sidewall.

Assignees

• United Technologies Corp

Inventors

• Kling Colin J
• Mcphail James J
• Rader Matthew R

Classifications

• B64C11/14

  Spinners · CPC title

• F02C7/05 Primary

  having provisions for obviating the penetration of damaging objects or particles · CPC title